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

TOMAHAWK PILOT’S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL AIRPLANE AIRPLANE SERIAL NO. __________________________ REGIST. NO. ______________________ PA-38-112 REPORT: 2126 FAA APPROVED BY: _____________________________________ WARD EVANS D.O.A. NO. SO-1 DATE OF APPROVAL: PIPER AIRCRAFT CORPORATION JANUARY 20,1978 VERO BEACH, FLORIDA FAA APPROVED IN NORMAL AND UTILITY CATEGORIES BASED ON FAR 23 AND FAR PART 21, SUBPART J. THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY FAR 23 AND FAR PART 21, SUBPART J AND CONSTITUTES THE APPROVED AIRPLANE FLIGHT MANUAL AND MUST BE CARRIED IN THE AIRPLANE AT ALL TIMES. HANDBOOK PART NO. 761 658 REPORT: VB-2126 ISSUED: JANUARY 20, 1978 ii REVISED: MAY 2, 2012 Published by PUBLICATIONS DEPARTMENT Issued: January 20, 1978 © 1978-1979, 1981-1982,1989,2012 PIPER AIRCRAFT, INC. All Rights Reserved WARNING EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS HANDBOOK TO APPLICABLE AIRCRAFT. THIS HANDBOOK IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED ON THE FACE OF THE TITLE PAGE. SUBSEQUENT REVISIONS SUPPLIED BY PIPER MUST BE PROPERLY INSERTED. APPLICABILITY Application of this handbook is limited to the specific Piper PA-38-112 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. REVISIONS The information compiled in the Pilot’s Operating Handbook, with the exception of the equipment list, will be kept current by revisions distributed to the airplane owners. The equipment list was current at the time the air- plane was licensed by the manufacturer and thereafter must be maintained by the owner. Revision material will consist of information necessary to update the text of the present handbook and/or to add information to cover added airplane equipment. I. Revisions Revisions will be distributed whenever necessary as complete page replacements or additions and shall be inserted into the handbook in accordance with the instructions given below: 1. Revision pages will replace only pages with the same page number. 2. Insert all additional pages in proper numerical order within each section. 3. Page numbers followed by a small letter shall be inserted in direct sequence with the same common numbered page. II. Identification of Revised Material Revised text and illustrations shall be indicated by a black vertical line along the outside margin of the page, opposite revised, added or deleted material. A line along the outside margin of the page opposite the page number will indicate that an entire page was added. REPORT: 2126 iii 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 2-9, 3-1 through 3-14, 4-1 through 4-22, 5-1 through 5-29, 6-1 through 6-30, 7-1 through 7-23, 8-1 through 8-17, 9-1, and 10-1 through 10-2. REPORT: 2126 iv PILOT’S OPERATING HANDBOOK LOG OF REVISIONS Current Revisions to the PA-38-112 Tomahawk Pilot’s Operating Handbook, REPORT: 2126 issued January 20, 1978. Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 1 1-3 Revised 1.7 (c) (2) and (3). 761 658 1-4 Revised item 1.11 (c). (PR780623) 1-l4 Revised ft.-lb. conversion. 1-16 Revised Kg conversion. 2-i Added item 2.18. 2-5 Added item 2.18. 3-1 Corrected para. 3.1. 4-i Revised page numbers. 4-6 Added new items; relocated items to pg. 4-7. 4-7 Added items from pg. 4-6; relocated item to pg. 4-8. 4-8 Added items from pg. 4-7; relocated items to pg. 4-9. 4-9 Added items from pg. 4-8; relocated items to pg. 4-10. 4-10 Added items from pg. 4-9; relocated items to pg. 4-11. 4-11 Added items from 4-10; relocated items to pg. 4-12. 4-12 Added items from pg. 4-11; relocated items to pg. 4-13. 4-13 Added items from pg. 4-13; relocated items to pg. 4-14. 4-14 Added items from pg. 4-14; relocated items to pg. 4-17. 4-15 Added item 4.13 (d); relocated items to pg. 4-18. 4-16 Relocated items to pgs. 4-18 and 4-l9. 4-17 Added new info.; added items from pg. 4-14; relocated items to pg. 4-20. REPORT: 2126 v PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 1 (cont) 4-18 Added items from pg. 4-15; relocated items to pgs. 4-20 and 4-21. 4-19 Added items from pgs. 4-16 and 4-17; relocated items to pgs. 4-21 and 4-22. 4-20 Added items from pg. 4-17; relocated items to pgs. 4-22 and 4-23. 4-21 Added items from pg. 4-18; relocated items to pg. 4-24. 4-22 Added items from pgs. 4-19 and 4-20; relocated items to pgs. 4-24 and 4-25. 4-23 Added page; added items from pgs. 4-20 and 4-21. 4-24 Added page; added items . from pg. 4-21. 4-25 Added page; added items from pg. 4-22. 5-12 Revised Figure 5-3. 6-9 Revised item 6.7. 6-10 Revised Figure 6-13. 6-14 Revised item 7. 6-20 Deleted item 101. 6-22 Revised items 125 and 127. 6-25 Revised items 171, 173 and 175. 6-26 Revised items 185, 187, 189, 191, 193, 195, 197, 199 and 201. 6-27 Revised items 203, 205, 207, 209, 211, 213, 2l5 and 217. 6-28 Revised items 219 and 223. 6-30 Added item 313. 7-16 Revised item 7.21. 8-11 Revised item 8.21 (b). Paul Everly 8-12 Removed chart. June 23, 1978 REPORT: 2126 vi PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 2 1-7,1-18 Revised spelling. 761 658 2-4 Added footnote. (PR781013) 3-6 Revised Spin Recovery info. 5-3 Revised Figure nos. 6-9,6-10 Revised footnote. 6-13 Revised TC no. 6-19 Added item 90. 6-25 Revised item no.; added new items 172 and 173; revised items 171 and 175. 6-26 Revised item 185. 6-27 Deleted item 209; revised item nos. 6-28 Revised item nos. 6-29 Revised item 301. 7-2 Revised alternator volt.; added oil cooler info.; relocated info. to pg. 7-3. 7-3 Added info. from pg. 7-2. 7-12 Revised Figure 7-11. 7-18 Revised Figure 7-17. 7-19 Added heat duct info.; relo- cated info. to pg. 7-21. 7-21 Added info. from pg. 7-19. 8-i, 8-17 Added para. 8.31, Winter- Paul E. Everly ization. Oct. 13, 1978 Rev. 3 2-2 Revised para. 2.5; 761 658 relocated info. to pg. 2-3. (PR781218) 2-3 Added info. from pg. 2-2. 2-7 Added placard to para. 2.25. 2-9 Added placard to para. 2.25. 3-2 Added new stall speeds. 3-4, 3-9 Revised approach speed; added footnote. 3-12 Revised para. 3.19. REPORT: 2126 vi-a PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 3 4-2 Revised para. 4.3 (e). 761 658 4-9 Revised approach speed. (PR781218) 4-20 Added info. from pg. 4-21. (cont) 4-21 Relocated info. to pg. 4-20; revised approach speed; added footnote. 4-24 Revised para. 4.43. 5-9 Added figures; revised pg. nos. 5-10 Added Fig. 5-l from pg. 5-11. 5-11 Relocated Fig. 5-l to pg. 5-10; added relocated Fig. from pg. 5-12. 5-12 Changed Fig. 5-3 to 5-2 and relocated to pg. 5-11; added new Fig. 5-3. 5-28 Revised Fig. 5-35. 5-28a Added pg. (Added Fig. 5-36). 5-28b Added pg. (Added Fig. 5-37 from pg. 5-29). 5-29 Relocated Fig. 5-37 to pg. 5-28b; added Fig. 5-38. 6-18 Revised item 59. 6-19 Added item 83. 6-23 Revised item 135. Paul E. Everly 6-30 Added item 315. Dec. 18, 1978 Rev. 4 1-3, 2-2 Revised to add optional 761 658 engine. (PR790301) 2-3 Revised item (1). 4-5 Revised engine cold start info. Relocated material to pg. 4-6. 4-6 Added relocated material. 4-14 Revised para. 4.13 (a) (b) & (c). Relocated material to pg. 4-15. REPORT: 2126 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. 4 4-15 Revised and relocated material 761 658 from pg. 4-14, para. 4.13 (c). (PR790301) 4-17 Added relocated & revised (cont) material from pg. 4-l8. 4-18 Relocated material to pg. 4-17 Added note at top of pg. 6-1, 6-2 Revised para. 6.1. 6-9, Added info. for seat position 6-10, arm aft datum 6-11 6-14 Revised items 7 & 15. 6-15 Added item 27. 6-19 Added item 87 & relocated items 89 & 90 to pg. 6-20. 6-20 Added relocated items 89 & 90. Revised item 103. 6-21 Deleted items 109, 111, 113, 115, 117 & 119. Added new items 109 & 119. Added re- located item 123 from pg. 6-22. 6-22 Relocated item 123 to pg. 6-21. Added items 129 & 131. 7-2 Revised to add optional engine. 7-8 Revised engine primer descrip- tion. 7-10 Added strobe light info. & warning. Relocated material to pg. 7-13. 7-13 Added relocated material from Pg 7-l0. Paul E. Everly 8-11 Revised to add optional engine. March 1, 1979 Rev. 5 1-4 Revised item 1.13. 761 658 2-3 Added winterization kit info. (PR790606) relocated info. to pg. 2-4. REPORT: 2126 vi-c PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 5 2-4 Added relocated info. from 761 658 pg. 2-3. (PR790606) 2-6 Revised noise level value. (cont) 2-9 Added winterization placard info. 3-i Revised index. 3-14 Added pitot-static pressure info. 4-6 Revised item. 4-7 Added item. 4-14 Revised item 4.13 (b). 4-18 Revised note. 5-1 Added 6.00 x 6 tire info. to item 5.3, relocated info. to pg. 5-2. 5-2 Added relocated items from pg. 5-1. 5-9 Revised list of Figures. 5-10 Relocated Fig. to pg. 5-10b. 5-10a Added pg. (added new Fig. 5-1). 5-10b Added pg. (added relocated Fig. from pg. 5-10). 6-9 Added values for sample problem. 6-21 Added item 104 and footnote; relocated items 121 and 123 to pg. 6-22. 6-22 Added relocated items from pg. 6-21. 6-25 Revised items 171, 172, 173, 174 and 175. 6-26 Revised items 201. 6-27 Revised items 205 and 213. 7-3 Added 6.00 x 6 tire info. to item 7.7. REPORT: 2126 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. 5 8-i Revised index. 761 658 8-8 Added 6.00 x 6 tire info. to (PR790606) item 8.15, relocated items to (cont) pg. 8-10. 8-10 Added items from pg. 8-8; re- located items to 8-11. 8-11 Added items from pg. 8-10; relocated items to 8-12. 8-12 Added items from pg. 8-11. 8-13 Relocated items to pg. 8-14. 8-14 Added and revised items re- located items to pg. 8-15. 8-15 Added items from pg. 8-14; relocated items to pg. 8-16. 8-16 Added items from pg. 8-15; relocated items to pg. 8-17. 8-17 Added items from pg. 8-16; relocated items to pg. 8-18. 8-18 Added pg; added and revised Paul E. Everly items from pg. 8-17. June 6, 1979 Rev. 6 2-5 Revised para. 2.18. 761 658 2-9 Added placard. (PR791206) 3-14 Revised para. 3.25. 4-7 Added to check list. 4-19 Revised para. 4.21. 5-13 thru Revised Figs. 5-5 thru 5-15. 5-18 5-20 thru Revised Figs. 5-10 thru 5-35. 5-28b Revised figs. 5-37. Paul E. Everly 7-12 Revised fig. 7-11. Dec. 6, 1979 REPORT: 2126 vi-e PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 7 ii Revised Warning. 761 658 1-2 Revised fig. 1-1. (PR810115) 1-4 Revised para. 1.13 (a) and (b). 2-i Revised Table of Contents. 2-5 Relocated para. 2.18 to pg. 2-6. 2-6 Relocated para. 2.23 to pg. 2-7; added para. 2.18 from pg. 2-5; revised para. 2.18 (a); added para. 2.18 (c). 2-7 Relocated para. 2.25 to pg. 2-8; added para. 2.23 from pg. 2-6. 2-8 Relocated placards to pg. 2-9; added placards from pg. 2-7. 2-9 Relocated placards to pg. 2-10; added placards from pg. 2-8. 2-10 Added pg.; added placards from pg. 2-9. 4-4 Revised normal procedures checklist. 4-12 Relocated info. to pg. 4-13; revised amplified normal procedures checklist; added new tire inflation specs. 4-13 Added info. from pg. 4-12. 4-17 Corrected spelling error. 6-i Revised Table of Contents. 6-14 Revised item 7. 6-16 Renumbered and relocated item to pg. 6-17; revised items 31 and 33. 6-17 Relocated items to pg. 6-17a; added new items 35 and 37; added item from pg. 6-16. REPORT: 2126 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. 7 6-17a Added pg.; added items from 761 658 pg. 6-17; added new items (PR810115) 51 and 53. (cont) 6-17b Added pg.; added items 57 thru 63 from pg. 6-18; revised item 59; added new item 62. 6-18 Relocated items 57 thru 63 to pg. 6-17b; added new item 69. 6-19 Revised item 87. 6-20 Revised item 103. 6-21 Revised item 104; deleted existing item 119; renum- bered item. 6-22 Revised item 121; deleted item 129. 6-23 Revised items 135, 139 thru 145. 6-24 Revised items 149 and 153. 6-25 Relocated item 175 to pg. 6-26; deleted existing item 171; added new item 171; revised item 173. 6-26 Added item 175 from pg. 6-25; changed items 197 to 198 and relocated items 198 thru 201 to pg. 6-27. 6-27 Added new item 196 and 197; added items 198 thru 201 from pg. 6-26; relocated items 211 thru 213 to pg. 6-28. 6-28 Changed items 219 and 221 to 221 and 223 respectively: added items 211 thru 213 from pg. 6-27; added new item 219. REPORT: 2126 vi-g PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 7 6-29 Revised items 301, 305 thru 761 658 311. (PR810115) 6-30 Added new item 317 thru (cont) 321; relocated form to pg. 6-31. 6-31 Added pg.; added form from pg. 6-30. 7-i Revised Table of Contents. 7-2 Added info. from pg. 7-3. 7-3 Relocated info. to pg. 7-2; added serial number effectivity to para. 7.7 7-11 Added serial number effectivity; revised schematic. 7-11a Added pg. 7-11b Added pg.; added fig. 7-9a. 7-13 Added serial number effectivity. 7-14 Revised fig. 7-13. 7-18 Revised fig. 7-17; added serial number effectivity. 7-19 Revised para. 7.25. 7-22 Corrected spelling error. 7-24 Added pg.; added para. 7.37. 8-8 Added serial number effectivity to para. 8.15. 8-14 Relocated info. to pg. 8-15; added serial number effectivity to para. 8.23. Paul E. Everly 8-15 Added info. from pg. 8-14. Jan. 15. 1981 Rev. 8 2-10 Revised para. 2.25. 761 658 2-11 New page; cont. revision (PR810430) para. 2.25. 4-i Changed pg. no. 4-23 Revised para. 4.35; moved para. 4.39 to pg. 4-24. REPORT: 2126 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. 8 4-24 Relocated para. 4.39 from 761 658 pg. 4.23; revised para. 4.4. (PR810430) 4-25 Cont. revision para. 4.43. (cont) 4-26, New page; cont. revision 4-27 para. 4.43. 5-22 Revised fig. 5-23. 5-23 Revised fig. 5-25. 5-24 Revised fig. 5-27. 5-25 Revised fig. 5-29. 7-5 Relocated info. from pg. 7-6. 7-6 Moved info. to pg. 7-5; revised para. 7.13. 7- 17 Revised fig. 7-15. Paul E. Everly 8-12 Revised para. 8.21. April 30, 1981 Rev. 9 5-2 Added Warning. 761 658 6-i Revised pg. no. (PR810630) 6-6 Revised Figure 6-7. 6-25 Renumbered items, revised and relocated item. 6-25a Added pg. (added new items 177 thru 182). 6-25b Added pg. (added revised, renumbered and relocated item 191; added new items 193 thru 197). 6-25c Added pg. 6-25d Added pg. (added revised, renumbered and relocated item 201; added new items 203 thru 207). 6-26 Relocated item; renumbered items; added relocated items. 6-27, Relocated items; re- 6-28 numbered items; revised items REPORT: 2126 vi-i PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 9 6-29 Added renumbered and re- 761 658 located items; added new (PR810630) items 255 and 257. (cont) 6-30 Added relocated items. 6-31 Added relocated items; re- Paul E. Everly moved info. June 30, 1981 Rev. 10 1-6 Corrected spelling error. 761 658 2-3 Revised para. 2.7 (e); revised (PR811102) para. 2.9 (c). 2-6 Revised para. 2.18 (a). 4-7 Revised para. 4.5. 4-12 Revised para. 4.9. 4-18 Revised para. 4.19. 6-1 Revised para. 6.1. 6-6 Added paren. to fig. 6-7. 6-18 Revised item 65. 6-27 Revised item 235. 7-5 Revised para. 7.9. 7-13 Revised para . 7.15. Paul E. Everly 8-18 Revised para. 8.27 (f). Nov. 2, 1981 Rev. 11 iii Revised revision para . 761 658 1-i Revised Table of Contents. (PR820510) 1-12 Removed para. 1.21. thru 1-21 2-1 Revised para. 2.1. 2-3 Revised para. 2.9. 3-i Revised Table of Contents. 3-1 Revised para. 3.1. 4-i Revised Table of Contents. 4-ii New page; cont. revised Table of Contents. 4-1 Revised para. 4.1. 4-18 Revised Note. REPORT: 2126 vi-j ISSUED: JANUARY 20, 1978 REPORT: VB-2126 vi-k PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cONT) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 11 4-19 Revised para. 4.21. 761 658 5-3 Revised para. 5.5(a), (b), (c), (PR820510) thru (d), (f), (g). (cont) 5-7 6-i Revised Table of Contents. 6-1 Revised para. 6.1. 6-2 Revised para. 6.3. 6-5 Revised para. 6.5. 6-6 Revised para. 6.7. 6-7 Revised para. 6.9. 6-13 Revised para. 6.9. 7-i Revised Table of Contents. 7-8 Revised para. 7.13. 7-14 Revised fig. 7-13. 7-16 Revised para. 7.21. Paul E. Everly 7-24 Added para. 7.39. May 10, 1982 Rev. 12 1-12 Delete pg. 761 658 2-i Revised Table of Contents (PR821029) 2-6 Relocated para. 2.21 to pg. 2-7; revised para. 2.18. 2-7 Added para 2.21 from pg. 2-6. 5-1 Revised para. 5.3. 8-2 Revised para. 8.3. 8-3 Revised para 8.3 info.; revised para. 8.5. 8-4 Deleted para 8.5 info. from Paul E. Everly pg. 8-4. Oct. 29, 1982 Rev. 13 3-1 Revised para. 3.1. 761 658 4-8 Revised Short Field, Obstacle (PR890428) Clearance Takeoff. 7-3 Revised para. 7.7. Added Warning. REPORT: VB-2126 ISSUED: JANUARY 20, 1978 vi-l REVISED: MAY 2, 2012 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cONT) Revision FAA Approval Number and Revised Description of Revision Signature and Code Pages Date Rev. 13 7-5, Revised para. 7.9. 761 658 7-6 (PR890428) 7-14 Revised fig. 7-13 callouts. (cont) 7-16 Revised serial numbers. 8-1 Revised para. 8.1 8-2 Revised paras. 8.1 and 8.3. 8-3 Revised para. 8.3. D. H. Trompler May 15, 1989 Date Rev. 14 ii Updated copyright. (PR120502) vi-l Added Rev. 14 to L of R. 4-23 Revised Para. 4.35. Wayne E. Gaulzetti May 2, 2012 TABLE OF CONTENTS SECTION 1 GENERAL SECTION 2 LIMITATIONS SECTION 3 EMERGENCY PROCEDURES SECTION 4 NORMAL PROCEDURES SECTION 5 P E R F O R M A N C E 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 O P E R ATING TIPS REPORT: 2126 vii 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: 2126 1-i 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 FAR 23 and FAR Part 21, Subpart J. 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 responsi- bility 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 left blank intentionally. PIPER AIRCRAFT CORPORATION SECTION 1 PA-38-112, TOMAHAWK GENERAL ISSUED: JANUARY 20, 1978 REPORT: 2126 1-1 THREE VIEW Figure 1-1 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 1-2 REVISED: JANUARY 15, 1981 1.3 ENGINE (a) Number of Engines 1 (b) Engine Manufacturer Lycoming (c) Engine Model Number O-235-L2C (with Slick Mags.)or O-235-L2A (with Bendix Mags.) (d) Rated Horsepower 112 (e) Rated Speed (rpm) 2600 (f) Bore (in.) 4.375 (g) Stroke (in.) 3.875 (h) Displacement (cu. in.) 233.3 (i) Compression Ratio 8.5:1 (j) Engine Type Four Cylinder, Direct Drive, Horizontally Opposed, Air Cooled 1.5 PROPELLER (a) Number of Propellers 1 (b) Propeller Manufacturer Sensenich (c) Model 72CK-0-56 (d) Number of Blades 2 (e) Propeller Diameter (in.) (1) Maximum 72 (2) Minimum 70 (f) Propeller Type Fixed Pitch 1.7 FUEL (a) Fuel Capacity (U.S. gal.) (total) 32 (b) Usable Fuel (U.S. gal.) (total) 30 (c) Fuel Grade, Aviation (1) Minimum Octane 100/130-Green (2) Specified Octane 100/130-Green 100-Green 100LL-Blue (3) Alternate Fuels* 115/145-Purple *Alternate Fuels refers to military grade with 4.6 ml of TEL. See Section 8.25, Fuel System. PIPER AIRCRAFT CORPORATION SECTION 1 PA-38-112, TOMAHAWK GENERAL ISSUED: JANAURY 20, 1978 REPORT: 2126 REVISED: MARCH 1, 1979 1-3 1.9 OIL (a) Oil Capacity (U.S. qts.) 6 (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 Normal Utility (a) Maximum Takeoff Weight (lbs.) 1670 1670 (b) Maximum Landing Weight (lbs.) 1670 1670 (c) Maximum Weight (lbs.) in Baggage Compartment at Fuselage Station 115.0 100 100 1.13 STANDARD AIRPLANE WEIGHTS* (a) Standard Empty Weight (lbs.): Weight of a standard airplane includ- ing unusable fuel, full operating fluids and full oil. 1128 (b) Maximum Useful Load (lbs.): The difference between the Maximum Takeoff Weight and the Standard Empty Weight. 542 1.15 BAGGAGE SPACE (a) Compartment Volume (cu. ft.) 20 (b) Floor Loading (lbs. per sq. ft.) 25 *These values are approximate and vary from one aircraft to another. Refer to Figure 6-7 for the Standard Empty Weight value and the Useful Load value to be used for C.G. calculations for the aircraft specified. SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 1-4 REVISED: JANUARY 15, 1981 1.17 SPECIFIC LOADINGS (a) Wing Loading (lbs. per sq. ft.) 13.39 (b) Power loading (lbs. per hp) 14.9 PIPER AIRCRAFT CORPORATION SECTION 1 PA-38-112, TOMAHAWK GENERAL ISSUED: JANUARY 20, 1978 REPORT: 2126 1-5 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY The following definitions are of symbols, abbreviations and termi- nology 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 air- craft as shown on the airspeed indicator when corrected for instrument error. IAS values published in this handbook assume zero instrument 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 airplane. VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 1-6 REVISED: NOVEMBER 2, 1981 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. VS Stalling Speed or the minimum steady flight speed at which the airplane is con- trollable. VSO Stalling Speed or the minimum steady flight speed at which the airplane 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 tempera- ture 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 inflight temperature indications or ground meteorological sources, adjusted for in- strument error and compressibility effects. PIPER AIRCRAFT CORPORATION SECTION 1 PA-38-112, TOMAHAWK GENERAL ISSUED: JANUARY 20, 1978 REPORT: 2126 REVISED: OCTOBER 13, 1978 1-7 Indicated 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 Pressure 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 altimeter. It is the indicated pressure altitude corrected for position and instrument 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 understood 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 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 1-8 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. C.G. Arm The arm obtained by adding the airplane’s individual moments and dividing the sum by the total weight. C.G. Limits The extreme center of gravity locations within which the airplane 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 govern- mental 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.) SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 1-10 Maximum Maximum weight approved for the start of Takeoff Weight the takeoff run. Maximum Maximum weight approved for the landing Landing Weight touchdown. Maximum Zero Maximum weight exclusive of usable fuel. Fuel Weight PIPER AIRCRAFT CORPORATION SECTION 1 PA-38-112, TOMAHAWK GENERAL ISSUED: JANUARY 20, 1978 REPORT: 2126 1-11 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 ............................................................................. 2-4 2.13 Center of Gravity Limits............................................................. 2-4 2 15 Maneuver Limits......................................................................... 2-5 2 17 Flight Maneuvering Load Factors............................................... 2-5 2.18 Service Life Limits ..................................................................... 2-6 2.19 Types of Operations .................................................................... 2-6 2.21 Fuel Limitations.......................................................................... 2-7 2.23 Noise Levels ............................................................................... 2-7 2.25 Placards....................................................................................... 2-8 REPORT: 2126 2-i SECTION 2 LIMITATIONS 2.1 GENERAL This section provides the “FAA Approved” operating limitations, instrument markings, color coding and basic placards necessary for the operation of the airplane and its systems. This airplane must be operated as a normal or utility category airplane in compliance with the operating limitations stated in the form of placards and markings and those given in this section and handbook. 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. 1670 lbs. 103 101 1277 lbs. 90 88 CAUTION Maneuvering speed decreases at lighter weight as the effects of aerodynamic forces become more pronounced. Linear interpolation may be used for intermediate gross weights. Maneuvering speed should not be exceeded while operating in rough air. PIPER AIRCRAFT CORPORATION SECTION 2 PA-38-112, TOMAHAWK LIMITATIONS ISSUED: JANUARY 20, 1978 REPORT: 2126 REVISED: MAY 10, 1982 2-1 SPEED KIAS KCAS Never Exceed Speed (VNE) - Do not exceed this speed in any operation. 138 143 Maximum Structural Cruising Speed (VNO) - Do not exceed this speed except in smooth air and then only with caution. 110 108 Maximum Flaps Extended Speed (VFE) - Do not exceed this speed with the flaps extended. 89 87 2.5 AIRSPEED INDICATOR MARKINGS MARKING IAS Red Radial Line (Never Exceed) 138 KTS Yellow Arc (Caution Range - Smooth 110 KTS to Air Only) 138 KTS Green Arc (Normal Operating Range) 48 KTS to (Outboard Flow Strips Installed) 110 KTS Green Arc (Normal Operating Range) 52 KTS to (Outboard and Inboard Flow Strips 110 KTS Installed) White Arc (Flap Down ) (Outboard Flow 47 KTS to Strips Installed) 89 KTS White Arc (Flap Down) (Outboard and 49 KTS to Inboard Flow Strips Installed) 89 KTS 2.7 POWER PLANT LIMITATIONS (a) Number of Engines 1 (b) Engine Manufacturer Lycoming (c) Engine Model No. O-235-L2C (with Slick Mags.) or O-235-L2A (with Bendix Mags.) SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 2-2 REVISED: MARCH 1, 1979 (d) Engine Operating Limits (1) Maximum Horsepower 112 (2) Maximum Rotation Speed (RPM) 2600 (3) Maximum Oil Temperature 245°F (e) Oil Pressure Minimum (red line) *15 PSI Maximum (red line) 100 PSI (f) Fuel Pressure Minimum (red line) .5 PSI Maximum (red line) 8 PSI (g) Fuel Grade - Minimum 100/130 - Green (h) Number of Propellers 1 (i) Propeller Manufacturer Sensenich (j) Propeller Model 72CK-0-56 (k) Propeller Diameter Maximum 72 IN. Minimum 70 IN. (l) Propeller Tolerance (static RPM at maximum permissible throttle setting) Not above 2350 RPM Not below 2200 RPM No additional tolerance permitted. (m) Winterization Kit (Optional) (1) Removed above 50° F OAT (2) OAT gauge required 2.9 POWER PLANT INSTRUMENT MARKINGS (a) Tachometer Green Arc (Normal Operating Range) 500 to 2600 RPM Red Line (Maximum Continuous Power) 2600 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) *15 PSI to 60 PSI Yellow Arc (Ground Warm-Up) 90 PSI to 100 PSI Red Line (Minimum) *15 PSI Red Line (Maximum) 100 PSI *Minimum limit reduced from 25 psi. All models approved for 15 psi. PIPER AIRCRAFT CORPORATION SECTION 2 PA-38-112, TOMAHAWK LIMITATIONS ISSUED: JANUARY 20, 1978 REPORT: 2126 REVISED: MAY 10, 1982 2-3 (d) Fuel Pressure Green Arc (Normal Operating Range) .5 PSI to 8 PSI Red Line (Minimum) .5 PSI Red Line (Maximum) 8 PSI 2.11 WEIGHT LIMITS Normal Utility (a) Maximum Weight 1670 lbs. 1670 lbs. (b) Maximum Baggage at Fuselage Station 115.0 100 lbs. 100 lbs.* CAUTION Baggage compartment loading should not exceed 25 lbs. per square foot. 2.13 CENTER OF GRAVITY LIMITS (a) Normal Category Weight Forward Limit Rearward Limit Pounds Inches Aft of Datum Inches Aft of Datum 1670 73.5 78.5 1277 72.4 78.5 (b) Utility Category Weight Forward limit Rearward Limit Pounds Inches Aft of Datum Inches Aft of Datum 1670 73.5 78.5 1277 72.4 78.5 *No baggage allowed for spins. SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 2-4 REVISED: JUNE 6, 1979 NOTES Straight line variation between points given. The datum used is 66.25 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 (a) Normal Category - All acrobatic maneuvers including spins prohibited. (b) Utility Category - Approved maneuvers for Utility Category Only. MANEUVER ENTRY SPEED Spins (flaps up) Stall Steep Turns 100 KIAS Lazy Eights 100 KIAS Chandelles 100 KIAS 2.17 FLIGHT MANEUVERING LOAD FACTORS Normal Utility (a) Positive Load Factor (Maximum) (1) Flaps Up 3.8 G 4.4 G (2) Flaps Down 2.0 G 2.0 G (b) Negative Load Factor (Maximum) No inverted maneuvers approved. PIPER AIRCRAFT CORPORATION SECTION 2 PA-38-112, TOMAHAWK LIMITATIONS ISSUED: JANUARY 20, 1978 REPORT: 2126 REVISED: JANUARY 15, 1981 2-5 2.18 SERVICE LIFE LIMITS (a) The lower longitudinal trim springs, drawing number 37523 or 61916-2, have a life limit of 1500 hours. (b) The service life of the wing, drawing number 77352, and associated structure has been established as 11,000 hours maximum. (c) The service life of the Steel Upper Rudder Hinge, drawing number 77610-03, has been established as 5000 hours of operation. (d) On aircraft with serial numbers 38-78A0001 through 38-80A0198, the service life of the fin spar attachment plate, drawing number 77553-05, has been established as 3000 hours of operation. (e) On aircraft with serial numbers 38-81A0001 through 38-82A0101 without Piper Kit 764 421 installed, the service life of the fin spar attachment plate, drawing number 77553-05, has been established as 3000 hours of operation. (f) On aircraft with serial numbers 38-81A0001 through 38-82A0101 with Piper Kit 764 421 installed, the service life of the fin spar attachment plate, drawing number 77553-05, has been established as 5000 hours of operation. (g) On aircraft with serial numbers 38-82A0102 and up, the service life of the fin spar attachment plate, drawing number 77553-05, has been established as 5000 hours of operation. 2.19 TYPES OF OPERATION The airplane is approved for the following operations when equipped in accordance with FAR 91. (a) Day V.F.R. (b) Night V.F.R. (c) Day I.F.R. (d) Night I.F.R. (e) Non Icing SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 2-6 REVISED: OCTOBER 29, 1982 2.21 FUEL LIMITATIONS (a) Total Capacity 32 U.S. GAL. (b) Unusable fuel 2 U.S. GAL . The unusable fuel for this airplane has been determined as 1.0 gallon in each wing in critical flight attitudes. (c) Usable Fuel 30 U.S. GAL. The usable fuel in this airplane has been determined as 15.0 gallons in each wing. (d) Fuel remaining when a quantity indi- cator reads zero cannot be used safely in flight. 2.23 NOISE LEVEL The noise level of this aircraft is 67.8d 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. PIPER AIRCRAFT CORPORATION SECTION 2 PA-38-112, TOMAHAWK LIMITATIONS ISSUED: JANUARY 20, 1978 REPORT: 2126 REVISED: OCTOBER 29, 1982 2-7 2.25 PLACARDS In full view of the pilot: Except as may be otherwise indicated on a placard, the markings and placards installed in this airplane contain operating limitations which must be complied with when operating this airplane in the normal category. Other operating limitations which must be complied with when operating this airplane in this category or in the utility category are contained in the Pilots Operating Handbook. Flaps up spins are approved for utility category operation. For spin recovery, use full rudder against the spin followed immediately by forward wheel. This airplane is approved for flight in day/night VFR/IFR when equipped in accordance with F.A.R. 91. Flight into known icing conditions is prohibited. DEMONSTRATED CROSSWIND COMPONENT 15 KNOTS FLAPS EXTENDED SPINS PROHIBITED UTILITY CATEGORY OPERATION ONLY MANEUVERS ARE LIMITED TO THE FOLLOWING ENTRY SPEED SPINS (FLAPS UP) STALL STEEP TURNS 100 KIAS LAZY EIGHTS 100 KIAS CHANDELLES 100 KIAS WARNING TURN OFF STROBE LIGHTS WHEN IN CLOSE PROXIMITY TO GROUND OR DURING FLIGHT THROUGH CLOUD, FOG OR HAZE. SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 2-8 REVISED: JANUARY 15, 1981 In full view of the pilot: TAKEOFF CHECK LIST Fuel - Proper Tank Belts/harness - Fastened Mixture - Set Flaps - Set Electric Fuel Pump - On Trim - Set Carburetor Heat - Off Controls - Free Engine Gages - Checked Doors - Latched Seats & Backs - Latched LANDING CHECK LIST Fuel - Proper Tank Seats & Backs - Latched Mixture - Rich Flaps - Set (White Arc) Electric Fuel Pump - On Belts/Harness - Fastened On baggage compartment aft bulkhead: BAGGAGE MAX. 100 LBS SEE PILOTS OPERATING HANDBOOK FOR LOAD DISTRIBUTION In full view of the pilot, near the airspeed indicator: MANEUVERING SPEED 103 KIAS AT 1670 LBS (SEE P.O.H.) In full view of the pilot, on the throttle quadrant: FUEL REMAINING WHEN THE QUANTITY INDICATORS READ ZERO CANNOT BE USED SAFELY IN FLIGHT 15 U. S. GAL. FUEL 15 U. S. GAL. USABLE USABLE L R TANK TANK PIPER AIRCRAFT CORPORATION SECTION 2 PA-38-112, TOMAHAWK LIMITATIONS ISSUED: JANUARY 20, 1978 REPORT: 2126 REVISED: JANUARY 15, 1981 2-9 In full view of the pilot, on the throttle quadrant: FUEL OFF In full view of the pilot, near the carburetor heat control: OFF CARB. HEAT ON On optional document container: THIS CONTAINER PROVIDED FOR AIRCRAFT DOCUMENTS MAXIMUM WEIGHT OF CONTENTS 1.5 LBS. In full view of the pilot: WINTERIZATION PLATES (4) REMOVE WHEN AMBIENT TEMPERATURE EXCEEDS 50°F On lower side panel, adjacent to pilot seat (Aircraft with serial numbers 38-78A0001 thru 38-81A0006): STATIC SYSTEM DRAIN SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 15, 1981 2-10 REVISED: APRIL 30, 1981 In view of the pilot (Aircraft with serial numbers 38-78A000l thru 38-81A0006): ALTERNATE STATIC SOURCE TO OPEN PUSH FORWARD In view of the pilot (Aircraft with serial numbers 38-81A0007 and up): ALTERNATE STATIC SOURCE STATIC SYSTEM DRAIN TO OPEN RAISE HANDLE PIPER AIRCRAFT CORPORATION SECTION 2 PA-38-112, TOMAHAWK LIMITATIONS ISSUED: APRIL 30, 1981 REPORT: 2126 2-11 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 Alternator Failure................................................................... 3-5 Spin Recovery ........................................................................ 3-5 Open Door.............................................................................. 3-6 Engine Roughness.................................................................. 3-6 3.5 Amplified Emergency Procedures (General).............................. 3-7 3.7 Engine Inoperative Procedures ................................................... 3-7 Engine Power Loss During Takeoff (Not Airborne).............. 3-7 Engine Power Loss During Takeoff (If Airborne) ................. 3-7 Engine Power Loss In Flight.................................................. 3-8 Power off Landing ................................................................. 3-9 3.9 Fire.............................................................................................. 3-9 Engine Fire During Start........................................................ 3-9 Fire In Flight .......................................................................... 3-10 3.1 I Loss of Oil Pressure.................................................................... 3-11 3.13 Loss Of Fuel Pressure................................................................. 3-11 3.15 High Oil Temperature ................................................................. 3-11 3.17 Alternator Failure........................................................................ 3-12 3.19 Spin Recovery (Unintentional Spin)........................................... 3-12 3.21 Open Door .................................................................................. 3-13 3.23 Engine Roughness ...................................................................... 3-13 3.25 Loss of Pitot-Static Pressure....................................................... 3-14 REPORT: 2126 3-i 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 in Section 9 (Supplements). The first portion of this section consists of an abbreviated emergency checklist 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. PIPER AIRCRAFT CORPORATION SECTION 3 PA-38-112, TOMAHAWK EMERGENCY PROCEDURES ISSUED: JANUARY 20, 1978 REPORT: 2126 REVISED: APRIL 28, 1989 3-1 3.3 EMERGENCY PROCEDURES CHECKLIST SPEEDS Stall speeds 1670 lbs (0° flap) (Outboard Flow Strips Installed)......................48 KIAS 1670 lbs. (full flap) (Outboard Flow Strips Installed)...................47 KIAS 1670 lbs. (0° flap) (Outboard and Inboard Flow Strips Installed) ............................................................................52 KIAS 1670 lbs. (full flap) (Outboard and Inboard Flow Strips Installed) ............................................................................49 KIAS Maneuvering speeds 1670 lbs......................................................................................103 KIAS 1277 lbs........................................................................................90 KIAS Never exceed speed.........................................................................138 KIAS Power off glide speeds 1670 lbs. (0° flap).........................................................................70 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. SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 3-2 REVISED: DECEMBER 18, 1978 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 above stall 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 (70 KIAS) and prepare for power off landing. PIPER AIRCRAFT CORPORATION SECTION 3 PA-38-112, TOMAHAWK EMERGENCY PROCEDURES ISSUED: JANUARY 20, 1978 REPORT: 2126 3-3 POWER OFF LANDING Trim for best glide angle (70 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 62 KIAS* or 67 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. *Outboard Flow Strips Installed **Outboard and Inboard Flow Strips Installed SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 3-4 REVISED: DECEMBER 18, 1978 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. ALTERNATOR FAILURE Verify failure Reduce electrical load as much as possible. Alternator circuit breaker.......................................................................check Alt switch ........................................................................OFF (for 1 second), then ON If no output: Alt switch ................................................................................................OFF Reduce electrical load and land as soon as practical. SPIN RECOVERY (UNINTENTIONAL SPIN) Ailerons ...............................................................................................neutral Rudder ....................................................................................full opposite to direction of rotation PIPER AIRCRAFT CORPORATION SECTION 3 PA-38-112, TOMAHAWK EMERGENCY PROCEDURES ISSUED: JANUARY 20, 1978 REPORT: 2126 3-5 Control wheel...............................................................................full forward Throttle ...................................................................................................close Rudder ...............................................................neutral (when rotation stops) Control wheel.............................................................as required to smoothly regain level flight attitude Flaps .....................................................................................................retract 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 90 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 ENGINE ROUGHNESS Carburetor heat..........................................................................................ON If roughness continues after one minute: 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. SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 3-6 REVISED: OCTOBER 13, 1978 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 INOPERATIVE PROCEDURES 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 CUT- OFF, 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. PIPER AIRCRAFT CORPORATION SECTION 3 PA-38-112, TOMAHAWK EMERGENCY PROCEDURES ISSUED: JANUARY 20, l978 REPORT: 2126 3-7 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 70 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 may 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. SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 3-8 POWER OFF LANDING If loss of power occurs at altitude, trim the airplane for best gliding angle (70 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 62 KIAS* or 67 BIAS** 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. It the engine is not running, continue cranking with the starter. This is an attempt to draw the fire back into the engine. *Outboard Flow Strips Installed **Outboard and Inboard Flow Strips Installed PIPER AIRCRAFT CORPORATION SECTION 3 PA-38-112, TOMAHAWK EMERGENCY PROCEDURES ISSUED: JANUARY 20, 1978 REPORT: 2126 REVISED: DECEMBER 18, 1978 3-9 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 an 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. SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 3-10 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. PIPER AIRCRAFT CORPORATION SECTION 3 PA-38-112, TOMAHAWK EMERGENCY PROCEDURES ISSUED: JANUARY 20, 1978 REPORT: 2126 3-11 3.17 ALTERNATOR FAILURE Loss of alternator output is detected through zero reading on the ammeter and illumination of the alternator warning light on the instrument panel. 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 breaker for a popped circuit breaker. The next step is to attempt to reset the overvoltage relay. This is accomplished by turning the ALT switch OFF for one second and then 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 zero 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. 3.19 SPIN RECOVERY (UNINTENTIONAL SPIN) Intentional spins are permitted only with flaps fully retracted for utility category operation. Should a spin be entered inadvertently, the following procedure should be initiated: (a) Neutralize the ailerons. (b) Apply and maintain full rudder opposite the direction of rotation. (c) As the rudder hits the stop, push the control wheel fully forward. As the stall is broken, relax forward pressure to prevent an excessive airspeed build up. (d) Close the throttle. (e) As rotation stops, neutralize the rudder and ease back on the control wheel to recover smoothly from the dive. (f) Retract the flaps if they have been extended. SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 3-12 REVISED: DECEMBER 18, 1978 NOTES For more detailed information, see Spins in Section 4 - Normal Procedures. Inappropriate use of the spin recovery procedure, such as during stall recovery, may induce a spin entry. 3.21 OPEN DOOR The cabin doors on the Tomahawk 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 90 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. 3.23 ENGINE ROUGHNESS Engine roughness is usually due to carburetor icing which is indicated by a drop in RPM, 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). RPM will decrease slightly and roughness will increase. Wait for a decrease in engine roughness or an increase in RPM, indicating ice removal. If no change in approximately one minute, return the carburetor heat to OFF. PIPER AIRCRAFT CORPORATION SECTION 3 PA-38-112, TOMAHAWK EMERGENCY PROCEDURES ISSUED: JANUARY 20, 1978 REPORT: 2126 3-13 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 to 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. 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 LOSS OF PITOT-STATIC PRESSURE If loss of either pitot or static pressure or both occurs, the alternate source must be used. The control lever located under the left side of the control quadrant should be pushed forward to the open position. Operation on an alternate static source will cause deviations in the altimeter, rate of climb indicator and airspeed indicator readings. See the correction card mounted on the left side of the control quadrant cover for deviations. If the problem is in the pitot head or pitot line and is caused by icing or heavy rain conditions, the optional pitot heat may be activated if it is installed. The switch for the heated pitot is located on the electrical switch panel to the left of the control panel. A partially or completely blocked pitot head will give erratic or zero readings on the airspeed indicator. SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 3-14 REVISED: DECEMBER 6, 1979 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 Engine Start............................................................................ 4-5 Warm Up ................................................................................ 4-6 Taxiing ................................................................................... 4-7 Ground Check ........................................................................ 4-7 Before Takeoff ....................................................................... 4-7 Takeoff ................................................................................... 4-8 Climb ..................................................................................... 4-9 Cruising.................................................................................. 4-9 Approach and Landing........................................................... 4-9 Stopping Engine..................................................................... 4-9 Parking ................................................................................... 4-10 4.7 Amplified Normal Procedures (General).................................... 4-11 4.9 Preflight Check ........................................................................... 4-11 4.11 Before Starting Engine ............................................................... 4-13 4.13 Starting Engine ........................................................................... 4-14 4.15 Warm-Up .................................................................................... 4-17 4.17 Taxiing ........................................................................................ 4-17 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 4.29 Approach and Landing ............................................................... 4-21 4.31 Stopping Engine.......................................................................... 4-22 REPORT: 2126 4-i TABLE OF CONTENTS (cont) SECTION 4 (cont) Paragraph Page No. No. 4.33 Parking ........................................................................................ 4-22 4.35 Stalls ........................................................................................... 4-23 4.37 Turbulent Air Operation ............................................................. 4-23 4.39 Weight and Balance .................................................................... 4-24 4.41 Maneuvers................................................................................... 4-24 4.43 Spins ........................................................................................... 4-24 REPORT: 2126 4-ii SECTION 4 NORMAL PROCEDURES 4.1 GENERAL This section describes the recommended procedures for the conduct of normal operations for the Tomahawk. All of the required (FAA regulations) procedures and those necessary for the 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. PIPER AIRCRAFT CORPORATION SECTION 4 PA-38-112, TOMAHAWK NORMAL PROCEDURES ISSUED: JANUARY 20, 1978 REPORT: 2126 REVISED: MAY 10, 1982 4-1 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 70 KIAS (b) Best Angle of Climb Speed 61 KIAS (c) Turbulent Air Operating Speed (See CAUTION Subsection 2.3) 103 KIAS (d) Maximum Flap Speed 89 KIAS (e) Landing Final Approach Speed Full Flaps, 34° (Outboard Flow Strips Installed) 62 KIAS Full Flaps, 34° (Outboard and Inboard Flow Strips Installed) 67 KIAS (f) Maximum Demonstrated Crosswind Velocity 15 KTS SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 4-2 REVISED: DECEMBER 18, 1978 WALK-AROUND Figure 4-1 4.5 NORMAL PROCEDURES CHECK LIST PREFLIGHT CHECK COCKPIT Control wheel .......................................................................release restraints Ignition ....................................................................................................OFF Master switch ............................................................................................ON Fuel quantity gauges ..............................................................................check Alternator warning light ........................................................................check Master switch ..........................................................................................OFF Primary flight controls ..........................................................proper operation Flaps .....................................................................................proper operation Static drain ..........................................................................................drained Windows.......................................................................................check clean Baggage.................................................................................stowed properly Required papers ................................................................................on board Parking brake .......................................................................................set ON PIPER AIRCRAFT CORPORATION SECTION 4 PA-38-112, TOMAHAWK NORMAL PROCEDURES ISSUED: JANUARY 20, 1978 REPORT: 2126 4-3 LEFT WING Surface condition ...................................................................................check Flap and hinges......................................................................................check Aileron and hinges.................................................................................check Wing tip .................................................................................................check Lights ....................................................................................................check Fuel cap...................................................................................................open Fuel quantity and color ..........................................................................check Fuel cap.................................................................................close and secure Fuel vent .................................................................................................open Fuel tank sump .......................................................................................drain Pitot head....................................................................................unobstructed Stall warning..........................................................................................check Landing gear and tire .............................................................................check Brake block and disc..............................................................................check Chock and tie down ...........................................................................removed NOSE SECTION Fuel strainer............................................................................................drain General condition ..................................................................................check Propeller and spinner .............................................................................check Air inlets .................................................................................................clear Engine compartment ..............................................................................check Oil............................................................................................check quantity Dipstick ..................................................................................properly seated Hydraulic fluid level ..............................................................................check Alternator belt ...........................................................................check tension Cowling...............................................................................closed and secure Nose wheel tire ......................................................................................check Nose gear strut..............................................proper inflation (3 in. exposure) Windshield..............................................................................................clean RIGHT WING Check as left wing. FUSELAGE (RIGHT SIDE) General condition ..................................................................................check Antennas................................................................................................check Side and rear window .............................................................................clean Static vents .................................................................................unobstructed SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 4-4 REVISED: JANUARY 15, 1981 EMPENNAGE General condition ..................................................................................check Hinges and attachments .........................................................................check Tie down ...........................................................................................removed FUSELAGE (LEFT SIDE) Check as right side. BEFORE STARTING ENGINE Cabin doors........................................................................closed and latched Overhead latch ...................................................................................engaged Seats ................................................................................adjusted and locked Seat belts and harnesses .....................................................................fastened Circuit breakers ...........................................................................................in Parking brake .............................................................................................set Carburetor heat..................................................................................full OFF Fuel selector ................................................................................desired tank ENGINE START STARTING ENGINE WHEN COLD Prime .............................................................................................as required On last priming stroke leave primer in out position. Throttle......................................................................................open 1/2 inch Master switch ............................................................................................ON Electric fuel pump .....................................................................................ON Mixture ...........................................................................................full RICH Starter ..................................................................................................engage Primer ......................................................................................push in slowly after engine start Throttle..................................................................................advance slightly Oil pressure ...........................................................................................check Electric fuel pump ...................................................................................OFF Fuel pressure..........................................................................................check Primer...................................................................................................locked PIPER AIRCRAFT CORPORATION SECTION 4 PA-38-112, TOMAHAWK NORMAL PROCEDURES ISSUED: JANUARY 20, 1978 REPORT: 2126 REVISED: MARCH 1, 1979 4-5 STARTING ENGINE WHEN HOT Throttle ...............................................................................................cracked Master switch ............................................................................................ON Electric fuel pump .....................................................................................ON Mixture ...........................................................................................full RICH Starter ..................................................................................................engage Throttle..................................................................................................adjust Oil pressure ...........................................................................................check Electric fuel pump ...................................................................................OFF Fuel 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 Fuel pressure..........................................................................................check STARTING WITH EXTERNAL POWER SOURCE* Master switch ..........................................................................................OFF All electrical equipment...........................................................................OFF Terminals ............................................................................................connect External power plug .............................................................insert in fuselage 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 ...............................................................................800 to 1200 RPM *Optional equipment SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-38-112, TOMAHAWK REPORT: 2126 ISSUED: JANUARY 20, 1978 4-6 REVISED: JUNE 6, 1979 TAXIING Radios .......................................................................................................ON Taxi area..................................................................................................clear Brakes....................................................................................................check Steering .................................................................................................check GROUND CHECK Brakes ........................................................................................................set Throttle ..........................................................................................1800 RPM Magnetos ........................................max. drop 175 RPM - max. diff. 50 RPM Vacuum .......................................................................................5.0” Hg ± .1 Oil temp.................................................................................................check Oil pressure ...........................................................................................check Carburetor heat ......................................................................................check Throttle..................................................................................................retard Magnetos .........................................................check grounding at low RPM, then set to BOTH BEFORE TAKEOFF Master switch ..................................................................................check ON Flight instruments ..................................................................................check Fuel selector..................................................................................proper tank Mixture.......................................................................................................set Electric fuel pump .....................................................................................ON Carburetor heat ........................................................................................OFF Engine gauges........................................................................................check Static source ........................................................................................normal Seats .........................................................................securely latched in track Seat backs ...............................................................................................erect Belts/harness......................................................................................fastened Empty seat................................................................seat belt snugly fastened Flaps...........................................................................................................set Trim tab......................................................................................................set Controls ....................................................................................................free Doors .................................................................................closed and latched Overhead latch ...................................................................................engaged PIPER AIRCRAFT CORPORATION SECTION 4 PA-38-112, TOMAHAWK NORMAL PROCEDURES ISSUED: JANUARY 20, 1978 REPORT: 2126 REVISED: NOVEMBER 2, 1981 4-7 TAKEOFF NORMAL Flaps...........................................................................................................set Tab .............................................................................................................set Accelerate to 53 KIAS. Control Wheel ..................................back pressure to rotate to climb attitude SHORT FIELD, OBSTACLE CLEARANCE Flaps ......................................................................................21° (first notch) Accelerate to 53 KIAS. Control wheel ...................................back pressure to rotate to climb attitude Accelerate to 61 KIAS until obstacle clearance. Accelerate to 70 KIAS, after obstacle is cleared. Flaps..........................................................................................retract slowly SHORT FIELD, NO OBSTACLE Flaps ......................................................................................21° (first notch) Accelerate to 53 KIAS. Control wheel ...................................back pressure to rotate to climb attitude After breaking ground accelerate to best rate of climb speed 70 KIAS. Flaps..........................................................................................retract slowly SOFT FIELD, OBSTACLE CLEARANCE Flaps ......................................................................................21° (first notch) Accelerate and lift off nose gear as soon as possible. Lift off at lowest possible airspeed. Accelerate just above ground to 61 KIAS to climb past obstacle height. Continue climbing while accelerating to best rate of climb speed, 70 KIAS. Flaps..........................................................................................slowly retract SOFT FIELD, NO OBSTACLE Flaps ......................................................................................21° (first notch) Accelerate and lift off nose gear as soon as possible. Lift off at lowest possible airspeed. Accelerate just above ground to best rate of climb speed, 70 KIAS. Flaps..........................................................................................slowl