Page 2 WARD EVANS DATE OF APPROVAL: D.O.A. NO. SO-1 JUNE 1, 1978 PIPER AIRCRAFT CORPORATION VERO BEACH, FLORIDA FAA APPROVED IN NORMAL CATEGORY BASED ON CAR 3. THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY CAR 3 AND CONSTITUTES THE APPROVED AIRPLANE FLIGHT MANUAL AND MUST BE CARRIED IN THE AIRPLANE AT ALL TIMES.
Page 3 EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS HANDBOOK TO APPLICABLE AIRCRAFT. THIS HAND- BOOK IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED ON THE FACE OF THE TITLE PAGE. SUBSEQUENT REVISIONS SUPPLIED BY PIPER AIRCRAFT CORPORATION MUST BE PROPERLY INSERTED. Published by PUBLICATIONS DEPARTMENT...
Page 5 REPORT: VB-910 ISSUED: JUNE 1, 1978...
Page 6 APPLICABILITY Application of this handbook is limited to the specific Piper P A-28-236 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 7 Black lines 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 material on a page will not be identified. ORIGINAL PAGES ISSUED The original pages issued for this handbook prior to revision are given below: Title, ii through vii, 1-1 through 1-21, 2-1 through 2-8, 3-1 through...
Page 8: Rev.
PILOT’S OPERATING HANDBOOK LOG OF REVISIONS Current Revisions to the PA-28-236 Dakota Pilot’s Operating Handbook, REPORT: VB-910 issued June 1, 1978. Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 1 Revised dimensions. 761 689 Revised note.
Page 9: Rev.
PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 2 . 6-i Revised pg. no. · 761 689 6-43- Revised Item 315; added item (PR790413) 316; relocated item 319 to pg. 6-44.
Page 10: Revised Item
PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev 3. (cont) 4-10 Added Descent to check list; relocated info. from pg. 4-9; relocated info. to pg. 4-10a. 4-10a Added page;...
Page 11: Report: Vb
PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 3 (cont) 6-29 Relocated item 189; added item 192; relocated item 195 from pg. 6-30. 6-30 Relocated item 195; removed item 20 I;...
Page 12 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 4 Revised para. I. 7 (c). 761 689 Revised fuel grade. (PR800801) Added placard. 3-15 Revised para. 3.22. 4-10 Revised Normal Procedures checklist (Descent).
Page 13: Rev. 4 (Cont)
PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 4 (cont) 6-28 Added item 181 from pg. 6~27. 6-32 Relocated item 231 to pg. 6-35; renumbered item; added new item 225.
Page 14 Relocated info. to pg. 8-14; added new info. to para. 8.2l(b). 8-14 Added para. 8.2l(c). from pg. 8-13. Added Supplement 5 (Century 21 Autopilot) and Supplement 6 (Piper Control Wheel Clock Installation). 9-19 Added pgs.; Added Supplement thru 5 info. 9-22 9-23 Added pgs.;...
Page 15 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 5 6-99 Added item 288. 761 689 Revised Table of Contents. (PR801210) 9-25 Added pgs. (Added Supple- thru ment 7 KNS 80 Navigation Ward Evans 9-28...
Page 16: Report: Vb
PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 6 (cont) 6-24 Revised item 129. 6-25 Relocated title (j). 6-30 Added item 206. 6-38 Moved item 281 to pg. 6-38a. 6-38a Added item 280;...
Page 17: Rev.
PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 7 (cont) 6-34 Revised item 251. 6-37 Renumbered item; moved item to pg. 6-37b. 6-37a New page. 6-37b New page;...
Page 18: Report: Vb
PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 8 (cont) 4-22 Relocated info. and para. 4.28 from pg. 4-21; added note to para. 4.29; moved info. to pg. 4-23. 4-23 Relocated info.
Page 19 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 8 (cont) 4-ii New pg.; relocated info. from pg. 4-i. Revised para. 4.1. 4-11 Revised para. 4.7. Revised index pg. Revised fig.
Page 20 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 10 7-16 Relocated para. 7.19 from pg. (cont) 7-14, moved info. to pg. 7-18. 7-18 Relocated info. from pg.7-16. 7-22 Revised para.
Page 21 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 12 Revised para. 6.1. (cont) Revised para. 6.3. Revised para. 6.5. 6-15 Revised item 19. Revised para. 7.9. 7-12 Revised para.
Page 22 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 16 vi-m, Added pages to Log of Revi- (PR900504) vi-n sions. 5-29 Revised Figure 5-35. 7-27 Added Narco ELT 910 info. 7-27a Added page.
Page 23 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date REPORT: VB-910 ISSUED: JUNE 1, 1978 vi-n...
Page 24 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 25 THIS PAGE INTENTIONALLy LEFT BLANK REPORT: VB-910 ISSUED: JUNE 1, 1978 viii...
Page 26: Table Of Contents
TABLE OF CONTENTS SECTION 1 GENERAL Paragraph Page Introduction ................Engine ..................Propeller .................. 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 ......ISSUED: JUNE 1, 1978 REPORT: VB-910...
Page 27 BLANK PAGE REPORT: VB-910 ISSUED: JUNE 1, 1978 1-ii...
Page 28: Introduction
PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-236, DAKOTA GENERAL SECTION 1 GENERAL 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 CAR 3. It also contains supplemental data supplied by the airplane manufacturer.
Page 29 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-28-236, DAKOTA THREE VIEW Figure 1-1 REPORT: VB-910 REPORT: VB-910 ISSUED: JUNE 1, 1978 ISSUED: JUNE 1, 1978 REVISED: JANUARY 15, 1979...
Page 30: Engine
PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-236, DAKOTA GENERAL ENGINES (a) Number of Engines (b) Engine Manufacturer Lycoming (c) Engine Model Number 0-540-J3A5D (d) Rated Horsepower (e) Rated Speed (rpm) 2400 (f) Bore (in.) 5,125 (g) Stroke (in.) 4.375 (h) Displacement (cu. in.) 541.5...
Page 31: Oil
SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-28-236, DAKOTA (a) Oil Capacity (U.S. qts.) (b) Oil Specification Refer to latest issue of Lycoming Service Instruction 1014. (c) Oil Viscosity Refer to Section 8 - paragraph 8.19. 1.11 MAXIMUM WEIGHTS (a) Maximum Ramp Weight (lbs.) 3011 (b) Maximum Takeoff Weight (lbs.)
Page 32: Specific Loadings
PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-236, DAKOTA GENERAL 1.17 SPECIFIC LOADINGS (a) Wing Loading (lbs. per sq. ft.) 17.6 (b) Power Loading (lbs. per hp) 12.8 ISSUED: JUNE 1, 1978 REPORT: VB-910...
Page 33: Symbols, Abbreviations And Terminology
SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-28-236, DAKOTA 1.21 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. (a) General Airspeed Terminology and Symbols...
Page 34 PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-236, DAKOTA GENERAL Never Exceed Speed or Mach Number is the speed limit that may not be exceeded at any time. Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution.
Page 35 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-28-236, DAKOTA Indicated Pressure T h e n u m b e r a c t u a l l y r e a d f r o m a n Altitude altimeter when the barometric subscale has been set to 29.92 inches of mercury (1013...
Page 36 PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-236, DAKOTA GENERAL (e) Airplane Performance and Flight Planning Terminology Climb Gradient The demonstrated ratio of the change in height during a portion of a climb, to the horizontal distance traversed in the same time interval.
Page 37 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-28-236, DAKOTA Center of Gravity The point at which an airplane would (C.G.) balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane.
Page 38 PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-236, DAKOTA GENERAL Maximum Maximum weight approved for the landing Landing Weight touchdown. Maximum Zero Maximum weight exclusive of usable fuel. Fuel Weight ISSUED: JUNE 1, 1978 REPORT: VB-910 1-11...
Page 39 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: JUNE 1, 1978 1-12...
Page 40 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 Maneuvering Load Factors ..........
Page 41 BLANK PAGE REPORT: VB-910 ISSUED: JUNE 1, 1978 2--ii...
Page 42: General
PIPER AIRCRAFT CORPORATION PA-28-236, DAKOTA SECTION 2 LImITATIONS 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 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 43: Airspeed Indicator Markings
PIPER AIRCRAFT CORPORATION PA-28-236, DAKOTA SPEED KIAS KCAS Never Exceed Speed (VNE)- Do not exceed this speed in any operation. Maximum Structural Cruising Speed (VNo) - Do not exceed this speed except in smooth air and then only with caution.
Page 44: Power Plant Instrument Markings
PIPER AIRCRAFT CORPORATION PA-28-236, DAKOTA (f) Fuel Pressure Minimum (red line) 0.5 PSI Maximum (red line) 8 PSI (g) Fuel (AVGAS ONLY) (minimum grade) 100 or 100LL Aviation Grade (h) Number of Propellers (i) Propeller Manufacturer Hartzell (j) Propeller Hub and Blade Mode...
Page 45: Center Of Gravity Limits
PIPER AIRCRAFT CORPORATION PA-28-236, DAKOTA 2.13 CENTER OF GRAVITY LImITS Weight Forward Limit Rearward Limit Pounds Inches Aft of Datum Inches Aft of Datum 3000 88.5 92.0 2500 82.5 92.0 1900 79.8 92.0 NOTES Straight line variation between points given.
Page 46: Fuel Limitations
PIPER AIRCRAFT CORPORATION PA-28-236, DAKOTA 2.21 FUEL LIMITATIONS (a) Total Capacity 77 U.S. GAL (b) Unusable Fuel 5 U.S. GAL The unusable fuel for this airplane has been determined as 2.5 gallons in each wing in critical flight attitudes. (c) Usable Fuel 72 U.S.
Page 47 PIPER AIRCRAFT CORPORATION PA-28-236, DAKOTA In full view of the pilot: TAKEOFF CHECK LIST Fuel on Proper Tank Propeller Set Auxiliary Fuel Pump - On Fasten· Belts / Harness Engine Gages Checked Flaps Set Carburetor Heat Off Trim Tap Set...
Page 48 PIPER AIRCRAFT CORPORATION PA-28-236, DAKOTA Adjacent to upper door latch: ENGAGE LATCH BEFORE FLIGHT On the instrument panel in full view of the pilot: DEMONSTRATED CROSSWIND COMPONENT 17 KTS DEMO. X-WIND 17 KTS In full view of the pilot: NO ACROBATIC MANEUVERS,...
Page 49 PIPER AIRCRAFT CORPORATION PA-28-236, DAKOTA In full view of the pilot, in the area of the air conditioner controls when the air conditioner is installed: · WARNING- AIR CONDITIONER MUST BE OFF TO INSURE NORMAL TAKEOFF CLIMB PERFORMANCE. Adjacent to fuel filler cap: FUEL- 100 OR IOOLL AVIATION GRADE FUEL - 100/130 AVIATION GRADE- MIN.
Page 50 PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-236, DAKOTA EMERGENCY PROCEDURES TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph Page General ..................Emergency Procedures Checklist ..........Speeds ..................Engine Inoperative Procedures ..........Fire ..................Loss of Oil Pressure ............... Loss of Fuel Pressure .............
Page 51: Paragraph Page
SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA TABLE OF CONTENTS (cont) SECTION 3 (cont) Paragraph Page 3.15 High Oil Temperature ..............3-13 3.17 Electrical Failures ............... 3-14 3.18 Electrical Overload ..............3-14 3.19 Spin Recovery ................3-15 3.21 Open Door ..................
Page 52: General
PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-236, DAKOTA EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES 3.1 GENERAL The recommended procedures for coping with various types of emergencies and critical situations are provided by this section. All of required (FAA regulations) emergency procedures and those necessary for operation of the airplane as determined by the operating and design features of the airplane are presented.
Page 53: Emergency Procedures Checklist
SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA 3.3 EMERGENCY PROCEDURES CHECK LIST SPEEDS Stall speeds 3000 lbs. (0° flap) ................65 KIAS 3000 lbs, (full flap) ................56 KIAS Maneuvering speeds 3000 lbs..................124 KIAS 1761 lbs...................96 KIAS. Never exceed speed ................173 KIAS Power off glide speed 3000 lbs.
Page 54 PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-236, DAKOTA EMERGENCY PROCEDURES Insufficient runway remaining: Airspeed ................. maintain above stall Throttle ....................close Mixture .................IDLE CUT-OFF Fuel selector ....................OFF Master switch...................OFF Magnetos ....................OFF Flaps ................as situation requires Directional control ............maintain - make only shallow turns to avoid obstacles.
Page 55: Fire
SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA POWER OFF LANDING Trim for best glide angle (85 KIAS). Locate most suitable landing area. Establish spiral pattern. 1000 feet above field at downwind position for normal landing approach. When field can be easily reached, slow to 72 KIAS for shortest landing with a full stall touchdown.
Page 56: Loss Of Oil Pressure
PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-236, DAKOTA EMERGENCY PROCEDURES Electrical fire (smoke in cabin): Master switch...................OFF Cabin heat ....................OFF Defroster ....................OFF Vents ................open to clear cabin Land as soon as practicable. LOSS OF OIL PRESSURE Land as soon as possible and investigate cause.
Page 57: Electrical Overload
SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA If power not restored ALT switch ....................OFF If alternator output cannot be restored, reduce electrical loads and land as soon as practical. The battery is the only remaining source of electrical power.
Page 58: Spin Recovery
PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-236, DAKOTA EMERGENCY PROCEDURES If alternator loads are not reduced ALT switch ....................OFF BAT switch ................... as required Land as soon as possible. Anticipate complete electrical failure. SPIN RECOVERY Rudder ..................full opposite to direction of rotation Control wheel ..............
Page 59: Engine Roughness
SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA ENGINE ROUGHNESS Carburetor heat ..................ON If roughness continues after one min: Carburetor heat ..................OFF Mixture ..............adjust for max. smoothness Electric fuel pump ..................ON Fuel selector ................switch tanks Engine gauges ..................check Magneto switch..............L then R, then Both...
Page 60: Amplified Emergency Procedures (General)
PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-236, DAKOTA 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 61: Engine Power Loss In Flight
SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA If sufficient altitude has been gained to permit a restart attempt, maintain a safe airspeed and switch the fuel selector to another tank containing fuel. Check the electric fuel pump to ensure that it is ON. Check that the mixture control is set RICH and that carburetor heat is ON.
Page 62: Power Off Landing
PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-236, DAKOTA EMERGENCY PROCEDURES POWER OFF LANDING If loss of power occurs at altitude, trim the airplane for best gliding angle (85 KIAS), and look for a suitable landing area. If the procedures for restoring power are not effective, and if time permits, check charts for airports in the immediate vicinity;...
Page 63: Fire In Flight
SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA If the fire continues, leave the fuel selector OFF and the mixture at IDLE CUT-OFF, and abandon the airplane, applying the best external extinguishing means available. If the fire is on the ground near the airplane, it may be possible to taxi to safety.
Page 64: Loss Of Oil Pressure
PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-236, DAKOTA EMERGENCY PROCEDURES 3.11 LOSS OF OIL PRESSURE Loss of oil pressure may be either partial or complete. A partial loss of oil pressure usually indicates a malfunction in the oil pressure regulating system, and a landing should be made as soon as possible to allow investigation of the cause and to prevent engine damage.
Page 65: Electrical Failures
SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA 3.17 ELECTRICAL FAILURES Loss of alternator output is detected through zero reading on the ammeter. Before executing the following procedure, insure that the reading is zero and not merely low by actuating an electrically powered device, such as the landing light.
Page 66: Spin Recovery
PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-236, DAKOTA EMERGENCY PROCEDURES - NOTE - Due to higher voltage and radio frequency noise, operation with the ALT switch ON and the BAT switch OFF should be made only when required by an electrical failure.
Page 67: Carburetor Icing
SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA 3.22 CARBURETOR ICING. Under certain moist atmospheric conditions at temperatures of -5° C to +20°C, it is possible for ice to form in the induction system, even in summer weather. This is due to the high air velocity through the carburetor venturi and the absorption of heat from this air by vaporization of the fuel.
Page 68: Propeller Overspeed
PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-236, DAKOTA EMERGENCY PROCEDURES If roughness persists, prepare for a precautionary landing at pilot’s discretion. NOTE Partial carburetor heat may be worse than no heat at all, since it may melt part of the ice, which will refreeze in the intake system.
Page 69 THIS PAGE INTENTIONALLY LEFT BLANK...
Page 70 TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Paragraph Page General ..................4-1 Airspeeds for Safe Operations ............ 4-1 Normal Procedures Checklist ............. 4-3 Preflight Check ..............4-3 Before Starting Engine ............4-5 Starting Engine When Cold ........... 4-6 Starting Engine When Hot ............ 4-6 Starting Engine When Flooded ..........
Page 71 TABLE OF CONTENTS (cont) SECTION 4 (cont) Paragraph Page 4-19 Ground Check ................4-17 4.21 Before Takeoff ................4-18 4.23 Takeoff ..................4-19 4.25 Climb ..................4-20 4.27 Cruising ..................4-20 4.28 Descent ..................4-22 4.29 Approach and Landing ............... 4-22 4.31 Stopping Engine .................
Page 72: General
PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES SECTION 4 NORMAL PROCEDURES 4.1 GENERAL This section describes the recommended procedures for the conduct of normal operations. 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 73 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-236, DAKOTA Performance for a specific airplane may vary from published figures depending upon the equipment installed, ·the condition of the engine, airplane and equipment, atmospheric conditions and piloting technique. (a) Best Rate of Climb Speed...
Page 74: Normal Procedures Checklist
PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES WALK-AROUND Figure 4-1 4.5 NORMAL PROCEDURES CHECK LIST PREFLIGHT CHECK COCKPIT Control wheel ..............release restraints Parking brake ..................... set All switches .....................OFF All avionics....................OFF Mixture ..................idle cut-off Master switch.................... ON Fuel gauges ................check quantity...
Page 75 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-236, DAKOTA Required papers ..............check on board Tow bar and baggage ..............stow properly secure Baggage door ................ close and secure RIGHT WING Surface condition ............clear of ice, frost, snow Flap and hinges ..................check Aileron and hinges .................check...
Page 76: Before Starting Engine
PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES Chock ....................remove Main gear strut ..................proper inflation (4.5 in.) Tire ......................check Brake block and disc ................check Fuel tank ..................check supply visually - secure cap Fuel tank vent ..................dear Fuel tank sump ............drain and check for water,...
Page 77: Starting Engine When Cold
SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-236, DAKOTA STARTING ENGINE WHEN COLD Master switch.................... ON Electric fuel pump ..................ON Mixture ................... full RICH Throttle ................... 1 / 4 open Starter ....................engage Throttle ....................adjust Oil pressure....................check If engine does not start, add 1 to 3 strokes of priming pump and repeat above.
Page 78: Warm-Up
PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES Proceed with normal start Throttle ................. lowest possible RPM External power plug ..........disconnect from fuselage Master switch..............ON - check ammeter Oil pressure....................check WARM-UP Throttle ................1000 to 1200 RPM TAXIING Chocks ....................
Page 79: Before Takeoff
SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-236, DAKOTA BEFORE TAKEOFF Master switch.................... ON Flight instruments ..................check Fuel selector .................proper tank Electric fuel pump ..................ON Engine gauges ..................check Carburetor heat ..................OFF Seat backs ....................erect Primer ....................locked Mixture ...................... set Prop ......................
Page 80: Climb
PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES Accelerate to best rate of climb speed - 85 KlAS and slowly retract the flaps while climbing out. SOFT FIELD, OBSTACLE CLEARANCE Flaps ................25° (second notch) Accelerate; pull nose wheel off as soon as possible.
Page 81: Descent
SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-236, DAKOTA DESCENT NORMAL Throttle ..............as required for 1000 FPM descent Propeller ..................2400 RPM Airspeed ..................137 KIAS Mixture .....................rich Carburetor heat ................. on if required POWER OFF Carburetor heat ................. on if required Throttle ....................closed...
Page 82: Parking
PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES PARKING Parking brake ..................... set Control wheel ..............secured with belts Flaps ....................full up Wheel chocks ..................in place Tie downs .....................secure ISSUED: AUGUST 27, 1979 REPORT: VB-910 4-10a...
Page 83 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: AUGUST 27, 1979 4-10b...
Page 84: Amplified Normal Procedures (General)
PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES 4.7 AMPLIFIED NORMAL PROCEDURES (GENERAL) The following paragraphs are provided to supply detailed information and explanations of the normal procedures necessary for operation of the airplane. 4.9 PREFLIGHT CHECK The airplane should be given a thorough preflight and walk-around check.
Page 85 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-236, DAKOTA Open the fuel cap and visually check the fuel color and the quantity should match the indication that was on the fuel quantity gauge, replace cap securely. The fuel tank vent should be clear of obstructions.
Page 86 PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES LEFT WING The wing surface should be clear of ice, frost, snow, or other extraneous substances. Check that the fresh air inlet is clear of foreign matter and remove the chock. Check the main gear strut for proper inflation, there should be 4.5 inches of strut exposure under a normal static load.
Page 87: Before Starting Engine
SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-236, DAKOTA NOTE If the fixed shoulder harness (non-inertia reel type) is installed, it must. be connected to the seat belt and adjusted to allow proper accessibility to all controls, including fuel selector, flaps, trim, etc., while maintaining adequate restraint for the occupant.
Page 88 (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 89: Warm-Up
SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-236, DAKOTA 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 90: Ground Check
PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES propeller set in low pitch, high RPM setting. While taxiing, make slight turns to ascertain the effectiveness of the steering. Observe wing clearances when taxiing near buildings or other stationary objects. If possible, station an observer outside the airplane.
Page 91: Before Takeoff
SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-236, DAKOTA The electric fuel pump should be turned OFF after starting or during warm-up to make sure that the engine driven pump is operating. Prior to takeoff the electric pump should be turned ON again to prevent loss of power during takeoff should the engine driven pump fail.
Page 92: Takeoff
PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES On air conditioned models, the air conditioner must be OFF to insure normal takeoff performance. 4.23 TAKEOFF The normal takeoff technique is conventional. The tab should be set slightly aft of neutral, with the exact setting determined by the loading of the airplane.
Page 93: Climb
SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-236, DAKOTA SOFT FIELD, NO OBSTACLE.· Lower flaps to 25° (second notch), accelerate aircraft, pull nose gear off as soon as possible and lift off at lowest possible airspeed. Accelerate just above the ground to best rate of climb speed, 85 KIAS, and climb out while slowly retracting the flaps.
Page 94 PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES Use of the mixture control in cruising flight reduces fuel consumption significantly, especially at higher altitudes. The mixture should be leaned during cruising operation above 5000 ft. altitude and at pilot’s discretion at lower altitudes when 75% power or less is being used.
Page 95: Descent
SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-236, DAKOTA 4.28 DESCENT NORMAL To achieve the performance on Figure 5-31 the power on descent must be used. The throttle should be set for 1000 FPM descent, propeller 2400 RPM, mixture full rich and maintain an airspeed of 137 KIAS. In case carburetor ice is encountered apply full carburetor heat.
Page 96: Stopping Engine
PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES Turn ON the electric fuel pump, and turn OFF the air conditioner. The mixture should be set in the full RICH position and the propeller at full INCREASE rpm to facilitate ample power for an emergency go-around.
Page 97: Parking
SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-236, DAKOTA The air conditioner and radios should be turned OFF, the propeller set in the full INCREASE position, and the engine stopped by disengaging the mixture control lock and pulling the mixture control back to idle cut-off. The throttle should be left full aft to avoid engine vibration while stopping.
Page 98: Turbulent Air Operation
PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES 4.37 TURBULENT AIR OPERATION In keeping with good operating practice used in all. aircraft, it is recommended that when turbulent air is encountered or expected, the airspeed be reduced to maneuvering speed to reduce the structural loads caused by gusts and to allow for inadvertent speed build-ups which may occur as a result of the turbulence or of distractions caused by the conditions.
Page 99 THIS PAGE INTENTIONALLY LEFT BLANK...
Page 100 TABLE OF CONTENTS SECTION 5 PERFORMANCE Paragraph Page General ..................5-1 Introduction- Performance and Flight Planning ......5-1 Flight Planning Example ............5-3 Performance Graphs ..............5-9 List of Figures ................ 5-9 ISSUED: JUNE 1, 1978 REPORT: VB-910...
Page 101 BLANK PAGE REPORT: VB-910 ISSUED: JUNE 1, 1978 5-ii...
Page 102 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-236, DAKOTA PERFORMANCE SECTION 5 PERFORMANCE 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).
Page 103 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-236, DAKOTA The information provided by paragraph 5.5 (Flight Planning Example) outlines a detailed flight plan using the performance charts in this section. Each chart includes its own example to show how it is used.
Page 104 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-236, DAKOTA PERFORMANCE FLIGHT PLANNING EXAMPLE (a) Aircraft Loading The first step in planning the 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 105 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-236, DAKOTA (b) Takeoff and Landing After determining the aircraft loading, all aspects of. takeoff and landing must be considered. All of the existing conditions at the departure and destination airport must be acquired, evaluated and’ maintained throughout the flight.
Page 106 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-236, DAKOTA PERFORMANCE (c) Climb The next step in the flight plan example is to determine the necessary climb segment components. The desired cruise pressure altitude and corresponding cruise outside air temperature values are the first variables to be considered in determining the climb components from the Fuel, Time and Distance to Climb graph (Figure 5-15).
Page 107 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-236, DAKOTA values from the graph (Figure 5-31). Now, subtract the values obtained from the field conditions from the values obtained from the cruise conditions to find the true fuel, time and distance values needed for the flight plan.
Page 108 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-236, DAKOTA PERFORMANCE (3) Cruise Power (Mixture leaned to 50° F rich of peak EGT) 65% rated power (4) Cruise Speed 134 KTS TAS* (5) Cruise Fuel Consumption 11.8 GPH* (6) Cruise Time (e)(2) divided by (e)(4), (592 naut.
Page 109 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: JUNE 1, 1978...
Page 110 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-236, DAKOTA PERFORMANCE 5.7 PERFORMANCE GRAPHS LIST OF FIGURES Paragraph Page Airspeed Calibration ..............5-11 Stall Speed Vs. Angle of Bank ..........5-12 Takeoff Ground Roll (0° Flaps) ..........5-13 Takeoff Distance Over 50 Ft. Barrier (0° Flaps) .....
Page 111 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: JUNE 1, 1978 5-10...
Page 112: Airspeed Calibration
PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-236, DAKOTA PERFORMANCE AIRSPEED CALIBRATION Figure 5-l ISSUED: JUNE 1, 1978 REPORT: VB-910 5-11...
Page 121 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: JUNE 1, 1978 5-20...
Page 134 PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-236, DAKOTA WEIGHT AND BALANCE 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 ......
Page 135 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: JUNE 1, 1978 6-ii...
Page 136: General
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-236, DAKOTA 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).
Page 137: Airplane Weighing Procedure
C.G. 6.3 AIRPLANE WEIGHING PROCEDURE At the time of licensing, Piper Aircraft Corporation provides each airplane with the basic empty weight and center of gravity location. This data is supplied by Figure 6-5.
Page 138 PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-236, DAKOTA WEIGHT AND BALANCE CAUTION Whenever the fuel system is completely drained and fuel is replenished it will be necessary to run the engine for a minimum of 3 minutes at 1000 RPM on each tank to insure no air exists in the fuel supply lines.
Page 139 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-236, DAKOTA Scale Scale Position and Symbol Reading Tare Weight Nose Wheel Right Main Wheel Left Main Wheel Basic Empty Weight, as Weighed (T) WEIGHING FORM Figure 6-1 (d) Basic Empty Weight Center of Gravity (1) The following geometry applies to the PA-28-236 airplane when it is level.
Page 140: Weight And Balance Data And Record
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-236, DAKOTA 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)
Page 141 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-236, DAKOTA MODEL PA-28-236, DAKOTA Airplane Serial Number _________________________ Registration Number ___________________________ Date ________________________________________ AIRPLANE BASIC EMPTY WEIGHT C.G. Arm Weight x (Inches Aft = Moment Item (Lbs) of Datum) (In-Lbs) Actual...
Page 142 PA-28-236 Page Number Serial Number Registration Number Running Basic Weight Change Empty Weight Description of Article Date or Modification Moment Moment (Lb.) (Lb.) (In.) /100 /100 As licensed...
Page 143 PA-28-236 Page Number Serial Number Registration Number Running Basic Weight Change Empty Weight Description of Article Date or Modification Moment Moment (Lb.) (Lb.) (In.) /100 /100...
Page 144: Weight And Balance Determination For Flight
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-236, DAKOTA 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 145 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-236, DAKOTA Arm Aft Weight Datum Moment (Lbs) (Inches) (In-Lbs) Basic Empty Weight Pilot and Front Passenger 80.5 Passengers (Rear Seats) 118.1 Fuel (72 Gallons Maximum) 95.0 Baggage (200 Lbs. Maximum) 142.8 Ramp Weight (3011 Lbs.
Page 146 PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-236, DAKOTA WEIGHT AND BALANCE LOADING GRAPH Figure 6-13 ISSUED: JUNE 1, 1978 REPORT: VB-910 6-11...
Page 147 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-236, DAKOTA C.G. RANGE AND WEIGHT Figure 6-15 REPORT: VB-910 ISSUED: JUNE 1, 1978 6-12 REVISED: AUGUST 1, 1980...
Page 148: Instructions For Using Weight And Balance Plotter
Heat can warp or ruin the plotter if it is left in the sunlight. Replacement plotters may be purchased from Piper dealers and distributors. The “Basic Empty Weight and Center of Gravity” location is taken from the Weight and Balance Form (Figure 6-5), the Weight and Balance Record (Figure 6-7) or the latest FAA major repair or alteration form.
Page 149 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-236, DAKOTA SAMPLE PROBLEM A sample problem will demonstrate the use of the weight and balance plotter. Assume a basic weight and C.G. location of 1800 pounds at 81.00 inches respectively. We wish to carry a pilot and 3 passengers. Two men weighing 180 and 200 pounds will occupy the front seats, and two children weighing 80 and 100 pounds will ride in the rear.
Page 150 PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-236, DAKOTA WEIGHT AND BALANCE SAMPLE PROBLEM ISSUED: AUGUST 1, 1980 REPORT: VB-910 6-12c...
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Page 152: Equipment List
Where no letter precedes an item, that item is not required equipment Unless otherwise indicated, the installation certification basis for the equipment included in this list is the aircraft’s approved type design. PIPER AIRCRAFT CORPORATION PA-28-236 DAKOTA SERIAL NO.
Page 177 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: JUNE 24, 1981 6-37a...
Page 196 7.29 Baggage Area ................7-24 7.31 Stall Warning ................7-24 7.33 Finish ..................7-24 7.35 Piper External Power ..............7-25 7.37 Emergency Locator Transmitter ..........7-25 7.39 Air Conditioning ................. 7-28 7.41 Carburetor Ice Detection System ..........7-29 ISSUED: JUNE 1, 1978...
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Page 198: The Airplane
PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-236, DAKOTA DESCRIPTION & OPERATION SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS 7.1 THE AIRPLANE The .PA-28-236 Dakota is a single-engine, low-wing monoplane of all metal construction. It has seating for up to four occupants and has a two hundred pound luggage compartment.
Page 199: Engine And Propeller
SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION & OPERATION PA-28-236, DAKOTA A vertical stabilizer, an all-movable horizontal stabilator, and a rudder make up the empennage. The stabilator incorporates an anti-servo tab which improves longitudinal stability and provides longitudinal trim. This tab...
Page 200: Induction System
PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-236, DAKOTA DESCRIPTION & OPERATION INDUCTION SYSTEM An induction scoop is located at the lower front of the cowling. This scoop is removable for access to the air filter which is attached to the air filter housing immediately behind the scoop.
Page 201 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION & OPERATION PA-28-236, DAKOTA MAIN WHEEL ASSEMBLY Figure 7-1 REPORT: VB-910 ISSUED: JUNE 1, 1978...
Page 202: Landing Gear
PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-236, DAKOTA DESCRIPTION & OPERATION LANDING GEAR The landing gears have 6.00 x 6 wheels. The main wheels (Figure 7-1) are equipped with hydraulically operated disc brakes. The nose wheel carries a four ply rating tube type tire and the main gear carry six ply rating tube type tires.
Page 203: Engine Controls
SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION & OPERATION PA-28-236, DAKOTA 7.11 ENGINE CONTROLS Engine controls consist of a throttle control, a propeller control and a mixture control lever. These controls are located on the control quadrant on the lower center of the instrument panel (Figure 7-3) where they are accessible to both the pilot and the copilot.
Page 204 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-236, DAKOTA DESCRIPTION & OPERATION CONTROL QUADRANT AND CONSOLE Figure 7-3 ISSUED: JUNE 1, 1978 REPORT: VB-910...
Page 205 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION & OPERATION PA-28-236, DAKOTA FLIGHT CONTROL CONSOLE Figure 7-5 REPORT: VB-910 ISSUED: JUNE 1, 1978...
Page 206: Flight Controls
PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-236, DAKOTA DESCRIPTION & OPERATION 7.13 FLIGHT CONTROLS Dual controls are provided as standard equipment, with a cable system used between the controls and the surfaces. The horizontal tail is of the all- movable slab type, with an anti-servo tab which also acts as a longitudinal trim tab, actuated by a control mounted on the control tunnel between the two front seats (Figure 7-5).
Page 207 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION & OPERATION PA-28-236, DAKOTA FUEL SELECTOR Figure 7-7 Fuel quantity and pressure are indicated on gauges on the instrument panel. There is a separate fuel quantity gauge for each tank. Each fuel tank has an individual quick drain located at the bottom inboard rear corner (see Figure 8-3).
Page 208 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-236, DAKOTA DESCRIPTION & OPERATION FUEL SYSTEM SCHEMATIC Figure 7-9 ISSUED: JUNE 1, 1978 REPORT: VB-910 7-11...
Page 209: Electrical System
SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION & OPERATION PA-28-236, DAKOTA 7.17 ELECTRICAL.SYSTEM The electrical system includes a 14-volt, 60 amp alternator, a voltage regulator, an overvoltage relay, and a master switch relay (Figure 7-11 ). The 12-volt battery is mounted in a thermoplastic box immediately aft of the baggage compartment.
Page 210 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-236, DAKOTA DESCRIPTION & OPERATION ALTERNATOR AND STARTER SCHEMATIC Figure 7-11 ISSUED: JUNE 1, 1978 REPORT: VB-910 REVISED: FEBRUARY 2, 1981 7-13...
Page 211 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION & OPERATION PA-28-236, DAKOTA NOTE On airplanes with interlocked BAT and ALT switches, the ALT switch is mechanically interlocked with the BAT switch. When ALT switch is turned ON, the BAT switch will also be turned ON.
Page 212 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-236, DAKOTA DESCRIPTION & OPERATION CIRCUIT BREAKER PANEL Figure 7-13 ISSUED: JUNE 1, 1978 REPORT: VB-910 7-15...
Page 213: Vacuum System
SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION & OPERATION PA-28-236, DAKOTA 7.19 VACUUM SYSTEM* The vacuum system operates the air driven gyro instruments. This system consists of an engine-driven vacuum pump, a vacuum regulator, a filter, a vacuum gauge, the necessary plumbing, and, when installed, the directional and attitude gyro instruments.
Page 215: Pitot-Static System
SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION & OPERATION PA-28-236, DAKOTA switch is also provided to give auxiliary power to the avionics bus in the event of a radio master switch circuit failure. The emergency bus switch is located behind the lower right shin guard left of the circuit breaker panel. An annunciator panel is mounted in the upper instrument panel to warn the pilot of a possible malfunction in the alternator, oil pressure or vacuum systems.
Page 217: Heating And Ventilating System
SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION & OPERATION PA-28-236, DAKOTA 7.25 HEATING AND VENTILATING SYSTEM The heating system is designed to supply warm air to the cabin during winter and cool weather flights. The system includes a heat shroud, heat ducts, defroster outlets, heat and defroster controls.
Page 219: Cabin Features
SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION & OPERATION PA-28-236, DAKOTA 7.27 CABIN FEATURES All seat backs have three positions: normal, intermediate and recline. The adjustment lever is located at the base of the seat back on the outboard side of the seat. The front seats adjust fore and aft for ease of entry and occupant comfort.
Page 220 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-236, DAKOTA DESCRIPTION & OPERATION CABIN DOOR LATCH Figure 7-21 ISSUED: JUNE 1, 1978 REPORT: VB-910 7-23...
Page 221: Baggage Area
SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION & OPERATION PA-28-236, DAKOTA 7.29 BAGGAGE AREA A 24 cubic foot baggage area, located behind the rear seats, is accessible either from the cabin or through an outside baggage door on the right side of the aircraft.
Page 222: Piper External Power
DESCRIPTION & OPERATION 7.35 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 wing. 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 223 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION & OPERATION PA-28-236, DAKOTA To use the ELT as a portable unit in an emergency, remove the cover and unlatch the unit from its mounting base. The antenna cable is disconnected by a left quarter-tum of the knurled nut and a pull. A sharp tug on the two small wires will break them loose.
Page 224 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-236, DAKOTA DESCRIPTION & OPERATION NOTE If the switch has been placed in the ON position for any reason, the OFF position has to be selected before selecting ARM. If ARM is selected directly from the ON position, the unit will continue to transmit in the ARM position.
Page 225 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION & OPERATION PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: MAY 4, 1990 7-27a...
Page 226 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-236, DAKOTA DESCRIPTION & OPERATION NOTE The warning light will not blink if the ELT is activated by an incident that also results in severance of the airplane’s power supply lines. Should the ELT be activated inadvertently it can be reset by either...
Page 227: Air Conditioning
SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION & OPERATION PA-28-236, DAKOTA 7.39 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.
Page 228: Carburetor Ice Detection System
PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-236, DAKOTA DESCRIPTION & OPERATION The FAN switch allows operation of the fan with the air conditioner turned OFF to aid cabin air circulation if desired. A “LOW,” “MED” or “HIGH” flow of air can be selected to the air conditioner outlets located in the overhead duct.
Page 229 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION & OPERATION PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: JUNE 1, 1978 7-30...
Page 230 TABLE OF CONTENTS SECTION 8 AIRPLANE HANDLING, SERVICING AND MAINTENANCE Paragraph Page General ..................8-1 Airplane Inspection Periods ............8-2 Preventive Maintenance ............. 8-3 Airplane Alterations ..............8-4 Ground Handling ................ 8-5 8.11 Engine Air Filter ................. 8-8 8.13 Brake Service ................8-9 8.15 Landing Gear Service ..............
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Page 232: General
This information is provided to all authorized Piper Service Centers. 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 233: Airplane Inspection Periods
Bulletins, Service Letters, and Service Spares Letters. This service is available to interested persons, such as owners, pilots, and mechanics at a nominal fee, and may be obtained through an authorized Piper Service Center or Piper’s Customer Services Department. Maintenance manuals, parts catalogs, and revisions to both are available from Piper Service Centers or Piper’s Customer Services Department.
Page 234: Preventive Maintenance
PIPER AIRCRAFT CORPORATION SECTION 8 PA-28-236, DAKOTA HANDLING, SERV & MAINT A spectographic analysis of the engine oil is available from several sources. This inspection, if performed properly, provides a good check of the internal condition of the engine. To be accurate, induction air filters must be cleaned or changed regularly, and oil samples must be taken and sent in at regular intervals.
Page 235: Airplane Alterations
SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING, SERV & MAINT PA-28-236, DAKOTA 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 236: Ground Handling
PIPER AIRCRAFT CORPORATION SECTION 8 PA-28-236, DAKOTA HANDLING, SERV & MAINT 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 in the rear baggage compartment or by power equipment that will not damage or excessively strain the nose gear steering assembly.
Page 237 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING, SERV & MAINT PA-28-236, DAKOTA (b) Taxiing Before attempting to taxi the airplane, ground personnel should be instructed and approved by a qualified person authorized by the owner. Engine starting and shut-down procedures as well as taxi techniques should be covered.
Page 238 PIPER AIRCRAFT CORPORATION SECTION 8 PA-28-236, DAKOTA HANDLING, SERV & MAINT (2) Set the parking brake by pulling back on the brake lever and depressing the knob on the handle. To release the parking brake, pull back on the handle until the catch disengages;...
Page 239: Brake Service
PIPER AIRCRAFT CORPORATION SECTION 8 PA-28-236, DAKOTA HANDLING, SERV & MAINT 8.13 BRAKE SERVICE The brake system is filled with MIL-H-5606 (petroleum base) hydraulic brake fluid. The fluid level should be checked periodically or at every 50 hour inspection and replenished when necessary. The brake reservoir is located on the left side of the fire wall in the engine compartment.
Page 241: Propeller Service
PIPER AIRCRAFT CORPORATION SECTION 8 PA-28-236, DAKOTA HANDLING, SERV & MAINT If fluid is below the bottom of the filler plug hole, oil should be added. Replace the plug with the valve core removed. Then attach a clear plastic hose to the valve stem of the filler plug and submerge the free end in a container of hydraulic fluid (MIL-H-5606).
Page 242: Oil Requirements
SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING, SERV & MAINT PA-28-236, DAKOTA 8.19 OIL REQUIREMENTS The oil capacity of the Lycoming 0-540 series engine is 12 quarts, and the minimum safe quantity is 2-3/4 quarts. It is recommended that engine oil be drained and replenished every 50 hours: The oil filter element should be changed every 50 hours of operation.
Page 243 PIPER AIRCRAFT CORPORATION SECTION 8 PA-28-236, DAKOTA HANDLING, SERV & MAINT Whenever 100 or 100LL grade fuel is not available, commercial grade 100/130 should be used; (See Fuel Grade Comparison Chart) Refer to the latest issue of Lycoming Service Instruction No. 1070 for additional information.
Page 244 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING, SERV & MAINT PA-28-236, DAKOTA FUEL TANK DRAIN Figure 8-3 (c) Filling Fuel Tanks Observe all safety precautions required when handling gasoline. Fill the fuel tanks through the filler located on the forward slope of the wing.
Page 245: Tire Inflation
PIPER AIRCRAFT CORPORATION SECTION 8 PA-28-236, DAKOTA HANDLING, SERV & MAINT (e) Draining Fuel System The bulk of the fuel may be drained from the fuel cells by the use of a siphon hose placed in the cell or tank through the filler neck.
Page 246: Cleaning
SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING, SERV & MAINT PA-28-236, DAKOTA 8.27 CLEANING (a) Cleaning Engine Compartment Before cleaning the engine compartment, place a strip of tape on the magneto vents to prevent any solvent from entering these units. (1) Place a large pan under the engine to catch waste.
Page 247 PIPER AIRCRAFT CORPORATION SECTION 8 PA-28-236, DAKOTA HANDLING, SERV & MAINT (3) Allow the solvent to remain on the gear from five to ten minutes. Then rinse the gear with additional solvent and allow to dry. (4) Remove the cover from the wheel and remove the catch pan.
Page 248 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING, SERV & MAINT PA-28-236, DAKOTA (3) Remove oil and grease with a cloth moistened with kerosene. CAUTION Do not use gasoline, alcohol, benzene, carbon tetrachloride, thinner, acetone, or window cleaning sprays. (4) After cleaning plastic surfaces, apply a thin coat of hard polishing wax.
Page 249 Piper Electric Pitch Trim ............9-11 Air Conditioning System Installation ......... 9-17 Century 21 Autopilot ..............9-19 Piper Control Wheel Clock Installation ........9-23 KNS 80 Navigation System ............9-25 KAP 100 Series Flight Control System ........9-29 KAP 150 Series Flight Control System ........9-49 Auxiliary Vacuum System ............
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Page 251: General
PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENTS SECTION 9 SUPPLEMENTS 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 252 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: JUNE 1, 1978...
Page 253: Autoflite Ii Autopilot Installation
PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA 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 in accordance with STC SA3066SW-D. The information contained within this supplement is to be used in conjunction with the complete handbook.
Page 254 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-236, DAKOTA SECTION 4 - NORMAL PROCEDURES PREFLIGHT INSPECTION (a) AutoFlite II master switch - ON. (b) Rotate turn command knob to left and right. Aircraft control wheels should rotate in corresponding directions. (c) With AutoFlite II on, rotate aircraft control wheel to left and right.
Page 255 PIPER AIRCRAFT CORPORATION PIPER AIRCRAFT CORPORATION SECTION 9 SECTION 8 PA-28-236, DAKOTA PA-28-236, DAKOTA HANDLING, SERV & MAINT SUPPLEMENTS (2) Trim knob - push IN for high sensitivity. Use high sensitivity position for localizer tracking and as desired for OMNI tracking.
Page 256 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: JUNE 1, 1978...
Page 257: Autocontrol Iiib Autopilot Installation
SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Piper AutoControl IIIB is installed in accordance with STC SA3065SW-D. The information contained within this supplement is to be used in conjunction with the complete handbook.
Page 258 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-236, DAKOTA (e) Emergency operation with optional NSD 360A (HSI) - Slaved and / or Non-Slaved: NSD 360A (l) Appearance of HDG flag: Check air supply gauge (vac or pressure) for adequate air supply (4 in. Hg. min.).
Page 259 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENTS NOTE In the localizer mode, the TO-FROM arrows may remain out of view, depending upon the design of the NAV converter used in the installation. SECTION 4 - NORMAL PROCEDURES PREFLIGHT INSPECTION...
Page 260 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-236, DAKOTA (c) Roll Section (1) To engage, center ROLL knob, push AP 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 261 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENTS (3) ILS - Back Course Set inbound, front localizer course on O.B.S. (HSI Course Knob). Select LOC-REV on radio coupler to intercept and track inbound on the back localizer course. Select LOC-NORM to intercept outbound on the back course to the procedure turn area.
Page 262 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: JUNE 1, 1978 9-12...
Page 263: 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 264 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-236, DAKOTA SECTION 4 - NORMAL PROCEDURES The electric trim system may be buried ON or OFF by a switch located above the ignition switch. The pitch trim may be changed when the electric trim system is turned on either by moving the manual pitch trim control wheel or by operating the trim control switch on the pilot’s control yoke.
Page 265: Climb Performance
PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA 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 in conjunction with the complete handbook.
Page 266 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-236, DAKOTA SECTION 3 - EMERGENCY PROCEDURES No changes to the basic Emergency Procedures provided by Section 3 of this Pilot’s Operating Handbook are necessary for this supplement. SECTION 4 - NORMAL PROCEDURES Prior to takeoff, the air conditioner should he checked for proper operation as follows: (a) Check aircraft master switch “ON.”...
Page 267 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENTS NOTE To insure maximum climb performance the air conditioner must be turned off manually before takeoff to disengage the compressor and retract the condenser door. Also the air conditioner must be turned off manually before the landing approach in preparation for a possible go- around.
Page 268 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: JUNE 1, 1978 9-18...
Page 269: Century 21 Autopilot
PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENTS SUPPLEMENT 5 CENTURY 21 AUTOPILOT INSTALLATION SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Century 21 Autopilot is installed in accordance with STC SA3352S W. The information contained within this supplement is to be used in conjunction with the complete handbook.
Page 270 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-236, DAKOTA (1) Altitude Loss During Malfunction: An autopilot malfunction during climb, cruise or descent w i t h a 3 second delay in recovery initiation could result in as much as 60° of bank and 320’ altitude Joss. Maximum altitude Joss was recorded at 155 KIAS during descent.
Page 271 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENTS - NOTE - Dead slaving meter needle or a needle displaced fully one direction indicates a slaving system failure. 5. Select slaving amplifier No. 2, if equipped. Reset heading card while checking slaving meter. If proper slaving indication is not obtained, switch to free gyro mode and periodically set card as an unslaved gyro.
Page 272 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-236, DAKOTA (b) AUTOPILOTWITH STANDARD D.G. (l) Engage autopilot. (2) Control wheel movement should correspond to HDG command input. (3) Grasp control wheel and override roll servo actuator to assure override capability. (4) With HDG bug centered select NAV or APPR mode and note control wheel movement toward VOR needle offset.
Page 273: 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 274 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-236, DAKOTA (b) DATE SETTING Pressing the RST button once will cause the date to appear with the month flashing. Pressing the ST-SP button will advance the month at one per second, or at one per push, until the right month appears.
Page 275: Kns 80 Navigation System
PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENTS SUPPLEMENT 7 KNS 80 NAVIGATION SYSTEM SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the optional KNS 80 Navigation System is installed. The information contained within this supplement is to be used in conjunction with the complete handbook.
Page 276 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-236, DAKOTA SECTION 4 - NORMAL PROCEDURES (a) KNS 80 OPERATION The KNS 80 can be operated in any of 3 basic modes: (a) VOR, (b) RNAV, or (c) ILS. To change from one mode to another, the...
Page 277 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENTS (5) DSP BUTTON Momentary pushbutton. Causes displayed waypoint to increment by 1 and data display to go to frequency mode. (6) DATA BUTTON Momentary pushbutton. Causes waypoint data display to change from FRQ to RAD to DST and back to FRQ.
Page 278 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-236, DAKOTA SECTION 5- PERFORMANCE No changes to the basic performance provided by Section 5 of this Pilot’s Operating Handbook are necessary for this supplement. REPORT: VB-910 ISSUED: DECEMBER 10, 1980 9-28...
Page 279: Kap 100 Series Flight Control System
PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 8 PILOT’S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 8 KING KAP 100 SERIES FLIGHT CONTROL SYSTEM This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when the King KAP 100 Series Flight Control System is installed in accordance with STC SA1565CE-D.
Page 280 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 8 PA-28-236, DAKOTA SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the optional King KAP 100 Series Flight Control System is installed. The Flight Control System must be operated within the limitations herein specified.
Page 281 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 8 SECTION 4 - NORMAL PROCEDURES (a) PREFLIGHT (PERFORM PRIOR TO EACH FLIGHT) (1) GYROS - Allow 3-4 minutes for gyros to come up to speed. (2) RADIO POWER Switch - ON (3) PREFLIGHT TEST BUTTON - PRESS momentarily and NOTE: All annunciator lights on (TRIM annunciator flashing).
Page 282 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 8 PA-28-236, DAKOTA (2) Autopilot Engagement AP ENG Button - PRESS. Note AP annunciator on. lf no other modes are selected the autopilot will operate in the wings level mode. (3) Heading Changes Manual Heading Changes CWS Button- PRESS and MANEUVER aircraft to the desired heading.
Page 283 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 8 NAV Mode Selector Button - PRESS. If the Course Deviation Bar is greater than 2 to 3 dots: the aircraft will continue in HDG mode (or wings level if HDG not selected) with the NAV annunciator flashing;...
Page 284 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 8 PA-28-236, DAKOTA (5) Approach (APR) Coupling When equipped with HSI Course Bearing Pointer - SET to desired course. NOTE When equipped with NAV 1 /NAV 2 switching and NAV 2 is selected, set OBS to the desired course.
Page 285 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 8 If the D-Bar is greater than 2 to 3 dots: the autopilot will annunciate HDG mode and APR flashing; when the computed capture point is reached the HDG annunciator will go out, the APR annunciator will illuminate steady and the selected course will be automatically captured and tracked.
Page 286 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 8 PA-28-236, DAKOTA Heading Selector Knob - ROTATE Bug to the ILS front course inbound heading. NOTE When BC is selected, the lateral operating mode will change from HDG (if selected) to wings level for 5 seconds. A 45° intercept angle will then be established based on the position of the bug.
Page 287 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 8 SECTION 7- DESCRIPTION AND OPERATION The KAP 100 Autopilot is certified in this airplane with roll axis control. The various instruments and the controls for the operation of the KAP 100 Autopilot are described in Figures 7-1 thru 7-11.
Page 288 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 8 PA-28-236, DAKOTA KC 190 AUTOPILOT COMPUTER Figure 7-1 1. KAP 100 AUTOPILOT COMPUTER - Complete Autopilot computer to include system mode annunciators and system controls. 2. MODE ANNUNCIATORS -Illuminate when a mode is selected by the corresponding mode selector button (PUSH ON- PUSH OFF).
Page 289 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 8 Figure 7-1 (cont) 6. PREFLIGHT TEST (TEST) BUTTON - When momentarily pushed, initiates preflight test sequence which automatically turns on all annunciator lights, tests the roll rate monitor, checks the manual trim drive voltage, checks the manual electric trim monitor and tests all autopilot valid and dump logic.
Page 290 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 8 PA-28-236, DAKOTA KG 258 VERTICAL GYRO Figure 7-3 1. KG 258 VERTICAL GYRO - Displays airplane attitude as a conventional attitude gyro. The gyro is air driven. 2. ROLL ATTITUDE INDEX- Displays airplane roll attitude with respect to the roll attitude scale.
Page 291 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 8 KI 204/206 VOR/LOC/ GLIDE SLOPE INDICATOR (TYPICAL) Figure 7-5 1. VOR/LOC/GLIDE SLOPE INDICATOR- Provides rectilinear display of VOR/LOC and Glide slope deviation. 2. COURSE INDEX - Indicates selected VOR course. 3. COURSE CARD - Indicates selected VOR course under course index.
Page 292 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 8 PA-28-236, DAKOTA Figure 7-5 (cont) 8. GLIDE SLOPE SCALE - Indicates displacement from glide slope beam center. A glide slope deviation needle displacement of 5 dots, represents full scale (0.7°) deviation above or below glide slope beam centerline.
Page 293 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 8 Figure 7-7 ( cont) 1. KI 525A HORIZONTAL SITUATION INDICATOR (HSI) - Provides a pictorial presentation of aircraft deviation relative to VOR radials or localizer beams. It also displays glide slope deviations and gives heading reference with respect to magnetic north.
Page 294 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 8 PA-28-236, DAKOTA Figure 7-7 (cont) 13. COURSE DEVIATION SCALE - A course deviation bar displacement of 5 dots represents full scale (VOR = ± 10°, LOC = ±2 1/ 2°, RNAV = 5NM, RNAV APR- 1 1/4NM) deviation from beam centerline.
Page 295 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 8 Figure 7-9 (cont) 1. KG 107 NON-SLAVED DIRECTIONAL GYRO (DG) - Provides a stable visual indication of aircraft heading to the pilot. The gyro is air driven. 2. LUBBER LINE - Indicates aircraft magnetic heading on compass card (4).
Page 296 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 8 PA-28-236, DAKOTA AUTOPILOT CONTROL WHEEL SWITCH CAP Figure 7-11 1. AUTOPILOT CONTROL WHEEL SWITCH CAP - Molded plastic unit mounted on the left horn of the pilot’s control wheel which provides mounting for three switch units associated with the autopilot and manual electric trim systems (only used with optional manual electric trim).
Page 297 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 8 The airplane MASTER SWITCH function is unchanged and can be used in an emergency to shut off electrical power to all flight control systems while the problem is isolated. The RADIO POWER switch supplies power to the avionics bus bar of the radio circuit breakers and the autopilot circuit breaker.
Page 298 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 8 PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: JULY 23, 1982 9-48...
Page 299: Kap 150 Series Flight Control System
PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 9 PILOT’S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 9 KING KAP 150 SERIES FLIGHT CONTROL SYSTEM This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when the King KAP 150 Series Flight Control System is installed in accordance with STC SA1565CE-D.
Page 300 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 PA-28-236, DAKOTA SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the optional King KAP 150 Series Flight Control System is installed. The Flight Control System must be operated within the limitations herein specified.
Page 301 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 9 (b) In case of Electric Trim Malfunction (either manual electric or autotrim): (1) AP DISC/TRIM INTER Switch - PRESS and HOLD throughout recovery. (2) PITCH TRIM Circuit Breaker - PULL. (3) Aircraft - RETRIM manually.
Page 302 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 PA-28-236, DAKOTA (4) MANUAL ELECTRIC TRIM- TEST as follows: Actuate the left side of the split switch to the fore and aft positions. The trim wheel should not move on its own. Rotate the trim wheel manually against the engaged clutch, to check the pilot’s overpower capability.
Page 303 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 9 Using Vertical Trim VERTICAL TRIM Control - PRESS .either up or down to modify aircraft attitude at a rate of .7 deg / sec. up to the pitch limits of +15° or -10°.
Page 304 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 PA-28-236, DAKOTA b. Heading Hold Heading Selector Knob - SET BUG to desired heading, HDG Mode Selector Button - PRESS. Note HDG mode annunciator ON. Autopilot will automatically turn the aircraft to the selected heading.
Page 305 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 9 Heading Selector Knob -ROTATE BUG to agree with OBS course. NOTE When NAV is selected, the lateral operating mode will change from HDG (if selected) to wings level for 5 seconds. A 45° intercept angle will then be automatically established based on the position of the bug.
Page 306 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 PA-28-236, DAKOTA If the D-Bar is less than 2 to 3 dots: the HDG mode will disengage upon selecting APR mode; the APR annunciator will illuminate steady and the capture/ track sequence will automatically begin.
Page 307 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 9 HEADING Selector Knob - SET BUG to provide desired intercept angle. BC Mode Selector Button - PRESS. If the Course Deviation Bar is greater than 2 to 3 dots: the aircraft will continue in HDG mode (or wings level if HDG not selected) with BC annunciated steady and APR annunciator flashing;...
Page 308 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 PA-28-236, DAKOTA If the D-Bar is less than 2 to 3 dots: the HDG mode will disengage upon selecting BC mode; the APR BC annunciator will illuminate steady and the capture/ track sequence will automatically begin.
Page 309 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 9 (11) Before Landing AP DISC/TRIM INTER Switch - PRESS to disengage AP. (c) FLIGHT DIRECTOR OPERATION (KFC 150 SYSTEMS ONLY) NOTE The flight director modes of operation are the same as those used for autopilot operations...
Page 310 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 PA-28-236, DAKOTA The following conditions will cause the Autopilot to automatically disengage: (a) Power failure. (b) Internal Flight Control System failure. (c) With the KCS 55A Compass System, a loss of compass valid (displaying HDG flag) disengages the Autopilot when a mode using heading information is engaged.
Page 311 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 9 Figure 7-1 (cont) KFC 150 SYSTEM KC 192 AUTOPILOT COMPUTER - Complete Flight Director and Autopilot computer to include system mode annunciators and system controls. MODE ANNUNCIATORS - Illuminates when a mode is selected...
Page 312 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 PA-28-236, DAKOTA Figure 7-1 (cont) 8. BACK COURSE APPROACH (BC) MODE SELECTOR BUTTON - When pushed, will select the Back Course Approach mode. This mode functions identically to the approach mode except that response to LOC signals is reversed. Glide slope coupling is inhibited in the Back Course Approach mode.
Page 313 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 9 KC 191 AUTOPILOT COMPUTER Figure 7-3 KFC 150 SYSTEM KC 191 AUTOPILOT COMPUTER - Complete Flight Director and Autopilot computer to include system mode annunciators and system controls. VERTICAL TRIM CONTROL - A spring loaded to center rocker switch which will provide up or down pitch command changes: while in ALT will adjust altitude at rate of about 500 fpm;...
Page 314 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 PA-28-236, DAKOTA Figure 7-3 (cont) 5. TRIM WARNING LIGHT (TRIM) - Illuminates continuously whenever trim power is not on or the system has not been preflight tested. Flashes and is accompanied by an audible warning whenever a manual trim fault is detected.
Page 315 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 9 Figure 7-3 (cont) 11. NAVIGATION (NAV) MODE SELECTOR BUTTON - When pushed, will select the Navigation mode. The mode provides all angle intercept (with HSI) or a fixed angle intercept of 45° (with DG), automatic beam capture and tracking of VOR, RNAV or LOC signals.
Page 316 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 PA-28-236, DAKOTA KI 256 FLIGHT COMMAND INDICATOR Figure 7-5 1. KI 256 FLIGHT COMMAND INDICATOR (FCI) - Displays airplane attitude as a conventional attitude gyro and displays commands for flight director operation. The gyro is air driven.
Page 317 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 9 KG 258 VERTICAL GYRO Figure 7-7 KG 258 VERTICAL GYRO - Displays airplane attitude as a conventional attitude gyro. The gyro is air driven. ROLL ATTITUDE INDEX- Displays airplane roll attitude with respect to the roll attitude scale.
Page 318 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 PA-28-236, DAKOTA KI 256 FLIGHT COMMAND INDICATOR Figure 7-5 1. KI 525A HORIZONTAL SITUATION INDICATOR (HSI) - Provides a pictorial presentation of aircraft deviation relative to VOR radials or localizer beams. It also displays glide slope deviations and gives heading reference with respect to magnetic north.
Page 319 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 9 Figure 7-9 (coot) COURSE BEARING POINTER- Indicates selected VOR course or localizer course on compass card (10}. The selected VOR radial or localizer heading remains set on the compass card when the compass card (10) rotates.
Page 320 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 PA-28-236, DAKOTA KG 107 NON-SLAVED DIRECTIONAL GYRO Figure 7-11 1. KG 107 NON-SLAVED DIRECTIONAL GYRO (DG) -Provides a stable visual indication of aircraft heading to the pilot. The gyro is air driven. 2. LUBBER LINE- Indicates aircraft magnetic heading on compass card (4).
Page 321 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 9 KI 204/206 VOR/LOC/ GLIDE SLOPE INDICATOR (TYPICAL) Figure 7-13 VOR/LOC/GLIDE SLOPE INDICATOR - Provides rectilinear display of VOR/LOC and glide slope deviation. COURSE INDEX - Indicates selected VOR course. COURSE CARD - Indicates selected VOR course under course index.
Page 322 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 PA-28-236, DAKOTA Figure 7-13 (cont) 8. GLIDE SLOPE SCALE - Indicates displacement from glide slope beam center. A glide slope deviation needle displacement of 5 dots, represents full scale (0.7°) deviation above or below glide slope beam centerline.
Page 323 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 9 Figure 7-15 (cont) AUTOPILOT CONTROL WHEEL SWITCH CAP - Molded plastic unit mounted on the left horn of the pilot’s control wheel which provides mounting for three switch units associated with the autopilot and manual electric trim systems.
Page 324 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 9 PA-28-236, DAKOTA The airplane MASTER SWITCH function is unchanged and can be used in an emergency to shut off electrical power to all flight control systems while the problem is isolated. The RADIO POWER switch supplies power to the avionics buss bar of the radio circuit breakers and the autopilot circuit breaker.
Page 325: Auxiliary Vacuum System
This supplement must be attached to the Piiot’s Operating Handbook and FAA Approved Airplane Flight Manual when the Piper Auxiliary Vacuum System is installed in accordance with Piper Drawing No. 87775-2. The information contained herein supplements or supersedes the basic Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed.
Page 326 PA-28-236, DAKOTA SECTION 1- GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Piper Auxiliary Vacuum System is installed. The information contained within this supplement is to be used in conjunction with the complete handbook.
Page 327 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 10 SECTION 4 - NORMAL PROCEDURES 1. Preflight Check. Turn battery switch on and verify that VAC OFF light is illuminated. NOTE Due to electrical power requirements of the auxiliary vacuum pump it is suggested that the engine be operating while making the following checks.
Page 328 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 10 PA-28-236, DAKOTA SECTION 7 · DESCRIPTION AND OPERATION The auxiliary dry air pump system provides an independent back-up source of pneumatic power to operate the gyro flight instruments in the event the engine driven air pump fails.
Page 330 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 10 PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: OCTOBER 14, 1986 9-80...
Page 331: Century 31 Autopilot
PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 11 PILOT’S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 11 CENTURY 31 AUTOPILOT MODEL AK924 This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when the Century 31 Autopilot System Model AK924 is installed in accordance with STC SA5680SW.
Page 332 SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Century 31 Autopilot Model AK924 is installed in accordance with FAA Approved Piper data. SECTION 2- LIMITATIONS 1. Autopilot OFF during takeoff and landing.
Page 333 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 11 Autopilot is disconnected by: (1.) Pressing AP OFF bar on pilot’s trim switch. (2.) Pressing the AP ON-OFF switch on the programmer OFF. (3.) Depressing master disconnect switch. Autotrim is disconnected by: (1.) Any action in step a.
Page 334 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 11 PA-28-236, DAKOTA (3.) With card disabled VOR/Localizer and glide slope displays are still functional; use card set to rotate card to aircraft heading for correct picture. (4.) Slaving Failure - (i.e. failure to self correct for gyro drift): (a.) Check gyro slaving switch is set to No.
Page 335 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 11 SECTION 4 - NORMAL PROCEDURES 1. PREFLIGHT PROCEDURES NOTE During system functional check the system must be provided adequate de voltage (12.0 Vdc min.) and instrument air (4.8 in. Hg. min.).
Page 336 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 11 PA-28-236, DAKOTA (14.) Press the DN switch - the TEST light remains off as long as the DN switch is held. (15.) Press the UP switch - the TEST light remains off as long as the UP switch is held.
Page 337 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 11 For navigation operations select modes as required by the operation being conducted and in accordance with the mode description provided in Section 7.1. For specific instructions relating to coupled instrument approach operations, refer to Special Operations and Information.
Page 338 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 11 PA-28-236, DAKOTA NOTE The autopilot will not decouple from the GS or localizer in the event of radio failure, however, warnings will flash in the mode appropriate to the failure. Monitor course guidance raw data during the approach to assure signal quality.
Page 339 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 11 The Century 31 is activated with the aircraft master switch and operates in a low power state until the autopilot is engaged. Mode selection is made by pushing the desired mode switch on the mode programmer. The selected mode will illuminate on the annunciator panel.
Page 340 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 11 PA-28-236, DAKOTA 7.1 COCKPIT CONTROLS AND FUNCTIONS ID 762-C CONTROLLER/FLIGHT COMPUTER Figure 7-1 1. Trim System Master switch (Figure 7-3) - provides power for all autotrim and control wheel electric trim operations. 2. Autopilot ON - OFF switch- Momentary rocker type switch which engages or disengages the autopilot roll, pitch and trim servos and lights or extinguishes autopilot (AP) annunciator, as appropriate.
Page 341 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 11 Figure 7-1 (cont) 4. NAV (Navigation) Mode Selector switch - provides automatic 45° VOR-LOC intercept angle; tracking and crosswind correction. The autopilot utilizes the HDG bug as the VOR course reference and a...
Page 342 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 11 PA-28-236, DAKOTA Figure 7-1 (cont) the modifier UP or DN will cause a pitch attitude change at a rate of 0. 7° per second. In ALT mode, actuation of the pitch modifier will cause the autopilot to enter the ATT mode with subsequent operation as described above.
Page 343 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 11 GS mode activation (GS capture) is. indicated by the active pitch mode annunciator extinguishing, leaving only the GS annunciator lighted. Since GS mode activation results from a combination of position and rate information, GS capture will...
Page 344 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 11 PA-28-236, DAKOTA HDG mode annunciator. Selected angle intercepts of over 60° are not recommended. NOTE If radio information becomes invalid (Flag) after initiation of a selected angle intercept the applicable navigation mode annunciator will flash and the autopilot will remain in HDG mode.
Page 345 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 11 (a.) Interlocks Autopilot engagement is inhibited unless an excitation signal is being provided to the attitude gyro. Selection of ALT mode is inhibited if the system altitude information is unreliable or if the entire system has not been powered for approximately 3 minutes to allow stabilization of the altitude source.
Page 346 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 11 PA-28-236, DAKOTA b. REMOTE CONTROL SWITCHES AUTOPILOT CONTROL WHEEL SWITCH CAP Figure 7-3 (l) Command trim switch - Split action type switch requiring the top bar to be depressed and the rocker to be moved fore or aft to cause the electric trim to function from the control wheel switch.
Page 347 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 11 7.3 INSTRUMENTS ATTITUDE GYRO Figure 7-5 (1.) Standard 3 inch air driven attitude indicator gyro. (2.) Symbolic airplane - Serves as a stationary symbol of the aircraft. Aircraft pitch and roll attitudes are displayed by the relationship between the fixed symbolic aircraft and the movable background.
Page 348 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 11 PA-28-236, DAKOTA NSD-360A NAVIGATION SITUATION DISPLAY Figure 7-7 (1.) NSD-360A Compass System - (For details of any other compass system, refer to manufacturer’s information.) (2.) Slaving Meter - Oscillation of needle indicates that compass is slaved to magnetic flux detector.
Page 349 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 11 DIRECTIONAL GYRO Figure 7-9 1. Non-slaved directional gyro - Provides a stable visual indication of aircraft heading to the pilot. The gyro is air driven. 2. Lubber line - Indicates aircraft magnetic heading on compass card (4).
Page 350 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 11 PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: OCTOBER 14, 1986 9-100...
Page 351 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 12 PILOT’S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 12 BENDIX/KING KLN 90A GPS NAVIGATION SYSTEM WITH KAP 100/150 AUTOPILOT SYSTEM This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when the optional Bendix/King KLN 90A GPS Navigation System is installed per Equipment List.
Page 352 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 12 PA-28-236, DAKOTA SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Bendix/King KLN 90A GPS Navigation System is installed. The Navigation System must be operated within the limitations herein specified.
Page 353 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 12 SECTION 2 - LIMITATIONS A. The KLN 90A GPS Pilot’s Guide, Bendix/King p/n 006-08743-0000, dated September 1993 (or later applicable revision) must be immediately available to the flight crew whenever navigation is predicated on the use of the system.
Page 354 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 12 PA-28-236, DAKOTA SECTION 4 - NORMAL PROCEDURES (CONT’D) (c) EXTERNAL ANNUNCIATORS: (OPTIONAL) Waypoint (WPT) Approximately 36 seconds prior to reaching a direct to waypoint or 20 seconds prior to the beginning of turn anticipation (turn anticipation function enabled) the waypoint alert annunciator will begin flashing.
Page 355 This supplement must be attached to the Pilot’s Operating Handbook and the FAA Approved Airplane Flight Manual when the optional WX-1000/ WX-1000+ Stormscope System is installed per Piper Drawing CA34-2- 024-4. The information contained herein supplements or supersedes the information in the basic Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein.
Page 356 This supplement supplies information necessary for the operation of the airplane when the optional WX-1000 or WX-1000+ Stormscope system is installed in accordance with FAA Approved Piper data. SECTION 2 - LIMITATIONS (a) The WX-1000/WX-1000+ Stormscope system signal displays are not intended for the purpose of penetrating thunderstorm areas or areas of severe turbulence;...
Page 357 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-236, DAKOTA SUPPLEMENT 13 SECTION 5 - PERFORMANCE No change. SECTION 6 - WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in the Equipment List attached to the Pilot’s Operating Handbook.
Page 358 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENT 13 PA-28-236, DAKOTA WX-1000 STORMSCOPE Figure 7-1 REPORT: VB-910 ISSUED: DECEMBER 07, 1993 9-108, 4 of 4...
Page 359 TABLE OF CONTENTS SECTION 10 OPERATING TIPS Paragraph Page 10.1 General ..................10-1 10.3 Operating Tips ................10-1 ISSUED: JUNE 1, 1978 REPORT: VB-910 10-i...
Page 360 THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-910 ISSUED: JUNE 1, 1978 10-ii...
Page 361 PIPER AIRCRAFT CORPORATION SECTION 10 PA-28-236, DAKOTA OPERATING TIPS SECTION 10 OPERATING TIPS 10.1 GENERAL This section provides operating tips of particular value in the operation of the Dakota. 10.3 OPERATING 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 362 SECTION 10 PIPER AIRCRAFT CORPORATION OPERATING TIPS PA-28-236, DAKOTA (g) The rudder pedals are suspended from a torque tube which extends across the fuselage. The pilot should become familiar with the proper positioning of his feet on the rudder pedals so as to avoid interference with the torque tube when moving the rudder pedals or operating the toe brakes.

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