Pilot's Operating Handbook and FAA Approved Airplane Flight Manual

Piper PA-32 Saratoga II TC · Pilot's Operating Handbook

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Overview

This Pilot's Operating Handbook (POH) is specifically designed for the Piper PA-32R-301 Saratoga II HP. It serves as a comprehensive operating guide for pilots, containing essential information required by the FAA and additional data provided by the manufacturer. The handbook emphasizes the importance of maintaining airworthiness and understanding operational limitations. It is not a substitute for flight training or instruction but is intended to enhance the pilot's knowledge of the aircraft's systems, performance, and procedures. The handbook is structured for easy reference, with sections dedicated to limitations, emergency procedures, normal operations, performance, and maintenance.

Maximum Takeoff Weight: 3600 lbs
Maximum Landing Weight: 3600 lbs
Maximum Ramp Weight: 3615 lbs
Fuel Capacity: 107 U.S. gallons (usable: 102 U.S. gallons)
Engine: Lycoming IO-540-K1G5, 300 HP
Propeller: Hartzell F7663DR, 3 blades, 77-78 inches diameter
Never Exceed Speed (VNE): 191 KIAS
Maximum Structural Cruising Speed (VNO): 160 KIAS

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Originally published by stpeteair.org. 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: 470
File size: 11 MB
Publisher: stpeteair.org

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In this document

General

This section introduces the Pilot's Operating Handbook, outlining its purpose as a guide for pilots. It emphasizes the importance of understanding the aircraft's limitations and operational characteristics before flight. The handbook is divided into sections for quick reference, with critical information like limitations and emergency procedures prioritized for accessibility.

Limitations

This section details the FAA-approved operating limitations for the Piper PA-32R-301. It includes airspeed limitations, weight limits, and center of gravity limits. Specific speeds such as Never Exceed Speed (VNE), Maximum Structural Cruising Speed (VNO), and Maneuvering Speed (VA) are provided, along with cautionary notes regarding their application.

Emergency Procedures

This section outlines the necessary steps to take in various emergency situations. It includes procedures for engine failure, electrical failure, and other critical scenarios. The aim is to equip pilots with the knowledge to handle emergencies effectively.

Normal Procedures

This section covers standard operating procedures for the aircraft, including preflight checks, takeoff, landing, and in-flight operations. It provides detailed instructions to ensure safe and efficient operation of the aircraft.

Performance

This section provides performance data for the Piper PA-32R-301, including takeoff and landing distances, climb rates, and fuel consumption. It is essential for flight planning and operational efficiency.

Weight and Balance

This section details the weight and balance requirements for the aircraft, including maximum weights, standard empty weight, and useful load calculations. Proper weight and balance management is crucial for safe flight operations.

Description and Operation of the Airplane and its Systems

This section describes the various systems of the Piper PA-32R-301, including the engine, fuel system, and electrical system. Understanding these systems is vital for effective operation and troubleshooting.

Airplane Handling, Servicing and Maintenance

This section provides guidelines for the proper handling, servicing, and maintenance of the aircraft. It includes routine maintenance checks and servicing requirements to ensure the aircraft remains in airworthy condition.

Supplements

This section includes additional information and updates relevant to the aircraft, such as modifications and equipment changes that may affect operation.

Operating Tips

This section offers practical tips for operating the Piper PA-32R-301 effectively, including advice on handling characteristics and performance optimization.

Safety notes

Ensure the handbook is current and applicable to the specific aircraft before use.
The pilot is responsible for determining the aircraft's airworthiness before flight.
Maneuvering speed decreases at lighter weights; exercise caution in rough air.

Full document text

. \ SARATOGA II HP AIRPLANE SERIAL NO. 3246223 PA-32R-301 SN 3246088 AND UP PILOT'S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL AIRPLANE REGIST. NO. N3101Q PA-32R-301 ~ c ~ ,- REPORT: VB-1669 FAA APPROVED BY: ~ C ·~ ~ DATE OF APPROVAL: JUNE 30, 1997 PETER E. PECK D.O.A. NO. S0-1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA FAA APPROVED IN NORMAL CATEGORY BASED ON CAR 3. THIS HANDBOOK INCLUDES THE 1\<IATERV\L REQUIRED TO BE FURNISI:illD TO THE PILOT BY CAR 3 AND CONSTITUTES THE APPROVED AIRPLANE FLIGHT MANUAL AND MUST BE CARRillD IN THE AIRPLANE AT ALL TIMES . • WARNING EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS HANDBOOK TO APPLICABLE AIRCRAFT. THIS HAND- BOOK IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED ON THE FACE OF THE TITLE PAGE. SUBSEQUENT REVISIONS SUPPLIED BY PIPER MUST BE PROPERLY INSERTED. REPORT: VB-1669 II Published by PUBLICATIONS DEPARTMENT Issued: June 30, 1997 © 1997 The New Piper Aircraft, Inc. All Rights ReseiTed. ISSUED: JUNE 30, 1997 ' APPLICABILITY Application of this handbook is limited to the specific Piper PA-32R-301 model airplane designated by serial number on the face of the title page of this handbook. This handbook cannot be used for operational purposes unless kept in a current status. WARNING INSPECTION, MAINTENANCE AND PARTS REQUIREMENTS FOR ALL NON-PIPER APPROVED STC INSTALLATIONS ARE NOT INCLUDED IN TillS HANDBOOK. WHEN A NON-PIPER APPROVED STC INSTALLATION IS INCORPORATED ON THE AIRPLANE, THOSE PORTIONS OF THE AIRPLANE AFFECTED BY THE INSTALLATION MUST BE INSPECTED IN ACCORDANCE WITH THE INSPECTION PROGRAM PUBLISHED BY THE OWNER OF THE STC. SINCE NON-PIPER APPROVED STC INSTALLATIONS MAY CHANGE SYSTEMS INTERFACE, OPERATING CHARACTERISTICS AND COMPONENT LOADS OR STRESSES ON ADJACENT STRUCTURES, PIPER PROVIDED INSPECTION CRITERIA MAY NOT BE VALID FOR AIRPLANES WITH NON-PIPER APPROVED STC INSTALLATIONS. REVISIONS The information compiled in the Pilot's Operating Handbook, with the exception of the equipment list, will be kept current by revisions distributed to the airplane owners. The equipment list was current at the time the air-plane was licensed by the manufacturer and thereafter must be maintained by the owner. Revision material will consist of information necessary to update the text of the present handbook and/or to add information to cover added airplane equipment. ISSUED: JUNE 30, 1997 REVISED: OCTOBER 15, 2003 REPORT: VB-1669 iii I. Revisions 'Revisions will be distributed whenever necessary as complete page replacements or additions and shall be inserted into the handbook in accordance with the instructions given below: 1. Revision pages will replace only pages with the same page number. 2. Insert all additional pages in proper numerical order within each section. 3. Page numbers followed by a small letter shall be inserted in direct sequence with the same common numbered page. II. Identification of Revised Material Revised text and illustrations shall be indicated by a black vertical line along the outside margin of the page, opposite revised, added or deleted material. A line along the outside margin of the page opposite the page number will indicate that an entire page was added. Black lines will indicate only current revisions with changes and additions to or deletions of existing text and illustrations. Changes in capitalization, spelling, punctuation or the physical location of material on a page will not be identified. ORIGINAL PAGES ISSUED The original pages issued for this handbook prior to revision are given below: Title, ii through vii, 1-1 through 1-12, 2-1 through 2-12, 3-1 through 3-18,4-1 through 4-28,5-1 through 5-32, 6-1 through 6-14, 7-1 through 7-46, 8-1 through 8-18, 9-1 through 9-38, 10-1 through 10-2. REPORT: VB-1669 iv ISSUED: JUNE 30, 1997 REVISED: OCTOBER 15, 2003 PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Current Revision to thePA-32R-301, Saratoga IT HP Pilot's Operating Handbook/REPORT: VB-1669 issued June 30, 1997. Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev.l (PR980810) v Added Rev. 1 to L of R page. 2-4 Revised Para. 2.9. 4-ii Revised T of C. 4-8 Revised Para. 4.5. Or f.c;::;k4-21 Revised Para. 4.17. 4-27 Added Para. 4.39. Peter E. Peck 4-28 Added Para. 4.39. 7-35 Revised Para. 7.17. Aug. 10, 1998 9-8 Revised Section 3. Date Rev. 2 v Added Rev. 2 to L of R page. q f.c;::;k (PR981218) 9-i Revised T of C. Peter E. Peck 9-39 Added page. 9-40 Added page. Dec. 18, 1998 Date Rev. 3 v Added Rev. 3 to L of R page. (PR990212) 7-i Revised T of C. 7-7 RevisedPara. 7.8. 7-9 Revised Fig. 1. 7-10 Revised Para. 7.8 and Fig. 2 & 3. 7-11 Revised Fig. 4. 7-12 Revised Fig. 5 & 6. 7-13 Revised Fig. 7 & 8. 7-14 Revised Fig. 9 & 10. 7-15 Added info. to Para. 7.8. q f.Ck7-16 Added info. to Para. 7.8. 7-17 Revised Para. 7.8 and Fig. 13 Peter E. Peck & 14. 7-18 Revised Para. 7. 8 and Fig. 15. Feb. 12, 1999 7-19 Revised Para. 7.8. Date ISSUED: JUNE 30, 1997 REVISED: FEBRUARY 12, 1999 REPORT: VB-1669 v PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revision , Number and Revised Code Pages Rev.4 VI (PR991122) 9-i 9-41 thru 9-48 Rev. 5 VI (PR000612) 2-9 3-5 3-6 3-15 4-4 4-5 4-14 4-15 5-9 5-14 7-36 8-10 9-i 9-47 9-49 tlrru 9-56 9-57 thru 9-64 9-65 thru 9-70 9-71 thru 9-74 REPORT: VB-1669 vi • FAA Approved Description of Revisions Signature and Date Added Rev. 4 to L of R page. ~~t!k Revised T of C. Added pages and Christina L. Mars Supplement 8. Nov. 22, 1999 Date Added Rev. 5 to L of R page. Revised Para. 2.25. Revised Para. 3.5. Revised Para. 3.5. Revised Para. 3.27. Revised Para. 4.5. Revised Para. 4.5. Revised Para. 4.7. Revised Para. 4. 7. Revised List of Figures. Revised Figure 5-7 title. Revised Figure 7-21. Revised Para. 8.15. Revised T of C. Revised Section 4. Added Supplement 9. Added Supplement 10. Added Supplement 11. ~~,~~ Christina L. Marsh

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Added Supplement 12. June 12,2000 Date ISSUED: JUNE 30, 1997 REVISED: JUNE 12, 2000 PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revisiqn Number and Revised Description of Revisions Code Pages Rev. 6 vi-a Added page (PR010109) and Rev. 6 to L of R. vi-b Added page. 3-7 Revised para. 3.5. 3-16 Revised para. 3.31. 9-i Revised T of C. 9-75 Added pages thru and Supplement 13. 9-84 9-85 Added pages thru and Supplement 14. 9-86 9-87 Added pages thru and Supplement 15. 9-92 9-93 Added pages thru and Supplement 16. 9-98 9-99 Added pages thru and Supplement 17. 9-102 Rev. 7 VI-a Added Rev. 7 to L of R. (PR010705) 2-3 Revised Para. 2.7. 2-4 Revised Para. 2.9. 2-11 Revised Para. 2.25. Rev. 8 vi-a Added Rev. 8 to L of R. (PR020311) 2-9 Revised para. 2.25. 4-2 Revised para. 4.3. ISSUED: JUNE 30, 1997 REVISED: MARCH 11, 2002 FAA Approved Signature and Date cL.dn4'frfW4 Christina L. Marsh Jan. 9, 2001 Date q f.Ck Peter E. Peck July 5, 2001 Date ~Albert J. Mill March 11, 2002 Liate REPORT: VB-1669 vi-a PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revision •Number and Revised Code Pages Rev. 9 ... 111 (PR031015) IV vi-b 5-29 8-1 8-1a 8-1b 8-2 9-72 Rev. 10 vi-b (PR031210) 9-i 9-56 9-63 9-72 9-73 9-103 thru 9-106 Rev. 11 vi-b (PR040305) 9-i 9-107 thru 9-124 9-125 thru 9-128 REPORT: VB-1669 vi-b FAA Approved Description of Revisions Signature and Date Added Warning. Moved info. from page iii. Added Rev. 9 to L of R. Revised Figure 5-37. Moved info. to page 8-1 b and revised para. 8.1. Added page and revised para. 8.1. G)~Added page and moved info. from pages 8-1 and 8-2. Moved info. to page 8-1b and Albert J. Mill revised para. 8.3. Revised Section 1. Oct. 15, 2003 Date Added Rev. 10 to L of R. Revised T of C. Revised Section 4. Revised Section 4. Moved info. to page 9-73 and ~~ revised Section 1. Moved info. from page 9-72. Added pages Albert J. Mill and Supplement 18. Dec. 10, 2003 Date Added Rev. 11 to L of R. Revised T of C. CA~ Added pages and Supplement 19. AlbertJ.Mill Added pages and Supplement 20. March 5, 2004 Date ISSUED: JUNE 30, 1997 REVISED: MARCH 5, 2004 PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revision Numbe1'and Revised Code Pages Rev. 12 VI-C (PR040419) vi-d 8-11 9-108 Rev. 13 Vl-C (PR040812) 4-4 4-5 4-14 4-15 7-32 9-108 Rev. 14 Vl-C (PR050523) 9-i 9-107 thru 9-134 9-135 thru 9-138 Rev. 15 VI-C (PR050607) 9-i 9-139 thru 9-166 ISSUED: JUNE 30, 1997 REVISED: JUNE 7, 2005 Description of Revisions Added page and Rev. 12 to L of R. Added page. Revised para. 8.19. Revised Section 1. Added Rev. 13 to L of R. Revised para. 4.5. Revised para. 4.5. Revised para. 4.7. Revised para. 4.7. Revised para. 7.15. Revised Section 1. Added Rev. 14 to L of R. Revised T of C. Revised Supplement 19. Revised page numbers. Added Rev. 15 to L ofR. Revised T of C. Added pages and Supplement 21. FAA Approved Signature and Date O;pJJ Albert J. Mill April 19, 2004 Date -~- Linda J. Dicken August 12, 2004 ~- ~ Linda J. Dicken May 23,2005 -~- Linda J. Dicken ~ June 7, 2005 REPORT: VB-1669 vi-c PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revision , Number and Revised Code Pages Rev. 16 vi-d (PR050711) 7-41 9-ii 9-167 thru 9-176 Rev. 17 vi-d (PR050829) 9-110 9-111 Rev. 18 vi-d (PR051017) 9-ii 9-119 9-177 thru 9-210 Rev. 19 vi-d (PR051121) 9-112 9-115 Rev. 20 vi-d (PR051212) 9-i 9-107 thru 9-134 9-181 thru 9-183 REPORT: VB-1669 vi-d FAA Approved Description of Revisions Signature and Date Added Rev. 16 to L of R. Revised para. 7.23. Revised T of C. ~_,&- Added pages and Supplement 22. Linda J. Dicken July 11, 2005 Added Rev. 17 to L of R. -~- Moved info. from page 9-111. - Revised Section 2. Linda J. Dicken August 29, 2005 Added Rev. 18 to L of R. Revised T of C. Revised Section 3. -~- Added pages - and Supplement 23. Linda J. Dicken October 17, 2005 Added Rev. 19 to L ofR. .~· Revised Section 3. Linda J. Dicken Revised Section 3. · Nov. 21,2005 Added Rev. 20 to L of R. Revised T of C. Revised Supplement 19. Revised Section 2. ~__,&· - Linda J. Dicken Dec. 12, 2005 ISSUED: JUNE 30, 1997 REVISED: DECEMBER 12,2005 PILOT'S OPERATING HANDBOOK LOG OF REVISIONS• Revisidn Number and Revised Description of Revisions Code Pages Rev. 21 VI-e Added page and Rev. 21 (PR060116) to L ofR. vi-f Added page. 9-139 Revised Supplement title. 9-140 Revised Section 1. 9-146 Revised Section 3. 9-147 Revised Section 3. 9-148 Revised Section 5. 9-149 Revised Table 1. 9-150 Revised Section 7. 9-152 Revised Section 7. 9-153 Revised Section 7. 9-154 Revised Figure 7-5. 9-160 Revised Section 8. ISSUED: JUNE 30,1997 REVISED: JANUARY 16, 2006 FAA Approved Signature and Date .~· - Linda J. Dicken Jan. 16, 2006 REPORT: VB-16~9~ VI-e PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Revision •Number and Revised Code Pages - REPORT: VB-1669 vi-f FAA Approved Description of Revisions Signature and Date ISSUED: JUNE 30, 1997 REVISED: JANUARY 16, 2006 ' 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: JUNE 30, 1997 REPORT: VB-1669 vii , TillS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1669 · ISSUED: JUNE 30, 1997 viii • { . ·' r en .,m mO Z-t m- j!O rz • TABLE OF CONTENTS SECTION 1 GENERAL Paragraph Page No. No. 1.1 Introduction................................................................................... 1-1 1.3 Engine........................................................................................... 1-3 1.5 Propeller........................................................................................ 1-3 1.7 Fuel ............................................................................................. 1-4 1.9 Oil ............................................................................................. 1-4 1.11 Maximum Weights........................................................................ 1-5 1.13 Standard Airplane Weights ........................................................... 1-5 1.15 Baggage Space.............................................................................. 1-5 1.17 Specific Loading ........................................................................... 1-5 1.19 Symbols, Abbreviations and Terminology.................................... 1-6 . ISSUED: JUNE 30,1997 REPORT: VB-1669 1-i PA-32R-301, SARATOGA II HP • THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1669 ISSUED: JUNE 30,1997 PA-32R-301, SARATOGA II HP ' SECTION1 GENERAL 1.1 INTRODUCTION SECTION 1 GENERAL This Pilot's Operating Handbook is designed for maximum utilization as an operating guide for the pilot. It includes the material required to be furnished to the pilot by FAR/CAR. It also contains supplemental data supplied by the airplane manufacturer. This handbook is not designed as a substitute for adequate and competent flight instruction, knowledge of current airworthiness directives, applicable federal air regulations or advisory circulars. It is not intended to be a guide for basic flight instruction or a training manual and should not be used for operational purposes unless kept in a current status. Assurance that the airplane is in an airworthy condition is the responsibility of the owner. The pilot in command is responsible for determining that the airplane is safe for flight. The pilot is also responsible for remaining within the operating limitations as outlined by instrument markings, placards, and this handbook. Although the arrangement of this handbook is intended to increase its in-flight capabilities, it should not be used solely as an occasional operating reference. The pilot should study the entire handbook to familiarize himself with the limitations, performance, procedures and operational handling characteristics of the airplane before flight. The handbook has been divided into numbered (arabic) sections each provided with a "finger-tip" tab divider for quick reference. The limitations and emergency procedures have been placed ahead of the normal procedures, performance and other sections to provide easier access to information that may be required in flight. The "Emergency Procedures" Section has been furnished with a red tab divider to present an instant reference to the section. Provisions for expansion of the handbook have been made by the deliberate omission of certain paragraph numbers, figure numbers, item numbers and pages noted as being intentionally left blank. ISSUED: JUNE 30, 1997 REPORT: VB-1669 1-1 SECTION! GENERAL , 1 2' 1 1 ~ "--- PA-32R-301, SARATOGA II HP Wing Area (sq. ft.) Min. Turning Radius (ft.) (from pivot point to wing tip) I 78.3 0.0 3 [6'6"T7'1"- ' _t _] - __f 1..--- - --- I· I I REPORT: VB-1669 1-2 [ I ·l I....... II .,.,.,. I'- II / \ t} \} 1----11'1" --I THREE VIEW Figure 1-1 --.- II ·I ~ ISSUED: JUNE 30, 1997 PA-32R-301, SARATOGA II HP 1.3 ENGINE 1.5 • (a) Number of Engines (b) Engine Manufacturer (c) Engine Model Number (d) Rated Horsepower (e) Rated Speed (rpm) (f) Bore (inches) (g) Stroke (inches) (h) Displacement (cubic inches) (i) Compression Ratio G) Engine Type PROPELLER (a) Number of Propellers (b) Propeller Manufacturer (c) Blade Model (d) Number of Blades (e) Hub Model (f) Propeller Diameter (inches) (1) Minimum (2)Maximum (g) Propeller Type ISSUED: JUNE 30,1997 SECTION 1 GENERAL 1 Lycoming I0-540-K1 05 300 2700 5.125 4.375 541.5 8.7:1 Six Cylinder, Direct Drive, Horizontally Opposed, Air Cooled, Fuel Injected 1 Hartzell F7663DR 3 HC-13YR-1RF 77 78 Constant Speed, Hydraulically Actuated REPORT: VB-1669 1-3 SECTION 1 GENERAL • 1.7 FUEL AVGASONLY (a) Fuel Capacity (U.S. gal.) (total) (b) Usable Fuel (U.S. gal.) (total) (c) Fuel Grade, Aviation (1) Minimum Grade (2) Alternate Fuels 1.9 OIL (a) Oil Capacity (U.S. quarts) (b) Oil Specification PA-32R-301, SARATOGA II HP 107 102 100- Green or IOOLL- Blue Aviation Grade Refer to latest revision of Lycoming Service Instruction 1070 12 ·Refer to latest issue of Lycoming Service Instruction 1014. (c) Oil Viscosity per Average Ambient Temp. for Starting (I) Above 80°F (2) Above 60°F (3) 30°F to 90°F (4) 0° to 70°F (5) 0°F to 70°F (6) O~F to 90°F REPORT: VB-1669 1-4 SINGLE 60 50 40 30 20 20 MULTI 60 40 or 50 40 30, 40 or 20W-30 20W50 or 15W-50 30 or 20W-30 ISSUED: JUNE 30, 1997 PA-32R-301, SARATOGA II HP • 1.11 MAXIMUM WEIGHTS (a) Maximum Takeoff Weight (lbs.) (b) Maximum Landing Weight (lbs.) (c) Maximum Ramp Weight (lbs.) Compartments 1.13 STANDARD AIRPLANE WEIGHTS FORWARD 100 SECTION! GENERAL 3600 3600 3615 AFf 100 Refer to Figure 6-5 for the Standard Empty Weight and the Useful Load. 1.15 BAGGAGE SPACE (a) Compartment Volume (cubic feet) (b) Entry Width (inches) (c) Entry Height (inches) 1.17 SPECIFIC LOADING (a) Wing Loading (lbs. per sq. ft.) (b) Power Loading (lbs. per hp) . ISSUED: JUNE 30, 1997 FORWARD 7.0 16.0 22.0 AFf 17.3 48.0 26.0 20.2 12.0 REPORT: VB-1669 1-5 SECTION 1 GENERAL PA-32R-301, SARATOGA II HP 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 Terminology and Symbols CAS KCAS GS lAS KIAS M TAS REPORT: VB-1669 1-6 Calibrated Airspeed means the indicated speed of an aircraft, corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. Calibrated Airspeed expressed in "Knots." Ground Speed is the speed of an airplane relative to the ground. Indicated Airpseed 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." Mach number is the ratio of true airspeed to the speed of sound. · True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude, temperature and compressibility. Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstress the airplane. Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. ISSUED: JUNE 30, 1997 PA-32R-301, SARATOGA II HP SECTION 1 GENERAL • VNiMNE v X ISSUED: JUNE 30, 1997 Maximum Landing Gear Extended Speed is the maximum speed at which an aircraft can be safely flown with the landing gear extended. Maximum Landing Gear Operating Speed is the maximum speed at which the landing gear can be safely extended .or retracted. Never Exceed Speed or Mach Number is the speed limit that may not be exceeded at any time. Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution. Stalling Speed or the minimum steady fi ight 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. 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. REPORT: VB-1669 1-7 SECTION 1 GENERAL PA-32R-301, SARATOGA II HP (b) Meteorological Terminology • ISA OAT Indicated Pressure Altitude Pressure Altitude Station Pressure Wind REPORT: VB-1669 1-8 International Standard Atmosphere in which: The air is a dry perfect gas; the temperature at sea level is 15° Celsius (59° Fahrenheit); The pressure at sea level is 29.92 inches Hg (1013.2 mb); the temperature gradient from sea level to the altitude at which the temperature is -56.5° C (-69.7°F) is -0.00198°C (-0.003564°F) per foot and zero above that altitude. Outside Air Temperature is' the free air static temperature, obtained either from inflight temperature indications or ground meteorological sources, adjusted for instrument error and compressibility effects. The number actually read from an altimeter when the barometric subscale has been set to 29.92 inches of mercury (1013.2 millibars). Altitude measured from standard sea-level pressure (29.92 in Hg) by a pressure or barometric altimeter. It is the indicated pressure altitude corrected for position and instrument error. In this handbook, altimeter instrument errors are assumed to be zero. Actual atmospheric pressure at field elevation. The wind velocitieG rec'Jrded as variables on the charts of this handbook are to be understood as the headwind or tail wind components of the re~orted winds. ISSUED: JUNE 30, 1997 PA-32R-301, SARATOGA II HP SECTION 1 GENERAL (c) Power Terminology • Takeoff Power Maximum Con- tinuous Power Maximum Climb Power Maximum Cruise Power (d) Engine Instruments EGTGauge Maximum power permissible for takeoff. Maximum power permissible contin- uously during flight. Maximum power permissible during climb. Maximum power permissible during crmse. Exhaust Gas Temperature Gauge (e) Airplane Performance and Flight Planning Terminology Climb Gradient Demonstrated Crosswind Velocity Accelerate-Stop Distance Route Segment ISSUED: JUNE 30,1997 The demonstrated ratio of the change in height during a portion of a climb, to the horizontal distance traversed in the same time interval. The demonstrated crosswind velocity is the velocity of the crosswind 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, assuming 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. REPORT: VB-1669 1-9 SECTION 1 GENERAL PA-32R-301, SARATOGA II HP (f) Weight a,nd Balance Tenninology Reference Datum Station Arm Moment Center of Gravity (C.G.) C.G.Arm C.G. Limits Usable Fuel Unusable Fuel Standard Empty Weight REPORT: VB-1669 An imaginary vertical plane from which all horizontal distances are measured for balance purposes. A location along the airplane fuselage usually given in terms of distance 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 multiplied by its arm. (Moment divided by a constant is used to simplify balance calculations 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. The arm obtained by adding the airplane's individual moments and dividing the sum by the total weight. 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 with govern- mental regulations. Weight of a standard airplane including unusable fuel, full operating fluids and full oil. ISSUED: JUNE 30, 1997 PA-32R-301, SARATOGA II HP SECTION 1 GENERAL Basic Empty Weight Payload Useful Load Maximum Ramp Weight Maximum Takeoff Weight Maximum Landing Weight Maximum Zero Fuel Weight . ISSUED: JUNE 30, 1997 Standard empty weight plus optional equipment. Weight of occupants, cargo and baggage. Differe.nce 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. REPORT: VB-1669 1-11 SECTION 1 GENERAL I PA-32R-301, SARATOGA ll HP THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1669 1-12 ISSUED: JUNE 30,1997 • ( rn em lOo -i-1 ~- oO zzrnl\) , Paragraph No. TABLE OF CONTENTS SECTION2 LIMITATIONS Page No. 2.1 General.......................................................................................... 2-1 2.3 Airspeed Limitations·····································:............................... 2-1 2.5 Airspeed Indicator Markings ........................................................ 2-2 2.7 Power Plant Limitations................................................................ 2-3 2.9 Power Plant Instrument Markings................................................. 2-4 2.11 Weight Limits................................................................................ 2-4 2.13 Center of Gravity Limits ............................................................... 2-5 2.15 Maneuver Limits........................................................................... 2-5 2.17 Flight Load Factors....................................................................... 2-5 2.19 Types of Operation........................................................................ 2-6 2.21 Fuel Limitations . ....... ....... ......... ...... .. . ... ... .. . .............. ... .. .. . .. . .. .. ... .. 2-6 2.25 Placards......................................................................................... 2-8 ISSUED: JUNE 30, 1997 REPORT: VB-1669 2-i PA-32R-301, SARATOGA II HP , THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1669 2-ii ISSUED: JUNE 30,1997 PA-32R-301, SARATOGA II HP • SECTION2 LIMITATIONS 2.1 GENERAL SECTION2 LIMITATIONS This section provides the "FAA Approved" operating limitations, instrument markings, color coding and basic placards necessary for operation of the airplane and its systems. Limitations associated with those optional systems and equipment which require handbook supplements can be found in Section 9 (Supplements). 2.3 AIRSPEED LIMITATIONS SPEED Never Exceed Speed (VNE) - Do not ex- ceed this speed in any operation. Maximum Structural Cruising Speed (VNO) - Do not exceed this speed except in smooth air and then only .with caution. Design Maneuvering Speed (VA)- Do not make full or abrupt control move- ments above this speed. At 3600 LBS. G.W. At 2230 LBS. G.W. ISSUED: JUNE 30, 1997 KIAS 191 160 134 105 KCAS 189 158 132 104 REPORT: VB-1669 2-1 SECTION2 LIMITATIONS PA-32R-301, SARATOGA II HP CAUTION, Maneuvering speed decreases at lighter weight as the effects of aerodynamic forces become more pronounced. Linear interpolation may be used for intermediate gross weights. Maneuvering speed should not be exceeded while operating in rough air.. SPEED Maximum Flaps Extended Speed (VFE) - Do not exceed this speed with the flaps extended. Maximum Landing Gear Extension Speed (VLO) - Do not exceed this speed when extending the landing gear. Maximum Landing Gear Retraction Speed (VLO) - Do not exceed this speed when retracting the landing gear. Maximum Landing Gear Extended Speed (VLE) Do not exceed this speed with the landing gear extended. 2.5 AIRSPEED INDICATOR MARKINGS MARKING KIAS 110 132 110 132 KCAS 109 130 109 130 lAS Red Radial Line (Never Exceed) Yellow Arc 191 KTS 160 KTS to 191 KTS (Caution Range- Smooth Air Only) Green Arc (Normal Operating Range) White Arc (Flap Down) REPORT: VB-1669 2-2 67 KTS to 160 KTS 63 KTS to 110 KTS ISSUED: JUNE 30, 1997 PA-32R-301, SARATOGA ll HP 2.7 POWER PLANT LIMITATIONS • (a) Number of Engines (b) Engine Manufacturer (c) Engine Model No. (d) Engine Operating Limits (1) Maximum Horse Power (2) Maximum Rotation Speed (RPM) (3) Maximum Oil Temperature (°F) (e) Oil Pressure Minimum (red line) Maximum (red line) (f) Fuel Grade (minimum grade) (g) Number of Propellers (h) Propeller Manufacturer (i) Propeller Hub and Blade Model (j) Propeller Diameter (inches) Minimum Maximum (k) Blade Angle Limits Low Pitch Stop High Pitch Stop ISSUED: JUNE 30, 1997 REVISED: JULY 5, 2001 SECTION2 LIMITATIONS 1 Lycoming I0-540-K1G5 300 2700 245 25 PSI 115 PSI 100 - Green or IOOLL- Blue Aviation Grade 1 Hartzell HC-13YR-1 RF F7663DR 77 78 12.4° ± 0.2° 32.0° ± 1.0° REPORT: VB-1669 2-3 SECTION2 LIMITATIONS PA-32R-301, SARATOGA II liP 2.9 POWER PLANT INSTRUMENT MARKINGS • (a) Tachometer Green Arc (Normal Operating Range) Red Line (Maximum) (b) Oil Temperature Green Arc (Normal Operating Range) Red Line (Maximum) (c) Oil Pressure Green Arc (Normal Operating Range) Yellow Arc (Caution Range) (Idle) Yellow Arc (Caution Range) (Start and Warm Up) Red Line (Minimum) Red Line (Maximum) 600 to 2700 RPM 2700RPM 100° to 245°F 245F 55 PSI to 95 PSI 25 PSI to 55 PSI 95 PSI to 115 PSI 25 PSI 115 PSI (d) Cylinder Head Temperature (Not required equipment) Green Arc (Normal Operationg Range) 200° to 500°F 500°F Red Radial Line (Maximum) (e) Fuel Flow/Pressure Normal Operating Range (f) Vacuum Pressure Green arc (normal operating rartge) Red Line (minimum) Red Line (maximum) -or- Green arc (normal operating range) Red Line (minimum) Red Line (maximum) 2.11 WEIGHT LIMITS (a) Maximum Takeoff Weight (b) Maximum Ramp Weight 0 gal/hr. to 34.9 gal/hr. 4.8 to 5.2 in. Hg. 4.8 in. Hg. 5.2 in. Hg. 4.5 to 5.2 in. Hg. 4.5 in. Hg. 5.2 in. Hg. (c) Maximum Baggage (100 lbs. each compartment) 3600LBS. 3615 LBS. 200LBS. NOTE Refer to Section 5 (Performance) for maximum weight as limited by performance. REPORT: VB-1669 2-4 ISSUED: JUNE 30, 1997 REVISED: JULY 5, 2001 PA-32R-301, SARATOGA II HP 2.13 CENTER OF GRAVITY LIMITS Weight Pounds 3600 3200 ' 2400 (and less) Forward Limit Inches Aft of Datum 91.4 83.5 78.0 NOTES SECTION2 LIMITATIONS Rearward Limit Inches Aft of Datum 95.0 95.0 95.0 Straight line variation between points given. The datum used is 78.4 inches ahead of the wing leading edge at the intersection of the untapered and inboard tapered section. It is the responsibility of the airplane owner and the pilot to insure that the airplane is properly loaded. See Section 6 (Weight and Balance) for proper loading instructions. 2.15 MANEUVER LIMITS No acrobatic maneuvers including spins approved. 2.17 FLIGHT LOAD FACTORS 3.8 G (a) Positive Load Factor (Maximum) (b) Negative Load Factor (Maximum) No inverted maneuvers approved (c) Positive Load Factor- Flaps Down (Maximum) 2.0 G (d) Negative Load Factor- Flaps Down (Maximum) No inverted ISSUED: JUNE 30, 1997 maneuvers approved REPORT: VB-1669 2.-5 SECTION2 LIMITATIONS 2.19 TYPES OF OPERATIONS • PA-32R-301, SARATOGA TI HP The airplane is approved for the following operations when equipped in accordance with FAR 91 or FAR 135. (a)Day VF.R. (b)Night VF.R. (c)Day I.F.R. (d)Night I. P.R. (e)Non Icing 2.21 FUEL LIMITATIONS (a) Total Capacity ................................................................. 107 U.S. GAL. (b) Unusable Fuel ..................................................................... 5 U.S. GAL. The unusable fuel for this airplane has been determined as 2.5 gallons in each wing in critical flight attitudes (2.5 gallons is the total per side, each side having two interconnected tanks). (c) Usable Fuel ........................... :......................................... 102 U.S. GAL. The usable fuel in this airplane has been determined as 51 gallons in each wing (51 gallons is the total per side, each side having two interconnected tanks). REPORT: VB-1669 ISSUED: JUNE 30,1997 PA-32R-301, SARATOGA II HP , SECTION2 LIMITATIONS INTENTIONALLY LEFT BLANK ISSUED: JUNE 30, 1997 REPORT: VB-1669 2-7 SECTION2 LIMITATIONS 2.25 PLACARDS, In full view of the pilot: PA-32R-301, SARATOGA II HP THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE Wl'lli THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUAlS. NO ACROBATIC MANEUVERS INCLUDING SPINS, APPROVED. THIS AIRCRAFT APPROVED FOR V.F.R., I.F.R., DAY AND NIGHT NON-ICING FLIGHT WHEN EQUIPPED IN ACCORDANCE WITH FAR 91 OR FAR 135. WARNING TURN OFF STROBE LIGHTS WHEN IN CLOSE PROXIMITY TO GROUND, OR DURING FLIGHT THROUGH CWUD,FOG OR HAZE. In full view of the pilot: WARNING TURN OFF STROBE LIGHTS WHEN IN CLOSE PROXIMITY TO GROUND OR DURING FLIGHT THROUGH CLOUD, FOG OR HAZE. In full view of the pilot and passengers: NO SMOKING Adjacent to front door latch: CAUTION DO NOT ATTEMPT TO CLOSE DOOR WITH HANDLE IN LATCHED POSITION. REPORT: VB-1669 2-8 ISSUED: JUNE 30, 1997 PA-32R-301, SARATOGA II HP On the instrument panel in full view of the pilot: • VA 134 AT 3600 LBS (SEE A.F.M.) On the instrument panel in full view of the pilot: DEMO X-WIND 17 KTS In full view of the pilot: Vw 132 DN. 110 UP VLE132MAX Near gear selector switch: GEAR UP DOWN Adjacent to upper door latch (rear door): 110KIASMAX 132KIASMAX ENGAGE LATCH BEFORE FLIGHT In full view of the pilot: SECTION2 LIMITATIONS DO NOT EXCEED 23 INCHES OF MANIFOLD PRESSURE BELOW 2100 RPM. If required, on the aft close out panel: REAR PASSENGER/BAGGAGE AREAS MAXIMUM ALLOWABLE WEIGHT MAXIMUM ALLOWABLE COMBINED WEIGHT IN AFT SEATS IS POUNDS LOAD IN ACCORDANCE WITH WEIGHT BALANCE DATA ISSUED: JUNE 30,1997 REVISED: MARCH 11, 2002 REPORT: VB-1669 2-9 SECTION2 LIMITATIONS , PA-32R-301, SARATOGA II HP In full view of the pilot, in the area of the air conditioner controls when the air conditioner is installed: WARNING AIR CONDITIONER MUST BE OFF TO INSURE NORMAL TAKEOFF CLIMB PERFORMANCE. On the inside of the forward baggage compartment: MAXIMUM BAGGAGE THIS COMPART- MENT 100 LBS. SEE THE LIMITATIONS SECTION OF THE AIRPLANE FLIGHT MANUAL. On aft baggage closeout: MAXIMUM BAGGAGE THIS COMPART- MENT 100 LBS. NO HEAVY OBJECTS ON HAT SHELF. On storm window: DO NOT OPEN ABOVE 129 KIAS. On executive writing table: CAUTION - THIS TABLE MUST BE STOWED DURING TAKEOFF AND LANDING. REPORT: VB-1669 2-10 ISSUED: JUNE 30, 1997 PA-32R-301, SARATOGA IT HP Adjacent to fuel tank filler caps: SECTION2 LIMITATIONS AVGAS ONLY ,,GRADE 100LL In full view of the pilot: GRADE 100 ARMRESTS ARE TO BE IN THE STOWED POSITION FOR TAKEOFF AND LANDING ISSUED: JUNE 30, 1997 REVISED: JULY 5, 2001 REPORT: VB-1669 2-11 SECTION2 LIMITATIONS • PA-32R-301, SARATOGA ll liP On right hand side of of console top: REPORT: VB-1669 2-12 MONITOR, ALL LOOSE ITEMS, AND CONSOLE TOP ARE TO BE IN THE STOWED POSITION FOR TAKEOFF AND LANDING MAXIMUM, WEIGIIT ALLOWABLE ON THE CONSOLE TOP IN THE EXTENDED POSITION IS 10 LBS ISSUED: JUNE 30, 1997 ' Paragraph No. TABLE OF CONTENTS SECTION3 EMERGENCY PROCEDURES Page No. 3.1 General.......................................................................................... 3-1 3.3 Airspeeds for Safe Operation........................................................ 3-2 3.5 Emergency Procedures Checklist.................................................. 3-2 Engine Fire During Start.......................................................... 3-2 Engine Power Loss During Takeoff......................................... 3-2 Engine Power Loss In Flight.................................................... 3-3 Power Off Landing................................................................... 3-3 Fire In Flight............................................................................. 3-4 Loss of Oil Pressure ................................................................ · 3-4 Loss of Fuel Flow..................................................................... 3-4 Engine-Driven fuel pump Failure ............................................ 3-4 High Oil Temperature............................................................... 3-5 Electrical Failures..................................................................... 3-5 Electrical Overload................................................................... 3-5 Propeller Overspeed .................... .... .. .... .. .... .. ..... .. ....... ............. 3-6 Emergency Landing Gear Extension........................................ 3-7 Spin Recovery ........................ :................................................. 3-7 Open Door ..................................................... ;.......................... 3-8 3. 7 Amplified Emergency Procedures (General)................................ 3-9 3.9 Engine Fire During Start............................................................... 3-9 3.11 Engine Power Loss During Takeoff.............................................. 3-9 3.13 Engine Power Loss In Flight......................................................... 3-10 3.15 Power Off Landing........................................................................ 3-11 3.17 Fire In Flight................................................................................. 3-12 ISSUED: JUNE 30, 1997 REPORT: VB-1669 3-i Paragraph No. • TABLE OF CONTENTS (cont) SECTION 3 (cont) 3.19 Loss of Oil Pressure .................................................................... . 3.21 Loss of Fuel Flow ........................................................................ . Page No. 3-13 3-13 3.23 Engine-Driven fuel pump Failure ................................ .-................ 3-14 3.25 High Oil Temperature ................................................................... 3-14 3.26 Electrical Failures ......................................................................... · 3-14 3.27 Electrical Overload ....................................................................... 3-15 3.29 Propeller Overspeed ...................................................................... 3-16 3.31 Emergency Landing Gear Extension ............................................ 3-16 3.33 Spin Recovery............................................................................... 3-16 3.35 Open Door..................................................................................... 3-17 I 3.37 Engine Roughness......................................................................... 3-17 REPORT: VB-1600 3-ii ISSUED: JUNE 30, 1997 PA-32R-301, SARATOGA II HP SECTION3 EMERGENCY PROCEDURES • 3.1 GENERAL SECTION3 EMERGENCY PROCEDURES The recommended procedures for coping with various types of emergencies and critical situations are provided by this section. All of the required (FAA regulations) emergency procedures and those necessary for operation of the airplane as determined by the operating and design features of the airplane are presented. Emergency procedures associated with those optional systems and equipment which require handbook supplements are provided in Section 9 (Supplements). The first portion of this section consists of an abbreviated emergency checklist which supplies an action sequence for critical situations with little emphasis on the operation of systems. ' The remainder of the section is devoted to amplified emergency procedures containing additional information to provide the pilot with a more complete understanding of the procedures. These procedures are suggested as a course of action for coping with the particular condition described, but are not a substitute for sound judgment and common sense. Pilots should familiarize themselves with the procedures given in this section and be prepared to take appropriate action should an emergency arise.. Most basic emergency procedures, such as a power off landings, are a normal part of pilot training. Although these emergencies are discussed here, this information is not intended to replace such training, but only to provide a source of reference and review, and to provide information on procedures which are not the same for all aircraft. It is suggested that the pilot review standard emergency procedures periodically to remain proficient in them. ' ISSUED: JUNE 30, 1997 REPORT: VB-1669 3-1 SECTION3 EMERGENCY PROCEDURES PA-32R-301, SARATOGA II HP 3.3 AIRSPEEDS FOR SAFE OPERATION, Staii3~ofbs (Gear Up, oo Flap) ............................................................ 67 KIAS 3600 lbs (Gear Down, 40° Flap) ..................................................... 63 KIAS Maneuvering Speeds 3600 lbs ..............................................•........................................... l34 KIAS 2230 lbs .......................................................................................... 105 KIAS Never Exceed Speed ............................................................................. 191 KIAS Power Off Glide Speed 3600 lbs (Gear Up, 0° Flap) ............................................................ 83 KIAS - 3.5 EMERGENCY PROCEDURES CHECKLIST ENGINE FIRE DURING START Start.. .................................................................................................crank engine Mixture ............................................................................................... .idle cut-off Throttle ................................................................................:......................... open Electric fuel pump .......................................................................................... OFF Fuel selector ................................................................................................... OFF Abandon if fire continues ENGINE POWER LOSS DURING TAKEOFF If sufficient .runway remains for a normal landing, leave gear down and land straight ahead. gea;~e~~:ir i:~~~~~·--~-~-~~~-~-~~.~~~~.~~~.~~.~.~~.~.~~~~·~·~·~·~-~: .....................UP If sufficient altitude has been gained to attempt a restart: Maintain safe airspeed Fuel selector .................................................................................... switch to tank containing fuel Electric fuel pump .................................................................................. check ON Mixture ..............................................................................................check RICH Alternate air ................................................................................................ OPEN If power is not regained, proceed with power offlanding. ENGINE POWER LOSS IN FLIGHT If at low altitude: Airspeed .............................................................•...............MAINTAIN 83 KIAS Prepare for power off landing. REPORT: VB-1669 3-2 Minimum ISSUED: JUNE 30, 1997 PA-32R-301, SARATOGA II HP SECTION3 EMERGENCY PROCEDURES ENGINE POWER LOSS IN FLIGHT (continued) If altitud~ permits: Fuel selector .................................................................................... switch to tank containing fuel Electric fuel pump ......................................................................................: .... ON Mixture ........................................................................................................ RICH Alternate air ................................................................................................ OPEN Engine gauges ....................................................................... check for indication of cause of power loss If no fuel flow is indicated, check tank selector position to be sure it is on a tank containing fuel. When power is restored: Alternate air ...........................................................................................CLOSED Electric fuel pump .......................................................................................... OFF Mixture ................................................................................... adjust as necessary If power is not restored prepare for power off landing. POWER OFF LANDING Trim for 83 KIAS Locate suitable field. Establish spiral pattern. 1000 ft. above field at downwind position for normal landing approach. When field can easily be reached extend full flaps for shortest landing. Touchdowns should normally be made at lowest possible airspeed with full flaps. · When committed to landing: Landing gear selector ................................................................................DOWN Flaps ................................................... :.................................................As desired Throttle ......................................................................................................... Close Mixture ............................................................................................... .idle cut-off Magnetos ........................................................................................................ OFF Battery Master switch .................................................................................... OFF ALTR Switch ................................................................................................. OFF Fuel selector ................................................................................................... OFF Seat belt and harness ......................................................................................tight NOTE: If battery master switch is OFF, the landing gear can not be retracted and the gear position lights and flaps will be inoperative ISSUED: JUNE 30, 1997 REPORT: VB-1669 3-3 SECTION3 EMERGENCY PROCEDURES PA-32R-301, SARATOGA II HP FIRE IN FLIGHT • Source of fire ............................................................................................... check Electrical fire (smoke in cabin): Batt. Master switch ........................................................................................ OFF ALTR switch .... .' ............................................................................................. OFF Vents ..............................................................................................................open Cabin heat ...................................................................................................... OFF Land as soon as practicable. Engine fire: Fuel selector ................................................................................................... OFF Throttle .......................................................................................... ,....... CLOSED Mixture ............................................................................................... .idle cut-off Electric fuel pump ............................................................................... check OFF Heater and defroster ....................................................................................... OFF Proceed with power off landing procedure NOTE: The possibility of an engine fire in flight is extremely remote. The procedure given is general and Pilot judgment should be the determining factor for action in such an emergency. LOSS OF OIL PRESSURE Land as soon as possible and investigate cause. Prepare for power off landing. . LOSS OF FUEL FLOW Electric fuel pump ........................................................................................... ON Fuel selector ....... .'............................................................................ check on tank containing usable fuel ENGINE DRIVEN FUEL PUMP FAILURE. Throttle ........................................................................................................ retard Electric fuel pump ........................................................................................... ON Throttle ............................ ;........................................................... reset as required CAUTION: If normal engine operation and fuel flow is not immediately re-established, the electric fuel pump should be turned OFF. The lack of a fuel flow indication while the electric fuel pump is on could indicate a leak in the fuel system or fuel exhaustion. If fuel system leak is verified, switch fuel selector to off. REPORT: VB-1669 3-4 ISSUED: JUNE 30, 1997 PA·32R·301, SARATOGA II HP SECTION3 EMERGENCY PROCEDURES IITGH OIL TEMPERATURE 'Land at nearest airport and investigate the problem. Prepare for power off landing. ELECTRICAL FAILURES Alternator Inop annunciator light illuminated Alternator ammeter ............................................................. Verify approximately Zero output Battery ammeter .............................................................Verify battery supplying aircraft power (neg. reading) If indications verify loss of alternator output ALT switch ..................................................................................................... OFF Reduce electrical loads to minimum ALT circuit breaker ...................................................................... check and reset as required ALT switch ...................................................................................................... ON If alternator output not restored ALT switch ..................................................................................................... OFF If alternator output cannot be restored, reduce electrical loads and land as soon as practical. The battery is the only remaining source of electrical power. The Low Bus Voltage annunciator light will illuminate as battery power is depleted. Note: If the battery is depleted, the landing gear must be lowered using the Emergency Extension Procedure. The gear position lights and flaps will be inoperative. ISSUED: JUNE 30, 1997 REVISED: JUNE 12, 2000 REPORT: VB-1669 3-5 SECTION3 EMERGENCY PROCEDURES PA-32R-301, SARATOGA II HP ELECTRICAL OVERLOAD (ALTERNATOR OVER 20 AMPS ABOVE KNOWN ELECTRICAL LOAD) If electrical overload condition is present and abnormally high battery charge load persists (longer than 5 minutes): ALT switch ......................................................................................................ON BAT switch ..................................................................................................... OFF Land as soon as practical. NOTE Due to increased system voltage and radio · frequency noise, operation with ALT switch ON and BAT switch OFF should be made only when required by an electrical system failure. If electrical overload condition is present and battery charge load is normal: ALT switch..................................................................................................... OFF Electrical load ........................................................................reduce to minimum BAT switch .......................................................................................... as required Land as soon as possible. Anticipate complete electrical failure. The Low Bus Voltage annunciator light will illuminate if prolonged battery power usage is required. NOTE If the battery is depleted, the landing gear must be lowered using the emergency extension procedure. The gear position lights and flaps will be inoperative. PROPELLER OVERSPEED Throttle ........................................................................................................retard Oil pressure ..................................................................................................check Prop control ....................................................................... full DECREASE rpm, $en set if any control available Airspeed ......................................................................................................reduce Throttle ................................................................................ as required to remain REPORT: VB-1669 3-6 below 2700 rpm ISSUED: JUNE 30, 1997 REVISED: JUNE 12, 2000 PA-32R-301, SARATOGA II HP SECTION3 EMERGENCY PROCEDURES EMERGENCY LANDING GEAR EXTENSION • NOTE: Refer to paragrap;h 4.39 for differences when emergency gear extension is being performed for training purposes. Prior to emergency extension procedure: Batt. Master switch ...............................................................................check ON ALTR switch ......................................................................................... check ON Circuit breakers ............................................................................................ check Day /night dimming switch (in daytime) .......................................................day Gear indicator bulbs ..............................................................check by depressing Annunc. test If landing gear does not check down and locked: Airspeed ..........................................................................Reduce below 90 KIAS Landing gear selector ....................................................................GEAR DOWN POSITION If landing gear still does not check down and locked: Landing Gear Pump Circuit Breaker...........................................................PULL I Emergency gear knob ......................................PULL, while fish tailing airplane (under normal conditions will take approx. 10 seconds to be down and locked) If all electrical power has been lost, the landing gear must be extended using the above procedures. The gear position indicator lights will not illuminate. SPIN RECOVERY Rudder ...........................................................................................full opposite to direction of rotation Control wheel ........................................................................... full forward while neutralizing ailerons Throttle ........................................................................................................... .idle Rudder ..................................................................... neutral (when rotation stops) Control wheel .................................................................. as required to smoothly ISSUED: JUNE 30,1997 REVISED: JANUARY 9, 2001 regainlevelflightattitude REPORT: VB-1669 3-7 SECTION3 EMERGENCY PROCEDURES PA-32R-301, SARATOGA IT HP OPEN DOOR If the door latch is open, the door will trail slightly open and airspeeds will be reduced slightly. To close the door in flight: Slow airplane to 90 KIAS Cabin vents .................................................................................................... close Storm window ............................................................................................... open If door latch is open ............................................................pull on armrest while REPORT: VB-1669 3-8 moving latch handle to latched position ISSUED: JUNE 30, 1997 PA-32R-301, SARATOGA TI HP SECTION3 EMERGENCY PROCEDURES 3.7 EMERGENCY PROCEDURES (GENERAL) • The following paragraphs are presented to supply additional information for the purpose of providing the pilot with a more complete understanding of the recommended course of action and probable cause of an emergency situation. 3.9 ENGINE FIRE DURING START Engine fires during start are usually the result of overpriming. The first attempt to extinguish the fire is to try to start the engine and draw the excess fuel back into the induction system. If a fire is present before the engine has started, move the mixture control to idle cut-off, open the throttle and crank the engine. This is an attempt to draw the fire back into the engine. If the engine has started, continue operating to try to pull the fire into the engine. In either case (above), if fire continues more than a few seconds, the fire should be extinguished by the best available external means. The fuel selector valve should be OFF and the mixture at idle cut-off if an external fire extinguishing method is to be used. 3.11 ENGINE POWER LOSS DURING TAKEOFF The proper action to be taken if loss of power occurs during takeoff will depend on the circumstances of the particular situation. If sufficient runway remains to complete a normal landing, leave the landing gear down and land straight ahead. If the area ahead is rough, or if it is necessary to clear obstructions, move the gear selector switch to the UP position. If sufficient altitude has been gained to attempt a restart, maintain a safe airspeed and switch the fuel selector to another tank containing fuel. Check the electric fuel pump to. insure that it is ON and that the mixture is RICH. The alternate air should be OPEN. ISSUED: JUNE 30, 1997 REPORT: VB-1669 3-9 SECTION3 EMERGENCY PROCEDURES PA-32R-301, SARATOGA II HP If engine failure was caused by fuel exhaustion, power will not be regained after switching fuel tanks until the empty fuel lines are filled. This · may require up to ten seconds. If power is not regained, proceed with Power Off Landing procedure (refer to the emergency checklist and paragraph 3.15). 3.13 ENGINE POWER LOSS IN FLIGHT Complete engine power loss is usually caused by fuel flow interruption and power will be restored shortly after fuel flow is restored. If power loss occurs at a low altitude, the first step is to prepare for a power off landing (refer to paragraph 3.15). An airspeed of at least 83 KI~S should be maintained. If altitude permits, switch the fuel selector to another tank containing fuel and tum the electric fuel pump ON. Move the mixture control to RICH and the alternate air to OPEN. Check the engine gauges for an indication of the cause of the power loss. If no fuel flow is indicated, check the tank selector position to be sure it is on a tank containing fuel. When power is restored move the alternate air to the CLOSED position, tum OFF the electric fuel pump and adjust the mixture control as necessary. If the preceding steps do not restore power, prepare for an emergency landing. If time permits, secure (OFF) one magneto at a time, then back to ON. Move the throttle and mixture control levers to different settings. This may restore power if the problem is too rich or too lean a mixture or if there is a partial fuel system restriction. Try other fuel tanks. Water in the fuel could take some time to be used up, and allowing the engine to windmill may restore power. If power loss is due to water, fuel flow indications will be normal. . If engine failure was caused by fuel exhaustion, power will not be restored after switching fuel tanks until the empty fuel lines are filled. This may require up to ten seconds. If power is not regained, proceed with the Power Off Landing procedure (refer to the emergency checklist and paragraph 3.15). REPORT: VB-1669 3-10 ISSUED: JUNE 30, 1997 PA-32R-301, SARATOGA II HP 3.15 POWER OFF LANDING ' SECTION3 EMERGENCY PROCEDURES If Joss of power occurs at altitude, trim the aircraft for best gliding angle (83 KIAS, Air Cond. off) and look for a suitable field. If measures taken to restore power are not effective, and if time permits, check your charts for airports in the immediate vicinity; it may be possible to land at one if you have sufficient altitude. At best gliding angle, with no wind, with the engine windmilling and the propeller control in full DECREASE rpm, the aircraft will travel approximately 1.5 miles for each thousand feet of altitude in a no wind condition. If possible, notify the FAA or any other authority, by radio of your difficulty and intentions. If another pilot or passenger is aboard, let them help. When you have located a suitable field, establish a spiral pattern around this field. Try to be at 1000 feet above the field at the downwind position, to make a normal landing approach. When the field can easily be reached, extend full flaps for the shortest landing. Excess altitude may be lost by widening your pattern, using flaps or slipping, or a combination of these. Whether to attempt a landing with gear up or down depends on many factors. If the field chosen is obviously smooth and firm, and long enough to bring the plane to a stop, the gear should be down. If there are stumps or rocks or other large obstacles in the field, the gear in the down position will better protect the occupants of the aircraft. If, however, the field is suspected to be excessively soft or short, or when landing in water of any depth, a wheels-up landing will normally be safer and do less damage to the airplane. Touchdown should normally be made at the lowest possible airspeed with flaps fully extended. When committed to landing, verify the landing gear selector position as required by field conditions. Lower the flaps as desired, close the throttle, move the mixture to idle cut-off, and shut off the magnetos. Tum the battery master and alternator switches OFF. Move the fuel selector valve to OFF. The seat belts and shoulder harness should be tightened. NOTE If the battery master switch is OFF, the gear cannot be retracted. The gear position lights and flaps will be inoperative. ISSUED: JUNE 30, 1997 REPORT: VB-1669 3-11 PA-32R-301, SARATOGA II HP 3.17 FIRE IN FLIGHT , SECTION3 EMERGENCY PROCEDURES The presence of fire is noted through smoke, smell and heat in the cabin. It is essential that the source of the fire by promptly identified through instrument readings, character of smoke, or other indications since the action to be taken differs somewhat in each case. Check for the source of the fire first. If an electrical fire is indicated (smoke in the cabin), turn the battery master and alternator switches OFF. The cabin vents should be opened and the cabin heat turned OFF. A landing should be made as soon as possible. If an engine fire is present, switch the fuel selector to OFF, close the throttle, and move the mixture to idle cut-off. Check that the electric fuel pump is OFF. In all cases, the heater and defroster should be OFF. If radio communication is not required select battery master and alternator· switches OFF. If the terrain permits, a landing should be made immediately. N01E The possibility of an engine fire in flight is extremely remote. The procedure given is general and pilot judgment should be the determining factor for action in such an emergency. REPORT: VB-1669 3-12 ISSUED: JUNE 30, 1997 PA-32R-301, SARATOGA II HP 3.19 LOSS OF OIL PRESSURE SECTION3 EMERGENCY PROCEDURES Loss of oil pressure may be either partial or complete. A partial Joss of oil pressure usuaily indicates a malfunction in the oil pressure regulating system, and a landing should be made as soon as possible to investigate the cause and prevent engine damage. A complete loss of oil pressure indication may signify oil exhaustion or may be the result of a faulty gauge. In either case, proceed toward the nearest airport and be prepared for a forced landing. If the problem is not a pressure gauge malfunction, the engine may stop suddenly. Maintain altitude until such time as a dead stick landing can be accomplished. Don't change power settings unnecessarily, as this may hasten complete power loss. Depending on the circumstances, it may be advisable to make an off airport landing while power is stiii available, particularly if other indications of actual oil pressure loss, such as sudden increases in temperatures, or oil smoke, are apparent, and an airport is not close. If engine stoppage occurs, proceed with Power Off Landing. 3.21 LOSS OF FUEL FLOW The most probable cause of loss of fuel flow is either fuel depletion in the fuel tank selected or failure of the engine driven fuel pump. If loss of fuel flow occurs, turn ON the electric fuel pump and check that the fuel selector is on a tank containing usable fuel. If loss of fuel pressure is due to failure of the engine driven fuel pump the electric fuel pump will supply sufficient fuel flow. After fuel flow and power are regained, turn the electric fuel pump OFF. If fuel flow starts to drop, turn the electric fuel pump ON and land at the nearest suitable airport as soon as possible and have the cause investigated. CAUTION If normal engine operation and fuel flow is not immediately re-established, the electric fuel pump should be turned off. The lack of fuel flow indication could indicate a leak in the fuel system, or fuel exhaustion. • ISSUED: JUNE 30, 1997 REPORT: VB-1669 3-13 SECTION3 EMERGENCY PROCEDURES PA-32R-301, SARATOGA II HP 3.23 ENGINE DRIVEN FUEL PUMP FAILURE • If an engine driven fuel pump failure is indicated, retard the throttle and tum ON the electric fuel pump. The throttle should then be reset as required. A landing should be made at the nearest appropriate airport as soon as possible and the cause of the failure investigated. CAUTION If normal engine operation and fuel flow is not immediately re-established, the electric fuel pump should be turned off. The lack of a fuel flow indication while the electric fuel pump is on could indicate a leak in the fuel system, or fuel exhaustion. If fuel system leak is verified, switch fuel selector to off. 3.25 IDGH OIL TEMPERATURE An abnormally high oil temperature indication may be caused by a low oil level, an obstruction in the oil cooler, damaged or improper baffle seals, a defective gauge, or other causes. Land as soon as practical at an appropriate airport and have the cause investigated. A steady, rapid rise in oil temperature is a sign of trouble. Land at the nearest airport imd let a mechanic investigate the problem. Watch the oil pressure gauge for an accompanying loss of pressure. 3.26 ELECTRICAL FAILURES Loss of alternator output is detected through Alternator Inop annunciator illumination, zero alternator ammeter indication and negative battery ammeter indications (battery is supplying aircraft power). If these indications are present, the battery is the only source of aircraft power and electrical loads should be reduced to a minimum. First, check the alternator circuit breaker for a popped circuit (breaker out). Next reset the alternator by moving the ALT switch to OFF for one second and then to ON. If the trouble was caused by a momentary overvoltage condition (30.5 volts and up) this procedure should return the ammeter to a normal reading. REPORT: VB-1669 3-14 ISSUED: JUNE 30, 1997 PA-32R-301, SARATOGA II HP SECTION3 EMERGENCY PROCEDURES If the alternator and battery ammeters continue to indicate alternator failure, or' if the alternator will not remain reset, turn off the ALT switch, maintain minimum electrical load and land as soon as practical. All electrical load is being supplied by the battery. The Low Bus Voltage annunciator will illuminate as battery power is depleted. 3.27 ELECTRICAL OVERLOAD (alternator over 20 amps above known electrical load)' If abnormally high alternator output is observed (more than 20 amps above known electrical load for the operating conditions) it may be caused by a low battery, a battery fault or other abnormal electrical load. If the cause is a low battery, the battery charge indication should begin to decrease toward normal within 5 minutes. If the high battery charge load persists, turn the battery master switch OFF and land as soon as practical. All electrical loads are being supplied by the alternator. If the electrical overload condition is present and the battery charge load is normal, turn the alternator OFF and reduce the electrical loads to a minimum. Battery power should be used only as required and the flight should be terminated as soon as possible. If battery power is required for flight, the Low Bus Voltage annunciator light will illuminate as battery power is depleted. Complete electrical failure is possible if prolonged battery power usage is required. NOTE Due to higher voltage and radio frequency noise, operation with the ALT switch ON and the BAT switch OFF should be made only when required by an electrical failure. NOTE If the battery is depleted, the landing gear must be lowered using the emergency extension procedure. The gear position lights and flaps will be inoperative. ISSUED: JUNE 30, 1997 REVISED: JUNE 12, 2000 REPORT: VB-1669 3-15 SECTION3 EMERGENCY PROCEDURES PA-32R-301, SARATOGA ll HP 3.29 PROPELLER OVERSPEED Propeller overspeed is caused by a malfunction in the propeller governor or low oil pressure which allows the propeller blades to rotate to full low pitch. If propeller overspeed should occur, retard the throttle and check the oil pressure. The propeller control should be moved to full DECREASE rpm and then set if any control is available. Airspeed should be reduced and throttle used to maintain below 2700 RPM. 3.31 EMERGENCY LANDING GEAR EXTENSION Prior to proceeding with an emergency gear extension, check to insure that the battery master and alternator switches are ON and that the circuit breakers have not opened. If it is daytime, the day/night dimmer switch should be in the day position. Check the landing gear indicators for faulty bulbs by depressing the annunciator press to test.. NOTE Refer to Par. 4.39 for differences when emergency extension procedure is performed for training purposes. If the landing gear does not check down and locked, reduce the airspeed to below 90 KIAS. Move the landing gear selector to the DOWN position. If Ithe landing gear still does not check down and locked, PULL the landing gear pump circuit breaker and PULL the emergency extend knob while fish tailing the airplane. Under normal conditions, the above procedure, will require approximately 10 seconds for the gear to extend and lock down. If all electrical power has been lost, the landing gear must be extended using the above procedure. The gear position indicator lights will not illuminate. 3.33 SPIN RECOVERY Intentional spins are prohibited in this airplane. If a spin is inadvertently entered, immediately apply full rudder opposite to the direction of rotation. Move the 2ontrol wheel full forward while neutralizing the ailerons. Move the throttle to IDLE. When the rotation stops, neutralize the rudder and ease back on the control wheel as required to smoothly regain a level flight attitude. REPORT: VB-1669 3-16 ISSUED: JUNE 30, 1997 REVISED: JANUARY 9, 2001 PA-32R-301, SARATOGA II HP 3.35 OPEN DOOR • SECTION3 EMERGENCY PROCEDURES The cabin door is latched through a pin mechanism, so the chances of its springing open in flight is remote. However, should you forget to fully engage the door latch, the door may spring partially open. This will usually happen at takeoff or soon afterward. A partially open door will not affect normal flight characteristics, and a normal landing can be made with the door open. If the door latch is open, the door will trail slightly open, and airspeed will be reduced slightly. To close the door in flight, slow the airplane to 90 KIAS, close the cabin vents and open the storm window. If the door latch is open, pull on the armrest while moving the latch handle to the latched position. 3.37 ENGINE ROUGHNESS Engine roughness may be caused by dirt in the injector nozzles, induction filter icing, or ignition problems. First adjust the mixture for maximum smoothness. The engine will run rough if the mixture is too rich or too lean. Move the alternate air to OPEN and then turn ON the electric fuel pump. Switch the fuel selector to another tank to see if fuel contamination is the problem. Check the engine gauges for abnormal readings. If any gauge readings are abnormal proceed accordingly. Secure (OFF) one magneto at a time, then back to ON. If operation is satisfactory on either magneto, proceed on that magneto at reduced power with full RICH mixture to a landing at the first available airport. If roughness persists, prepare for a precautionary landing at pilot's discretion. ISSUED: JUNE 30, 1997 REPORT: VB-1669 3-17 SECTION3 EMERGENCY PROCEDURES PA-32R-301, SARATOGA II HP • THIS PAGE INTENTIONALLY LEFTBLANK REPORT: VB-1669 3-18 ISSUED: JUNE 30,1997 "'w <I" a: => z 0 w 2 0 0 a: l "- J l <( IJ ::;; a: 0 z • • TABLE OF CONTENTS SECTION4 NORMAL PROCEDURES Paragraph Page No. No. 4.1 General.......................................................................................... 4-1 4.3 Airspeeds for Safe Operations ...................................................... 4-1 4.5 Normal Procedures Checklist........................................................ 4-3 Preflight Check.......................................................................... 4-3 Engine Start GeneraL................................................................. 4-6 Before Starting Engine .............................................................. 4-6 Normal Start- Cold Engine...................................................... 4-6 Normal Start- Hot Engine........................................................ 4-7 Engine Start When Flooded....................................................... 4-7 Starting With External Power Source........................................ 4-7 Warm-Up ................................................................................... 4-8 Taxung. ... ..... .. ... .. ....... .. . .. .. ... ... ........ .. ... ...... .. .. .... .. ......... ... ....... ... 4-8 Ground Check............................................................................. 4-8 Before Takeoff........................................................................... 4-9 Takeoff...................·................................. ................. .................. 4-9 Climb ... ... ........ ..... ... .. .... .. ... ... ... ... . .. ... . .. ...... .. ...... .. ... ..... ...... ..... ... 4- 10 Cruise......................................................................................... 4-10 Approach and Landing . ... ..... ...... ... . .. .... ....... ...... .. ... .. . ... .. ... ... .. .. . 4-10 Go-Around................................................................................. 4-1 1 Stopping Engine ....................................... .............................. .. . 4-11 Mooring..................................................................................... 4-12 4. 7 Preflight Check ............................................. ................................ 4-13 4.9 Before Starting Engine.................................................................. 4-17 4.11 StartingEngine ........................................ ,..................................... 4-17 4.13 Warm-Up....................................................................................... 4-19 4.15 Taxiing........................................................................................... 4-19 ISSUED: JUNE 30, 1997 REPORT: VB-1669 4-i Paragraph No. , TABLE OF CONTENTS (coot) SECTION 4 (coot) Page No. 4.17 Ground Check............................................................................... 4-21 4.19 Before Takeoff..................................................... ;......................... 4-22 4.21 Takeoff.......................................................................................... 4-22 4.23 Climb............................................................................................. 4-23 4.25 CruiSing......................................................................................... 4-23 4.27 Approach and Landing.................................................................. 4-25 4.29 Go-Around.................................................................................... 4-26 4.30 After Landing................................................................................ 4-26 4.31 Stopping Engine............................................................................ 4-26 4.33 Parking.......................................................................................... 4-26 4.35 Stalls ............................................................................................. 4-27 4.37 Turbulent Air Operation................................................................ 4-27 4.39 Landing Gear................................................................................. 4-27 4.41 Weight and Balance....................................................................... 4-28 4.43 Noise Level................................................................................... 4-28 REPORT: VB-1669 4-ii ISSUED: JUNE 30, 1997 REVISED: AUGUST 10, 1998 PA-32R-301, SARATOGA II HP • SECTION 4 NORMAL PROCEDURES SECTION4 NORMAL PROCEDURES 4.1 GENERAL This section describes the recommended procedures for the conduct of normal operations for the airplane. All of the required (FAA regulations) procedures and those necessary for operation of the airplane as determined by the operating and design features of the airplane are presented. Normal procedures associated with those optional systems and equipment which require handbook supplements are provided in Section 9 (Supplements). These procedures are provided to present a source of reference and review and to supply information on procedures which are not the same for all aircraft. Pilots should familiarize themselves with the procedures given in this section in order to become proficient in the normal operations of the airplane. The first portion of this section consists of a short form check list which supplies an action sequence for normal operations with little emphasis on the operation of the systems. The remainder of the section is devoted to amplified normal procedures which provide detailed information and explanations of the procedures and how to perform them. This portion of the section is not intended for use as an in-flight reference due to the lengthy explanation. The short form checklist should be used for this purpose. 4.3 AIRSPEEDS FOR SAFE OPERATIONS The following airspeeds are those which are significant to the operation of the airplane. These figures are for standard airplanes flown at gross weight under standard conditions at sea level. ISSUED: JUNE 30,1997 REPORT: VB-1669 4-1 SECTION4 NORMAL PROCEDURES PA-32R-301, SARATOGA II HP Performance for a specific airplane may vary from published figures depending upo'n the equipment installed, the condition of the engine, airplane and equipment, atmospheric conditions and piloting technique. (a) Best Rate of Climb Speed gear down, flaps up ........................................................... 85 KIAS gear up, flaps up ................................................................ 93 KIAS (b) Turbulent Air Operating Speed (See Subsection 2.3) ............ 134 KIAS (c) Maximum Flap Speed ............................................................ 110 KIAS (d) Landing Final Approach Speed (Full Flaps) ............................ 80 KIAS (e) Maximum Demonstrated Crosswind Velocity ........................... 17 KTS REPORT: VB-1669 4-2 ISSUED: JUNE 30, 1997 REVISED: MARCH 11, 2002 PA-32R-301, SARATOGA II HP SECTION4 NORMAL PROCEDURES ' r-·~•ooouooo! i g ~ ~ i.... ................................. .................................... . r·u" ~ i ~ . . ······· .. 04 •••••••••• , ....... _ • + ··············· .,.. •• ,,._,,u, .. ,, .. , .. ~ r •••••••••••• ,,, r t r····· ..·· .......... . + +!oooooooooooooooooououoooooooooooo: WALK-AROUND Figure4-1 4.5 NORMAL PROCEDURES CHECKLIST PREFLIGHT CHECK CAUTION: The flaps must be placed in the up position for the flap to support weight. Passengers should be cautioned accordingly. COCKPIT CAUTION: When draining any amount offuel, care should be taken to ensure that no fire hazard exists before starting engine. Fuel strainer .................................................drain & check for water & sediment Control wheel ............................................................................. release restraints Gear Handle ..................................................................................................down Parking brake .................................................................................................... set Avionics ......................................................................................................... OFF All switches ...................................................................................................OFF Mixture ............................................................................................... .idle cut-off Magneto switches .......................................................................................... OFF Battery master switch ...................................................................................... ON Fuel gauges .................................................................................... check quantity Annunciator panel ........................................................................................ check Flaps ...........................................................................................................extend Battery master switch .................................................................................... OFF Primary flight controls ................................................................ proper operation Trim ............................................................................................................ neutral Pitot and static systems ...................................................................................... drain Windows ..................................................................................................check clean Required papers and POH ..................................................................check on board Tow bar and baggage .............................................................. stow properly - secure Baggage door-Rear ........................................................................... close and secure ISSUED: JUNE 30, 1997 REPORT: VB-1669 4-3 SECTION4 NORMAL PROCEDURES PA-32R-301, SARATOGA II HP RIGHT WING- Surface condition ................................................................. clear of ice, frost, snow ·. Flap and hinges ................................................................................................ check Aileron and hinges ........................................................................................... check Static wicks ........................................................................................ check - secure Wmg tip and nav/strobe lights .........................................................................check Landing light. ................................................................................................... check Fuel tank ................................................................................. check supply visually -secure cap Fuel quantity gauge.......................................................................................... check Fuel tank vent .................................................................................................... clear CAUTION: When draining any amount of fuel, care should be taken to ensure that no fire hazard exists before starting engine. Fuel tank sumps ......................................................................... drain and check for water, sediment and proper fuel Tie down and chock ...................................................................................... remove Main gear strut ........................................................ proper inflation (4.00 ± .25 in.) Tire .................................................................................................................. check Brake block and disc ........................................................................................check 1 Fresh air inlet. .................................................................................................... clear NOSE SECTION Baggage door ................................................................................. close and secure General condition............................................................................................. check Baggage door .................................................................................close and secure Cowling ........................................................................................................... secure Windshield ........................................................................................................ clean Propeller and spinner ............................................................................. ,......... check Air inlets ............................................................................................................ clear Engine baffle seals ........................................................................................... check Chock ............................................................................................................ remove Nose gear strut ........................................................ proper inflation (3.25 ± .25 in.) Nose Gear Doors ..............................................................................................check Nose wheel tire ................................................................................................ check ILanding light (s/n 3246001 thru 3246224 only) ............................................. secure Oil .................................................................................................... check quantity Dipstick. ............................................................................................ properly seated , Oil filler cap .................................................................................................... secure REPORT: VB-1669 4-4 ISSUED: JUNE 30, 1997 REVISED: AUGUST 12, 2004 PA-32R-301, SARATOGA II HP LEFT WING SECTION4 NORMAL PROCEDURES Surface condition ................................................................ clear of ice, frost, snow Fresh air inlet ................................................................................................... clear CAUTION: When draining any amount of fuel, care should be taken to ensure that no fire hazard exists before starting engine. Fuel tank sump ..........................................................................drain and check for water, sediment and proper fuel Tie down and chock .....................................................................................remove Main gear strut... .................................................... proper inflation (4.00 ± .25 in.) Tire ................................................................................................................. check Brake block and disc ...................................................................................... check Fuel tank vent.. ................................................................................................. clear Fuel quantity gauge ........................................................................................ check Fuel tank ................................................................................ check supply visually -secure cap Stall warning vanes ......................................................................................... check Pi tot head ....................................................................... remove cover - holes clear Landing light .................................................................................................. check Wing tip and nav/strobe lights ........................................................................ check Aileron and hinges .......................................................................................... check Flap and hinges ............................................................................................... check Static wicks .........................................................................................check secure FUSELAGE Antennas ......................................................................................................... check Static Vents .......................................................................................................clear Empennage ......................................................................... clear of ice, frost, snow Stabilator and trim tab .................................................................................... check Tie down ......................................................................................................remove MISCELLANEOUS Battery master switch ......................................................................................... ON Flaps .............................................................................................................. retract Interior lighting ................................................................................. ON and check Pitot heat switch ................................................................................................. ON Pitot heat Off/Inop annunciator ........................................................................ OFF CAUTION: Care should be taken when an operational check of the heated pitot head is being performed. The unit becomes very hot. Ground operation should be limited to three minutes to avoid damaging the heater elements. Exterior lighting switches .................................................................. ON and check Pitot ..................................................................................................... check - warm ISSUED: JUNE 30, 1997 REVISED: AUGUST 12, 2004 REPORT: VB-1669 4-5 SECTION4 NO~LPROCEDURES PA-32R-301, SARATOGA ll HP Stall warning hom ............................................................................................ check All lighting switches .......................................................................................... OFF Pitot heat switch .................................................................................................OFF Pitot heat Off/Inop annunciator .......................................................................... ON Battery master switch ........................................................................................OFF Passengers ........................................................................................................board Doors ............................................................................................Closed and secure Seats ...................................................................................... Adjusted & Locked Seat belts and harness ...........................................................................fasten/adjust check inertia reel NOTE: With the shoulder harness fastened and adjusted, a pull test of it's locking restraint feature should be performed. ENGINE START ·GENERAL CAUTION: Do not attempt flight if there is no indication of alternator output. CAUTION: If a positive oil pressure is not indicated within 30 seconds following an engine start, stop the engine and determine the trouble. In cold weather it will take a few seconds longer to get a positive oil pressure indication. NOTE: Starter manufacturers recommend that starter cranking periods be limited to 30 seconds with a two minute rest period between cranking periods. Longer cranking periods will shorten the life of the starter. ! BEFORE STARTING ENGINE Brakes .................................................................................................. ow .... ••••••• set Circuit breakers ........................................................................................ check in Alternate air ................................................................................................... OFF Propeller .............................................................................. full INCREASE rpm Avionics ......................................................................................................... OFF Fuel selector .......................................................................................desired tank NORMAL START· COLD ENGINE Throttle ............................................................................................... 112 in. open Battery master switch ......................................................................................ON Alternator switch .............................................................................................ON Magneto switches ............................................................................................ ON Electric fuel pump ........................................................................................... ON Mixture ........................................................................... prime- then idle cut-off Propeller..........................................................................................................clear Starter ......................................................................................................... engage Mixture .................................................................................................. full RICH Throttle ........................................................................................................ adjust Oil pressure ..................................................................................................check REPORT: VB-1669 4-6 ISSUED: JUNE 30, 1997 PA-32R-301, SARATOGA II HP NORMALSTART-HOTENGmE • SECTION4 NORMAL PROCEDURES Throttle ............................................................................................... l/2 in. open Battery master switch ...................................................................................... ON Alternator switch ............................................................................................. ON Magneto switches ............................................................................................ ON Electric fuel pump ................................................................. ;......................... ON Mixture ............................................................................................... .idle cut-off Propeller ........................................................................................................clear Starter .........................................................................................................engage Mixture ..................................................................................................... advance Throttle ........................................................................................................ adjust Oil pressure .................................................................................... ,............. check., ENGmE START WHEN FLOODED Throttle .................................................................................................... open full Battery master switch ...................................................................................... ON . Alternator switch ............................................................................................. ON Magneto switches ............................................................................................ ON Electric fuel pump .......................................................................................... OFF Mixture ............................................................................................... .idle cut-off Propeller ........................................................................................................ clear Starter ......................................................................................................... engage Mixture .....................................................................................................advance Throttle ........................................................................................................ retard Oil Pressure .................................................................................................. check STARTING WITH EXTERNAL POWER SOURCE CAUTION: It is possible to use the ship's battery in parallel by turning only the battery master switch ON. This will give longer cranking capabilities, but will not increase the amperage. Care should be exercised because if the ship's battery has been depleted, the external power supply can be be reduced to the level of the ship's battery. This can be tested by turning on the battery master switch momentarily while the starter is engaged. If cranking speed increases, the· ship's battery is at a higher level than the external power supply. NOTE: F()r all normal operations using external power, the battery master and alternator switches should be OFF. Battery master switch .................................................................................... OFF Alternator switch ........................................................................................... OFF Magneto switches ............................................................................................ ON ISSUED: JUNE 30, 1997 REPORT: VB-1669 4-7 SECTION4 NORMAL PROCEDURES PA-32R-301, SARATOGA ll HP All electrical equipment ................................................................................... OFF External power plug ....... ~ ............................................................ .insert in fuselage Proceed with normal start Throttle ................................................................................. .lowest possible RPM External power plug ........................................................ disconnect from fuselage Battery master switch .........................................................................................ON Alternator switch ................................................................... ON - check ammeter Oil pressure ..................................................................................................... check WARM-UP Throttle ...................................................................................... 1000 to 1200 RPM TAXIING Taxi area ........................................................................................................... clear Parking brake ................................................................................................ release Prop ......................................................................................................... high RPM Throttle ................................................................................................ apply slowly Brakes ...................................

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