DAKOTA PILOT’S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL

5-2 Relocated info. from pg. 5-I; added Warning. 5-3,5-5, Revised para. 5.5 (a), (c), 5-6, 5-7 (d), (e), (f) and (g). 5-18 Revised fig. 5-15. 5-19 Revised fig. 5-17; revised footnote. 5-23 Revised figs. 5-23, 5-25, 5-27, thru 5-29, 5-31 and 5-33. 5-28 6-1, 6-2 Revised para. 6.1. 6-3 Added Caution; relocated fig. 6-1 to pg. 6-4. 6-4 Relocated fig. 6-1; relocated info. to pg. 6-5. 6-5 Relocated info. from pg. 6-4. 6-6 Revised fig. 6-5. 6-16 Revised item 23. 6-28 Removed item 185; relocated item 189 from pg. 6-29. REPORT: VB-910 ISSUED: JUNE 1, 1978 vi-b 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; added item 202. 6-33 Revised items 235 and 237. 6-34 Changed item 241 to 242 and item 243 to 244; added items 241 and 243; relocated items 245 and 2471:o pg. 6-35. 6-35 Relocated items 245 and 247; relocated item 251 to pg. 6-36. 6-36 Relocated item 251 from pg. 6-35; added item 252; relocated items 259 and 263 to pg. 6-37. 6-37 Relocated items 259 and 263 from pg. 6-36; added item 260; relocated item 271 to pg. 6-38. 6-38 Relocated item 271 from pg. 6-37. 6-44 Revised item 323. 6-45 Revised items 407 and 409. 7-12 Added Warning. Added optional light; moved info. to pg. 7-14. 7-14 Relocated info. from pg. 7-12. 7-16 Revised para. 7.21 7-17 Revised fig. 7-15. 7-20 Revised para. 7.25 7-21 Revised fig. 7-19. 8-11 Revised para. 8.15 Ward Evans 10-1 Revised para. 10.3 (f). Aug. 27, 1979 ISSUED: JUNE 1, 1978 REPORT: VB-910 vi-c Rev. 4 1-3 Revised para. I. 7 (c). 761 689 2-3 Revised fuel grade. (PR800801) 2-8 Added placard. 3-15 Revised para. 3.22. 4-10 Revised Normal Procedures checklist (Descent). 5-9 Revised List of Figures, added pgs. 5-31 and 5-32, added new figs. 5-39 and 5-41. 5-29 Revised fig. 5-35. 5-30 Revised fig. 5-37. 5-31 Added pg:, added new fig. 5-39. 5-32 Added pg.; added new fig. 5-41. 6-i Revised Table of Contents. 6-4 Added page. 6-5 Added page. 6-12 Relocated text to page 3-8b. 6-12a Added text from page 3-10. 6-12b Relocated text to page 3-9. 6-12c Added pg.; added new info. 6-12d Added pg. 6-17 Revised item 31. 6-19 Relocated items; added items 49 and 51. 6-20 Added items 65 and 67. 6-22 Added item 103b. 6-23 Added item 119. 6-24 Relocated item; added item 129. 6-25 Relocated item 151 to pg. 6-26; added item 137 from pg. 6-24. 6-26 Added item 151 from pg. 6-25; added new items 153 thru 159; renumbered items. 6-27 Relocated items from pg. 6-26; renumbered items. 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-d 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. 6-33 Relocated items; added new items 235 thru 245. 6-34 Relocated items; added new items 247 thru 251. 6-35 Relocated items from pg. 6-32 and pg. 6-33; renumbered items. 6-36 Relocated items .hom pg. 6~33 and pg. 6-34; renumbered items. 6-37 Relocated items from pg. 6-34 and pg. 6-35;· renumbered items. 6-38 Relocated items from pg. 6-35 and pg. 6-36; renumbered item:s. 6-39 Relocated items from pg. 6-36 and pg. 6-37; renumbered items; added new items 291 and 293. 6-40 Relocated items. from pg. 6-37; revised items 299 and 301; added new item 303; renumbered items. 6-41 Relocated items from pg. 6-37 and pg. 6-38; renumbered items. 6-42 Relocated items from pg. 6-39; renumbered items. 6-43 Relocated items from pg. 6-40; renumbered items. 6-44 Relocated items froin pg. 6-41; renumbered items. · 6-44a Relocated items from pg. 6-42; renumbered items. 6-44b Relocated items from pg. 6-43; renumbered items ISSUED: JUNE 1, 1978 REPORT: VB-910 vi-e Rev. 4 (cont) 6-45 Relocated items from pg. 6-44; renumbered items. 6-46 Relocated items from pg. 6-44a; renumbered items; relocated items 407 thru 411 from pg. 6-45. 6-47 Relocated items from pg. 6-45 and pg. 6-46. 6-48 Added pg.; relocated items 427 and 435 from pg. 6-46; added new items 429 thru 433; renumbered items. 6-49 Added pg.; relocated items from pg. 6-47; renumbered items. 7-i Revised Table of Contents. 7-9 Revised para. 7.15; relocated info. to pg. 7-10. 7-10 Relocated info. from pg. 7-9. 7-22 Revised para. 7.27. 7-29 Added new para. 7 .41. 8-12 Revised para. 8.2l(b). 8-13 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. 9-i 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.; Added Supplement thru Ward Evans 9-24 August 1, 1980 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-f 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 9-i Revised Table of Contents. (PR801210) 9-25 Added pgs. (Added Supple- thru ment 7 KNS 80 Navigation Ward Evans 9-28 System.) Dec. 10, 1980 Rev. 6 3-i Retitled and added para. and 761 689 pg. no. (PR810202) 3-5 Changed Alternator Failure to Electrical Failures; moved info. to pg. 3-7. 3-6 Added Electrical Overload; moved info. to pg. 3-7. 3-7 Continued Electrical Overload; relocated info. from pg. 3-5 and 3-6; moved info. to pg. 3-8. 3-8 Relocated info. from pg. 3-7. 3-14 Retitled and revised para. 3.17; added para. 3.18; moved info. to pg. 3-15. 3-15 Continued para. 3.18, relocated info. from pg. 3-14; moved info. to pg. 3-16. 3-16 Relocated info. from pg. 3-15; moved info. to pg. 3-17. 3-17 New pg., relocated info. from pg. 3-16. 6-i Revised Table of Contents. 6-21 Revised items 99 and 101; moved item 101 to pg. 6-22. 6-22 Relocated item 101 from pg. 6-21; revised item 103; moved title (g) to pg. 6-23. 6-23 Relocated title (g) from pg. 6-22. ISSUED: JUNE 1, 1978 REPORT: VB-910 vi-g 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; relocated item 281 from pg. 6-38; re- located item 283 from pg. 6-39. 6-38b New page. 6-39 Moved item 283 to pg. 6-38a; revised item 293; added item 288. 6-41 Revised item 307. 6-44b Added item 342; moved item 349 to pg. 6-45. 6-45 Relocated item 349 from pg. 6-44b. 6-48 Revised items 429, 431 and 433; moved items 433 and 435 to pg. 6-49. 6-49 Relocated items 433 and 435 from pg. 6-48; moved info. to pg. 6-50. 6-50 New pg.; relocated info. from pg. 6-49. 7-13 Revised Figure 7-11. 7-14 Revised para. 7.17; added note; moved info. to pg. 7-16. 7-16 Relocated info. from pg. 7-14. 7-22 Revised para. 7.27. Ward Evans 9-24 Revised 4 (c). Feb. 2, 1981 Rev. 7 ii Revised Warning. 761 689 1-4 Revised para. 1.13. (PR810624) 6-15 Revised item 17. 6-25 Revised item 143. 6-33 Revised item 243. 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-h 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; added items 274 and 275; relocated re- numbered item from pg. 6-37. 6-38a Added item 282. 6-38b Relocated items 285 thru 289 from pg. 6-39. 6-39 Moved items 285 thru 289 to pg. 6-38b; relocated items 295 thru 299 from pg. 6-40. 6-40 Moved items 295 thru 299 to pg. 6-39; added item 303. 6-50 Removed info. 7-12 Revised para. 7.15. Ward Evans 8-15 Corrected date. June 24, 1981 Rev. 8 4-i Revised Table of Contents. (PR811120) 4-5 Revised procedure. 4-8 Revised procedure. 4-10 Revised procedure. 4-14 Added note to para. 4.9. 4-18 Added note to para. 4.21; moved para. 4.23 to pg. 4- I 9. 4-19 Relocated para. 4.23 from pg. 4-18; moved info. to pg. 4-20. 4-20 Relocated info. from 4-19; moved info. to pg. 4-21. 4-21 Relocated info. from pg. 4-20; moved info. and para. 4.28 to pg. 4-22. ISSUED: JUNE 1, 1978 REPORT: VB-910 vi-i 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. from pg. 4.22; moved info. and para. 4.33 to pg. 4-24. 4-24 Relocated info. and para. 4.33 from pg. 4-23; moved para. 4.37 and 4.39 to pg. 4.25. 4-25 New page; relocated para. 4.37 and 4.39 from pg. 4-24. 6-13 Revised para. 6.11. 6-38b Revised items 288 and 289. 6-44b Renumbered item; added new item 343. 6-50 Added item 445. Ward Evans 7-22 Revised para. 7.27. Nov. 20, 1981 Rev. 9 iii Revised handbook info. 761 689 1-i Removed para. 1.21 - (PR820723) coversion factor reference. 1-3 Revised para. 1.7. 1-4 Added info. to para. 1.11. 2-1 Revised para. 2.1. 2-3 Added info. to para. 2.11. 3-i Expanded emerg. procedure index; moved info. to new pg. 3-ii. 3-ii New pg.; relocated info. from pg. 3-i. 3-1 Revised para. 3.1. 4-i Expanded normal procedure index; moved info. to new pg. 4-ii. 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-j 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. 4-1 Revised para. 4.1. 4-11 Revised para. 4.7. 6-i Revised index pg. 6-6 Revised fig. 6-5 info. 6-7 Revised fig. 6-7. 6-9 Added info. to fig. 6-9. 6-10 Added info. to fig. 6-11. 6-12a Revised para. 6.9. 7-2 Revised para. 7.5. 7-22 Revised para. 7.27. 7-24 Revised para. 7.33 .. 9-i Updated supplement index pg. 9-13 Revised Supplement 3 (pitch trim). 9-29 Added new Supplement 8. thru 9-48 9-49 Added new Supplement 9. thru Ward Evans 9-74 July 23, 1982 Rev. 10 1-4 Revised para. 1.11. 761 689 1-12 Deleted para. 1.21 and pages. (PR821122) thru 1-21 2-3 Revised para. 2.11. 5-3 Revised para. 5.5. thru 5-7 6-9 Revised fig. 6-9. 6-10 Revised fig. 6-11. 7-i Revised Table of Contents. 7-14 Added Caution; moved para. 7.19 to pg. 7-16. ISSUED: JUNE 1, 1978 REPORT: VB-910 vi-k 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. 7.27. 8-2 Revised para. 8.3. 8-3 Revised para. 8.3 and 8.5, relocated info. from pg. 8-4. 8-4 Moved info. to pg. 8-3, re- located info. from pg. 8-5. 8-5 Moved info. to pg. 8-4, re- located info. from pg. 8-6. Ward Evans 8-6 Moved info. to pg. 8-5. Nov. 22, 1982 Rev. 11 1-9 Deleted MBA .. 761 689 1-12 Deleted pg. 1-12, para. 1.21. (PR830805) 2-8 Added GAMA placard. 5-3 Revised para. 5.5. 6-9 Revised fig. 6-9. 8-2 Revised para. 8.3. 8-3 Revised para. 8.5. 9-35 Revised Supplement No. 8. Ward Evans 9-57 Revised Supplement No. 9. Aug. 5, 1983 Rev. 12 vii Revised Table of Contents. 761 689 1-3 Revised para. 1.7. (PR840713) 2-3 Revised para. 2.7 (g). 3-1 Revised para. 3.1. 4-4, Revised para. 4.5 info. 4-5, 4-7, 4-8 4-14 Revised para. 4.11. 4-16 Revised para. 4.17. 4-17 Revised para. 4.19. 4-18 Revised para. 4.21. 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-l PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 12 6-1 Revised para. 6.1. (cont) 6-2 Revised para. 6.3. 6-5 Revised para. 6.5. 6-15 Revised item 19. 7-5 Revised para. 7.9. 7-12 Revised para. 7.17. 7-22 Revised para. 7.27. 7-24 Revised para. 7.33. 8-12 Revised para. 8.21 (b). 10-i Revised Table of Contents. 10-1 Revised Title; revised para. 10-1 and para. 10.3. Ward Evans 10-2 Revised Title. July 13, 1984 Rev. 13 7-I2 Added Info to (PR860830) · para. 7.17 D.H.Trompler Date Rev. 14 9-i Revised Table (PR861014) of Contents. 9-75 Added new thru Supplemeot 10. 9-80 D.H.Trompler 9-81 Added new thru Supplement 11. 9-100 Date Rev. 15 8-1 Revised para. 6.1. (PR880701) Relocated info from page 8-2. 8-2 Moved info to page 8-l. Relocated info from page 8-3. D.H. Trompler 8-3 Moved info to page 8-2. 9-7 Revised Section 3, para. (a). Date . ISSUED: JUNE 1, 1978 REPORT: VB-910 vi-m 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. 7-27b Added page. Added Narco ELT 910 info. 8-1 Revised para. 8.1. Moved info. to p. 8-2. 8-2 Relocated info. from p. 8-1. Revised paras. 8.1 and 8.3. Moved info. to p. 8-3. 8-3 Relocated info. from p. 8-2. Revised para. 8.3. 8-12 Revised para. 8.19. Moved info. to p. 8-13. 8-13 Relocated info. from p. 8-12. Revised Fuel Grade Comparison Chart. D. H. Trompler May 11. 1990 Date Rev. 17 9-i Revised Table of Contents (PR931207) 9-101 Added pgs;Added Supplement Thru No. 12 9-104 9-105 Added pgs;Added Supplement Thru No. 13 W. R. Moreu 9-108 DEC. 07, 1993 Date 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 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date ISSUED: JUNE 1, 1978 REPORT: VB-910 vii 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 SECTION 10 SAFETY TIPS REPORT: VB-910 ISSUED: JUNE 1, 1978 viii THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: JUNE 1, 1978 REPORT: VB-910 1-i TABLE OF CONTENTS SECTION 1 GENERAL Paragraph Page No. No. 1.1 Introduction ............................................................................. 1-1 1.3 Engine ...................................................................................... 1-3 1.5 Propeller .................................................................................. 1-3 1.7 Fuel .......................................................................................... 1-3 1.9 Oil .......................................................................................... 1-4 1.11 Maximum Weights .................................................................. 1-4 1.13 Standard Airplane Weights...................................................... 1 4 1.15 Baggage Space......................................................................... 1-4 1.17 Specific Loadings .................................................................... 1-5 1.19 Symbols, Abbreviations and Terminology .............................. 1-6 REPORT: VB-910 ISSUED: JUNE 1, 1978 1-ii BLANK PAGE PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-236, DAKOTA GENERAL ISSUED: JUNE 1, 1978 REPORT: VB-910 1-1 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 CAR 3. It also contains supplemental data supplied by the airplane manufacturer. This handbook is not designed as a substitute for adequate and competent flight instruction, knowledge of current airworthiness directives, applicable federal air regulations or advisory circulars. It is not intended to be a guide for basic flight instruction or a training manual and should not be used for operational purposes unless kept in a current status. Assurance that the airplane is in an airworthy condition is the responsibility of the owner. The pilot in command is responsible for determining that the airplane is safe for flight. The pilot is also responsible for remaining within the operating limitations as outlined by instrument markings, placards, and this handbook. Although the arrangement of this handbook is intended to increase its in-flight capabilities, it should not be used solely as an occasional operating reference. The pilot should study the entire handbook to become familiar with the limitations, performance, procedures and operational handling characteristics of the airplane before flight. The handbook has been divided into numbered (arabic) sections, each provided with a “finger-tip” tab divider for quick reference. The limitations and emergency procedures have been placed ahead of the normal procedures, performance and other sections to provide easier access to information that may be required in flight. The “Emergency Procedures” Section has been furnished with a red tab divider to present an instant reference to the section. Provisions for expansion of the handbook have been made by the deliberate omission of certain paragraph numbers, figure numbers, item numbers and pages noted as being intentionally left blank. REPORT: VB-910 ISSUED: JUNE 1, 1978 1-2 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 1-2 REVISED: JANUARY 15, 1979 THREE VIEW Figure 1-1 Wing Area (sq. ft.) Min. Turning Radius (ft.) (from pivot point to wingtip) '_425.11"' __1 170.0 30.0 PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-236, DAKOTA GENERAL ISSUED: JUNE 1, 1978 REPORT: VB-910 1-3 REVISED: JULY 13, 1984 1.3 ENGINES (a) Number of Engines 1 (b) Engine Manufacturer Lycoming (c) Engine Model Number 0-540-J3A5D (d) Rated Horsepower 235 (e) Rated Speed (rpm) 2400 (f) Bore (in.) 5,125 (g) Stroke (in.) 4.375 (h) Displacement (cu. in.) 541.5 (i) Compression Ratio 8.5:1 (j) Engine Type Six Cylinder, Direct Drive, Horizontally Opposed, Air Cooled, 1.5 PROPELLERS (a) Number of Propellers 1 (b) Propeller Manufacturer Hartzell (c) Blade Model F8468A-4R (d) Number of Blades 2 (e) Hub Model HC-F2YR-1( )F (f) Propeller Diameter (in.) (1) Maximum 80 (2) Minimum 78 (g) Propeller Type Constant Speed, Hydraulically Actuated 1.7 FUEL AVGAS ONLY (a) Fuel Capacity (U.S. gal) (total) 77 (b) Usable Fuel (U.S. gal) (total) 72 (c) Fuel (1) Minimum Grade 100 Green or 100LL Blue Aviation Grade (2) Alternate Fuels Refer to latest issue of Lycoming Instruction No. 1070. SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 1-4 REVISED: NOVEMBER 22, 1982 1.9 OIL (a) Oil Capacity (U.S. qts.) 12 (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.) 3000 (c) Maximum Landing Weight (lbs.) 3000 (d) Maximum Weights in Baggage Compartment (lbs.) 200 1.13 STANDARD AIRPLANE WEIGHTS * Refer to Figure 6-5 for the Standard Empty Weight and the Useful Load. 1.15 BAGGAGE SPACE (a) Compartment Volume (cu. ft.) 24 (b) Entry Width (in.) 22 (c) Entry Height (in.) 20 PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-236, DAKOTA GENERAL ISSUED: JUNE 1, 1978 REPORT: VB-910 1-5 1.17 SPECIFIC LOADINGS (a) Wing Loading (lbs. per sq. ft.) 17.6 (b) Power Loading (lbs. per hp) 12.8 REPORT: VB-910 ISSUED: JUNE 1, 1978 1-6 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 CAS Calibrated Airspeed means the indicated speed of an aircraft, corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. KCAS Calibrated Airspeed expressed in “Knots.” GS Ground Speed is the speed of an airplane relative to the ground. IAS Indicated Airspeed is the speed of an aircraft as shown on the airspeed indicator when cor-rected for instrument error. IAS values pub-lished in this handbook assume zero instru-ment error. KIAS Indicated Airspeed expressed in “Knots.” M Mach Number is the ratio of true airspeed to the speed of sound. TAS True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude, temperature and compressibility. VA Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstress the aircraft. VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-236, DAKOTA GENERAL ISSUED: JUNE 1, 1978 REPORT: VB-910 1-7 VNE/MNE Never Exceed Speed or Mach Number is the speed limit that may not be exceeded at any time. VNO Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution. V S Stalling Speed or the minimum steady flight speed at which the airplane is controllable. VSO Stalling speed or the minimum steady flight speed at which the aircraft is controllable in the landing configuration. VX Best Angle-of-Climb Speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance. VY Best Rate-of-Climb Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time. (b) Meteorological Terminology ISA 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); The temperature gradient from sea level to the altitude at which the temperature is -56.5°C (-69.7°F) is -0.00198°C (-0.003566°F) per foot and zero above that altitude. OAT Outside Air Temperature is the free air static temperature, obtained either from in-flight temperature indications or ground meteorological sources, adjusted for instru- ment error and compressibility effects. REPORT: VB-910 ISSUED: JUNE 1, 1978 1-8 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 millibars). Pressure Altitude Altitude measured from standard sea-level pressure (29.92 in. Hg) by a pressure or barometric al timeter. It is the indicated pressure altitude corrected for position and instru ment error. In this handbook, altimeter instrument errors are assumed to be zero. Station Pressure Actual atmospheric pressure at field elevation. Wind The wind velocities recorded as variables on the charts of this handbook are to be under- stood as the headwind or tailwind components of the reported winds. (c) Power Terminology Takeoff Power Maximum power permissible for takeoff. Maximum Con- Maximum power permissible continuously tinuous Power during flight. Maximum Climb Maximum power permissible during Power climb. Maximum Cruise Maximum power permissible during Power cruise. (d) Engine Instruments EGT Gauge Exhaust Gas Temperature Gauge PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-236, DAKOTA GENERAL ISSUED: JUNE 1, 1978 REPORT: VB-910 1-9 REVISED: AUGUST 5, 1983 (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. Demonstrated The demonstrated crosswind velocity is the Crosswind velocity of the crosswind component for Velocity which adequate control of the airplane during (DEMO t a k e o f f a n d l a n d i n g w a s a c t u a l l y X-WIND) demonstrated during certification tests. Accelerate-Stop The distance required to accelerate an air- Distance plane to a specified speed and, assuming failure of an engine at the instant that speed is attained, to bring the aircraft to a stop. Route Segment A part of a route. Each end of that part is identified by (1) a geographical location; or (2) a point at which a definite radio fix can be established. (f) 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. Arm The horizontal distance from the reference datum to the center of gravity (CG) of an item. Moment The product of the weight of an item multi- plied by its arm. (Moment divided by a constant is used to simplify balance calculations by reducing the number of digits.) REPORT: VB-910 ISSUED: JUNE 1, 1978 1-10 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. CG Arm The arm obtained by adding the airplane’s individual moments and dividing the sum by the total weight. CG Limits The extreme center of gravity locations within which the aircraft must be operated at a given weight. Usable Fuel Fuel available for flight planning. Unusable Fuel Fuel remaining after a runout test has been completed in accordance with government regulations. Standard Empty Weight of a standard airplane including Weight unusable fuel, full operating fluids, and full oil. Basic Empty Standard empty weight plus optional Weight equipment. Payload Weight of occupants, cargo, and baggage. Useful Load Difference between takeoff weight, or ramp weight if applicable, and basic empty weight. Maximum Ramp Maximum weight approved for ground Weight maneuver. (It includes weight of start, taxi, and run up fuel.) Maximum Maximum weight approved for the start of Takeoff Weight the takeoff run. PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-236, DAKOTA GENERAL ISSUED: JUNE 1, 1978 REPORT: VB-910 1-11 Maximum Maximum weight approved for the landing Landing Weight touchdown. Maximum Zero Maximum weight exclusive of usable fuel. Fuel Weight REPORT: VB-910 ISSUED: JUNE 1, 1978 1-12 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-28-236, DAKOTA THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: JUNE 1, 1978 REPORT: VB-910 2--i TABLE OF CONTENTS SECTION 2 LIMITATIONS Paragraph Page No. No. 2.1 General ....................................................................................... 2-1 2.3 Airspeed Limitations .................................................................. 2-1 2.5 Airspeed Indicator Markings ...................................................... 2-2 2.7 Power Plant Limitations ............................................................. 2-2 2.9 Power Plant Instrument Markings .............................................. 2-3 2.11 Weight Limits ............................................................................. 2-3 2.13 Center of Gravity Limits ............................................................ 2-4 2.15 Maneuver Limits ........................................................................ 2-4 2.17 Flight Maneuvering Load Factors .............................................. 2-4 2.19 Types of Operations ................................................................... 2-4 2.21 Fuel Limitations.......................................................................... 2-5 2.23 Noise Level ................................................................................. 2-5 2.25 Placards....................................................................................... 2-5 REPORT: VB-910 ISSUED: JUNE 1, 1978 2--ii BLANK PAGE PIPER AIRCRAFT CORPORATION PA-28-236, DAKOTA ISSUED: JUNE 1, 1978 REPORT: VB-910 2-1 REVISED: JULY 23, 1982 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 category airplane in compliance with the operating limitations stated in the form of placards and markings and those given in this section and handbook. Limitations associated with those optional systems and equipment which require handbook supplements can be found in Section 9 (Supplements). 2.3 AIRSPEED LIMITATIONS SPEED KIAS KCAS Design Maneuvering Speed (VA) - Do not make full or abrupt control movements above this speed. 3000 lbs. · 124 122 1761 lbs. 96 94 CAUTION Maneuvering speed decreases at lighter weight as the effects of aerodynamic forces become more pronounced. Liriear interpolation may be used for intermediate gross weights. Maneuvering speed should not be exceeded while operating in rough air. PIPER AIRCRAFT CORPORATION PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 2-2 SPEED KIAS KCAS Never Exceed Speed (VNE)- Do not exceed this speed in any operation. 173 171 Maximum Structural Cruising Speed (VNo) - Do not exceed this speed except in smooth air and then only with caution. 137 135 Maximum Flaps Extended Speed (VFE)- Do not exceed this speed with the flaps extended. 102 100 2.5 AIRSPEED INDICATOR MARKINGS MARKING IAS Red Radial Line (Never Exceed) 173 KTS Yellow Arc (Caution Range - Smooth Air Only) 137 KTS to 173 KTS Green Arc (Normal Operating Range) 65 KTS to 137KTS White Arc (Flap Down) 56 KTS to 102 KTS 2.7 POWER PLANT LIMITATIONS (a) Number of Engines 1 (b) Engine Manufacturer Lycoming (c) Engine Model No. O-540-J3A5D (d) Engine Operating Limits (1) Maximum Horsepower 235 (2) Maximum Rotation Speed (RPM) 2400 (3) Maximum Oil Temperature 245°F (e) Oil Pressure Minimum (red line) 25 PSI Maximum (red line) 100 PSI PIPER AIRCRAFT CORPORATION PA-28-236, DAKOTA ISSUED: JUNE 1, 1978 REPORT: VB-910 2-3 REVISED: JULY 13, 1984 (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 1 (i) Propeller Manufacturer Hartzell (j) Propeller Hub and Blade Mode HC-F2YR-1( )F/ F8468A-4R (k) Propeller Diameter Minimum 80 IN. Maximum 78 IN. (1) Blade Angle Limits (at 30 inch station) Low Pitch Stop 16.25º ± 0.25° High Pitch Stop 32º ± 2.0° 2.9 POWER PLANT INSTRUMENT MARKINGS (a) Tachometer Green Arc (Normal Operating Range) 500 to 2400 RPM Red Line (Maximum Continuous Power) 2400 RPM (b) Oil Temperature Green Arc (Normal Operating Range) 75° to 245°F Red Line (Maximum) 245°F (c) Oil Pressure Green Arc (Normal Operating Range) 60 PSI to 90 PSI Yellow Arc (Caution Range) (Idle) 25 PSI to 60 PSI Yellow Arc (Ground Warm-Up) 90 PSI to 100 PSI Red Line (Minimum) 25 PSI Red Line (Maximum) 100 PSI (d) Fuel Pressure Green Arc (Normal Operating Range) 0.5 PSI to 8 PSI Red Line (Minimum) 0.5 PSI Red Line (Maximum) 8 PSI Red Line (Maximum) 41 IN. HG. 2.11 WEIGHT LIMITS (a) Maximum Ramp Weight 3011 lbs. (b) Maximum Weight 3000 lbs. (c) Maximum Baggage 200 lbs. PIPER AIRCRAFT CORPORATION PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 2-4 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. The datum used is 78.4 inches ahead of the wing leading edge. It is the responsibility of the airplane owner and the pilot to insure that the airplane is properly loaded. See Section 6 (Weight and Balance) for proper loading instructions. 2.15 MANEUVER LIMITS No acrobatic maneuvers, including spins, approved. 2.17 FLIGHT MANEUVERING LOAD FACTORS (a) Positive Load Factor (Maximum) 3.8 G (b) Negative Load Factor (Maximum) No inverted maneuvers approved 2.19 TYPES OF OPERATIONS The airplane is approved for the following operations when equipped in accordance with FAR 91 or FAR 135. (a) Day V.F.R. (b) Night V.F.R. (c) Day I.F.R. (d) Night I.F.R. (e) Non Icing PIPER AIRCRAFT CORPORATION PA-28-236, DAKOTA ISSUED: JUNE 1, 1978 REPORT: VB-910 2-5 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. GAL The usable fuel in this airplane has been determined as 36 gallons in each wing. (d) Fuel remaining when the quantity indi- cator reads zero cannot be used safely in flight. 2.25 NOISE LEVEL The noise level of this aircraft is 72.9 d B(A). No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or unacceptable for operation at, into, or out of, any airport. The above statement notwithstanding, the noise level stated above has been verified by and approved by· the Federal Aviation Administration in noise level test flights conducted in accordance with FAR 36, Noise Standards - Aircraft Type and Airworthiness Certification. This aircraft model is in compliance with all FAR 36 noise standards applicable to this type. 2.25 PLACARDS In full view of the pilot: THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS. T H I S A I R C R A F T A P P R O V E D F O R N I G H T l.F.R. NON-ICING FLIGHT WHEN EQUIPPED IN ACCORDANCE WITH FAR 91 OR FAR 135. PIPER AIRCRAFT CORPORATION PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 2-6 REVISED: AUGUST 27, 1979 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 Seat Backs Erect Controls Free Primer Locked Door Latched Mixture Set Air Conditioner Off LANDING CHECK LIST Seat Backs Erect Mixture Rich Fasten Belts / Harness Propeller Set Fuel on Proper Tank Flaps Set (White Arc) Electric Fuel Pump On Air Conditioner Off The “Air Conditioner Off’ item in the above Takeoff and Landing Check List is mandatory for air conditioned aircraft only. On the aft baggage compartment: MAXIMUM BAGGAGE 200 LBS. NO HEAVY OBJECTS ON HAT SHELF In full view of the pilot, near the airspeed indicator: MANEUVERING SPEED 124 KIAS AT 3000 LBS (SEE A.F.M.) OR V A = 124 KIAS AT 3,000# (SEE P.O.H.) In full view of the pilot: FUEL REMAINING WHEN THE QUANTITY INDICATORS READ ZERO CANNOT BE USED SAFELY IN FLIGHT PIPER AIRCRAFT CORPORATION PA-28-236, DAKOTA ISSUED: JUNE 1, 1978 REPORT: VB-910 2-7 REVISED: AUGUST 27, 1979 Adjacent to upper door latch: ENGAGE LATCH BEFORE FLIGHT On the instrument panel in full view of the pilot: DEMONSTRATED CROSSWIND COMPONENT 17 KTS OR DEMO. X-WIND 17 KTS In full view of the pilot: NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED WARNING T U R N O F F S T R O B E L I G H T S W H E N INCLOSE PROXIMITY TO GROUND OR DURING FLIGHT THROUGH CLOUD, FOG OR HAZE. On the instrument panel in full view of the pilot when the AutoFlite is installed: OPERATION TURN AUTOFLITE ON. ADJUST TRIM KNOB FOR MINIMUM HEADING CHANGE: FOR HEADING CHANGE, PRESS’ DISENGAGE SWITCH ON CONTROL WHEEL, CHANGE HEADING, RELEASE SWITCH. ROTATE TURN KNOB FOR TURN COMMANDS. PUSH TURN KNOB IN TO ENGAGE TRACKER. PUSH TRIM KNOB IN FOR HI SENSITIVITY. LIMITATIONS AUTOFLITE OFF FOR TAKEOFF AND LANDING. PIPER AIRCRAFT CORPORATION PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 2-8 REVISED: AUGUST 5, 1983 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 OR FUEL - 100/130 AVIATION GRADE- MIN. USABLE CAPACITY 36 GAL. USABLE CAPACITY TO BOTTOM OF FILLER NECK INDICATOR 25 GAL. Adjacent to fuel filler cap (serial numbers 28-8311009 and up): ISSUED: JUNE 1, 1978 REPORT: VB-910 3-i PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-236, DAKOTA EMERGENCY PROCEDURES TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph Page No. No. 3.1 General ....................................................................................... 3-1 3.3 Emergency Procedures Checklist ............................................... 3-2 Speeds .................................................................................... 3-2 Engine Inoperative Procedures .............................................. 3-2 Fire ......................................................................................... 3-4 Loss of Oil Pressure ............................................................... 3-5 Loss of Fuel Pressure ............................................................. 3-5 High Oil Temperature ............................................................ 3-5 Electrical Failures .................................................................. 3-5 Electrical Overload ................................................................ 3-6 Spin Recovery ........................................................................ 3-7 Open Door ............................................................................. 3-7 Carburetor Icing ..................................................................... 3-7 Engine Roughness ................................................................. 3-8 Propeller Overs peed.............................................................. 3-8 3.5 Amplified Emergency Procedures (General) ............................. 3-9 3.7 Engine Inoperative Procedures ................................................... 3-9 Engine Power Loss During Takeoff (Not Airborne) ............. 3-9 Engine Power Loss During Takeoff (If Airborne) ................ 3-9 Engine Power Loss In Flight ................................................. 3-10 Power Off Landing ................................................................ 3-11 3.9 Fire .............................................................................................. 3-11 Engine Fire During Start ........................................................ 3-11 Fire In Flight .......................................................................... 3-12 3.11 Loss of Oil Pressure.................................................................... 3-13 3.13 Loss of Fuel Pressure.................................................................. 3-13 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 3-ii TABLE OF CONTENTS (cont) SECTION 3 (cont) Paragraph Page No. No. 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 .................................................................................. 3-15 3.22 Carburetor Icing.......................................................................... 3-16 3.23 Engine Roughness ...................................................................... 3-16 3.25 Propeller Overspeed ................................................................... 3-17 ISSUED: JUNE 1, 1978 REPORT: VB-910 3-1 PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-236, DAKOTA EMERGENCY PROCEDURES REVISED: JULY 13, 1984 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. Emergency procedures associated with those optional systems and equipment which require handbook supplements are provided by Section 9 (Supplements). The first portion of this section consists of an abbreviated emergency check list which supplies an action sequence for critical situations with little emphasis on the operation of systems. The remainder of the section is devoted to amplified emergency procedures containing additional information to provide the pilot with a more complete understanding of the procedures. These procedures are suggested as a course of action for coping with the particular condition described, but are not a substitute for sound judgment and common sense. Pilots should familiarize themselves with the procedures given in this section and be prepared to take appropriate action should an emergency arise. Most basic emergency procedures, such as power off landings, are a normal part of pilot training. Although these emergencies are discussed here, this information is not intended to replace such training, but only to provide a source of reference and review, and to provide information on procedures which are not the same for all aircraft. It is suggested that the pilot review standard emergency procedures periodically to remain proficient in them. SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 3-2 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. (0° flap) .............................................................................85 KIAS ENGINE INOPERATIVE PROCEDURES ENGINE POWER LOSS DURING TAKEOFF (NOT AIRBORNE) Sufficient runway remaining: Throttle .............................................................................. close immediately Brakes ..................................................................................apply as required Stop straight ahead. Insufficient runway remaining: Throttle .............................................................................. close immediately Brakes ..................................................................................apply as required Mixture .................................................................................IDLE CUT-OFF Fuel selector ............................................................................................OFF Master switch..........................................................................................OFF· Magnetos .................................................................................................OFF Maintain directional control and maneuver to avoid obstacles. ENGINE POWER LOSS DURING TAKEOFF (IF AIRBORNE) Sufficient runway remaining: Airspeed ......................................................................... maintain above stall Directional control ............................................................................ maintain Land straight ahead. ISSUED: JUNE 1, 1978 REPORT: VB-910 3-3 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. If sufficient altitude has been gained to attempt a restart: Airspeed ......................................................................maintain safe airspeed Fuel selector ....................................................................switch to other tank containing fuel Electric fuel pump .................................................................................... ON Mixture ................................................................................................. RICH Carburetor heat ......................................................................................... ON If power is not regained proceed with power off landing. ENGINE POWER LOSS IN FLIGHT Fuel selector ....................................................................switch to other tank containing fuel Electric fuel pump .................................................................................... ON Mixture ................................................................................................. RICH Carburetor heat ......................................................................................... ON Engine gauges ................................................................. check for indication of cause of power loss Primer .................................................................................................. locked If no fuel pressure is indicated, check that fuel selector is on a tank containing fuel. If power has not been restored: Ignition switch ...................................................... L then R, then back to BOTH Throttle and mixture ............................................................ try different settings When power is restored: Carburetor heat............................................................................................. OFF Electric fuel pump ......................................................................................... OFF If power cannot be restored: Trim for best glide angle (85 KIAS) and prepare for power off landing. SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 3-4 REVISED: JANUARY 15, 1979 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. Touchdowns should normally be made at lowest possible airspeed with full flaps. When committed to landing: Ignition ....................................................................................................OFF Master switch...........................................................................................OFF Fuel selector ............................................................................................OFF Mixture .................................................................................IDLE CUT-OFF Seat belts and harness ............................................................................. tight FIRE ENGINE FIRE DURING START Starter .........................................................................................crank engine Mixture .................................................................................IDLE CUT-OFF Throttle .................................................................................................. open· Electric fuel pump ..................................................................................OFF· Fuel selector ............................................................................................OFF Abandon airplane if fire continues. FIRE IN FLIGHT Source of fire .........................................................................................check Engine fire: Fuel selector ............................................................................................OFF Throttle .................................................................................................closed Mixture .................................................................................IDLE CUT-OFF Electric fuel pump ...................................................................................OFF Cabin heat ................................................................................................OFF Defroster ..................................................................................................OFF Prepare for power off landing. ISSUED: JUNE 1, 1978 REPORT: VB-910 3-5 PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-236, DAKOTA EMERGENCY PROCEDURES REVISED: FEBRUARY 2, 1981 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. Prepare for power off landing. LOSS OF FUEL PRESSURE Electric fuel pump ................................................................................... ON Fuel selector ...................................................................... check on full tank HIGH OIL TEMPERATURE Land at nearest airport and investigate the problem. Prepare for power off landing. ELECTRICAL FAILURES ALT annunciator light illuminated Ammeter ................................................................................. check to verify inop. alt. If ammeter shows zero ALT switch ..............................................................................................OFF Reduce electrical loads to minimum ALT circuit breaker ............................................................... check and reset as required ALT switch ............................................................................................... ON SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 3-6 REVISED: FEBRUARY 2, 1981 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. ELECTRICAL OVERLOAD (alternator over 20 amps above known electrical load) FOR AIRPLANES WITH INTERLOCKED BAT AND ALT SWITCH OPERATION Electrical load ...................................................................................... reduce If alternator loads are not reduced ALT switch ..............................................................................................OFF Land as soon as practical. Battery is the only remaining source of power. Anticipate complete electrical failure. FOR AIRPLANES WITH SEPARATE BAT AND ALT SWITCH OPERATION ALT switch ............................................................................................... ON BAT switch ..............................................................................................OFF If alternator loads are reduced Electrical load .................................................................. reduce to minimum Land as soon as practical. NOTE Due to increased system voltage and radio frequency noise, operation with ALT switch ON and BAT switch OFF should be made only when required by an electrical system failure. ISSUED: JUNE 1, 1978 REPORT: VB-910 3-7 PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-236, DAKOTA EMERGENCY PROCEDURES REVISED: FEBRUARY 2, 1981 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 .................................................................... full forward while neutralizing ailerons Throttle ...................................................................................................close Rudder .............................................................. neutral (when rotation stops) Control wheel ............................................................as required to smoothly regain level flight attitude OPEN DOOR If both upper and side latches are open, the door will trail slightly open and airspeeds will be reduced slightly. To close the door in flight: Slow airplane to 83 KIAS. Cabin vents .............................................................................................close Storm window......................................................................................... open If upper latch is open .............................................................................. latch If side latch is open ...................................................... pull on arm rest while moving latch handle to latched position. If both latches are open ........................................................... latch side latch then top latch CARBURETOR ICING Carburetor heat ......................................................................................... ON Mixture ................................................................adjust for max. smoothness SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 3-8 REVISED: FEBRUARY 2, 1981 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 If operation is satisfactory on either one, continue on that magneto at reduced power and full “RICH” mixture to first airport. Prepare for power off landing. PROPELLER OVERSPEED Throttle ................................................................................................. retard Oil pressure............................................................................................check Prop control ................................................................. full DECREASE rpm, then set if any control available Airspeed .............................................................................................. reduce Throttle ......................................................................... as required to remain below 2400 rpm ISSUED: JUNE 1, 1978 REPORT: VB-910 3-9 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. 3.7 ENGINE FIRE DURING START ENGINE POWER LOSS DURING TAKEOFF (NOT AIRBORNE) If engine failure occurs before the airplane has lifted off, and if there is sufficient runway left for a safe stop, simply maintain directional control, close the throttle, and brake to a stop. If there is not sufficient runway remaining for a safe stop, close the throttle, apply maximum braking, pull the mixture control to IDLE CUTOFF, and turn OFF the fuel selector, the master switch and the magnetos. Maintain directional control, slow the airplane as much as possible, and maneuver to avoid obstacles. ENGINE POWER LOSS DURING TAKEOFF (IF AIRBORNE) If engine failure occurs after the airplane has lifted off, and if sufficient landing area remains for a touchdown and stop, lower the nose and maintain airspeed to avoid a stall. Maintain directional control and land and stop straight ahead. If liftoff has occurred and there is not sufficient landing area remaining for a safe landing and stop, maintain a safe airspeed to avoid a stall. Close the throttle, pull the mixture control to IDLE CUT-OFF, and turn OFF the fuel selector, the master switch, and the magnetos. Use of flaps depends upon the circumstances; however, normally full flaps allow the slowest and softest touchdown. At low altitudes with a failed engine, turns should not be attempted, except for slight and gentle deviations to avoid obstacles. A controlled crash landing straight ahead is preferable to risking a stall which could result in an uncontrolled roll and crash out of a turn. SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 3-10 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. If engine failure was caused by fuel exhaustion, power will not be regained after switching tanks until the empty fuel lines are filled. This may require up to ten seconds. If the propeller has stopped turning, it will be necessary to engage the starter to execute a restart. If power is not regained, proceed with a Power Off Landing. ENGINE POWER LOSS IN FLIGHT A complete loss of power is usually caused by a fuel flow interruption, in which case power will be restored shortly after fuel flow is restored. If power loss occurs at a low altitude, the first step should be to prepare for an emergency Power Off Landing. Maintain an airspeed of at least 85 KIAS. If altitude permits, attempt a restart. Switch the fuel selector to another tank containing fuel. Turn ON the electric fuel pump, set the mixture RICH, and turn ON carburetor heat. Check the engine gauges for an indication of the cause of the power loss. Be sure that the primer is locked if one is installed. If no fuel pressure is indicated, check the fuel selector to be sure that it is on a tank containing fuel. If fuel exhaustion is the problem, it may take up to ten seconds after switching· tanks for empty fuel lines to fill and for power to be restored. If there is water contamination of the fuel, fuel pressure indications will be normal. Water in the fuel could take some time to be passed through, and allowing the propeller to windmill may restore power. If the propeller has stopped turning, engage the starter. When power is restored and the engine is operating smoothly, turn OFF the carburetor heat and the electric fuel pump. If the preceding steps do not restore power, prepare for an emergency Power Off Landing. If time permits, try turning the ignition switch to L, then to R, then back to BOTH. Try moving the throttle and mixture controls to various settings. This rna y restore power if the problem is too rich or too lean a mixture or if there is a partial fuel system restriction. If power is not regained, proceed with preparations for a Power Off Landing. ISSUED: JUNE 1, 1978 REPORT: VB-910 3-11 PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-236, DAKOTA EMERGENCY PROCEDURES REVISED: JANUARY 15, 1979 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; it may be possible to reach one if the airplane’s altitude is sufficient. If possible, notify the FAA by radio of the situation and intended course of action. If another pilot or a passenger is aboard, that person may assist. After locating the most suitable landing area, establish a spiral pattern around the field. Try to be at 1000 feet above the field at the downwind position to make a normal landing approach. When assured of reaching the field, slow to 72 KIAS for the shortest landing. Excess altitude may be lost by widening the pattern, extending flaps, slipping, or a combination of these methods. Once committed to a landing, shut OFF the ignition, the master switch, and the fuel selector. Pull the mixture to IDLE CUT-OFF. Tighten seat belts and shoulder harness. Flaps may be used as deemed necessary. Normally a full stall touchdown should be made at the lowest possible airspeed with flaps fully extended. 3.9 FIRE ENGINE FIRE DURING START Engine fires during start are usually the result of overpriming. The first step in extinguishing the fire is to cut off the source of fuel and to keep the engine turning to use up excess fuel. Continue cranking the engine with the starter, while pulling the mixture control to IDLE CUT-OFF and advancing the throttle fully open. Turn OFF the electric fuel pump and the fuel selector. Radio for assistance if possible. If the engine has started, it should be left running. If the engine is not running, continue cranking with the starter. This is an attempt to draw the fire back into the engine. SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 3-12 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. FIRE IN FLIGHT The presence of fire is indicated by smoke, smell, or heat. 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 in each case. If an engine fire is indicated, immediately turn the fuel selector OFF and close the throttle. Pull the mixture control to IDLE CUT-OFF. Be sure that the electric fuel pump is OFF. Turn OFF the cabin heat and defroster. If radio transmission is not required, turn OFF the master switch. Proceed with a Power Off Landing. NOTE The possibility of an engine fire in flight is extremely remote. The procedure given is general and pilot judgment should be the determining factor for action in such an emergency. If smoke or fumes in the cabin indicate ail electrical fire, turn OFF the master switch. Turn OFF the cabin heat and defroster, and open the vents, to clear smoke and fumes from the cabin. Land as soon as practicable. NOTES When the master switch is turned off, the stall warning system will not function. During night flight a flashlight should be in hand before turning off the master switch. ISSUED: JUNE 1, 1978 REPORT: VB-910 3-13 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. A complete loss of oil pressure indication may signify oil exhaustion or may be the result of a faulty gauge. In either case, proceed toward the nearest airport, and be prepared for a forced landing. If the problem is not a pressure gauge malfunction, the engine may stop suddenly. Maintain altitude until such time as a power off landing can be accomplished. Do not change power settings unnecessarily, as this may hasten complete power loss. Depending on the circumstances, it may be advisable to make an off airport landing while power is still available, particularly if other indications of actual oil pressure loss, such as sudden increases in temperatures, or oil smoke, are apparent, and an airport is not close. If engine stoppage occurs, proceed with Power Off Landing. 3.13 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 tank containing fuel. · If the problem is not an empty tank, land as soon as practical and have the engine-driven fuel pump and fuel system checked. 3.15 HIGH OIL TEMPERATURE An abnormally high oil temperature indication may be caused by a low oil level, an obstruction in the oil cooling installation, damaged or improper baffle seals, a defective gauge, or other causes. Land as soon as possible at an appropriate airport and have the cause investigated. A steady, rapid rise in oil temperature is a sign of trouble. Land at the nearest airport and let a mechanic investigate the problem. Watch the oil pressure gauge for an accompanying loss of pressure. SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 3-14 REVISED: FEBRUARY 2, 1981 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. If no increase in the ammeter reading is noted, alternator failure can be assumed. The electrical load should be reduced as much as possible. Check the alternator circuit breakers for a popped circuit. The next step is to attempt to reset the overvoltage relay. This is accomplished by moving the ALT switch to OFF for one second and then to ON. If the trouble was caused by a momentary overvoltage condition (16.5 volts and up) this procedure should return the ammeter to a normal reading. If the ammeter continues to indicate “0” output, or if the alternator will not remain reset, turn off the ALT switch, maintain minimum electrical load and land as soon as practical. All electrical load is being supplied by the battery. 3.18 ELECTRICAL OVERLOAD (Alternator over 20 amps above known electrical load) If abnormally high alternator output is observed (more than 20 amps above known electrical load for the operating conditions) it may be caused by a low battery, a battery fault or other abnormal electrical load. If the cause is a low battery, the indication should begin to decrease toward normal within 5 minutes. If the overload condition persists attempt to reduce the load by turning off nonessential equipment. For airplanes with interlocked BAT and ALT switch operation, when the electrical load cannot be reduced turn the ALT switch OFF and land as soon as practical. The battery is the only remaining source of electrical power. Also anticipate complete electrical failure. For airplanes with separate BAT and ALT switch operations, turn the BAT switch OFF and the ammeter should decrease. Turn the BAT switch ON and continue to monitor the ammeter. If the alternator output does not decrease within 5 minutes, turn the BAT switch OFF and land as soon as practical. All electrical loads are being supplied by the alternator. ISSUED: JUNE 1, 1978 REPORT: VB-910 3-15 PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-236, DAKOTA EMERGENCY PROCEDURES REVISED: FEBRUARY 2, 1981 - 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. 3.19 SPIN RECOVERY Intentional spins are prohibited in this airplane. Should a spin be entered inadvertently, the following procedure should be initiated: (a) Apply and maintain full rudder opposite the direction of rotation. (b) As the rudder hits the stop, push the control wheel fully forward and neutralize ailerons. As the stall is broken, relax forward pressure as necessary to prevent an excessive nose down attitude. (c) Close the throttle. (d) As rotation stops, neutralize the rudder and ease back on the control wheel to recover smoothly from the dive. 3.21 OPEN DOOR The cabin doors on the Dakota are double latched; so the chances of one springing open in flight at both the top and side are remote. However, if improperly latched, a door may spring partially open. This will usually happen at takeoff or soon afterward. A partially open door will not affect normal flight characteristics, and a normal landing can be made with the door open. If both upper and side latches are open, the door will trail slightly open, and airspeed will be reduced slightly. To close the door in flight, slow the airplane to 83 KIAS, close the cabin vents and open the storm window. If the top latch is open, latch it. If the side latch is open, pull on the arm rest while moving the latch handle to the latched position. If both latches are open, close the side latch then the top latch. SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 3-16 REVISED: FEBRUARY 2, 1981 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. To avoid this, carburetor preheat is provided to replace the heat lost by vaporization. Carburetor heat should be full on when carburetor ice is encountered. Adjust mixture for maximum smoothness. 3.23 ENGINE ROUGHNESS Engine roughness is usually due to carburetor icing which is indicated by a drop in manifold pressure, and may be accompanied by a slight loss of airspeed or altitude. If too much ice is allowed to accumulate, restoration of full power may not be possible; therefore, prompt action is required. Turn carburetor heat ON (See Note). Manifold pressure will decrease slightly and roughness will increase. Wait for a decrease in engine roughness or an increase in manifold pressure, indicating ice removal. If no change in approximately one minute; return the carburetor heat to OFF. If the engine is still rough, adjust the mixture for maximum smoothness. The engine will run rough if too rich or too lean. The electric fuel pump should be switched to ON and the fuel selector switched to the other tank to see if fuel contamination is the problem. Check the engine gauges for abnormal readings. If any gauge readings are abnormal, proceed accordingly. Move the magneto switch to L then R, then back to BOTH. If operation is satisfactory on either magneto, proceed on that magneto at reduced power, with mixture full RICH, to a landing at the first available airport. ISSUED: FEBRUARY 2, 1981 REPORT: VB-910 3-17 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. When using carburetor heat, therefore, always use full heat, and . when ice is removed return the control to the full cold position. 3.25 PROPELLER OVERSPEED Propeller overspeed is caused by a malfunction in the propeller governor or low oil pressure which allows the propeller blades to rotate to full low pitch. If propeller overspeed should occur, retard the throttle and check the oil pressure. The propeller control should be moved to full “DECREASE rpm” and then set if any control is available. Airspeed should be reduced and throttle used to maintain 2400 RPM. THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: JUNE 1, 1978 REPORT: VB-910 4-i TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Paragraph Page No. No. 4.1 General ....................................................................................... 4-1 4.3 Airspeeds for Safe Operations .................................................... 4-1 4.5 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 .............................................. 4-6 Starting With External Power ................................................ 4-6 Warm-Up ............................................................................... 4-7 Taxiing ................................................................................... 4-7 Ground Check ........................................................................ 4-7 Before Takeoff ....................................................................... 4-8 Takeoff ................................................................................... 4-8 Climb ..................................................................................... 4-9 Cruising.................................................................................. 4-9 Descent .................................................................................. 4-10 Approach and Landing .......................................................... 4-10 Stopping Engine..................................................................... 4-10 Parking ................................................................................... 4-10a 4.7 Amplified Normal Procedures (General) ................................... 4-11 4.9 Preflight Check ........................................................................... 4-11 4.11 Before Starting Engine ............................................................... 4-14 4.13 Starting Engine ........................................................................... 4-14 4.15 Warm-Up .................................................................................... 4-16 4.17 Taxiing ........................................................................................ 4-16 REPORT: VB-910 ISSUED: JUNE 1, 1978 4-ii TABLE OF CONTENTS (cont) SECTION 4 (cont) Paragraph Page No. No. 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 ......................................................................... 4-23 4.33 Parking ........................................................................................ 4-24 4.35 Stalls ........................................................................................... 4-24 4.37 Turbulent Air Operation ............................................................. 4-25 4.39 Weight and Balance .................................................................... 4-25 ISSUED: JUNE 1, 1978 REPORT: VB-910 4-1 PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES REVISED: JULY 23, 1982 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. Normal procedures associated with those optional systems and equipment which require handbook supplements are provided by Section 9 (Supplements). These procedures are provided to present a source of reference and review and to supply information on procedures which are not the same for all aircraft. Pilots should familiarize themselves with the procedures given in this section in order to become proficient in the normal operations of the airplane. The first portion of this section consists of a short form check list which supplies an action sequence for normal operations with little emphasis on the operation of the systems. The remainder of the section is devoted to amplified normal procedures which provide detailed information and explanations of the procedures and how to perform them. This portion of the section is not intended for use as an in-flight reference due to the lengthy explanations. The short form check list should be used for this purpose. 4.3 AIRSPEEDS FOR SAFE OPERATIONS The following airspeeds are those which are significant to the safe operation of the airplane. These figures are for standard airplanes flown at gross weight under standard conditions at sea level. SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 4-2 REVISED: JANUARY 15, 1979 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 85 KIAS (b) Best Angle of Climb Speed 73 KIAS (c) Turbulent Air Operating Speed (See Subsection 2.3) 124 KIAS (d) Maximum Flap Speed 102 KIAS (e) Landing Final Approach Speed (Flaps 40°) 72 KIAS (f) Maximum Demonstrated Crosswind Velocity 17 KTS ISSUED: JUNE 1, 1978 REPORT: VB-910 4-3 PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES REVISED: AUGUST 27, 1979 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 Annunciator panel..................................................................................check Master switch...........................................................................................OFF Primary flight controls ..........................................................proper operation Flaps .....................................................................................proper operation Trim .....................................................................................................neutral Pitot and static systems ...........................................................................drain Windows ...................................................................................... check clean WALK-AROUND Figure 4-1 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 4-4 REVISED: JULY 13, 1984 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 Wing tip and lights ................................................................................check Fuel tank .................................................................................... check supply visually - secure cap Fuel tank vent ......................................................................................... clear Fuel tank sump ......................................................drain and check for water, sediment and proper fuel Tie down and chock ............................................................................ remove Main gear strut ..................................................................................... proper inflation (4.5 in.) Tire ........................................................................................................check Brake block and disc ..............................................................................check Fresh air inlet .......................................................................................... clear NOSE SECTION General condition ..................................................................................check Cowling ................................................................................................secure Windshield............................................................................................. clean Propeller and spinner .............................................................................check Air inlets ................................................................................................. clear Alternator belt........................................................................... check tension Chock ................................................................................................. remove Nose gear strut ..................................................................................... proper inflation (3.25 in.) Nose wheel tire ......................................................................................check Oil............................................................................................check quantity Dipstick ..................................................................................properly seated Fuel strainer ............................................................................................drain LEFT WING Surface condition .......................................................clear of ice. frost, snow Fresh air inlet .......................................................................................... clear ISSUED: JUNE 1, 1978 REPORT: VB-910 4-5 PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES REVISED: JULY 13, 1984 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, sediment and proper fuel Tie down ............................................................................................. remove Pi tot head ............................................................................... remove cover - holes clear Wing tip and lights ............................................................................... check Aileron and hinges .................................................................................check Flap and hinges ..................................................................................... check FUSELAGE Antennas ................................................................................................check Left static pad ......................................................................................... clear Empennage ................................................................clear of ice, frost, snow Fresh air inlet .......................................................................................... clear Stabilator and trim tab ...........................................................................check Tie down ............................................................................................. remove Right static pad ....................................................................................... clear Master switch............................................................................................ ON Cockpit lighting .....................................................................................check Nav and strobe lights .............................................................................check Stall warning: ........................................................................................check Pitot heat ................................................................................................check All switches .............................................................................................OFF Passengers .............................................................................................board Cabin door ............................................................................ close and secure Seat belts and harness ............................................................. fasten/ adjust - check inertia reel BEFORE STARTING ENGINE Parking brake ............................................................................................. set Propeller ........................................................................ full INCREASE rpm Fuel selector ................................................................................desired tank Carburetor heat ........................................................................................OFF Radios ......................................................................................................OFF SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-236, DAKOTA REPORT: VB-910 ISSUED: JUNE 1, 1978 4-6 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. After engine starts, lock primer. STARTING ENGINE WHEN HOT Throttle .......................................................................................... I / 2” open Master switch............................................................................................ ON Electric fuel pump .................................................................................... ON Mixture ........................................................................................... full RICH Starter ..................................................................................................engage Throttle ................................................................................................. adjust Oil pressure............................................................................................check STARTING ENGINE WHEN FLOODED Throttle .............................................................................................open full Master switch............................................................................................ ON Electric fuel pump ...................................................................................OFF Mixture ......................................................................................... idle cut-off Starter ..................................................................................................engage Mixture ..............................................................................................advance Throttle ................................................................................................. retard Oil pressure............................................................................................check STARTING WITH EXTERNAL POWER SOURCE Master switch...........................................................................................OFF All electrical equipment ...........................................................................OFF Terminals ........................................................................................... connect External power plug .............................................................insert in fuselage ISSUED: JUNE 1, 1978 REPORT: VB-910 4-7 PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-236, DAKOTA NORMAL PROCEDURES REVISED: JULY 13, 1984 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 ...........