Pilot's Operating Handbook and FAA Approved Airplane Flight Manual

Piper PA-34 Seneca V · Pilot's Operating Handbook

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Overview

This Pilot's Operating Handbook (POH) is specifically designed for the Piper PA-34-220T Seneca V, providing essential information required by the Federal Aviation Regulations and additional details from the manufacturer. It serves as the FAA Approved Airplane Flight Manual and must be carried in the aircraft at all times. The handbook is not a substitute for flight training or operational guidance and should be kept current. It includes sections on general information, limitations, emergency procedures, normal procedures, performance, weight and balance, and descriptions of the airplane and its systems. Pilots are encouraged to familiarize themselves with the entire handbook to ensure safe operation of the aircraft.

Max Ramp Weight: 4430 lbs (2009 kg)
Max Takeoff Weight: 4407 lbs (1999 kg)
Max Landing Weight: 4407 lbs (1999 kg)
Max Zero Fuel Weight: 4407 lbs (1999 kg)
Fuel Capacity: 128 U.S. gallons (total)
Usable Fuel: 122 U.S. gallons (total)
Engine: Teledyne Continental TSIO-360RB, 220 BHP

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Originally published by www.flyace.at. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

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Document details

Type: Pilot's Operating Handbook
Year: 1997
Pages: 422
File size: 12 MB
Publisher: www.flyace.at

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In this document

General

This section introduces the handbook and outlines its purpose as an operating guide for pilots. It emphasizes the importance of understanding the aircraft's limitations, performance, and operational characteristics before flight.

Limitations

This section details the operational limitations of the aircraft, including airspeed limits, weight limits, and center of gravity limits, ensuring pilots are aware of the constraints under which the aircraft must be operated.

Emergency Procedures

This section provides critical information on how to handle various emergency situations that may arise during flight, ensuring pilots are prepared to respond effectively.

Normal Procedures

This section outlines standard operating procedures for the aircraft, including pre-flight checks, takeoff, landing, and in-flight operations.

Performance

This section includes performance data for the aircraft, such as takeoff and landing distances, climb rates, and fuel consumption, allowing pilots to plan flights effectively.

Weight and Balance

This section provides guidelines for calculating the weight and balance of the aircraft, which is crucial for safe operation.

Description and Operation of the Airplane and Its Systems

This section describes the various systems of the aircraft, including the engine, fuel system, and electrical system, providing pilots with a comprehensive understanding of the aircraft's operation.

Supplements

This section includes additional information and updates related to the aircraft, ensuring pilots have access to the latest operational data.

Operating Tips

This section offers practical tips for operating the aircraft efficiently and safely.

Safety notes

This handbook must be kept current to be valid for operational purposes.
Extreme care must be exercised to limit the use of this handbook to applicable aircraft.

Full document text

SENECA V PA-34-220T (1999 KG) SN 3449001 AND UP PILOT1S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL AIRPLANE AIRPLANE U� SERIAL NO. 3449221 REGIST. NO. PA-34-220T(1999 KG) REPORT: VB-1649 FAA APPROVED B . P TE E. PECK D.O.A. NO. SO-1 DATE OF APPROVAL: THE NEW PIPER AIRCRAFT, INC. JANUARY 23, 1997 VERO BEACH, FLORIDA THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY THE FEDERAL AVIATION REGULATIONS AND ADDITIONAL INFORMATION PROVIDED BY THE MANUFACTURER' AND CONSTITUTES THE FAA APPROVED AIRPLANE F L IG H T MANUAL. TH IS HANDBOOK MUST BE CARRIED IN THE AIRPLANE AT ALL TIMES. P;�r PA-34-220T, SENECA V WARNING EXTRE ME CARE MUST BE EXERCISED T O LIMIT THE USE OF THIS HANDBOOK TO APPLICA BLE AIRCRA FT. THIS HA ND BOOK IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED ON TIlE FA CE OF THE TITLE PAGE. SUBSEQUENT REV ISIONS SUPPLI ED BY THE NEW PIP ER A IRCRA FT, INC. MUST BE PROP ERLY INSERTED. REPORT: VB-1649 ii Published by P UBLICATIONS DEPARTMENT The New Piper Aircraft, Inc. Issued: JA NUARY 23, 1997 © 1997 The New P iper Aircraft, Inc. All Rights Reserved. PA-34-220T, SENECA V APPLIC ABILI T Y Application of this handbook is limited to the specific Piper PA-34-220T model airplane designated by serial number and registration number on the face of the title page of this handbook. WARNING THIS HANDBOOK CANNO T BE USED FOR O P ERATION AL PURPOSES UNLESS KEP T IN A CURREN T S TATUS. WARNING INSPECTION, MAIN T ENANCE AND PARTS REQUIREMEN T S FOR ALL NON-PIPER APPROV ED S T C INSTALLATIONS ARE NOT INCLUDED IN THIS HANDBOOK . WHEN A NON-PIPER APPROVED STC INSTALLATION IS INCORPORATED ON THE AIRPLAN E , THOSE PORTIONS OF THE AIRP L AN E AFFECTED B Y T HE INSTALLATION MUST BE INSPECTED I N ACCO RD ANCE WI TH THE INSPEC T IO N PROGRAM PUBLISHED BY THE OWNER OF THE STC. SINCE NON-PIPER APPROV ED STC INSTALLATIONS MAY CHANGE SYST EMS IN T ERFAC E , O P ERATING CHARAC T ERI S T ICS A N D COMP ONE N T LO A D S O R S T RESSES O N ADJ ACE N T STRU C T URES, PIPER PROVIDED INSP ECTION CRI TERIA MAY NO T B E VALID FOR AIRPLANES WI TH NON-P I P E R APPROVED STC INSTALLATIONS. REVISIONS The Pilot's Operating Handbook and FA A Approved Airplane Flight Manual, with the exception of the equipment list, is kept cun-ent by revisions which are distributed to the registered airplane owners. The equipment list was cun-ent at the time the airplane was licensed by the manufacturer and thereafter must be maintained by the owner. Revision material will consist of information necessary to add, update or correct the text of the present handbook and/or to add suppleme n t al information to cover added airplane equipment. ISSUED: JANUARY 23, 1997 REVISED: APRIL 30, 2003 REPORT: VB-1649 iii PA-34-220T, SENECA V I. Identifying Revised Material Each handbook page is dated at the bottom of the page showing both the date of original issue and the date of the latest revision. Revised text and illustrations are indicated by a black vertical line located along the outside margin of each revised page opposite the revised, added, or deleted information. A vertical line next to the page number indicates that an entire page has been changed or added. Vertical black lines indicate current revisions only. Correction of typographical or grammatical errors or the physical relocation of infonnation on a page will not be indicated by a symbol. II. Revision Procedure Revisions will be distributed whenever necessary as complete page replacements or additions and shall be inserted into the handbook in accordance with the instmctions given below. 1. Revision pages will replace only pages with the same page nmnber. 2. Insert all additional pages in proper numerical order within each section. Discard old page. 3. Insert page numbers followed by a small letter in direct sequence with the same commonly numbered page. ORIGINAL PAGES ISSUED The original pages issued for this handbook prior to revision are given below: Title, ii through viii, l-i, l-ii, 1-1 through 1-12, 2-i, 2-ii, 2-1 through 2-14, 3-i through 3-iv, 3-1 through 3-40, 4-i through 4-iv, 4-1 through 4-54, 5-i, 5-ii, 5-1 through 5-36, 6-i, 6-ii, 6-1 through 6-14, 7-i, 7-ii, 7-1 through 7-68, 8-i, 8-ii, 8-1 through 8-20, 9-i, 9-ii, 9-1 through 9-64, lO-i, lO-ii, 10-1 through 10-4 REPORT: VB-1649 iv ISSUED: JANUARY 23, 1997 REVISED: APRIL 30, 2003 PA-34-220T, SENECA V PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Current Revisions to the PA-34-220T, Seneca V Pilot's Operating Handbook, REPORT: VB-1649 issued JANUARY 23,1997. Revision FAA Approved Nurnber and Revised Description of Revisions Signature Code Pages and Date Rev. I v Added Rev. I to L of R page. (PR970926) 3-ii Revised Table of Contents. 3-iii Revised Table of Contents. 3-iv Revised Table of Contents. 3-12 Added para. 3.5d. 3-13 Added para. 3.5d. 3-14 Revised para's. 3.5e thru 3.5p, thru and relocated information. 3- 31 3-31a Added page and para. 3.14. 3-31b Added page and para. 3.15. 3-32 Revised para's. 3.17, 3.19, thru 3.21,3.23,3.25,3.27,3.29 3-40 3.31,3.33 & 3.35, and relocated information. 4-i Revised Table of Contents. 4-9 Revised para. 4.5c. 4-10 Revised para. 4.5c. 4-11 Revised para. 4.5c. 4-12 Revised para. 4.5c. ·4-13 Revised para. 4.5e. 4-15 Revised para. 4.5g. 4-16 Revised para. 4.5h. 4-17 Revised para. 4.5h. 4-29 Revised para's. 4.13 thru thru 4.13f. 4-35 4-36 Revised para. 4.17. 4-39 Revised para. 4.21. 4-41 Revised para's. 4.23a & 4.23b. Peter E. Peck 5-23 Revised Fig. 5-23. 5-31 Revised Fig. 5-39. Sept. 26, 1997 9-5 Revised Section 2. Date ISSUED: JANUARY 23, 1997 REVISED: SEPTEMBER 26, 1997 REPORT: VB-I649 v PA-34-220T, SENECA V PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision Number and Revised Code Pages Rev. 2 (PR980422) 2-i 2-S 2-9 3-2 3-29 4-iii 4-1 4-2 4-5 4-15 4-]6 4-17 4-24 4-39 4-40 4-42 4-45 4-55 4-56 5-16 5-17 5-IS 5-20 7-2 7-43 7-47 REPORT: VB·I649 vi FAA Approved Description of Revisions Signature and Date Added Rev. 2 to L of R page.

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Revised Table of Contents. Revised para. 2.29 by adding Icing Information. Revised para. 2.29 Revised para. 3.3. Revised para. 3.9i, item 4. Revised Table of Contents. Revised para. 4.1. Revised para. 4.3, item (b). Revised para. 4.5a. Revised para. 4.5g, by adding Warning. Revised para. 4.5h, by adding Warning. Revised para. 4.5i. Revised para. 4.9c. Revised para. 4.21, by adding Warning. Revised para. 4.23, by adding Warning. Revised para. 4.25a. Revised para. 4.27. Added para. 4.55, Icing Information. Added Blank Page. Revised Fig. 5-11. Revised Fig. 5-13. Revised Fig. 5-15. Revised Fig. 5-17. Revised para. 7.5. Peter E. Peck Revised Fig. 7-35. Revised Fig. 1. April 22, 1995 Date ISSUED: JANUARY 23, 1997 REVISED: APRIL 22, 1998 PA-34-220T, SENECA V PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision N umber and Revised Description of Revisions Code Pages Rev. 3 vii Added page and Rev. 3 . (pR980819) viii Added page. 2-8 Revised Para. 2.27. 3-21 Revised Para. 3.5k. 4-10 Revised Para. 4.5c. 4-11 Revised Para. 4.5c. 4-12 Revised Para. 4.5c. 4-14 Revised Para. 4.5 f . 4-30 Revised Para's. 4.13a & b. 4-31 Revised Para's . 4.13c & d. 4-33 Revised Para. 4.13e. 4-38 Revised Para. 4.19. 4-55 Corrected typo. 7-31 Revised Para. 7.19. 9-i Revised T of C. 9-18 Revised Section 3. 9-65 Added S upplement 9 - thru BendixlKing KX 155A 9-76 Comm/Nav System. Rev. 4 vi-a Added Rev. 4 and corrected (pR991119) page number in footer. vi-b Corrected page number in footer. 9-14 Revised S upplement 3 by adding Section 2 Placard. Rev. 5 vi-a Added Rev. 5 to L of R . (pROO0207) vi-b Added Rev. 5 to L of R . 4-5 Revised Para. 4.5a. 4-11 Revised Para. 4.5c. 4-13 Revised Para. 4.5e. 4-18 Revised Para. 4.5k. 4-20 Revised Para. 4.50. ISSUED: JANUARY 23, 1997 REVISED: FEBRUARY 7, 2000 FAA Approved Sig nat ure and Date Peter E. Peck August 19, 1998 Date Christi na L. Marsh Nov. 19, 1999 Date REPORT: VB-I649 vi-a PA-34-220T, SENECA V PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision Number and Revised Code Pages Rev. 5 4-24 (PROO207) 7-37 (continued) 9-i 9-22 9-77 thru 9-84 9-85 thru 9-86 10-3 Rev. 6 vi-b (PROO522) 9-14 Rev. 7 vi-b (PROO 612) vi- c vi- d 2-13 4-48 7-25 7-26 7-29 9-i 9-ii 9-83 9-87 thru 9-94 REPORT: V B-1649 vi-b FAA Approved Description of Revisions Signature and Date Revised Para. 4.9b & 4.9c. Revised Para. 7.23. Revised T of C. Revised Section 4. Added Supplement 10 - Garmin GNS 430 CommlNav. Added Supplement 11 - S-TEC System 55 Autopilot. Christina L. Marsh Revised Para. 10.3. Feb. 7,2000 Date Added Rev. 6 to L ofR. Christina L. Marsh Revised Section 2. May 22, 200 Date Added Rev. 7 to L of R. Added Page & Rev. 7 to L of R. Added Page. Revised para. 2.31. Revised para. 4.33. Revised para. 7.17. Revised Figure 7-21 title. Revised para. 7.17. Revised T of C. Revised T of C. Revised Section 4. Added Supplement 12 - Garmin GNS 430 CommJNav wi Traffic Adv. & Lightning Strike Adv. Data. ISSUED: JANUARY 23, 1997 REVISED: JUNE 12, 200 PA-34-220T, SENECA V PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision Nwnber and Revised Description of Revisions Code Rev. 7 9-95 Added Supplement 13 - (PROO612) thru Gannin GNS 530 CommlNav continued 9-102 wi Trafc Adv. & Lightning Strike Adv. Data. 9-103 Added Supplement 14 - thru BF Goodrich Skywatch 9-108 Traffic Advisory System Model SKY497. 9-109 Added Supplement 15 - thru Avidyne 5-RR-MFC Series 9-116 FlightMax Flight Situation Display wi Software 530-0104. 9-117 Added Supplement 16 - thru BF Goodrich Aerospace 9-120 WX-5OO Stormscope Series IT Weather Mapping Sensor. Rev. 8 vi-c Added Rev. 8 to L ofR. (PRO10223) vi-d Added Rev. 8 to L ofR. 4-54 Revised para. 4.53. 6-11' Revised Fig. 6-9. 9-ii Revised T of C. 9-121 Added pages thru and Supplement 17. 9-130 9-131 Added pages thru and Supplement 18. 9-140 9-141 Added pages thru and Supplement 19. 9-142 9-143 Added pages thru and Supplement 20. 9-148 ISSUED: JANUARY 23, 1997 REVISED: FEBRUARY 23, 2001 FAA Approved Signature and Date Christina L. Marsh June 12, 2000 Date REPORT: VB-I649 vi-c PA-34-220T, SENECA V PILOT'S OP ERATING HANDBOOK LOG OF REVISIONS (conl) Revision Number and Revised Code Rev. 8 9-149 (pRO 10223) thru continued 9-154 9-155 thru 9-158 Rev. 9 vi-d (pROI1101) 9-i 9-ii 9- 159 thru 9-166 Rev. 10 vi-d (PR020107) 9-ii 9-167 thru 9-176 Rev. 11 vi-d (pR020225) 1-5 2-6 2-13 6-13 Rev. 12 vi-d (PR020531) 6-11 REPORT: VB-I649 vi-d FAA Approved Description of Revisions Signature and Date Added pages and Supplement 21. Christina L. Marsh Added pages and Supplement 22. Feb. 23,2001 Date Added Rev. 9 to L ofR . � Revised T of C. Revised T ofC. Added pages Albert 1. Mill and Supplement 23. Nov. 0 1, 2001 Date Added Rev. 10 to L of R. �.Revised T ofC. Added pages Albert J. Mill and Supplement 24. Jan. 07,2002 Date Added Rev. 1 1 to L of R. �Revised para. 1. 11 & 1.15. Albert 1. Mill Revised para. 2.11. Revised para. 2.31. Feb. 25, 2002 Revised Figure 6-13. Date Added Rev. 12 to L ofR. �Revised Figure 6-9. Albert 1. Mill May 31, 2002 Date ISSUED: JANUARY 23, 1997 REVISED: MAY 31, 2002 PA-34-220T, SENECA V PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision Number and Revised Description of Revisions Code Rev. 13 vi-e Added page and Rev. 13. (PR02121O) vi-f Added page. 9-i Revised T of C. 9-177 Added pages thru and Supplement 25. 9-178 Rev. 14 vi-e Added Rev. 14 to L of R. (PR030205) 7-5 Revised para. 7.5. 7-6 Revised para. 7.7. 7-9 Revised fig. 7-5. 7-9a Added page and fig. 7-5a. 7-9b Added page. 7-12 Revised para. 7.9. Rev. 15 iii Added Warning. (PR030430) iv Moved info. from page iii. vi-e Added Rev. 15 to L of R. vi-f Added Rev. 15 to L of R. 2-6 Revised para. 2.11. 6 12 Revised fig. 6-11. 8-1 Moved info. to page 8-1b and revised para. 8.1. 8-1a Added page and revised para. 8.1. 8-1b Added page and moved info. from pages 8-1 and 8-2. 8-2 Moved info. to page 8-1b and revised para. 8.3. 9-ii Revised T of C. 9-36 Revised Section 4. 9-164 Revised Section 7. ISSUED: JANUARY 23, 1997 REVISED: APRIL 30, 2003 FAA Approved Signature and Date �Albert J. Mill Dec. 10,2002 Date Albert J. Mill Feb. 5,2003 Date REPORT: VB-1649 vi-e PA-34-220T, SENECA V PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision Number and Revised Code Rev. 15 9-179 (PR030430) 9-180 continued lO-i 10-1 Rev. 16 vi-f (PR03111O) 3-4 3-8 3-25 3-27 4-16 4-17 9-118 Rev. 17 vi-f (PR040112) 9-ii 9-181 thru 9-184 Rev. 18 vi-f (PR041213) 4-18 4-46 Rev. 19 vi-f (PR060424) 5-23 Rev. 20 vi-f (PR070219) 4-49 REPORT: VB-1649 vi-f FAA Approved Description of Revisions Signature and Date Added pages �and Supplement 26. Revised T of C. Revised subject headings. Albert J. Mill April 30,2003 Date Added Rev. 16 to L of R. Revised para. 3.5a. Revised para. 3.5a. Revised para. 3.9d. �Revised para. 3.9h. Revised para. 4.5h. Revised para. 4.5h. Albert J. Mill Revised section 1. Nov. 10,2003 Date Added Rev. 17 to L of R. � Revised T of C. Added pages Albert J. Mill and Supplement 27. Jan. 12,2004 Date Added Rev. 18 to L of R. Revised para. 4.5m. Revised para. 4.31. Linda J. Dicken Dec. 13,2004 Added Rev. 19 to L of R. Revised Figure 5-23. Linda J. Dicken April 24,2006 Added Rev. 20 to L of R. Revised para. 4.35. Linda J. Dicken Feb. 19,2007 ISSUED: JANUARY 23,1997 REVISED: FEBRUARY 19, 2007 PA-34-220T, SENECA V TABLE OF CONTENTS SECTION 1 GENERAL SECTION 2 LIMITATIONS SECTION 3 EMERGENCY PROCEDURES SECTION 4 NORMAL PROCEDURES SECTION 5 PERFORMANCE SECTION 6 WEIGHT AND BALANCE SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS SECTION 8 AIRPLANE HANDLING, SERVICING AND MAINTENANCE SECTION 9 SUPPLEMENTS SECTION 10 OPERATING TIPS ISSUED: JANUARY 23, 1997 REP ORT: VB-1649 vii PA-34-220T, SENECA V THIS PAGE INTENTIONALLY LEFT BLANK REP ORT: VB-1649 viii ISSUED: JANUAR Y 23, 1997 SECTION 1 GENERAL SECTION 2 LIMITATIONS SECTION 3 EMERG.PROCEDURES SECTION 4 NORMAL PROCEDURES SECTION 5 PERFORMANCE SECTION 6 WEIGHT&BALANCE SECTION 7 DESC.&OPERATIONS PA-34-220T, SENECA V Paragraph No. TABLE OF CONTENTS SECTION 1 GENERAL SECTION 1 GENERAL Page No. 1.1 Introduction ....... ...... ..... ..... ................................ .... ................... 1-1 1.3 Engine. ........ ....... ............................................................... ........ 1-3 1.5 Propeller .............................................. ..................................... 1-3 1.7 Fuel........................................................................................... 1-4 1.9 Oi!............................................................................................. 1-4 1.11 Maximum Weights ...................... ............. ............ .................... 1-5 1.13 Standard Airplane Weights....................................................... 1-5 1.15 Baggage Space ..... .................................................................... 1-5 1.17 Specific Loadings.. ................................................................... 1-5 1.19 Symbols, Abbreviations and Terminology............................... 1-7 ISSUED: JANUARY 23, 1997 REPORT: VB-1649 l-i SECTION! GENERAL PA-34-220T, SENECA V THIS PAGE INTENTIONALLY LEFf BLANK REPORT: VB-1649 l-ii ISSUED: JANUARY 23, 1997 PA-34-220T, SENECA V 1.1 INTRODUCTION SECTION 1 GENERAL SECTION 1 GENERAL This Pilot's Operating Handbook is designed for maximum utilization as an operating guide for the pilot. It inclu des the material required to be furnished to the pilot by the Federal Aviation Regulations and additional information provided by the airplane manufacturer and constitutes the FAA Approved Airplane Flight Manual. This handbook is'not designed as a substitute for adequate and competent flight instruction, knowledge of current airworthiness directives and 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. Assu r a nce that the airplane is in a n airworthy condition i s the responsibility of the owner. The pilot in command is r esponsible 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 limitat i o ns, performance, pr o c e d u r es and operational h a n d l i n g characteristics o f the airplane before flight. The handbook has been divided into numbered sections, each provided with a finger-tip tab divider for quick reference. The limitations and emergency procedures have been placed ahead of the normal procedures, performance and other sections to provide easier access to information that may be required in flight. The Emergency Procedures Section has been furnished with a red tab divider to present an instant reference to the section. Provisions for expansion of the handbook have been made by the deliberate omission of certain paragraph numbers, figure numbers, item numbers and pages noted as being intentionally left blank. ISSUED: JANUARY 23, 1997 REPORT: VB-1649 1-1 SECTION 1 GENERAL PA-34-220T, SENECA V .2' 10.28' Wing Area (sq. ft.) 208.7 Min. Turning Radius (ft.) 33.2 (from pivot point to wingtip) -t5' 3.0' 10.87' 4' 2.4' �6' 4' DIAMETER 7° DIHEDRAL 4' 3.43' REPORT: VB-I649 1-2 STATIC GROUND LINE THREE VIEW Figure 1-1 ISSUED: JANUARY 23, 1997 PA-34-220T, SENECA V 1.3 ENGINE (a) Number of Engines b) Engine Manufacturer (c) Engine Model Number (1) Left (2) Right (d) Rated Horsepower (e) Rated Speed (rpm) (0 Bore (inches) (g) Stroke (inches) (h) Displacement (cubic inches) (i) Compression Ratio G> Engine Type 1.5 PROPELLER STANDARD (a) Number of Propellers (b) Propeller Manufacturer (c) Propeller Hub & Blade Models* (1) Left (2) Right (d) Number of Blades (e) Propeller Diameter (in.) (1) Maximum (2) Minimum (f) Propeller Type SECTION 1 GENERAL 2 Teledyne Continental TSIO-360RB LTSIO-360RB Max. Cont. Power 220BHP 260 4.438 3.875 360 7.5:1 Six Cylinder, Direct Drive, Horizontally Opposed, Air Cooled 2 Hartzell BHC-J2YF-2CUF/ FC8459B-SR BHC-J2YF-2CLUF/ FJC8459B-SR 2 76 75 Constant Speed, Hydraulically Activated, Full Feathering *The propellers have the same designation when deicing bots are installed. ISSUED: JANUARY 23, 1997 REPORT: VB-1649 1-3 SECTION 1 GENERAL OPTIONAL (a) Number of Propellers (b) Propeller Manufacturer (c) Propeller Hub & Blade Models* (1) Left (2) Right (d) Number of Blades (e) Propeller Diameter (in.) (1) Maximum (2) Minimum (f) Propeller Type 1.7 FUEL AVGASONLY (a) Fuel Capacity (U.S. gal.) (total) (b) Usable Fuel (U.S. gal.) (total) (c) Fuel (1) Minimum Grade (2) Alternate Fuels 1.9 OIL (a) Oil Capacity (U.S. qts.) (per engine) (b) Oil Specification PA-34-220T, SENECA V 2 McCauley 3AF32C522182NJA-6 3AF32C523JL82NJA-6 3 76 75 Constant Speed, Hydraulically Activated, Full Feathering 128 122 100 Green or lOOLL Blue Aviation Grade Refer to latest revision of Continental Service Bulletin Fuel and Oil Grades. 8 Refer to latest revision of Continental Ser vice Bulletin Fuel andOil Grades. *The propellers have the same designation when deicing boots are installed. REPORT: VB-I649 1-4 ISSUED: JANUARY 23, 1997 PA-34-220T, SENECA V (c) Oil Viscosity SECTION 1 GENERAL Aviation S.A.E. Grade No. (1) Below 40°F 1065 30 (2) Above 40°F 1100 50 When operating temperatures overlap indicated ranges, use the lighter grade of oil. Mu lti-viscosity oils meeting Teledyne Continental Motors' Specification MHS-24A are approved. 1.11 MAXIMUM WEIGHTS (a) Max. Ramp Weight (b) Max. Takeoff Weight (c) Max. Landing Weight (d) Max. Zero Fuel Weight - Std. (e) Max. Weights in Baggage Compartment (1) Forward (2) Aft 1.13 S TANDARD AIRPLANE WEIGHTS 4430 lbsl2009 kg. 4407lbsl l999 kg. 4407lbs/1999 kg. 44071bs/1999 kg. 100 Ibsl45 kg 85 lbs/38 kg I Refer to Figure 6-5 for the Standard Empty Weight and the Useful Load. 1.15 BAGGAGE SPACE (a) Maximum Baggage (b) Baggage Space (cu. ft.) (c) Baggage Door Size (in.) 1.17 SP ECIFIC LOADINGS (a) Wing Loading (lbs. per sq. ft.) (b) Power Loading (lbs. per hp) ISSUED: JANUARY 23, 1997 REVISED: FEBRUARY 25, 2002 FORWARD 100 Ibs/45 kg 15.3 24 x 21 AFT 85 Ibs/38 kgl 17.3 21.2 10.0 REPORT: VB-1649 1-5 SECTION 1 GENERAL PA-34-220T, SENECA V TIlS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-I649 1-6 ISSUED: JANUARY 23, 1997 PA-34-220T, SENECA V SECTION 1 GENERAL 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY The following definitions are of symbols, abbreviations and terminology used throughout the handbook and those which may be of added operational significance to the pilot (a) General Airspeed Tenninology and Symbols CAS KCAS GS lAS KIAS TAS Calibrated Airspeed means the indicated speed of an aircraft, corrected for position and instrument error. Calibrated airspeed is equal t o true airspeed in s t a ndard atmosphere at sea level. Calibrated Airspeed expressed in "Knots." Ground Speed is the speed of an airplane relative to the ground. Indicated Airspeed is the speed of an aircraft as shown on the airspeed indicator when corrected for instrument error. lAS values published in this handbook assume zero instrument error. Indicated Airspeed expressed in Knots. True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude, temperat u r e a n d compressibility. VA Maneuvering Speed is the maximum speed at which application of full a v a i l able aerodynamic control will not overstress the airplane. KTAS True Airspeed expressed in Knots. ISSUED: JANUARY 23, 1997 REPORT: VB-I649 1-7 SECTION 1 GENERAL PA-34-220T, SENECA V 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (cont) VFE VLE VLO YMCA VNE VNO Vs Vso REPORT: VB-I649 1-8 Maximum Flap Ex tend e d Speed is t he highest speed permissible with wing flaps in a prescribed extended position. Maximum Landing Gear Extended Speed is the maximum speed at which an aircraft can be safely flown with the l anding gear extended. Maximum Landing Gear Operating Speed is the maximum speed at which the landing gear can be safely extended or retracted. Air Minimum Control Speed is the mini mum flight speed at which the airplane is directionally controllable as determined in accordance with Federal Aviation Regu lations. Airplane certification conditions include one engine becoming inoperative and windmilling; not more than a 5° bank towards the operative engine; takeoff power on operative engine; landing gear up; flaps in takeoff position; and most rearward C.G. Never Exceed Speed is the speed limit that may not be exceeded at any time. Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution. Stalling Speed or the minimum steady flight speed at which the airplane is controllable. Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration. ISSUED: JANUARY 23, 1997 PA-34-220T, SENECA V VSSE Vx Vy SECTION 1 GENERAL Intentional One Engine Inoperative Speed is a minimum speed selected by the manu facturer for intentionally rendering one engine inoperative in flight for pilot training. Best Angle-of-Climb Speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance. Best Rate-of-Climb Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time. (b) Meteorological Terminology ISA I nternational S tandard Atmosphere in which: The air is a dry perfect gas; The temperature at sea level is 15° Celsius (590 Fahrenheit); The pressure at sea level is 29.92 inches Hg(1013.2mb); The tempera ture gradient from sea level to the altitude at w h ich t h e temperat u r e is -56.SoC (-69.7°F) is -O.OOI9SoC (-O.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 g round meteorological sources, adjusted for in strument error and compressibility effects. Indicated The number actually read from an altimeter Pressure Altitude when the barometric subscale has been set to 29.92 inches of mercury (1013.2 millibars). ISSUED: JANUARY 23, 1997 REPORT: VB-I649 1·9 SECTION 1 GENERAL PA·34·220T, SENECA V 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (cont) Pressure Altitude Station Pressure Wind (c) Power Terminology Takeoff Power Maximum Con tinuous Power Maximum Climb Power Maximum Cruise Power (d) Engine Instruments TIT Gauge Altitude measured from standard sea-level pressure (29.92 in. Hg) by a pressure or barometric altimeter. I t is the indicated pressure altitude corrected for position and instrument error. In this handbook, altimeter instrument errors are assumed to be zero. Actual atmospheric pressure at fi eld elevation. The wind velocities recorded as variables on the charts of this handbook are to be understood as the headwind or t ailwind components of the reported winds. Maximum power permissible for takeoff. Maximum power permissible continuously during flight. M a x i m u m p owe r p e r m is s ible during climb. M a x i m u m p ower p e rm i s s i b l e during cruise . Turbine Inlet Temperature Gauge (e) Airplane Performance and Hight Planning Terminology Climb Gradient REPORT: VB·I649 1·10 T he demonstrated ratio of the change in height during a portion of a climb, to the horizontal distance traversed in the same time interval. ISSUED: JANUARY 23, 1997 PA-34-220T, SENECA V Demonstrated Crosswind Velocity (DEMO. X-WIND) Accelerate-Stop Distance Route Segment SECTION! GENERAL The demonstrated cross wind velocity is the velocity of the cross wind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests. The distance required to accelerate an air plane to a specified speed and, assum ing failure of an engine at the instant that speed is attained, to bring the airplane to a stop. A part of a route. Each end of that part is identified by: (1) a geographical location; or (2) a point at which a definite radio fix can be established. (f) Weight and Balance Terminology Reference Datum Station Arm Moment Center Or Gravity (C.G.) ISSUED: JANUARY 23, 1997 An imaginary vertical plane from which all horizontal d istances are measured for balance purposes A location along the airplane fuselage usually given in terms of distance in inches from the reference datum. The horizontal distance from the reference datum to the center of gravity (C.G.) of an item. The product of the weight of an item multi plied by its arm. (Moment divided by a constant is used to simplify balance calcu lations by reducing the number of digits.) The point at which an airplane would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. REPORT: VB-I649 1-11 SECTION 1 GENERAL PA-34-220T, SENECA V 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (cont) C.G. An The arm obtained by adding the airplane's individual moments and dividing the sum by the total weight. C.G. Limits Usable Fuel Unusable Fuel Standard Empty Weight Basic Empty Weight Payload Useful Load Maximum Ramp Weight Maximum Takeoff Weight Maximum Landing Weight Maximum Zero Fuel Weight REPORT: VB-I649 1-12 The extreme center of gravity locations within which the airplane must be operated at a given weight. Fuel available for flight planning. Fuel remaining after a runout test has been completed in accordance w ith govern mental regulations. Weight of a standard airplane including unusable fuel, full operating fluids and full oil. Standard empty weight p l us optional equipment. Weight of occupants, cargo and baggage. Difference between takeoff weight, or ramp weight if applicable, and basic empty weight. Maximum weight approved for ground maneuver. (It includes weight of start, taxi and run up fuel.) Maximum weight approved for the start of the takeoff run. Maximum weight approved for the landing touchdown. Maximum weight exclusive of usable fuel. ISSUED: JANUARY 23, 1997 SECTION 1 GENERAL SECTION 2 LIMITATIONS SECTION 3 EMERG.PROCEDURES SECTION 4 NORMAL PROCEDURES SECTION 5 PERFORMANCE SECTION 6 WEIGHT&BALANCE SECTION 7 DESC.&OPERATIONS PA-34-220T, SENECA V Paragraph No. TABLE OF CONTENTS SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS Page No. 2.1 General ........................ ........ .................................... ............ ... .. 2-1 2.3 Airspeed Limitations ........................... ............ ........................ . 2-1 2.5 Airspeed Indicator Markings.................................................... 2-3 2.7 Power Plant Limitations ........................................................... 2-3 2.9 Power Plant Instrument Markings............................................ 2-5 2.11 Weight Limits .............................. .... ........... ..... ................ .. ...... . 2-6 2.13 Center of Gravity Limits .......................................... ................ 2-6 2. 15 Maneuver Limits ........................................ .............................. 2-6 2.17 Flight Maneuvering Load Factors ............................................ 2-7 2.19 Types of Operation ............ .......................................... ............. 2-7 2.21 Fuel Limitations ......................... .. ................. .................... ....... 2-7 2.23 Heater Limitations.................................................................... 2-8 2.25 Operating Altitude Limitations ................................................ 2-8 2.27 Gyro Suction Limits ................................................... .............. 2-8 2.29 Icing Information...................................................................... 2-8 2.31 Placards ........... ................... ..... ............. ....... ... ............. ...... ....... 2-9 ISSUED: JANUARY 23, 1997 REVISED: APRIL 22, 1998 REPORT: VB-1649 2-i SEC TION 2 LIMITATIONS PA-34.220T, SENECA V THIS PAGE INTENTIONALLY LEFT BLANK R EP OR T: VB·1649 2·ii ISSUED: JANUARY 23, 1997 PA-34-220T, SENECA V 2.1 GENERAL SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS 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 air plane m ust b e operated as a normal c ategory airpla n e i n 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 A IRSPEED LIMITATIONS SPEED Never Exceed Speed (VNE) - Do not exceed this speed in any operation. Maximum Structural Cruising Speed (VNO) - Do not exceed this speed except in smooth air and then only with caution. ISSUED: JANUARY 23, 1997 KIAS KCAS 204 203 164 165 REPORT: VB-IM9 2-1 SECTION 2 LIMITATIONS 2.3 AIRSPEED LIMITATIONS (Cont) SPEED Design Maneuvering Speed (VA) - Do not make full or abrupt control movements above this speed. 4407 Ibsll999 kg GW 3205 1bs. CAUTION PA-34-220T, SENECA V KIAS KCAS 135 137 113 115 Maneuvering speed decreases at lighter weight as the effects of aerodynamic forces become more pronounced. Linear interpolation may be used for intermediate g ross weights. Maneuvering speed should not be exceeded while operating in rough air. Maximum Gear Extended Speed (VLE) - Do not exceed this speed with landing gear extended. Maximum Landing Gear Operating Speed (VLO) - Do not extend or retract landing gear above these speeds. Extension Retraction Maximum Flaps Extended Speed (VFE) Do not exceed this speed with the flaps extended. One Engine Inoperative Best Rate of Climb Speed. (VYSE) Air Minimum Control Speed (VMCA) - Lowest airspeed at which airplane is con trollable with one engine operating at takeoff power and no flaps. REP ORT: VB-I649 2-2 128 128 107 113 88 66 130 130 109 113 91 67 ISSUED: JANUARY 23, 1997 PA.34·220T, SENECA V 2.5 AIRSPEED INDICATOR MARKINGS MARKING Red Radial Line (Never Exceed) Yellow Arc (Caution Range - Smooth Air Only) Green Arc (Normal Operating Range) White Arc (Flap Down) Blue Radial Line (One Engine Inoperative Best Rate of Climb Speed) Red Radial Line SECTION 2 LIMITATIONS KIAS 204 164 to 204 67 to 164 61 to 113 88 (One Engine Inoperative Air Minimum Control Speed) 66 2.7 POWER PLANT LIMITATIONS (a) Number of Engines (b) Engine Manufacturer (c) Engine Model Number (1) Left (2) Right (d) Engine Operating Limits (1) Rated Horsepower (BHP) (2) Max. Rotational Speed (RPM) (3) Max. Manifold Pressure (Inches of Mercury) (4) Max. CyHnder Head Temperature (5) Max. Oil Temperature (e) Oil Pressure Minimum (red line) Maximum (red line) ISSUED: JANUARY 23, 1997 2 Teledyne Continental TSIO-360RB LTSIO-360RB Max. Cont. Power 220 2600 38 4600P 2400P 10 PSI 100 PSI REPORT: VB-I649 2·3 SECTION 2 LIMITATIONS PA-34-220T, SENECA V 2.7 POWER PLANT LIMITATIONS (Cont) (f) Fuel Grade ( AVGAS ONLY) (Min. grade) 100 or looLL Aviation Grade (g) Number of Propellers (h) Propeller Manufacturer Hartzell (Two Blade) (Standard) Propeller Hub and Blade Models 2 a. Left b. Right BHC-J2 YF-2CUF/FCS459B-SR BHC-J2 YF-2CLUF/FJC8459B-SR NOTES (2-blade propellers only) Avoid continuous operation between 1900 and 2100 RPM above 32 IN. HG. manifold pressure. Avoid continuous ground operation between 1600 and 2100 RPM in cross and tail winds. McCauley (Three Blade) ( Optional) Propeller Hub and Blade Models a. Left b. Right 3AF32C522 ( )/( )82NJA-6 3AF32C523 ( )/( )L82NJA-6 (i) Propeller Diameter (inches) Maximum Minimum 76 75 2.7a POWER PLANT LEANING LIMITATIONS Mixture F UL L RICH at all engine powers above high speed cruise power. REPORT: VB-I649 2- 4 ISSUED: JANUARY 23, 1997 PA-34-220T, SENEC A V 2.9 POWER PLANT INSTRUMENT M ARKINGS (a) Tachometer (b) (c) (d) (e) (D Green Arc (Nonnal Operating Range) Red Line (Maximum) Cylinder Head Temperature Green Arc (Nonnal Range) Red Line ( Maximum) Oil Temperature Green Arc (Nonnal Operating Range) Red Line ( Maximum) Oil Pressure Red Line (Minimum) Yellow Arc (Caution - Ground Operation Only) Green Arc (Nonllal Operating Rtmge) Red Line (Maximum) Manifold Pressure Green /\.rc (Normal Operating Range) Red Line (Maximum) Turbine Inlet Temperature l:rreen Arc Red Line (Maximum) NOTE: SECTION 2 LIMITATIONS 600 RPM to 2600 RPM 2600 RPM 240"F to 460'F 460'F 100cF to 240'F 240'F LO PSI 10 PSI to 30 PSI a n d 8 0 PSI to 100 P SI 30 PSI to 80 PSI 100 PSI 10 IN. to 38 IN. HG. 38 IN. HG. 1200'F to 1650'F 1650'F A maximum temperature o f 1700'F is allowed for 60 seconds, in order to determine peak T.LT. for fuel management. ISSUED: JANUARY 23, 1997 REPORT: VB-1649 2-5 SECTION 2 LIMITATIONS 2.11 WEIGHT LIMITS (a) Max. Ramp Weight (b) Max. Takeoff Weight (c) Max. Landing Weight PA-34-220T, SENECA V 4430 Ibs12009 kg 4407 Ibs/1999 kg 4407 Ibs/1999 kg (d) Max. Weights in Baggage Compartments Forward 100 Ibs/45 kg 851bs/38 kg Aft 2.13 CENTER OF GRAVITY LIMITS Weight Pounds 3400 4250 4407 Forward Limit Inches Aft of Datum 82.0 86.7 88.0 NOTES: Rearward Limit Inches Aft of Datum 94.6 94.6 94.6 Straight line variation between points given. T he datum used is 78.4 inches ahead of the wing leading edge at the inboard edge of the fuel tank. It is the responsibility of the airplane owner and the pilot to ensure that the airplane is properly loaded. See Section 6 (Weight and Balance) for proper loading instructions. 2.15 MANEUVER LIMITS All intentional acrobatic maneuvers (including spins) are prohibited. Avoid abrupt maneuvers. REPORT: VB-1649 2-6 ISSUED: JANUARY 23, 1997 REVISED: APRIL 30, 2003 PA-34-220T, SENECA V 2.17 FLIGHT M ANEUVERING LOAD FACTORS (a) Positive Load Factor (Maximum) ( 1) Flaps Up (2) Flaps Down (b) Negative Load Factor (Maximum) 2.19 T YPES OF OPERATION SECTION 2 LIMITATIONS 3.8G 2.0G No inverted maneuvers approved. The airplane is approved for the following operations when equipped in accordance with FAR 9 1 or FAR 135. (a) Day Y.F.R. (b) Night Y.F.R. (c) Day I.F R. (d) Night I.F. R. (e) Icing conditions when equipped per Ice Protection System Instal lation Supplement (refer to Section 9). 2.21 FUEL LIMITATIONS NOTE The unusable fuel for this airplane has been determined as 3.0 U.S. gallons in each wing in critical flight attitude. (a) Total Capacity (b) Unusable Fuel (c) Usable Fuel ISSUED: JANUARY 23, 1997 128 U.S. GA LS. 6 U.S. GA LS. 122 U.S. GALS. REPORT: VB-I649 2-7 SECTION 2 LIMITATIONS 2.23 HEATER LIMITATIONS PA-34-220T, SENECA V Operation of the combustion heater above 25,00 feet is not approved. 2.25 OPERATING ALTITUDE LIMITATIONS Flight above 25,000 feet is not approved. Flight up to and including 25,000 feet is approved if equipped with oxygen in accordance with FAR 23.1441 and avionics in accordance with FAR 9 1 or FAR 135. 2.27 GYRO SUCTION LIMITS The operating limits for the suction system are 4.5 to 5.2 inches of mercury for all operations as indicated by the gyro suction gauge. - or- The operating limits for the suction system are 4.8 to 5.2 inches of mercury for all operations as indicated by the gyro suction gauge. 2.29 ICING INFORMATION "WARNING" Severe icing may result from environmental conditions outside of those for which the airplane is certified. Flight in freezing rain, freezing drizzle, or mixed icing conditions (supercooled liquid water and ice crystals) may result in ice build-up on protected surfaces exceeding the capability of the ice protection system, or may result in ice forming aft of the protected surfaces. This ice may not be shed using the ice protection systems, and may seriously degrade the performance and controllability of the airplane. During flight, severe icing conditions that exceed those for which the airplane is certificated shall be determined by the following visual cues. If one or more of these visual cues exists, immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the icing conditions. Unusually extensive ice accumulation on the airframe and windshield in areas not normally observed to collect ice. Accumulation of ice on the upper surface of the wing, aft of the protected area. Accumulation of ice on the engine nacelles and propeller spinners farther aft than normally observed. REPORT: VB-I649 2-8 ISSUED: JANU ARY 23, 1997 REVISED: AUGUST 19, 1998 PA-34-220T, SENECA V 2.29 ICING INFORMATION (cont) SECTION 2 LIMITATIONS Since the autopilot, when installed and operating, may mask tactile cues that indicate adverse changes in handling characteristics, use of the autopilot is prohibited when any of the visual cues specified above exist, or when unusual lateral trim requirements or autopilot trim warnings are encountered while the airplane is in icing conditions. All wing icing inspection lights must be operative prior to flight i nto known or forecast icing conditions at night . [NO TE: This supersedes any relief provided by the Master Minimum Equipment List (MMEL).J 2.31 PLACARDS In full view of the pilot: THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERAT ING LIMITATIONS STATED IN THE FORM OF PLA C A RDS, M A RK INGS. AN D M AN U AL S . N O AC ROBAT IC MANEUVERS ( IN CL UDING SPINS) APPROVED. THIS AIRCRAFT APPROVED FOR V.P.R., I.P.R., DAY, NIGHT & IC ING FLIGHT WHEN EQUIPP ED IN ACCORDANCE WITH FAR 91 OR FAR 135. MINIMUM SINGLE ENGIN E CONTROL SPEED 66 KIAS S INGLE ENGINE STALLS NOT RECOMMENDED. CAN CAUSE 400 FT. LOSS OF ALT ITUDE AND 15° P ITCH ANGLE. WA RNING - T U RN OFF ST R OBE L IGH T S WHEN TAXI ING IN VICIN IT Y OF OTHER AIRCRAFT, O R DURING FLIGHT THROUGH CLOUD, FOG OR HAZE. On side panel to left of pilot: CAUT ION - COMPASS CALIBRAT ION MAY BE IN ERRO R W IT H ELECT RICAL EQUIPMEN T O THER THAN AVION ICS ON. ISSUED: JANUARY 23, 1997 REVISED: APRIL 22, 1998 REPORT: VB-l.649 2-9 SECTION 2 LIMITATIONS PA-34-220T, SENECA V 2.31 PLACARDS (Cont) On instrument panel in full view of the pilot: VA 135 AT 4407 LBS. (SEE A.F.M.) VLO 128 DN. 107 UP VLE 128 MAX. DEMO X-WIND 17 KTS On instrument panel near emergency gear release: EMERGENCY GEAR EXTENSION PULL TO RELEASE. SEE A.F.M. BEFORE RE-ENGAGEMENT On instrument panel near gear selector switch: UP 107 KIAS MAX. GEAR DOWN 128 KIAS MAX. In full view of the pilot (adjacent to cowl flap controls): MAXIMUM TAKEOFF WEIGHT 4 407 POUNDS M AXIMUM LANDING WEIGHT 4407 POUNDS On storm window: REPORT: VB-I649 2-10 DO NOT OPEN ABOVE 129 KIAS ISSUED: JANUARY 23, 1997 PA-34-220T, SENECA V SECTION 2 LIMITATIONS On the instrument panel in full view of the pilot (2-blade propellers only) AVOID C ONfINUOUS GROUND OPERATION 160- 2 100 R PM IN CR OSS/TA IL WIND. AVOID C ONTINUOUS OPERATIONS 1900 - 2100 R PM ABOVE 32" MANIF OLD P RESSURE. Adjacent to upper door latch (rear door): ENGAGE LATCH BE F ORE FLIGHT On the inside of forward baggage compartment door: MAXIMU M BAGGAGE THIS C OM PA RT ME N T 100 LB S. SEE THE LIMITATI ONS SEC TI ON OF THE AI RPLA NE FLIGHT MANUA L. Adjacent to front door latch: Caution: DO NOT ATTEM PT TO CL OSE D O OR W I T H H ANDLE I N LATCHED POSITION. ISSUED: JANUARY 23, 1997 REPORT: VB-1649 2-11 SECTION 2 LIMITATIONS 2.31 PLACARDS (Cont) On the inside of cup dispenser door: MA XIMUM WEIGHT 2 LBS PA-34-220T, SENECA V On the inside of both oil filter access doors: OIL CO OLER WINTERIZATION PL ATE TO BE R EM O V ED WHEN AMBIE N T T EM P ERAT URE EXCEEDS 50°F. Adjacent to fuel tank filler caps: AVGAS ONLY pi,GRADE 100LL On aft baggage closeout: GRADE 100 MAXIMUM BAGGAGE T HIS COMPAR TMENT 85 LBS. NO HEAVY OBJECTS ON HAT S HELF. REPORT: VB-1649 2-12 ISSUED: JANUARY 23, 1997 PA-34-220T, SENECA V 2.31 PLACARDS (Cont) On the executive writing table: CAUTION SECTION 2 LIMITATIONS THIS TABLE MUST BE STOWED DURING TAKEOFF AND LANDING. In full view of the pilot and passengers: NO S MOKING In full view of the pilot: A RMRESTS ARE TO BE IN THE STOWED POSITION FOR TAKEOFF AND L A NDING ISSUED: JANUARY 23, 1997 REVISED: FEBRUARY 25, 2002 REPORT: VB-1649 2-13 SECTION 2 LIMITATIONS 2.31 PLACARDS (Cont) On right hand side of entertainment console top: MONITOR, ALL LOOSE ITEMS, A ND CONS OLE TOP ARE TO BE IN THE STOWED POSITION FOR TAKEOFF A ND LANDING On right hand side of entertainment console top: MAXIMUM WEIGHT ALLOWABLE ON THE CONSOLE T OP IN THE EXT ENDED POSITION IS 10 LBS. PA-34-220T, SENECA V REPORT: VB-I649 2-14 ISSUED: JANUARY 23, 1997 SECTION 1 GENERAL SECTION 2 LIMITATIONS SECTION 3 EMERG.PROCEDURES SECTION 4 NORMAL PROCEDURES SECTION 5 PERFORMANCE SECTION 6 WEIGHT&BALANCE SECTION 7 DESC.&OPERATIONS PA-34-220T, SENECA V SECTION 3 EMERGENCY PROCEDURES Paragraph No. TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Page No. 3.1 General .......................................................................................... 3-1 3.3 Airspeeds for Safe Operations ...................................................... 3-2 3.5 Emergency Procedures Checklist.................................................. 3-2 3.5a Engine Inoperative Procedures (3.9)............................................. 3-2 Identifying Dead Engine and Verifying Power Loss (3.9a)................................................ 3-2 Engine Securing Procedure (Feathering Procedure) (3.9b) .............................................. 3-2 Engine Failure During Takeoff (Speed Below 85 KIAS or Gear Down) (3.9c).................... 3-3 Engine Failure During Takeoff (Speed Above 85 KIAS) (3.9d) ........................................... 3-3 Engine Failure During Climb (3.ge) ........................................ 3-5 Engine Failure During Flight (Speed Below VMCA) (3.9!).......................... ....................... 3-6 One Engine Inoperative Landing (3.9g)................................... 3-7 One Engine Inoperative Go-Around (3.9h).............................. 3-8 ISSUED: JANUARY 23, 1997 REPORT: VB-1649 3-i SECTION 3 EMERGENCY PROCEDURES PA·34·220T, SENECA V TABLE OF CONTENTS (cont) SECTION 3 (cont) EMERGENCY PROCEDURES Paragraph Page No. No. 3.5b Air Starting Procedure (3.11) ......................................... ............... 3-8 Unfeathering Procedure! Starter Assisted (3.11a)........................................................ 3-9 Unfeathering Procedure! Unfeathering Accumulator Assisted (3.11b) ....................... 3-10 3.5c Engine Fire (3.13) ......................................................................... 3-11 Engine Fire During Start (3.13a).............................................. 3-11 Engine Fire In Hight (3.13b ).................................................... 3-11 3.Sd Turbocharger Failure (3.14) .......................................................... 3-12 3.5e Turbine Inlet Temperature (TIT) Indicator Failure (3.15) ............ 3-14 3.5f Fuel Management During One-Engine Inoperative Operation (3.17}.................................................... 3-15 Cruising (3.17a)........................................................................ 3-15 Crossfeed ...................... ..................... ................ ...................... 3-15 Corning out of Crossfeed.......................................................... 3-15 Landing (3.1 7b}........................................................................ 3-15 3.5g Engine-Driven Fuel Pump Failure (3.19) ..................................... 3-1 5 3.5h Landing Gear Unsafe Warnings (3.21) ......................................... 3-16 3.5i Landing Gear Malfunctions (3.23)................................................ 3-16 Manual Extension of Landing Gear (3.23a}............................. 3-16 Gear Up Landing (3.23b) ......................................................... 3-1 7 REPORT: VB·1649 3·ii ISSUED: JANUARY 23, 1997 REVISED: SEPTEMBER 26, 1997 PA-34-220T, SENECA V SECTION 3 EMERGENCY PROCEDURES Paragraph No. TABLE OF CONTENTS ( coot) SECTION 3 ( coot) EMERGENCY PROCEDURES 3.5j Electrical Failures (3.25) .... ........ ........ .... .. .... .. ....... .. ............... ...... . Single Alternator Failure (3.25a) ................................................ .. Dual Alternator Failure (3.25b) ................................................... .. 3.5k Vacuum System Failures (3.27) ....... .... .............................. .. ... ...... 3.5m Spin Recovery (3.29) .................................................................... 3.5n Emergency Descent (3.31) .......................................................... .. 3.50 Combustion Heater Overheat (3.33) ............................................. 3.5p Propeller Overspeed (3.35) ........................................................... 3.7 Amplified Emergency Procedures (General) ................................ 3.9 Engine Inoperative Procedures (3.5a) ........................................... 3.9a Identifying Dead Engine and Verifying Power Loss (3.5a) ......... . 3.9b Engine Securing Procedure (Feathering Procedure) (3.5a) ........... 3.9c Engine Failure During Takeoff (Speed Below 85 KIAS or Gear Down) (3.5a) ............................. 3.9d Engine Failure During Takeoff (Speed Above 85 KIAS) (3.5a) ............................................... . 3.ge Engine Failure During Climb (3.5a) ............................................. 3.9f Engine Failure During Flight (Speed Below Vmca) (3.5a) ................................................... .. Page No. 3-18 3-18 3-19 3-21 3-21 3-22 3-22 3-22 3-23 3-23 3-23 3-23 3-24 3-24 3-26 3-26 ISSUED: JANUARY 23, 1997 REVISED: SEPTEMBER 26, 1997 REPORT: VB-1649 3-iii SECTION 3 EMERGENCY PROCEDURES PA-34-220T, SENECA V TABLE OF CONTENTS (cont) SECTION 3 (cont) EMERGENCY PROCEDURES Paragraph Page No. No. 3.9g One Engine Inoperative Landing (3.5a)........................................ 3-27 3.9h One Engine Inoperative Go-Around (3.5a)................................... 3-27 3.9i Summary of Factors Afecting Single Engine Operations............ 3-28 3.11 Air Starting Procedure (3.5b)........................................................ 3-30 3.13 Engine Fire (3.5c) ......................................................................... 3-31 3.14 Turbocharger Failure (3.5d) .......................................................... 3-31a 3.15 Turbine Inlet Temperature (TIT) Indicator Failure (3.5e)............. 3-31b 3.17 Fuel Management During One Engine Inoperative Operation (3.5f)...................................... 3-32 3.19 Engine Driven Fuel Pump Failure (3.5g)...................................... 3-33 3.21 Landing Gear Unsafe Warnings (3.5h) ......................................... 3-35 3.23 Landing Gear Malfunctions (3.5i) ................................................ 3-35 3 .25 Electrical Failures (3.5j)................................................................ 3-37 3.27 Vacuum System Failures (3.Sk) .................................................... 3-39 3.29 Spin Recovery (Intentional Spins Prohibited) (3.5m)................... 3-39 3.31 Emergency Descent (3.5n) ............................................................ 3-40 3.33 Combustion Heater Overheat (3.50) ............................................. 3-40 3.35 Propeller Overspeed (3.5p) ........................................................... 3-40 REPORT: VB·I649 3-iv ISSUED: JANUARY 23, 1997 REVISED: SEPTEMBER 26, 1997 SENECA V SECTION 3 EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES 3.1 GENERAL This section provides the recommended procedures for coping w i th various emergency or critical situations. All of the emergency procedures required by the FAA as well as those necessary for operation of the airplane, as determined by its operating and design features, are presented. Emergency procedures associated with optional systems and equipment which require handbook supplements are presented in Section 9, Supplements. This section is divided into two basic parts. The first part contains the emergency procedures checklists. These checklists supply an immediate action sequence to be followed during critical situations with little emphasis on the operation of the systems. The numbers located in parentheses after each checklist heading indicate where the corresponding paragraph in the amplified procedures can be found. The second part of the section provides amplified emergency procedures corresponding to the emergency procedures checklist items. These amplified emergency procedures contain additional information to provide the pilot with a more complete description of the procedures so they may be more easily understood. The numbers located in parentheses after each paragraph heading indicates the corresponding checklist paragraph. Pilots must familiarize themselves with the procedures given in this section and must be prepared to take the appropriate action should an emergency situation arise. The procedures are offered as a course of action for coping with the particular situation or condition described.They are not a substitute for sound judgement and common sense. Most basic emergency procedures are a normal part of pilot training. The information presented in this section is not intended to replace this training. This information is intended to provide a source of reference for the procedures which are applicable to this airplane. The pilot should review standard emergency procedures periodically to remain proficient in them. ISSUED: JANUARY 23, 1997 REPORT: VB-I649 3-1 SECTION 3 EMERGENCY PROCEDURES PA-34-220T, SENECA V 3.3 AIRSPEEDS FOR SAFE OPERATIONS One engine inoperative air minimum control (VMCA) .............. .. . ... 66 KIAS One engine inoperative best rate of climb (VYSE) .... .. .... .................88 KIAS One engine inoperative best angle of climb (VXSE) ............ ............83 KIAS Maneuvering (VA - 4401 LBS) .............. ...................................... ... 135 KIAS Never exceed (VNE) ........................................... ............................204 KIAS 3.5 EMERGENCY PROCEDURES CHECKLIST 3.5a Engine Inoperative Procedures (3.9) IDENTIFYING DEAD ENGINE AND VERIFYING POWER LOSS (3.9a) Loss of thrust. Nose of aircraft will yaw in direction of dead engine (with coordinated controls). Rudder pedal force will be required in the direction away from the dead engine to maintain straight flight. ENGINE SECURING PROCEDURE (FEATHERING PROCEDURE) (3.9b) Throttle ..............................................................................................CLOSE Propeller ..........................................................FEATHER (800 RPM MIN.) Mixture ................................................................................IDLE CUT-OFF Cowl Flap ..........................................................................................CLOSE Fuel Selector ............................................................ ...............................OFF Airconditioner (If installed) ....................................................................OFF Altemator ................................................................................................ OFF Standby Fuel Pump .................................................................................OFF Magneto Switches...................................................................................OFF Prop Sync (If installed) ...........................................................................OFF Electrical Load ........................................................................ .......REDUCE Crossfeed .............................................................................AS REQUIRED REPORT: VB-I649 3·2 ISSUED: JANUARY 23, 1997 REVISED: APRIL 22, 1998 PA-34-220T, SENECA V SECTION 3 EMERGENCY PROCEDURES ENGINE FAILURE DURING TAKEOFF (SPEED BELOW 85 KIAS OR GEAR DOWN) (3.9c) H engine failure occurs during takeoff and 85 KIAS has not been attained: Throttles ................................................................IMMEDIATELy CLOSE Brakes (or land and brake) ...................................................AS REQUIRED Stop straight ahead If insu fficient runway remains for a complete stop: Throttles ................................................................IMMEDIATELY CLOSE Mixtures ...............................................................................IDLE CU1'-OFF Fuel Selectors ......................................................................................... OFF Magneto Switches... .................. ........ ....................... ..... .. .. .................... ..OFF Standby Fuel Pumps ...............................................................................OFF Battery Master Switch ............................................................................ OFF Brakes .............................................................................apply max. braking MAINTAIN DIRECI10NAL CONTROL, MANEUVERING TO AVOID OBSTACLES IF NECESSARY. ENGINE FAILURE DURING TAKEOFF (SPEED ABOVE 85 KIAS) (3.9d) If su fficient runway remains for a complete stop: Directional Control ........... .........................................................MAINTArn Throttles ................................................................IMEDIATELY CLOSE LAND IF AIRBORNE AND STOP STRAIGHT AHEA D Brakes ..................................................................................AS REQlJlRED ISSUED: JANUARY 23, 1997 REPORT; VB-I649 3·3 SECTION 3 EMERGENCY PROCEDURES PA-34-220T, SENECA V 3.5a Engine Inoperative Procedures (3.9d) (Continued) ENGINE FAILURE DURING TAKEOF F (SPEED ABOVE 85 KIAS) If runway remaining is inadequate for stopping and the decision is made to continue: WARNING Negative climb performance may result from an engine failure occurring after liftoff and before the failed engine's propeller has been feathered, the gear has been retracted, the cowl flap on the failed engine is closed and a speed of 88 KIAS has been attained. In many combinations of aircraft weight, configuration, ambient conditions and speed, negative climb pelformance may result. Refer to one engine inoperative climb chart for clean configuration positive climb performance. Mixture controls ..............................................................RJLL FORWARD P ropeller controls .............................................................RJLL FORWARD Throttles ................ .. , ............................................................38 in. Hg. MAP Directional Control .................................................................... MAINTAIN Flaps ...............................................................................................FULL UP Landing Gear (in level or climbing flight) ...................................RETRACT Inoperative Engine ................................................................IDENTIFY BY CLOSING THROT1LE P ropeller (Inop. Engine) .............................................................. FEATHER Establish Bank ................................. .20 to 3° INTO OPERATIVE ENGINE Climb Speed .............. .. ... .............. ......................................... ....... ...88 KIAS Trim ...............................................ADJUST TO 2° to 3° BANK TOWARD OPERATIVE ENGINE WITH APPROXIMATELY 112 BALL SLIP INDICATED O N THE TURN AND BANK INDICATOR Cowl Flap (Inop. Engine) ..................................................................CL OSE When a positive rate of climb has been established: Engine Securing .......................................................................COMPLETE LAND AS SOON AS PRACTICAL AT THE NEARES T SUITABLE AIRPORT. REPORT: VB-1649 3-4 ISSUED: JANUARY 23,1997 REVISED: NOVEMBER 10,2003 PA-34-220T, SENECA V SECTION 3 EMERGENCY PROCEDURES ENGINE FAILURE DURING CLIMB (3.ge) Airspeed ......................................................................MAINTAIN 88 KIAS Directional Control ....................................................................MAINTAIN Power ........................................................................MAX. CONTINUOUS Inoperative Engine ................................................IDENTIFY and VERIFY Inoperative Engine ....................................................COMPLE TE ENGINE SECURING PROCEDURE Trim .................................................................ADJUS T TO 2° to 3° BANK TOWARD OPERATIVE ENGINE WITH APPROXIMATELY 1/2 BALL SLIP INDICATE D ON THE TURN AND BANK INDICATOR Cowl Hap (Operative Engine) ........................ . . ............................ 112 OPEN lAND AS SOON AS PRAcrICALATTHE NEARESTSUITABLE AIRPORT. ISSUED: JANUARY 23, 1997 REPORT: VB·1649 3-5 SECTION 3 EMERGENCY PROCEDURES PA-34-220T, SENECA V 3.5a Engine Inoperative Procedures (Continued) ENGINE FAILURE DURING FLIGHT (SPEED BELOW VMCA) (3.9f) Rudder ...................................................................APPLY AGAINST YAW (Operative Engine) Throttles (Both Engines) ...................................RETARD TO S TOP TURN Pitch Attitude .......................................LOWER NOSE TO ACCELERATE ABOVE YMCA (66 K IAS) Operative Engine . ..............................INCREASE POWER AS AIRSPEED INCREASES ABOVE YMCA (66 K IAS) H altitude permits, a restart may be attempted. H restart fails or if altitude does not permit restart: Inoperative Engine Propeller........................................................FEATHER Trim ................................................................. ADJUST TO 2° to 3° BANK TOWARD OPERATIVE ENGINE WITH APPROXIMATELY 112 BALL SLIP INDICATED ON THE TURN AND BANK INDICATOR Inoperative Engine ............................................................. Complete Engine Securing Procedure Cowl Flap (Operative Engine) .... .................................................. 112 OPEN IAND AS SOON AS PRACI'ICALATTHE NEAREST SUITABLE AIRPORT. REPORT: VB·I649 3-6 ISSUED: JANUARY 23, 1997 PA-34-220T, SENECA V SECTION 3 EMERGENCY PROCEDURES ONE ENGINE INOPERATIVE LANDING (3.9g) Inoperative Engine ............................ENGINE SECURIN G PROCEDURE COMPLETE Seat BeltslHarnesses ....................................................... FAS1ENIADJUST Fuel Selector (Operative Engine) ............................................................. ON Standby Fuel Pump (Operative Engine) .......................................... ...... .. ON Mixture (Operative Engine) ......................................................FULL RICH Propeller Control (Operative Engine) ..............................FVLL FORWARD Cowl Flap (Operative Engine) ...................... .......... ........ ...... ....... . 112 OPEN Altit ude & Airspeed .........................................................MAKE NORMAL APPROACH When lAnding is Assured: Landing Gear ....................................................................................DOWN Flaps..................................................................................... AS REQlJIRED Final Approach Speed .......... ................................................ ...... .....90 KIAS Power ...................................................................RETARD SLOWLY AND FLARE AIRPLANE Trim ...................................................................AS POWER IS REDUCED ISSUED: JANUARY 23 , 1997 (AIRPLANE WILL YAW IN DIRECTION OF OPERATIVE ENGINE) REPORT: VB-I649 3-7 SECTION 3 EMERGENCY PROCEDURES PA-34-220T,SENECA V 3.5a Engine Inoperative Procedures (Continued) WARNING Under many conditions of loading and density altitude a go-around may be impossible and in any event the sudden a p plication of power d u r i n g one engine ino perative operation makes control of the airplane more difficult. WARNING O ne Engine Go-Around is not possible from the approach configuration unless sufficient altitude is available to raise flaps and landing gear in a descent. CAU TION: A one engine inoperative go-around should be avoided if at all possible. ONE ENGINE INOPERATIVE GO-AROUND Mixture ............................................................................VERIFY FULL FORWARD Propeller ...........................................................................VERIFy FULL FORWARD Throttle ................................................................... MAX ON OPERATIVE ENGINE Flaps ............................................................................................RE TRAC T SLOW LY Landing Gear ................................................................................................RETRAC T Airspeed ...........................................................................................................88 KIAS Trim .................................................................................ADJUS T TO 2°to 3° BANK TOWARD OPERATIVE ENGINE W ITH APPROXIMATELY 1/2 BALL SLIP INDICATED ON THE TURN AND BANK INDICATOR Cowl Flap (Operating Engine) ....................................................................... 1/2 OPEN REPORT: VB-1649 3-8 ISSUED: JANUARY 23,1997 REVISED: NOVEMBER 10, 2003 PA·34.220T, SENECA V 3.Sb Air Starting Procedure (3.11) SECTION 3 EMERGENCY PROCEDURES UNFEATHERING PROCEDURE! STARTER ASSISTED (3.11a) Fuel Selector (Inoperative Engine) .......................................................... ON Standby Fuel Pump .................................................................................. ON Throttle ...................................................................................Open 1/2 inch Mixture ........................................... ..........................................FlJLL RICH Magneto Switches (Inoperative Engine).................................................. ON Prop Control (Inoperative Engine) .........................................MID R ANGE Starter .................................................. :........ENGAGE until prop windmills Throttle ..........................................REDUCE POWER until engine is warm Standby Fuel Pump................................................................................. OFF Alternator (after restart) ........................................................................... ON Engine Instruments ..........................................................................CHECK Airconditioner (If installed) ................................................(As desired) ON Propeller ................................................Manual Sync with operative engine Throttle....................................................................................Set as Desired Prop Sync (If installed) ....................................................... (As desired) ON ISSUED: JANUARY 23, 1997 REPORT: VB·1649 J.9 SECTION 3 EMERGENCY PROCEDURES PA-34-220T, SENECA V * UNFE ATHERING PROCEDUREI UNFEATHER ING A C CU MULATOR ASSISTED (3.l1b) * NOTE With the propeller unfeathering system installed, the propeller will usually windmill automatically when the propeller control is moved forward. Fuel Selector (Inoperative Engine) ..........................................................ON Standby Fuel Pump (Inop. Engine)..........................................................ON Throttle ...................................................................................Opeii 1I4 inch Mixture .....................................................................................FULL RICH Magneto Switches (Inoperative Engine) ..................................................ON Prop Control ....................................................................FULL FORWARD Throttle .......................................... REDUCE POWER until engine is warm Standby Fuel Pump (Inop. Engine) ........................................................OFF Alternator .................................................................................................ON H engine does not start, prime as required and engage starter. NOTE Starter assist is required if the propeller is not windmiIling freely within 5-7 seconds after the propeller control has been moved forward. When propeller unfeathering occurs, it may be necessary to retard the prop control slightly to keep the prop from overspeeding. Optional Equipment with Hartzell Propeller installation. REPORT: VB-1649 3-10 ISSUED: JANUARY 23, 1 997 PA-34-220T, SENECA V 3.Sc Engine Fire (3.13) SECTION 3 EMERGENCY PROCEDURES ENGINE FIRE DURING START (3.13a) If engine has not started: Fuel Selector ........................................................................................... OFF Mixture ................................................................................ IDLE CUT-OFF TIrrottle ..................................................................................... FULL OPEN Starter ............................................................. CONTINUE to Crank Engine If engine has already started and is mnning, continue operating to try pulling the fire into the engine. If fire continues: Fuel Selector ...........................................................................................OFF Standby Fuel Pump.................................................................................OFF Mixture ............................................................................ ....IDLE CUT-OFF TIrrottle .....................................................................................FULL OPEN External Fire Extinguisher (If Available) ...............................................USE Airplane .....................................................................................EVACUATE NOTES: If fire continues, shut down both engines and evacuate. If fire has spread to the ground, it may be possible to taxi away. ENGINE FIRE IN FLIGHT (3.13b) Fuel Selector (Affected Engine) .............................................................OFF Throttle (Affected Engine) ................................................................ CLOSE Propeller (Affected Engine) ......................................................... FEATHER Mixture (Affected Engine) .............................. ....................IDLE CUT-OFF Heater ...................................................................................................... OFF Defroster ................................................................................................. OFF Cowl Flap ............................................................................................ OPEN Affected Engine ...........................COMPLE TE Engine Securing Procedure If fire persists: Airspeed........................................... INCREASE in attempt to blow out fire Land as soon as possible at the nearest suitable airport. ISSUED: JANUARY 23, 1997 REPORT: VB-1649 3-11 SECTION 3 EMERGENCY PROCEDURES PA-34-220T, SENECA V 3.Sd TURBOCHARGER FAILURE (3.14) CAUTION: If a turbocharger fa i l ure is the result of lo o s e, disconne c t e d or burned th rough exhaust s y s t e m components, a potentially serious fire hazard exists. If a failure within the exhaust system is suspected in flight, shut down the engine immediately and LAN D AS SOON AS POSSIBLE. If a suspected exhaust system failure occurs prior to takeoff, DO N O T FLY THE AIRCRAFT . NOTE: A turbocharger malfunction at altitudes above 10,00 feet MSL may result in an overly rich fuel mixture, which could result in a partial power loss and/or a rough running engine. In worst case conditions a complete loss of engine power may result. COMPLETE LOSS OF ENGINE POWER: If a suspected turbocharger or turbocharger control system failure results' in a complete loss of engine power, the following procedure is recommended: Mixture ..................................................... .. ......... ......... .. ........ .....IDLE CUTOFF Throttle ....................................................................................................CRUISE Propeller Control ............... ............................................ ......... FULL FORWARD Mixture ......................... . . . ... . ..... ....... . ADVANCE SLOWLY until engine restarts and adjust for smooth engine operation Reduce power and land as soon as possible. REPORT: VB-I649 3-12 ISSUED: JANUARY 23, 1997 REVISED: SEPTEMBER 26, 1997 PA-34-220T, SENECA V SECTION 3 EMERGENCY P ROCEDURES 3.Sd TURBOCHARGER FAILURE (3.14) (continued) PARTIAL LOSS OF ENGINE POWER If the turbocharger waste gate fails in the OPEN position, a partial loss o f engine power may result. The following procedure i s recommended i f a suspected turbocharger or turbocharger wastegate control failure results in a partial loss of engine power. Throttle .......................................................................................AS REQUIRED Propeller ......................................................................................AS REQUIRED Mixture .......................................................................................AS REQUIRED Land as soon as possible. ENGINE POWER OVERBOOST If the turbocharger wastegate control fails in the CLOSED position, an engine power overboost condition may occur. The following p rocedure i s recommended for an overboost condition: Throttle . ............REDUCE as necessary to keep manifold pressure within limits NOTE Ex p e ct manifold p r essure response to t h r ottle movements to be sensitive. Propeller ......................................................................................AS REQUIRED Mixture .............................................................................................FULL RICH Land as soon as possible. ISSUED: JANUARY 23, 1997 REVISED: SEPTEMBER 26, 1997 REPORT: VB-1649 3-13 SECTION 3 EMERGENCY PROCEDURES PA-34-220T, SENECA V 3.Se Thrbine Inlet Temperature (TIT) Indicator Failure (3.15) If failure occur s during takeoff, climb, or landing: Mixture ...................................................................................................Full Rich If failure occurs prior to setting cruise power: Power ..................................................................... Set Power per POH Section 5 Power Setting Table Mixture ......... ........................ .. .... .... ...... ..... ....... . Lean to Approx. POH Section 5 Power Setting Table Fuel Flow +4 GPH. Monitor CHT and Oil Temp. C AUTION Aircraft POH range and endurance data presented in Section 5 wil1 no longer be applicable. Less range/endurance will result due to higher fuel flow/fuel consumption. If failure occurs after setting cruise power and mixture: Power......................................................................NotelMaintain Power Setting Mixture ....................................................Increase Indicated Fuel Flow + 1 GPH. Monitor CHT and Oil Temp. CAUTION Aircraft POH range and endurance data presented in Section 5 will no longer be applicable. Less range/endurance will result due to higher fuel flow/fuel consumption. Iffailure occurs prior to or during descent: Power ............................................................................................ Set for Descent Mixture ................................................................................................... Full Rich REPORT: VB-I649 3-14 ISSUED: JANUARY 23, 1997 REVISED: SEPTEMBER 26, 1997 PA-34-220T, SENECA V SECTION 3 EMERGENCY PROCEDURES 3.5£ Fuel Management During One Engine Inoperative Operation (3.17) CRUISING (3.17a) CROSSFEED Fuel Selector (Operative Engine)............................................ CRO S SFEED Fuel Selector ( Inoperative Engine).........................................................OFF NOTE Use crossfeed in level cruise flight only. COMING OUT OF CROSSFEED (Prior to Landing) Standby Fuel Pump (Operative Engine) ..................................................ON Fuel Selector (Operative Engine).............................................................ON Fuel Selector ( Inoperative Engine).........................................................O FF Standby Fuel Pump ( Inoperative Engine) ..............................................OFF LANDING (3.17b) Fuel Selector (Operative Engine)............................................................. ON Fuel Selector (Inoperative Engine).........................................................OFF Standby Fuel Pump (Operative Engine) . ...... ......... ....... .. ....... .... .. ...... ...... ON 3.5g Engine Driven Fuel Pump Failure (3.19) Throttle ...........................................................................................RETARD Standby Fuel Pump (Affected Engine) .................................................... ON Throttle ....................................................................... RE SET (As Required) Mixture ....................................................................... RESET (As Required) CAUTION I f normal engine operation and fuel flow is not i mmediately re-established, the standby fuel pump should be turned off. The lack of a fuel flow indication could indicate a leak in the fuel system, or fuel exhaustion. If system leak is verified, switch fuel selector to OFF. Proceed with engine securing procedure. ISSUED: JANUARY 23, 1997 REVISED: SEPTEMBER 26, 1997 REPORT: VB-I649 3-15 SECTION 3 EMERGENCY PROCEDURES PA-34-220T, SENECA V 3.Sh Landing Gear Unsafe Warnings (3.21) Red gear warning annunciator light indicates when the gear is in transit. Recycle gear if indication continues. Red gear warning annunciator light will illuminate along with the gear warning horn should the gear not be down and locked if throttles are brought to a low setting. 3.Si Landing Gear Malfunctions (3.23) MANUAL EXTENSION OF L ANDING GEAR (3.23a) IT emergency gear extension is required due to electrical power failure, the gear position indicator lights will not illuminate. Check following before extending gear manlUly: DaylNight Dimming Switch (Daytime) ................................................ DAy Circuit Breakers ................................................................................ CHECK Battery Master Switch .............................................................................. ON Alternators ........................................................................................ CHECK To extend, reposition guard clip downward clear o f knob.and proceed as follows: Airspeed ..............................................................REDUCE (85 KlAS max.) Gear Selector ...................................................... GEAR DOWN POSITION E merg. Gear Extend Knob ...................................................................PULL Indicator Lights..................... ................... ..... .................................3 GREEN Leave emergency gear extension knob out. WARNING If the emergency gear extension knob has been pulled out to lower the gear due to a gear system malfunction, leave the control in its extended position until the airplane has been put on jacks to check the proper function of the landing gears hydraulic and electrical systems. REPORT: VB-I649 3-16 ISSUED: JANUARY 23, 1997 REVISED: SEPTEMBER 26, 1997 PA-34-220T, SENECA V GEAR UP LANDING (3.23b) Select suitable landing area. SECTION) EMERGENCY PROCEDURES Ground PersonneL.................................................... IN FORM ( I f possible) Fuel ....... ............ ...... ................................. .. .. ..BURN O F F ( I f time allowed) Seatbelts and Harness ...................................................... FASTENIADmST CHECK INERTIA REEL Passengers ........ .... ............................ ........... .... ... ............... ........ ........ .. BRIEF Normal Landing Checklist........................................................ COM PLETE Autopilot ............................... ..................................................................OFF Battery Master (Daytime).......................................................................OFF Approach ......................................................................................NORMAL When runway is made and landing is assured: Mixtures ...............................................................................IDLE CUTOFF Prop Controls ................................................................................ FEATIR Fuel Selectors .........................................................................................OFF Touch down at minimum airspeed and level attitude. Battery Master (Night)............................................................................OFF Evacuate when aircraft comes to a stop. ISSUED: JANUARY 23, 1997 REVISED: SEPrEMBER 26, 1997 REPORT: VB-I649 I 3-17 SECTION 3 EMERGENCY PROCEDURES PA·34·220T, SENECA V 3.5j Electrical Failures (3.25) SINGLE ALTERNATOR FAILURE (Alternator #1 or #2 Inop. Light muminated • Annunciator Panel). (3.25a) Verify Failure ...............................................................CHECK AMME1ER Electrical load ........................................................REDUCE until total load is less than 85 Amps Failed Alternator Switch .........................................................................OFF Failed Alternator Circuit Breaker ..............................CHECK·AND RESET Failed Alternator Switch (After OFF at least 1 second) .............................ON If power is NOT restored: Failed Alternator Switch.........................................................................OFF Amperage ............................................................................. MONlTOR and maintain below 85 Amps While one alternator will supply sufficient current for minimum required avionics and cockpit lighting, use of deicing equipment, particularly windshield or propeller heat, may be limited. Immediate action should be taken to avoid or exit icing conditions. Under no circumstances may the total electrical load exceed 85 amps. The cabin recirculation blowers, and position, strobe and landing lights should not be used unless absolutely necessary. REPORT: VB·I649 3·18 ISSUED: JANUARY 23, 1997 REVISED: SEPTEMBER 26, 1997 PA-34-220T, SENECA V SECTION 3 EMERGENCY PROCEDURES 3.5j Electrical Failures (3.25) (C ontinued) DUAL ALTERNATOR FAILURE (Alternator #1 and #2 Inop. Light muminated - Annunciator Panel). (3.25b) CAUTION The alternator output circuit breakers must not be opened manually when t h e al ternators are functioning properly. NOTE Any ti me total bus volt age i s below approximately 25 V dc, the LO BUS vo ltage annunciator will illuminate. Verify Failure ...............................................................CHECK AMlER Electrical load............................................................REDUCE to minimum required for safe flight Alternator Switches .............................................. ..................................OFF Alternator Circuit Breakers ............................................. CHECK & RESET AS REQUIRED Alternator Switches (One at a time after OFF at least 1 second) ....... ...................................... .... .. ........... ON IT only one alternat or resets: Operating Alternator Switch .......................................... .......................... ON Failed Alternator Switch ................................. ........................................ OFF Electrical load ..................................................................... MAINTAIN less than 85 Amps Amperage ....................................................................................MONITOR ISSUED: JANUARY 23, 1997 REVISED: SEPTEMBER 26, 1997 REPORT: VB·I649 3-19 SECTION 3 EMERGENCY PROCEDURES PA-34-220T, SENECA V 3.5j Electrical Failures (3.25) (Continued) DUAL ALTERNATOR FAILURE (Continued) If neither alternator resets: Both Alternator Switches........................................................................OFF CONTINUE FUGHT WITH REDUCED ELECTRICAL LOAD ON BATTERY POWER ONLY. Nom LO BUS voltage annunciator will also be illuminated. Land as soon as practical. Anticipate complete electrical failure. Duration of battery power available will be dependent on electrical load and battery condition prior to failure. WARNING Compass error may exceed 10 degrees with both alternators inoperative. Nom If battery is depleted, the landing gear must be lowered using the emergency gear extension procedure. Gear p o sition ligh t s wil l be inoperative. The flaps will also be inoperative and a flaps up landing will be required REPORT: V B-1649 3-20 ISSUED: JANUARY 23, 1997 REVISED: SEPTEMBER 26. 1997 PA-34-220T, SENECA V 3.5k Vac uum System Failure s (3.27) SECTION 3 EMERGENCY PROCEDURES (Left or right Vacuum Inop. Light lliuminated - Annunciator Panel). Gyro Suction Gauge ....................... CHECK (within normal operating range) Although either vacuum pump independently has sufficient capacity to operate the flight instruments and the deice boots in a nonnal manner, intentional or continued operation in icing conditions is not recommended. Immediate action should be taken to avoid or exit icing conditions. (Left and right Vac uum Inop. Light lliuminated - Annunciator Panel). If both vacuum systems are inoperable, the turn coordinator and pilot's directional gyro will be the only usable gyroscopic flight instruments, wing and tail deicer boots will be inoperative. A precautionary landing should be considered depending on operating conditions 3.5m Spin Recovery (In tentional Spin s Prohibited) (3.29) NOTE Federal Aviation Administration Regulations do not require spin demonstration of multi-engine airplanes ; spin tests have not been conducted. The recovery technique presented is based on the best available information. Throttles ........... ................................................................ RETARD to IDLE Rudder ... .. . .. .. . . . . .. . . . . . . . . . . . . . . . . . .. . . . . . . . . . . .. .. . . . . . .. . .. . . . . . .. . . . . . . FULL OPPOSITE TO DIRECTION OF SPIN Control wheel ...............................................................FULL FORWARD if nose does not drop Ailerons . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEUTRAL Rudder . .. . ... . . . . . . . . . . . . . .. .. . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . .. .... .. . . . . . NEUTRALIZE when rotation stops Control wheel ............................................... SMOOTH BACK PRESSURE ISSUED: JANUARY 23, 1997 REVISED: AUGUST 19, 1998 to recover from dive REPORT: VB-1649 3-21 SECTION 3 EMERGENCY PROCEDURES PA·34·220T, SENECA V 3.5n Emergency Descen t (3.31) Throttles. . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED Propellers . . . . . . . . . . . . . . . . . . . . . . ... . . ...... . . . . . ... . . . . . . . .. .. . ... . .. . . . . ... .. .....FULL FORWARD Mixture...........................................................................AS REQUIRED for smooth operation Landing gear ......................................................EXTEND below 128 KIAS Airspeed . .... .. . ... .. . . ... .. . . .... .... . . . .... . ... .. . . . . ... . . . . . . . . . . . . . . . . . . . . . . . . . . . .. 128 KIAS Max. 3.50 Combus tion Heater Overheat (3.33) Unit will automatically cut-off. Do not attempt to restart. 3.5p Propeller O verspeed (3.35) Throttle (Affected Engine) . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . ..... . . ..... . . . . . . ... . . . . . . . .RETARD Oil pressure (Affected Engine) .........................................................ClIECK Prop control (Affected Engine) .............................FULL DECREASE RPM (DO NOT FEATHER) THEN SET if any control available Airspeed ......................................................................................... REDUCE Throttle (Affected Engine) .................................. AS REQUIRED to remain REPORT: VB·1649 3·22 below 2600 rpm ISSUED: JANUARY 23, 1997 REVISED: SEPTEMBER 26, 1997 SECTION 3 EMERGENCY PROCEDURES PA-34-220T, SENECA V 3.7 AMPLIFIED EMERGENCY PROCEDURES (GENERAL) The following paragraphs are presented to supply additional infonnation 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. EMERGENCY PROCEDURES CHECKLIST (3.5) 3.9 Engine Inoperative Procedures (3.5a) 3 .9a Identifying Dead Engine and Verifying Power Los (3.5a) If it is suspected that an engine has lost power, the faulty engine must be identified, and its power loss verified. Rudder pressure required to maintain directional control will be on the side of the operative engine - in short, A DEAD FOOT INDICATES A DEAD ENGINE. Engine gauges like TIT and oil pressure may be of help in identifying the dead engine. 3.9b Engine Securing Procedure (Feathering Procedure) (3.5a) The engine securing procedure should always be accomplished in a sequential order according to the nature of the engine failure. Begin the securing procedure by moving the throttle of the inoperative engine towards IDLE. If no changes are noted, the correct identification of the dead engine is confirmed. Move the propeller control to FEATIIER (fully aft) before the propeller speed drops below 800 RPM. The propellers can be feathered only while the engine is rotating above 800 RPM. Loss of centrifugal force due to slowing rpm will actuate a stop pin that keeps the propeller from feathering each time the engine is stopped on the ground. One engine inoperative perfonnance will decrease significantly if the propeller of the inoperative engine is not feathered. The inoperative engine's mixture control should be moved fully aft to the IDLE CUTOFF position. Close its cowl flap to reduce drag. Move t he inoperative engine's fuel selector to the off position. Tum off the airconditioner (if installed). The alternator switch, magneto switches, standby fuel pump switch and prop sync (if installed), should all be turned off. Complete the procedure by reducing the electrical load and considering the use of the fuel crossfeed if the fuel quantity dictates. NOTE When an engine is feathered, the OIL, VACuum INOP, a n d ALTernator annunciator warning lights will remain illuminated. ISSUED: JANUARY 23, 1 997 REVISED: SEPTEMBER 26 , 1 997 REPORT: VB-I649 I 3-23 PA-34-220T, SENECA V SECTION 3 EMERGENCY PROCEDURES 3.9c E ngine Failure During Take off (Speed Below 85 KIAS or Gear Down) (3.5a) Determination of runway l e ngth, single engine climb rate, and accelerate/stop distance will aid in detennining the best course of action in the event of an engine failure during takeoff. If engine failure occurs during the takeoff roll, the takeoff MUST be aborted. If failure occurs after liftoff but before 85 KlAS is achieved or before the gear is retracted, the takeoff should also be aborted. Immediately CLOSE the throttles, land if airborne, apply brakes as required and stop straight ahead. If an engine failure occurs below 85 KIAS and there is not adequate runway remaining for landing, deceleration and stop, immediately retard the throttles fully aft and mixture controls to idle cut-off. Move the fuel selectors to the off position. Turn OFF the magneto switches followed by the stand by fuel pump and battery master switch while applying maximum braking. During these procedures maintain directional control and if necessary, maneuver to avoid obstacles. 3.9d Engine Fallure During Takeoff (Speed Above 85 KIAS) (3.5a) If engine failure occurs after liftoff with the gear still down and 85 KlAS has been attained, the course of action to be taken will depend on the runway remaining and aircraft configuration. Also the pilot's decision must be based on a personal judgement, taking into consideration such factors as obstacles, the type of terrain beyond the runway, altitude and temperature, weight and loading, weather, airplane condition, and the pilot's own proficiency and capability. If adequate runway remains, maintain heading. Close both throttle s immediately, land i f airborne, apply brakes as required and stop straight ahead. REPORT: VB-I649 3-24 ISSUED: JANUARY 23, 1997 REVISED: SEPTEMBER 26, 1997 SECTION 3 EMERGENCY PROCEDURES PA·34· 220T, SENECA V 3.9d Engine Failure Dm'ing Takeoff (Speed Above 85 KIAS) (3.5a) (Cont) WARNING hl many combinations of aircraft weight, configuration, ambient conditions and speed, negative climb perfonnance may result . Re fer to One Engine I no perat ive Climb chart for c l e a n configuration positive climb perfonnance. Negative climb perfonnance may result from an engine failure occuning after liftoff and before the failed engine's propeller has been feathered, the gear has been retracted, the cowI flap on the failed engine is closed and a speed of 88 KIAS has been attained . If the runway remaining is inadequate for stopping or the gear is in-transit or up, the pilot must decide whether to abort or to continue the takeoff and climb on a single engine. If a decision is made to continue the takeoff, the airplane will tend to t urn in the direction of the inoperative engine, since one engine will be inoperative and the other will be at maximum power. Rudder pressure force on the side of the operative engine will be necessary to maintain directional control. Verify the mixture, propeller and throttle controls are fully forward while maintaining directional control. Remember, keep in mind that the O ne Engine Inoperative A ir Minimum Control speed (VMCA) is 66 KIA S and the One Engine Inoperative Best Rate of Climb speed (VYSE) is 88 KIA S . Verify that the flaps and landing gear are up. O nce the faulty engine is identified and its power loss verified, feather its propeller. Establish a bank of 2° to 3° into the operative engine. Maintain 88 KIAS (VYSE). Trim the aircraft for 2° to 3° bank toward the operative engine with approxim ately 1 /2 ball slip indicated on the turn and bank indicator. Close the cowl flap on the inoperative engine. After the aircraft is tr immed, and a positive rate of climb has been established, complete the engine securing procedure. Land as soon as prac tical at the nearest suitable airport. ISSUED: JANUARY 23,1997 REVISED: N OVEMBER 10, 2003 REPORT: VB·1649 3· 25 PA-34-220T, SENECA V SECTION 3 EMERGENCY PROCEDURES 3.ge Engine Failure During Climb (3.Sa) If engine failure occurs during climb, a minimum airspeed of 88 K1AS (VVSE) should be maintained. Since one engine will be inoperative and the other will be at maximum power, the airplane will have a tendency to tum in the direction of the inoperative engine. Rudder pedal force on the side of the operative engine will be necessary to maintain directional control. After the faulty engine has been identified and power loss has been verified, complete the Engine Securing Procedure. Continue a straight ahead climb until sufficient altitude (minimum of 10 feet above ground elevation) is reached to' execute the normal Single Engine Landing procedure at the nearest suitable airport. For maximum climb perfonnance in single engine flight, sideslip must be minimized by banking towards the operating engine 20 to 30. The ball of the turn and slip indicator will be approximately 1 /2 diameter out of center towards the operating engine for straight flight and should remain so displaced during any maneuvering necessary. The cowl flap on the operative engine should be set to 112 open. Land as soon as practical at the nearest suitable airport. 3.9f Engine Failure During F ligh t (Speed Below VMCA)(3.Sa) Should an engine fail during flight at an airspeed below YMCA (66 KIAS) apply rudder towards the operative engine to minimize the yawing motion. The throttles should be retarded to stop the yaw towards the inoperative engine. Lower the nose of the aircraft to accelerate above 66 KIAS and increase the power on the operative engine as the airspeed exceeds 66 KIAS. The airplane should be banked 5° towards the operating engine during this recovery to maximize control effectiveness. After an airspeed of at least 88 KIAS (VYSE) has been established, an engine restart attempt may be made if altitude permits. If the restart has failed. or altitude does not permit. the engine should be secured. Move the propeller control of the inoperative engine to FEATHER and complete the engine securing procedure. Adjust the trim to a 2° to 3<l bank into the operative engine with approximately 112 ball slip indicated on the tum and bank indicator. The cowl flap on the operative engine should be set to 1 /2 open to maintain engine temperatures within allowable limits. REPORT: VB-1649 3-26 ISSUED: JANUARY 23, 1997 REVISED: SEPTEMBER 26, 1997 SECTION 3 EMERGENCY PROCEDURES PA-34-220T, SENECA V 3.9g One Engine Inoperative Landing (3.5a) Complete the Engine Securing Procedure. The landing gear should not be extended and the wing naps should not be lowered until certain of making the field. Check seat belts and harnesses are properly secured. Check that the fuel selector and the standby fuel pump of the operative engine are ON and t he mixture control is FULL RICH . Move the propeller control FULL FORWARD. Adj ust the cowl nap control of the operating engine to the 112 open position to keep temperatures within limits. Maintain a nonnal approach, keeping in mind that landing should be made right the first time and that a go-around should be avoided if at all possible. W hen landing is assured, extend the landing gear and lower the naps as required. Establish a final approach speed of 90 KIAS and retard the power slowly to touchdown using trim as required. 3.9h One Engine Inoperative Go-Around ( 3.5a) CAUTION: A one engine inoperative go-around should be avoided if at all possible. WARNING: Under some conditions of loading and density altitude a go ar ound may be impo ssib le, and in any event the sudd en application of power during one engine inoperative operation makes control of the airplane more difficult. WARNING O ne Engine Go-Around is not possible from the approach configuration unless sufficient altitude is available to raise naps and landing gear in a descent. To execute a one engine inoperative go-around, verify the mixt ure and propeller levers are full forward. The throttle should be advanced slowly to the maximum manifold pressure 38 in. H g . Retract the naps slowly. After a positive rate of climb has been established, retract the landing gear. Maintain airspeed at the one engine inoperative best rate of climb speed of 88 KIAS. Trim the aircraf t for 20 to 30 bank toward the operative engi ne w i t h approximately 112 ball slip indicated on the turn and bank indicator. Set the cowl flaps of the operating engine to the 112 open position. ISSUED: JANUARY 23, 1997 REVISED: NOVEMBER 10, 2003 REPORT: VB - 1 649 3-27 PA-34-220T, SENECA V SECTION 3 EMERGENCY PROCEDURES 3.9i Summary of Fac tors Afecting Single Engine Operations. Significant climb perfonnance penalties can result from landing gear, flap, or windmilling propeller drag. These penalties are approximately as l isted below: Landing gear extendedlRaps Up ........................................-200 ft.lrnin. Flaps extended 2So/Gear Down .......................................... -300 ft.lmin. Flaps extended fully/Gear Down .......................................- 350 ft.lmin. Inoperative engine propeller windmilling (Gear and Flaps Up) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .-200 ft.lmin. WARNING The propeller on the inoperative engine must be feathered, the landing gear retracted, and the wing flaps r�tracted for continued flight. REPORT: VB-1649 3-28 ISSUED: JANUARY 23, 1997 REVISED: SEPTEMBER 26, 1997 SECTION 3 EMERGENCY PROCEDURES PA-34-220T, SENECA V 3.9i Summary of Factors Affecting Single Engine Operations. (Continued) The following general facts should be used as a guide if an engine failure occurs: 1 . Discontinuing a takeoff upon engine failure is advisable under most circumstances. Continuing the takeoff, if engine failure occurs prior to r

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