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Piper SARATOGA II TC Pilot Operating Handbook

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SARATOGA II TC

REFERENCE ONLY

THIS ELECTRONIC VERSION

OF THE POH IS

NOT APPROVED TO

REPLACE ANY OPERATING

INFORMATION REQUIRED

BY THE REGULATIONS.

AIRPlAne

SeRIAl nO. ____________________

PA-32R-301T

RePORT: vb-1975 fAA APPROved by:

dATe Of APPROvAl:

APRIl 9, 2007

THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE

PILOT BY THE FEDERAL AVIATION REGULATIONS AND ADDITIONAL INFORMATION

PROVIDED BY THE MANUFACTURER AND CONSTITUTES THE FAA APPROVED

AIRPLANE FLIGHT MANUAL. THIS HANDBOOK MUST BE CARRIED IN THE AIRPLANE

AT ALL TIMES.

THIS FLIGHT MANUAL IS EASA

APPROVED UNDER APPROVAL

NUMBER P-EASA.IM.A.C. 01651.

THIS APPROVAL IS VALID FOR

THE AFM/POH VB-1975 AND

AFMS NO. 1 TO 5.

PA-32R-301T

Sn 3257447, 3257455 And uP

OPeRATInG

hAndbOOk

AIRPlAne flIGhT mAnuAl

AIRPlAne

ReGIST. nO. ________________

lIndA J. dICken

dOA-510620-Ce

PIPeR AIRCRAfT, InC.

veRO beACh, flORIdA

PIlOT'S

And

fAA APPROved

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Summary of Contents for Piper SARATOGA II TC

Page 1 SARATOGA II TC PA-32R-301T Sn 3257447, 3257455 And uP REFERENCE ONLY PIlOT’S THIS ELECTRONIC VERSION OPeRATInG OF THE POH IS NOT APPROVED TO REPLACE ANY OPERATING hAndbOOk INFORMATION REQUIRED BY THE REGULATIONS. fAA APPROved AIRPlAne flIGhT mAnuAl AIRPlAne AIRPlAne SeRIAl nO. ____________________ ReGIST.
Page 2 PA-32R-301T, SARATOGA II TC Published by TECHNICAL PUBLICATIONS Issued: April 9, 2007 © 2007-2009, 2012 PIPER AIRCRAFT, INC. All Rights Reserved REPORT: VB-1975 ISSUED: April 9, 2007 REVISED: August 27, 2012...
Page 3 PA-32R-301T, SARATOGA II TC APPLICABILITY Application of this handbook is limited to the specific Piper PA-32R-301T model airplane designated by serial number and registration number on the face of the title page of this handbook. This handbook cannot be used for operational purposes unless kept in a current status.
Page 4 PA-32R-301T, SARATOGA II TC 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 airplane was licensed by the manufacturer and thereafter must be maintained by the owner.
Page 5 PIlOT’S OPERATIng hAnDBOOk lOg Of REVISIOnS Current Revisions to the PA-32R-301T Saratoga II TC Pilot’s Operating Handbook, REPORT: VB-1975 issued April 9, 2007. Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 1 Updated copyright.
Page 6 PIlOT’S OPERATIng hAnDBOOk lOg Of REVISIOnS (cont) Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 3 3-34 Relocated to 3-35. (Continued) 3-35 Relocated to 3-36. 3-36 Relocated to 3-37. 3-37 Relocated to 3-38. 3-38 Relocated to 3-39.
Page 7 PA-32R-301T, SARATOGA II TC 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...
Page 8 PA-32R-301T, SARATOGA II TC THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1975 ISSUED: April 9, 2007 viii...
Page 9 SECTION 1 PA-32R-301T, SARATOGA II TC GENERAL TABLE OF CONTENTS SECTION 1 GENERAL Paragraph Page Introduction ................... Engine ................... Propeller ..................Fuel ......................................1.11 Maximum Weights ................ 1.13 Standard Airplane Weights............1.15 Baggage Space ................1.17 Specific Loading ................
Page 10 SECTION 1 GENERAL PA-32R-301T, SARATOGA II TC THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1975 ISSUED: April 9, 2007 1-ii...
Page 11 SECTION 1 PA-32R-301T, SARATOGA II TC GENERAL SECTION 1 GENERAL INTRODUCTION This Pilot’s Operating Handbook is designed for maximum utilization as an operating guide for the pilot. It includes the material required to be furnished to the pilot by FAR/CAR. It also contains supplemental data supplied by the airplane manufacturer.
Page 12 SECTION 1 GENERAL PA-32R-301T, SARATOGA II TC THREE VIEW Figure 1-1 REPORT: VB-1975 ISSUED: April 9, 2007...
Page 13 SECTION 1 PA-32R-301T, SARATOGA II TC GENERAL ENGINE (a) Number of Engines (b) Engine Manufacturer Lycoming (c) Engine Model Number TIO-540-AH1A (d) Rated Horsepower (e) Rated Speed (rpm) 2500 (f) Bore (inches) 5.125 (g) Stroke (inches) 4.375 (h) Displacement (cubic inches) 541.5...
Page 14 SECTION 1 GENERAL PA-32R-301T, SARATOGA II TC FUEL AVGAS ONLY (a) Fuel Capacity (U.S. gal.) (total) (b) Usable Fuel (U.S. gal.) (total) (c) Fuel (1) Minimum Grade 100 - Green or 100LL - Blue Aviation Grade (2) Alternate Fuels Refer to latest revision of Lycoming Service Instruction 1070 (a) Oil Capacity (U.S.
Page 15 SECTION 1 PA-32R-301T, SARATOGA II TC GENERAL 1.11 MAXIMUM WEIGHTS (a) Maximum Takeoff Weight (lbs.) 3600 (b) Maximum Landing Weight (lbs.) 3600 (c) Maximum Ramp Weight (lbs.) 3615 FORWARD (d) Maximum Weights in Baggage Compartments (lbs.) 1.13 STANDARD AIRPLANE WEIGHTS Refer to Figure 6-5 for the Standard Empty Weight and the Useful Load.
Page 16 SECTION 1 GENERAL PA-32R-301T, SARATOGA II TC 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...
Page 17 SECTION 1 PA-32R-301T, SARATOGA II TC GENERAL M a x i m u m L a n d i n g G e a r E x t e n d e d Speed is the maximum speed at which an aircraft can be safely flown with the landing gear extended.
Page 18 SECTION 1 GENERAL PA-32R-301T, SARATOGA II TC (b) Meteorological Terminology 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 (1013.2...
Page 19 SECTION 1 PA-32R-301T, SARATOGA II TC GENERAL (c) Power Terminology Takeoff Power Maximum power permissible for takeoff. Maximum Con- M a x i m u m p ow e r p e r m i s s i b l e c o n t i n - tinuous Power uously during flight.
Page 20 SECTION 1 GENERAL PA-32R-301T, SARATOGA II TC (f) Airplane Performance and Flight Planning Terminology Climb Gradient The demonstrated ratio of the change in height during a portion of a climb, to the horizontal distance traversed in the same time interval.
Page 21 SECTION 1 PA-32R-301T, SARATOGA II TC GENERAL (g) Weight and Balance Terminology Reference Datum An imaginary vertical plane from which all horizontal distances measured balance purposes. Station A location along the airplane fuselage usually given in terms of distance from the reference datum.
Page 22 SECTION 1 GENERAL PA-32R-301T, SARATOGA II TC Basic Empty S t a n d a r d e m p t y w e i g h t p l u s o p t i o n a l Weight equipment.
Page 23 SECTION 2 PA-32R-301T, SARATOGA II TC LIMITATIONS TABLE Of CONTENTS SECTION 2 LIMITATIONS Paragraph Page General ..................Airspeed Limitations ..............Airspeed Indicator Markings............Power Plant Limitations ............... Power Plant Instrument Markings..........2.11 Weight Limits ................2.13 Center of Gravity Limits ..............
Page 24 SECTION 2 LIMITATIONS PA-32R-301T, SARATOGA II TC THIS PAGE INTENTIONALLY LEfT BLANK REPORT: VB-1975 ISSUED: April 9, 2007 2-ii...
Page 25 SECTION 2 PA-32R-301T, SARATOGA II TC LIMITATIONS SECTION 2 - LIMITATIONS GENERAL This section provides the FAA Approved operating limitations, instrument markings, color coding and basic placards necessary for operation of the airplane and its systems. Limitations associated with those optional systems and equipment which require handbook supplements can be found in Section 9 (Supplements).
Page 26 SECTION 2 LIMITATIONS PA-32R-301T, SARATOGA II TC THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1975 ISSUED: April 9, 2007...
Page 27 SECTION 2 PA-32R-301T, SARATOGA II TC LIMITATIONS AIRSPEED LIMITATIONS SPEED KIAS KCAS Never Exceed Speed (V ) - Do not exceed this speed in any operation. Maximum Structural Cruising Speed ) - Do not exceed this speed except in smooth air and then only with caution.
Page 28 SECTION 2 LIMITATIONS PA-32R-301T, SARATOGA II TC 2.5 AIRSPEED INDICATOR MARKINGS PFD and Standby airspeed indicator markings and their color code significance are shown in the table below. Marking KIAS Significance Red band 20 - 63 Low speed awareness -...
Page 29 SECTION 2 PA-32R-301T, SARATOGA II TC LIMITATIONS POWER PLANT LIMITATIONS (a) Number of Engines (b) Engine Manufacturer Lycoming (c) Engine Model No. TIO-540-AH1A (d) Engine Operating Limits (1) Maximum Horsepower (2) Maximum Rotation Speed (RPM) 2500 (3) Maximum Oil Temperature (°F)
Page 30 SECTION 2 LIMITATIONS PA-32R-301T, SARATOGA II TC 2.9 POWER PLANT INSTRUMENT MARKINGS Power plant instrument markings and their color code significance are shown in the table below. NOTE When an indication lies in the caution range, the legend for that display will change to the color of the caution range.
Page 31 SECTION 2 PA-32R-301T, SARATOGA II TC LIMITATIONS 2.11 WEIGHT LIMITS (a) Maximum Takeoff and Landing Weight 3600 LBS. (b) Maximum Ramp Weight 3615 LBS. (c) Maximum Baggage (100 lbs. each compartment) 200 LBS. NOTE Refer to Section 5 (Performance) for maximum weight as limited by performance.
Page 32 SECTION 2 LIMITATIONS PA-32R-301T, SARATOGA II TC 2.19 TYPES OF OPERATIONS The airplane is approved for the following operations when equipped in accordance with FAR 91 or FAR 135. a) Day VFR b) Night VFR c) Day IFR d) Night IFR...
Page 33 SECTION 2 PA-32R-301T, SARATOGA II TC LIMITATIONS 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).
Page 34 SECTION 2 LIMITATIONS PA-32R-301T, SARATOGA II TC 2.27 GARMIN G1000 AVIONICS SYSTEM LIMITATIONS 1. The Garmin G1000 Cockpit Reference Guide for the Piper PA32, Garmin p/n 190-00416-01, latest revision, must be immediately available to the flight crew. NOTE The Cockpit Reference Guide contains additional Warnings, Cautions and Notes with which the pilot should become aware.
Page 35 7. If not previously defined, the following default settings must be made in the “SYSTEM SETUP” menu of the Garmin G1000 prior to operation (refer to the Garmin G1000 Pilot’s Guide for the Piper PA32, Garmin p/n 190-00692-00, latest revision, if necessary).
Page 36 SECTION 2 LIMITATIONS PA-32R-301T, SARATOGA II TC 8. GPSS mode must not be used on the final approach segment of a VLOC approach (ILS, LOC or non-GPS-overlay VOR). GPSS mode must be deselected (i.e., NAV mode selected) prior to the turn onto the final approach course.
Page 37 SECTION 2 PA-32R-301T, SARATOGA II TC LIMITATIONS 15. If the optional Chartview function is enabled, the data is limited to supplemental use only. Current paper copies of navigation charts and data appropriate to the intended operation must be available to the pilot.
Page 38 SECTION 2 LIMITATIONS PA-32R-301T, SARATOGA II TC 22. If a GIA #2 failure is experienced, the autopilot HDG annunciator disappears from the PFD but remains illuminated on the autopilot computer. The autopilot will hold the wings level and will not respond to heading bug changes.
Page 39 SECTION 2 PA-32R-301T, SARATOGA II TC LIMITATIONS normal mode is approved by pressing the DISPLAY BACKUP button (button will be IN) on the audio panel. If the system returns to normal mode, leave the DISPLAY BACKUP button IN and continue. If the...
Page 40 SECTION 2 LIMITATIONS PA-32R-301T, SARATOGA II TC 2.31 MID-CONTINENT ELECTRIC ATTITUDE INDICATOR LIMITATIONS If the standby attitude indicator fails to remain erect during ground operations with electrical power applied, IFR flight is prohibited. REPORT: VB-1975 ISSUED: April 9, 2007 2-16...
Page 41 SECTION 2 PA-32R-301T, SARATOGA II TC LIMITATIONS 2.33 PLACARDS In full view of the pilot: THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS. NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED.
Page 42 SECTION 2 LIMITATIONS PA-32R-301T, SARATOGA II TC On lower instrument panel near emergency landing gear extension control: On center post of windshield in full view of the pilot: CAUTION COMPASS CAL. MAY BE IN ERROR WITH ELECT. EQUIPMENT OTHER THAN AVIONICS ON.
Page 43 SECTION 2 PA-32R-301T, SARATOGA II TC LIMITATIONS On instrument panel near elevator trim switch (if elevator trim installed): ELEV. TRIM PUSH ON/OFF Adjacent to flap selector switch: 0° 10° 25° 40° On instrument panel near oxygen system control (if oxygen system...
Page 44 SECTION 2 LIMITATIONS PA-32R-301T, SARATOGA II TC On instrument panel near EMER BATT switch: USE OF EMERGENCY BATTERY WILL DISABLE ALL MAIN BUS EQUIPMENT On instrument panel near alternate air control: CLOSE ALT. OPEN On instrument panel in full view of the pilot (if TKS ice protection system...
Page 45 SECTION 2 PA-32R-301T, SARATOGA II TC LIMITATIONS On executive writing table (if installed): THIS TABLE MUST BE STOWED CAUTION DURING TAKE-OFF & LANDING MAX. WT.-12 LBS. On aft baggage closeout: SOFT WEAR ONLY MAXIMUM BAGGAGE THIS COMPARTMENT 100 LBS. NO HEAVY OBJECTS...
Page 46 SECTION 2 LIMITATIONS PA-32R-301T, SARATOGA II TC On rear cabin door near upper door latch (inside): On rear cabin door near upper door latch (outside): DOOR RELEASE On outside of rear cabin door next to key slot: RELEASE ABOVE LATCH...
Page 47 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES TABlE Of CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph Page General ..................Annunciator Descriptions ............Airspeeds for Safe Operation............Emergency Procedures Checklist ..........Engine Fire During Start ............Engine Power Loss During Takeoff ........
Page 48 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC TABlE Of CONTENTS (continued) SECTION 3 (continued) Paragraph Page Amplified Emergency Procedures (General) ....... 3-34 Engine Fire During Start .............. 3-34 3.11 Engine Power Loss During Takeoff ..........3-34 3.13 Engine Power Loss In Flight ............
Page 49 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES GENERAL The recommended procedures for coping with various types of emergencies and critical situations are provided by this section. All of the emergency procedures required by the FAA and those necessary for operation of the airplane as determined by the operating and design features of the airplane are presented.
Page 50 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC Overriding Considerations In all emergencies, the overriding consideration must be to: • Maintain Airplane Control. • Analyze the situation. • Take proper action. Terminology Many emergencies require some urgency in landing the aircraft. The degree of urgency varies with the emergency;...
Page 51 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: April 9, 2007 REPORT: VB-1975...
Page 52 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC Annunciator Descriptions Warning Systems The aircraft system annunciations are displayed to the right of the altitude and vertical speed boxes on the Primary Flight Display (PFD), or on the Multi-Function Display (MFD) if the system is in reversionary mode.
Page 53 NOTE The Garmin G1000 Cockpit Reference Guide for the Piper PA32, Garmin p/n 190-00416-01, latest revision and the Garmin G1000 Pilot’s Guide for the Piper PA32, Garmin p/n 190-00692-00, latest revision, contain detailed descriptions of the annunciator system and all warnings, cautions and advisories.
Page 54 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC Annunciator Descriptions (continued) Caution Yellow - Annunciations - single aural tone Annunciation Cause TERRAIN Terrain is in close proximity. BAGGAGE DOOR Baggage door is open. AIR COND DR Air conditioning door is open with take-off power applied.
Page 55 PFD or MFD. Consult the Garmin G1000 Cockpit Reference Guide for the Piper PA32, Garmin p/n 190-00416-01, latest revision and the Garmin G1000 Pilot’s Guide for the Piper PA32, Garmin p/n 190-00692-00, latest revision, for detailed descriptions of each annunciation as necessary.
Page 56 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC AIRSPEEDS FOR SAFE OPERATION Stall Speeds 3600 lbs (Gear Up, 0° Flaps) ............67 KIAS 3600 lbs (Gear Down, 40° Flaps)............63 KIAS Maneuvering Speeds 3600 lbs ..................134 KIAS 2230 lbs ..................105 KIAS Never Exceed Speed ................191 KIAS Power Off Glide Speed 3600 lbs (Gear Up, 0°...
Page 57 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES 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.
Page 58 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC ENGINE POWER LOSS IN FLIGHT If at low altitude: Airspeed ..............maintain 83 KIAS minimum Prepare for power off landing. If altitude permits: Fuel selector ...................switch to tank containing fuel Electric fuel pump ...................ON Mixture ......................RICH...
Page 59 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES 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.
Page 60 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC FIRE IN FLIGHT Source of fire..................determine 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.
Page 61 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES Electrical fire (smoke in cabin) (continued): BATT MASTR switch..................OFF MAIN ALT switch..................OFF STBY ALT switch ..................OFF Vents ......................open Cabin heat ......................OFF EMER BATT voltage ................monitor NOTE As long as the EMER BATT switch is ON, all non-essential equipment will be disabled and the aircraft main alternator will be off-line.
Page 62 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC Electrical fire (smoke in cabin) (continued): If smoke and fumes continue: If conditions permit a safe landing in VFR conditions and a dark cockpit environment: EMER BATT switch ..................OFF BATT MASTR switch ................verify OFF MAIN ALT switch ................verify OFF...
Page 63 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES Electrical fire (smoke in cabin) (continued): If smoke and fumes continue (continued): If conditions do not permit a safe landing in VFR conditions and a dark cockpit environment (continued): NOTE Items on the emergency bus are fuse protected and will...
Page 64 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC Electrical fire (smoke in cabin) (continued): If smoke and fumes clear (continued): NOTE The above electrical configuration approximates the same items on the emergency bus that will now be powered by the main battery. At the pilot’s discretion, additional electrical items may be powered by resetting (leaving in) the corresponding circuit breaker.
Page 65 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES Electrical fire (smoke in cabin) (continued): If smoke and fumes clear (continued): If electrical power is required beyond the time supplied by the main battery and emergency battery: EMER BATT switch................verify ON BATT MASTR switch ................verify ON...
Page 66 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC 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...
Page 67 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES HIGH CYLINDER HEAD TEMPERATURE Power......................Reduce Mixture .......................Enrich Airspeed................Increase, if practical HIGH OIL TEMPERATURE Land at nearest airport and investigate the problem. Prepare for power off landing. TURBINE INLET TEMPERATURE (TIT) INDICATOR FAILURE If failure occurs during takeoff, climb, or landing: Mixture ....................Full rich...
Page 68 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC ELECTRICAL FAILURES Main Alternator Failure A Main Alternator Failure is indicated by a red ALTNTR INOP annunciator on the PFD. Verify failure ........Check MAIN ALT on EIS-ENGINE page If MAIN ALT current is zero or negative: ALTR switch ....................OFF...
Page 69 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES Main and Standby Alternator Failure If STBY ALT FAIL annunciation is also displayed on the PFD then: EMER BATT switch ..................ON Land as soon as practical. WARNING Compass error may exceed 10 degrees with the Main Alternator Inoperative and Standby Alternator and/or the Emergency Battery ON.
Page 70 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC Essential Bus Low Annunciation: When the main battery voltage on the essential bus drops below 24.5 Volts an ESS BUS LOW annunciator will be displayed on the PFD. Land as soon as practical.
Page 71 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES ELECTRICAL OVERLOAD Alternator Load over 20 Amps above known electrical load: BATT Load ....................Check If battery load is excessive: ALTR switch ..................Verify ON BATT MASTR switch..................OFF Electrical Load ..................Reduce Land as soon as practical.
Page 72 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC AVIONICS EMERGENCIES PFD Failure If the MFD automatically entered reversionary mode: DISPLAY BACKUP button on audio panel ..PUSH (button will be OUT) The system will remain in reversionary mode even if the problem causing the automatic entry of reversionary mode is resolved.
Page 73 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES MFD Failure If the PFD automatically entered reversionary mode: DISPLAY BACKUP button on audio panel ..PUSH (button will be OUT) The system will remain in reversionary mode even if the problem causing the automatic entry of reversionary mode is resolved.
Page 74 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC AHRS Failure NOTE A failure of the Attitude and Heading Reference System (AHRS) is indicated by a removal of the sky/ground presentation and insertion of a red X and a yellow “AHRS FAILURE”...
Page 75 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES WARNING Information normally derived from GPS turns amber. Information will become more inaccurate over time. WARNING TAWS is Inoperative. NOTE DR mode uses heading, airspeed and last known GPS position to estimate the airplanes current position.
Page 76 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC Air Data Computer (ADC) Failure NOTE Complete loss of the Air Data Computer (ADC) is indicated by a red X and yellow text over the airspeed, altimeter, vertical speed, TAS and OAT displays. Some FMS functions, such as true airspeed and wind calculations, will be lost.
Page 77 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES Erroneous or Loss of Warning/Caution Annunciators NOTE Loss of an annunciator may be indicated when engine or fuel displays show an abnormal or emergency situation and the annunciator is not present. An erroneous annunciator may be identified when an annunciator appears which does not agree with other displays or system information.
Page 78 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC TURBOCHARGER FAILURE CAUTION If a turbocharger failure is the result of loose, disconnected or burned through exhaust system components, a potentially serious fire hazard exists as well as the risk of carbon monoxide migration into the passenger compartment of the aircraft.
Page 79 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES ENGINE POWER OVERBOOST If the turbocharger wastegate control fails in the CLOSED position, an engine power overboost condition may occur. The following procedure is recommended for an overboost condition: Throttle ....REDUCE as necessary to keep manifold pressure within limits...
Page 80 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC EMERGENCY LANDING GEAR EXTENSION NOTE Refer to paragraph 4.47 for differences when emergency gear extension is being performed for training purposes. Prior to emergency extension procedure: Battery master switch ................check ON ALTR switch..................check ON STBY ALTR switch................check ON...
Page 81 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES OPEN DOOR Cabin Door: If the cabin 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...
Page 82 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC AMPLIFIED EMERGENCY PROCEDURES (GENERAL) The following paragraphs are presented to supply additional information for the purpose of providing the pilot with a more complete understanding of the recommended course of action and probable cause of an emergency situation.
Page 83 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES 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).
Page 84 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC 3.15 POWER OFF LANDING If loss 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;...
Page 85 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES 3.17 FIRE IN FLIGHT The presence of fire is noted through smoke, smell and heat in the cabin. It is essential that the source of the fire be promptly identified through instrument readings, characteristics of the smoke, or other indications, since the action to be taken differs somewhat in each case.
Page 86 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC 3.17 FIRE IN FLIGHT (continued) Turn the BATT MASTR, MAIN ALT, and STBY ALT switches OFF. The cabin vents should be opened and the cabin heater and defroster turned OFF. Monitor the EMER BATT voltage and land as soon as possible.
Page 87 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES 3.17 FIRE IN FLIGHT (continued) NOTE When operating the aircraft with the LDG GR PUMP circuit breaker pulled, the pilot must perform a manual gear extension. Landing gear position indicator lights will not...
Page 88 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC 3.17 FIRE IN FLIGHT (continued) If additional electrical power is required beyond the time supplied by the main battery and emergency battery, the standby alternator may be used to provide supplemental power for an indefinite period of time. The battery master switch and standby alternator switch should be turned on and the propeller control should be set to maintain a minimum of 2400 RPM.
Page 89 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES 3.19 LOSS OF OIL PRESSURE Loss of oil pressure may be either partial or complete. A partial loss of oil pressure usually indicates a malfunction in the oil pressure regulating system, and a landing should be made as soon as possible to investigate the cause and prevent engine damage.
Page 90 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC 3.23 ENGINE DRIVEN FUEL PUMP FAILURE If an engine driven fuel pump failure is indicated, retard the throttle and turn 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.
Page 91 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES 3.26 TURBINE INLET TEMPERATURE (TIT) INDICATOR FAILURE In the event the Turbine Inlet Temperature (TIT) indicator or sensor fails during flight, continued flight is possible using conservative mixture/TIT settings. If TIT failure occurs during takeoff, climb, descent, or landing, maintain a full rich mixture to assure adequate fuel flow for engine cooling.
Page 92 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC 3.27 ELECTRICAL FAILURES Main Alternator Failure WARNING Compass error may exceed 10 degrees with the Main Alternator Inoperative and Standby Alternator and/or the Emergency Battery ON. Loss of main alternator failure is indicated by a red ALTNTR INOP annunciator on the primary flight display.
Page 93 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES 3.27 ELECTRICAL FAILURES (continued) Main and Standby Alternator Failure If STBY ALT FAIL is also annunciated on the primary flight display, turn the EMER BATT switch ON and land as soon as practical.
Page 94 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC 3.27 ELECTRICAL FAILURES (continued) The following equipment is available on the Essential Bus. This equipment may be deselected by pulling the associated circuit breaker as noted. Some equipment is dual fed via the emergency battery and the essential bus therefore cannot be disabled as long as the EMER BATT switch is engaged.
Page 95 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES 3.29 ELECTRICAL OVERLOAD If abnormally high alternator output is observed (more than 20 amps above known electrical load for the operating conditions) it may be caused by a low battery, a battery fault or other abnormal electrical load. If the cause is a low battery, the indication should begin to decrease toward normal within 5 minutes.
Page 96 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC 3.31 AVIONICS EMERGENCIES PFD or MFD Display Failure Should a failure occur in either display, push the DISPLAY BACKUP button on the audio panel to enter reversionary mode, which will present critical flight and engine instrumentation on the remaining display. Minimal navigation capability will also be available on the remaining display.
Page 97 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES Dual GPS Failure In the event of a dual GPS failure alternate sources of navigation (i.e. ILS, LOC, VOR, DME, ADF) can be used to continue the flight. Should alternate navigation sources not be available and the aircraft is greater than 30 NM from the destination airport the Dead Reckoning (DR) mode feature of the Garmin, G-1000 can be used for enroute navigation.
Page 98 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC Erroneous or Loss of Engine and Fuel Displays NOTE Loss of an engine parameter is indicated by a red X through the data field. Erroneous information may be identified by indications which do not agree with other system information.
Page 99 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES Loss of Standby Attitude Indicator If the OFF warning flag is in view or if the standby attitude indicator has tumbled or is showing an erroneous attitude display, immediately establish the aircraft in straight and level unaccelerated flight.
Page 100 SECTION 3 EMERGENCY PROCEDURES PA-32R-301T, SARATOGA II TC 3.33 TURBOCHARGER FAILURE CAUTION If a turbocharger failure is the result of loose, disconnected or burned through exhaust system components, a potentially serious fire hazard exists as well as the risk of carbon monoxide migration into the passenger compartment of the aircraft.
Page 101 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES 3.33 TURBOCHARGER FAILURE (continued) ENGINE POWER OVERBOOST If the turbocharger wastegate control fails in the CLOSED position, an engine power overboost condition may occur. The following procedure is recommended for an overboost condition: Throttle ....REDUCE as necessary to keep manifold pressure within limits...
Page 102 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES 3.37 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. Check that the landing gear selector is in the gear down position.
Page 103 SECTION 3 PA-32R-301T, SARATOGA II TC EMERGENCY PROCEDURES 3.41 OPEN DOOR Cabin Door: 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.
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Page 105 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Paragraph Page General ..................Airspeeds for Safe Operations ............Normal Procedures Checklist ............Preflight Check................Engine Start General ..............Before Starting Engine .............. 4-10 Normal Start - Cold Engine ............
Page 106 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC TABLE OF CONTENTS (continued) SECTION 4 (continued) Amplified Normal Procedures ............4-25 Preflight Check ................4-25 4.11 Before Starting Engine..............4-31 4.13 Starting Engine................4-32 4.15 Warm-Up..................4-35 4.17 Taxiing................... 4-36 4.19 Ground Check ................
Page 107 GENERAL This section provides the normal operating procedures for the PA-32R-301T Saratoga II TC. All of the normal operating procedures required by the FAA, as well as those procedures that have been determined as necessary for the operation of the airplane, as determined by the operating and design features of the airplane, are presented.
Page 108 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC 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.
Page 109 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: April 9, 2007 REPORT: VB-1975...
Page 110 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC 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. WALK-AROUND Figure 4-1 REPORT: VB-1975 ISSUED: April 9, 2007...
Page 111 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES COCKPIT CAUTION When draining any amount of fuel, care should be taken to ensure that no fire hazard exists before starting engine. Control wheel ................release restraints Fuel strainer ..........drain & check for water & sediment Parking brake ....................set...
Page 112 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC RIGHT WING Surface condition ..............clear of ice, frost, snow Flap and hinges....................check Aileron and hinges...................check Static wicks ..................check - secure Wing tip and nav/strobe lights.................check Fuel tank.................check supply visually - secure cap External fuel quantity gauge................check...
Page 113 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES LEFT WING 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.
Page 114 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC MISCELLANEOUS BATT MASTR switch..................ON Flaps................retract to full up position Interior lighting (Night flight) ............ON and check Pitot heat switch ....................ON PITOT OFF/PITOT FAIL annunciators on PFD......extinguished CAUTION Care should be taken when an operational check of the heated pitot head is being performed.
Page 115 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES ENGINE START - GENERAL WARNING IFR flight should not be initiated if the condition of the emergency battery is not known to be in satisfactory condition prior to takeoff. CAUTION Do not attempt flight if there is no indication of alternator output.
Page 116 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC BEFORE STARTING ENGINE Parking brake ....................set Fuel selector..................desired tank Circuit breakers ..................check in Alternate air....................CLOSE Friction control handle................as desired Mixture....................idle cut-off Propeller..................full INCREASE Throttle......................idle Avionics Bus MASTR switch ...............OFF EMER BATT switch..................OFF Electrical switches ..................OFF...
Page 117 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES NORMAL START - COLD ENGINE Throttle....................1/2 in. open BATT MASTR switch................. Verify ON ALTR switch ....................ON STBY ALTR switch ..................ON Electric fuel pump ...................ON Magneto switches....................ON Fin strobe......................ON Engine instruments ..............Verify no Red-X’s Mixture ................prime - then idle cut-off...
Page 118 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC ENGINE START WHEN FLOODED Throttle ....................open full BATT MASTR switch................Verify ON ALTR switch ....................ON STBY ALTR switch ..................ON Electric fuel pump ..................OFF Magneto switches....................ON Fin Strobe ......................ON Engine instruments ..............Verify no Red-X’s Mixture ....................idle cut-off...
Page 119 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES STARTING WITH EXTERNAL POWER SOURCE CAUTION It is possible to use the main 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 main battery has been depleted, the external power supply can be reduced to the level of the main battery.
Page 120 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC WARM-UP Throttle..................1000 to 1200 RPM Avionics Bus MASTR switch ........ON/check database currency Autopilot MASTR switch........ON/verify self-test completed Standby attitude indicator ..............Verify ERECT Electrical equipment ...............ON as required Environmental system ................as desired Fuel quantity....................check Fuel totalizer ............adjust to current fuel quantity...
Page 121 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES TAXIING Taxi area......................clear Parking brake....................release Propeller ..................full INCREASE Throttle....................apply slowly Brakes ......................check Steering......................check NOTE During taxi in hot and/or high altitude conditions, activation of the electric fuel pump may be required for smooth engine operation.
Page 122 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC GROUND CHECK Parking brake ....................set Propeller..................full INCREASE Throttle ....................2000 RPM Magnetos ................max. drop 175 RPM - max. diff. 50 RPM Propeller .............exercise - then full INCREASE CAUTION Alternate air is unfiltered. Use of alternate air during ground or flight operations when dust or other contaminants are present may result in damage from particle ingestion.
Page 123 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES BEFORE TAKEOFF BATT MASTR switch................Verify ON ALTR switch ..................Verify ON STBY ALTR switch ................Verify ON Electric fuel pump ...................ON Magneto switches.................Verify ON Engine instruments ..................check Flight instruments ..................check Alternate air....................CLOSE Mixture....................full forward Propeller..................full INCREASE...
Page 124 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC TAKEOFF NOTE Takeoffs are normally made with full throttle. However, under some off-standard conditions, the manifold pressure indication can exceed its indicated limit at full throttle. Limit manifold pressure to 38 in. Hg. maximum.
Page 125 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES CLIMB NOTE The electric fuel pump must be ON during ALL climb conditions. Mixture .....................full rich Propeller ....................2500 RPM Manifold pressure................38.0 In. Hg. Best rate (3600 lb) (gear down, flaps up)..........80 KIAS Best rate (3600 lb) (gear up, flaps up) ...........95 KIAS...
Page 126 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC NORMAL DESCENT NOTE The figures below are established to meet the values shown in the Time, Fuel and Distance to Descend chart in Section 5. Descent at values other than those shown or if wind is present will yield different results.
Page 127 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES APPROACH AND LANDING CHECK Approach ....................Loaded Nav frequencies ................verify as required Fuel selector valve ..............select fullest tank Seats .....................Adjust & Lock Seat backs......................erect Seat belts/shoulder harnesses............fasten/adjust NOTE With the shoulder harness fastened and adjusted, a pull test of its locking restraint feature should be performed.
Page 128 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC LANDING Normal Technique Flaps ....................as required Airspeed....................90 KIAS Throttle ....................as required After touchdown: Brakes....................as required Short Field Technique Flaps ........................40° Airspeed....................80 KIAS Throttle ....................as required Over obstacle: Throttle...................Reduce to idle Touchdown: Touchdown speed ..................full stall Brakes ....................maximum...
Page 129 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES GO-AROUND Mixture .....................full rich Propeller..................full INCREASE Throttle..................full FORWARD Control wheel ..............back pressure to rotate to climb attitude Autopilot..........Disconnect, if not already disconnected Airspeed....................80 KIAS Flaps ....................retract slowly Landing gear..........UP (after achieving positive climb rate) Trim .....................as required...
Page 130 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC STOPPING ENGINE CAUTION The flaps must be placed in the up position for the flap stop to support weight. Passengers should be cautioned accordingly. Flaps......................retract Electric fuel pump ..................OFF Air conditioner....................OFF Avionics Bus MASTR switch ...............OFF Electrical switches ..................OFF...
Page 131 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES AMPLIFIED NORMAL PROCEDURES (GENERAL) The following paragraphs are provided to supply detailed information and the explanation of the normal procedures for operation of the airplane. PREFLIGHT CHECK Prior to entering the cockpit place a container under the fuel strainer valve located under the fuselage.
Page 132 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC COCKPIT CAUTION When draining any amount of fuel, care should be taken to ensure that no fire hazard exists before starting engine. Upon entering the cockpit, release the seat belts securing the control wheel.
Page 133 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES RIGHT WING Begin the walk-around at the trailing edge of the right wing by checking that the wing surface and control surfaces are clear of ice, frost, snow or other extraneous substances. Check the flap, aileron and hinges for damage and operational interference.
Page 134 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC NOSE SECTION Check the windshield and clean if necessary. Check the general condition of the nose section. Look for oil or fluid leakage and that the cowling is secure. Verify the nose baggage door is closed and secured. The propeller and spinner should be checked for detrimental nicks, cracks, or other defects.
Page 135 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES FUSELAGE Verify all baggage is stowed properly and the rear baggage door is closed and secured. Check the condition of any antennas located on the fuselage. Check that the static vent holes are free of obstructions. Check aft oxygen discharge disc for rupture.
Page 136 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC ENGINE START - GENERAL WARNING IFR flight should not be initiated if the condition of the emergency battery is not known to be in satisfactory condition prior to takeoff. CAUTION Do not attempt flight if there is no indication of alternator output.
Page 137 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES 4.11 BEFORE STARTING ENGINE Set the parking brake and move the fuel selector to the desired tank before starting the engine. Check to make sure all the circuit breakers are in and the alternate air is in the CLOSE (off) position.
Page 138 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC 4.13 STARTING ENGINE (a) NORMAL START: Cold Engine Open the throttle lever approximately 1/2 inch. Verify the battery master switch is ON, and turn on the alternator and standby alternator switches. Turn on the electric fuel pump and magneto switches.
Page 139 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES (d) Starting Engine With External Power Source CAUTION It is possible to use the ship’s battery in parallel by turning the battery master switch ON. This will give longer cranking capabilities, but will not increase the amperage.
Page 140 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC (d) Starting Engine With External Power Source (continued) Starter manufacturers recommend that cranking periods be limited to thirty seconds with a two minute rest between cranking periods. Longer cranking periods will shorten the life of the starter.
Page 141 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES 4.15 WARM-UP NOTE Do not operate the engine at high RPM when running up or taxiing over ground containing loose stones, gravel or any loose material that may cause damage to the propeller blades.
Page 142 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC 4.17 TAXIING NOTE Do not operate the engine at high RPM when running up or taxiing over ground containing loose stones, gravel or any loose material that may cause damage to the propeller blades.
Page 143 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES 4.19 GROUND CHECK Set the parking brake. The magnetos should be checked at 2000 RPM with the propeller set at high RPM. Drop off on either magneto should not exceed 175 RPM and the difference between the magnetos should not exceed 50 RPM.
Page 144 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC 4.21 BEFORE TAKEOFF All aspects of each particular takeoff should be considered prior to executing the takeoff procedure. After all aspects of the takeoff are considered, a pre-takeoff check procedure must be performed.
Page 145 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES 4.23 TAKEOFF NOTE Takeoffs are normally made with full throttle. However, under some off-standard conditions, the manifold pressure indication can exceed its indicated limit at full throttle. Limit manifold pressure to 38 in. Hg. maximum.
Page 146 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC 4.25 CLIMB NOTE The electric fuel pump must be ON during ALL climb conditions. The best rate of climb at gross weight and maximum continuous power will be obtained at 95 KIAS. The recommended procedure for climb is to use maximum continuous power with the mixture full rich, propeller speed set to 2500 RPM and manifold pressure at 38.0 inches of mercury.
Page 147 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES 4.27 CRUISE WARNING Operation above 20,000 feet is not approved. NOTE To obtain the performance presented in the Performance Section of this handbook, all conditions listed on the performance charts must be met.
Page 148 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC 4.27 CRUISE (continued) In order to keep the airplane in best lateral trim during cruise flight, the fuel should be used alternately from each tank at one hour intervals. Always remember that the electric fuel pump should be turned ON before switching tanks, and should be left on for a short period thereafter.
Page 149 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES 4.31 APPROACH AND LANDING Accomplish the Landing Checklist early in the landing approach. NOTE If flying an LNAV/VNAV or LPV approach, be prepared to fly the LNAV only approach prior to reaching the final approach fix (FAF). If the GPS...
Page 150 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC 4.33 LANDING Normal technique When available runway length is in excess of required runway length, a normal landing technique may be utilized. The aircraft should be flown down the final approach course at 90 KIAS with flaps set as required and power set as required to maintain the desired approach angle.
Page 151 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES 4.35 GO-AROUND To initiate a go-around from a landing approach, the mixture control should be moved to full rich, the propeller control should be set to full increase and the throttle should be advanced to full forward while the pitch attitude is increased to obtain the balked landing climb speed of 80 KIAS.
Page 152 4.43 STALLS The stall characteristics of the Saratoga II TC are conventional. An approaching stall is indicated by a stall warning horn which is activated between five and ten knots above stall speed. Mild airframe buffeting and gentle pitching may also precede the stall.
Page 153 SECTION 4 PA-32R-301T, SARATOGA II TC NORMAL PROCEDURES 4.45 TURBULENT AIR OPERATION In keeping with good operating practice used in all aircraft, it is recommended that when turbulent air is encountered or expected, the airspeed be reduced to maneuvering speed to reduce the structural...
Page 154 SECTION 4 NORMAL PROCEDURES PA-32R-301T, SARATOGA II TC 4.49 WEIGHT AND BALANCE It is the responsibility of the owner and pilot to determine that the airplane remains within the allowable weight vs. center of gravity envelope while in flight. For weight and balance data, refer to Section 6 (Weight and Balance).
Page 155 SECTION 5 PA-32R-301T, SARATOGA II TC PERFORMANCE TABLE OF CONTENTS SECTION 5 Paragraph Page General ..................Introduction - Performance and Flight Planning ......Demonstrated Operating Temperature .......... Flight Planning Example............... Performance Graphs List of Figures ..............ISSUED: April 9, 2007...
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Page 157 GENERAL All of the required (FAA regulations) and complementary performance information applicable to the Saratoga II TC is provided in this section. Performance information associated with those optional systems and equipment which require handbook supplements is provided in Section 9 (Supplements).
Page 158 SECTION 5 PERFORMANCE PA-32R-301T, SARATOGA II TC DEMONSTRATED OPERATING TEMPERATURE Satisfactory engine cooling has been demonstrated for this model aircraft to an Outside Air Temperature (OAT) of ISA +22°C for a standard day. This is not to be considered as an operating limitation. Reference should be made to Section 2 for engine operating limitations.
Page 159 SECTION 5 PA-32R-301T, SARATOGA II TC PERFORMANCE FLIGHT PLANNING EXAMPLE (a)Aircraft Loading The first step in planning the flight is to calculate the airplane weight and center of gravity by utilizing the information provided by Section 6 (Weight and Balance) of this handbook.
Page 160 SECTION 5 PERFORMANCE PA-32R-301T, SARATOGA II TC (b) Takeoff and Landing After determining the aircraft loading, all aspects of the takeoff and landing must be considered. All of the existing conditions at the departure and destination airport must be acquired, evaluated and maintained throughout the flight.
Page 161 SECTION 5 PA-32R-301T, SARATOGA II TC PERFORMANCE NOTE The remainder of the performance charts used in this flight plan example assume a no wind condition. The effect of winds aloft must be considered by the pilot when computing climb, cruise and descent performance.
Page 162 SECTION 5 PERFORMANCE PA-32R-301T, SARATOGA II TC (d) Descent The descent data will be determined prior to the cruise data to provide the descent distance for establishing the total cruise distance. Utilizing the cruise pressure altitude and OAT, determine the basic fuel, distance and time for descent (Figure 5-51).
Page 163 SECTION 5 PA-32R-301T, SARATOGA II TC PERFORMANCE The cruise time is found by dividing the cruise distance by the cruise speed and the cruise fuel is found by multiplying the cruise fuel consumption by the cruise time. The cruise calculations established for the cruise segment of the...
Page 164 SECTION 5 PERFORMANCE PA-32R-301T, SARATOGA II TC (g) Total Fuel Required Determine the total fuel required by adding the fuel to climb, the fuel to descend and the cruise fuel. When the total fuel (in gallons) is determined, multiply this value by 6 lb/gal to determine the total fuel weight used for the flight.
Page 165 SECTION 5 PA-32R-301T, SARATOGA II TC PERFORMANCE PERFORMANCE GRAPHS LIST OF FIGURES Figure Page Fahrenheit to Celsius Temperature Conversion ....5-11 ISA Conversion ..............5-12 Feet to Meters Conversion (0 to 20,000 feet) ..... 5-13 Feet to Meters Conversion (0 to 100 feet) ......
Page 166 SECTION 5 PERFORMANCE PA-32R-301T, SARATOGA II TC PERFORMANCE GRAPHS (continued) LIST OF FIGURES (continued) Figure Page 5-51 Fuel, Time and Distance to Descend........5-38 5-53 Glide Range................. 5-39 5-55 Balked Landing Climb Performance........5-40 5-57 Landing Performance ............5-41 5-59 Landing Ground Roll ............
Page 167 SECTION 5 PA-32R-301T, SARATOGA II TC PERFORMANCE Fahrenheit to Celsius Temperature Conversion Figure 5-1 ISSUED: April 9, 2007 REPORT: VB-1975 5-11...
Page 169 SECTION 5 PA-32R-301T, SARATOGA II TC PERFORMANCE Feet to Meters Conversion (0 to 20,000 feet) Figure 5-5 ISSUED: April 9, 2007 REPORT: VB-1975 5-13...
Page 170 SECTION 5 PERFORMANCE PA-32R-301T, SARATOGA II TC Feet to Meters Conversion (0 to 100 feet) Figure 5-7 REPORT: VB-1975 ISSUED: April 9, 2007 5-14...
Page 171 SECTION 5 PA-32R-301T, SARATOGA II TC PERFORMANCE Pounds to Kilograms Conversion (600 to 3,600 pounds) Figure 5-9 ISSUED: April 9, 2007 REPORT: VB-1975 5-15...
Page 172 SECTION 5 PERFORMANCE PA-32R-301T, SARATOGA II TC Pounds to Kilograms Conversion (0 to 600 pounds) Figure 5-11 REPORT: VB-1975 ISSUED: April 9, 2007 5-16...
Page 173 SECTION 5 PA-32R-301T, SARATOGA II TC PERFORMANCE Inches to Centimeters Conversion Figure 5-13 ISSUED: April 9, 2007 REPORT: VB-1975 5-17...
Page 174 SECTION 5 PERFORMANCE PA-32R-301T, SARATOGA II TC Inches of Mercury to Millibars Conversion Figure 5-15 REPORT: VB-1975 ISSUED: April 9, 2007 5-18...
Page 175 SECTION 5 PA-32R-301T, SARATOGA II TC PERFORMANCE U.S. Gallons to Liters Conversion Figure 5-17 ISSUED: April 9, 2007 REPORT: VB-1975 5-19...
Page 176 SECTION 5 PERFORMANCE PA-32R-301T, SARATOGA II TC Wind Components Figure 5-19 REPORT: VB-1975 ISSUED: April 9, 2007 5-20...
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Page 189 SECTION 5 PA-32R-301T, SARATOGA II TC PERFORMANCE NOTE This chart defines the maximum manifold pressure allowed for normal operations and should not be exceeded. Under standard day conditions, 300 bhp (38” MAP @ 2500 rpm) is available at 12,000 ft. density altitude minimum.
Page 199 SECTION 6 PA-32R-301T, SARATOGA II TC WEIGHT AND BALANCE TABLE OF CONTENTS SECTION 6 WEIGHT AND BALANCE Paragraph Page General ..................Airplane Weighing Procedure ............Weight and Balance Data and Record .......... General Loading Recommendations..........Weight and Balance Determination for Flight......
Page 200 SECTION 6 WEIGHT AND BALANCE PA-32R-301T, SARATOGA II TC THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1975 ISSUED: April 9, 2007 6-ii...
Page 201 SECTION 6 PA-32R-301T, SARATOGA II TC WEIGHT AND BALANCE SECTION 6 WEIGHT AND BALANCE GENERAL In order to achieve the performance and flying characteristics which are designed into the airplane, it must be flown with the weight and center of gravity (C.G.) position within the approved operating range (envelope).
Page 202 Following this is the method for computing takeoff weight and C.G. AIRPLANE WEIGHING PROCEDURE At the time of licensing, Piper provides each airplane with the basic empty weight and center of gravity location. This data is supplied by Figure 6-5.
Page 203 SECTION 6 PA-32R-301T, SARATOGA II TC WEIGHT AND BALANCE CAUTION Whenever the fuel system is completely drained and fuel is replenished it will be necessary to run the engine for a minimum of three minutes at 1000 RPM on each tank to insure that no air exists in the fuel supply lines.
Page 204 SECTION 6 WEIGHT AND BALANCE PA-32R-301T, SARATOGA II TC Scale Position Scale and Symbol Reading Tare Weight Nose Wheel Right Main Wheel Left Main Wheel Basic Empty Weight, as Weighed WEIGHING FORM Figure 6-1 (d) Basic Empty Weight Center of Gravity (1) The following geometry applies to the PA-32R-301T airplane when it is level.
Page 205 SECTION 6 PA-32R-301T, SARATOGA II TC WEIGHT AND BALANCE (2) The basic empty weight center of gravity (as weighed including optional equipment, full oil and unusable fuel) can be determined by the following formula: C.G. Arm = N (A) + (R + L) (B)
Page 206 SECTION 6 WEIGHT AND BALANCE PA-32R-301T, SARATOGA II TC MODEL PA-32R-301T Saratoga II TC Airplane Serial Number _____________________ Registration Number________________________ Date _____________________________________ AIRPLANE BASIC EMPTY WEIGHT C.G. Arm Weight x (Inches Aft = Moment Item (Lbs) of Datum) (In-Lbs) Actual...
Page 207 Page Number Serial Number PA-32R-301T Registration Number Running Basic Weight Change Description of Article Empty Weight DATE or Modification Moment Moment (in) (lb) (lb) /100 /100 As licensed...
Page 208 Page Number Serial Number PA-32R-301T Registration Number Running Basic Weight Change Description of Article Empty Weight DATE or Modification Moment Moment (in) (lb) (lb) /100 /100...
Page 209 SECTION 6 PA-32R-301T, SARATOGA II TC WEIGHT AND BALANCE GENERAL LOADING RECOMMENDATIONS The following general loading recommendation is intended only as a guide. The charts, graphs and instructions should be checked to assure that the airplane is within the allowable weight vs. center of gravity envelope.
Page 210 SECTION 6 WEIGHT AND BALANCE PA-32R-301T, SARATOGA II TC WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (a) Add the weight of all items to be loaded to the basic empty weight. (b) Use the Loading Graph (Figure 6-13) to determine the moment of all items to be carried in the airplane.
Page 211 SECTION 6 PA-32R-301T, SARATOGA II TC WEIGHT AND BALANCE Arm Aft Weight Datum Moment (Lbs) (Inches) (In-Lbs) Basic Empty Weight 2272 83.4 189485 Pilot and Front Passenger 340.0 85.5 29070 Passengers (Center Seats)(Aft Facing) 119.1 Passengers (Rear Seats) 340.0 157.6...
Page 212 SECTION 6 WEIGHT AND BALANCE PA-32R-301T, SARATOGA II TC Arm Aft Weight Datum Moment (Lbs) (Inches) (In-Lbs) Basic Empty Weight Pilot and Front Passenger 85.5 Passengers (Center Seats) (Aft Facing) 119.1 Passengers (Rear Seats) 157.6 Fuel (102 Gallon Maximum) 94.0 Baggage (Forward) (100 Lb.
Page 213 SECTION 6 PA-32R-301T, SARATOGA II TC WEIGHT AND BALANCE LOADING GRAPH Figure 6-13 ISSUED: April 9, 2007 REPORT: VB-1975 6-13...
Page 214 SECTION 6 WEIGHT AND BALANCE PA-32R-301T, SARATOGA II TC C.G. RANGE AND WEIGHT Figure 6-15 REPORT: VB-1975 ISSUED: April 9, 2007 6-14...
Page 215 SECTION 7 PA-32R-301T, SARATOGA II TC DESCRIPTION & OPERATION TABLE OF CONTENTS SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS Paragraph Page The Airplane ................ Airframe ................Engine and Propeller ............Engine Controls..............Landing Gear ............... 7.11 Flight Controls..............
Page 216 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1975 ISSUED: April 9, 2007 7-ii...
Page 217 OF THE AIRPLANE AND ITS SYSTEMS THE AIRPLANE The Saratoga II TC is a single engine, low wing, retractable landing gear airplane. It is all metal, seats up to six occupants, and has two separate one hundred pound capacity baggage compartments.
Page 218 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC The wing is of a semi-tapered design and employs a laminar flow NACA -415 airfoil section. The main spar is located at approximately 40% of the chord aft of the leading edge. The wings are attached to the fuselage by the insertion of the butt ends of the spar into a spar box carry-through, which is an integral part of the fuselage structure.
Page 219 SECTION 7 PA-32R-301T, SARATOGA II TC DESCRIPTION & OPERATION ENGINE AND PROPELLER The six cylinder, horizontally opposed, fuel injected, turbocharged engine is rated at 300 horsepower at 2500 rpm and 38 inches of MAP. Oil flow is thermostatically controlled through a remote mounted oil cooler, and filtration is provided by an engine mounted oil filter.
Page 220 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC To obtain maximum efficiency and time from the engine, follow the procedures recommended in the Textron Lycoming Operators Manual provided with the airplane. The constant speed propeller is controlled by a governor mounted at the left forward side of the crankcase.
Page 221 SECTION 7 PA-32R-301T, SARATOGA II TC DESCRIPTION & OPERATION CONTROL QUADRANT AND CONSOLE Figure 7-1 ISSUED: April 9, 2007 REPORT: VB-1975...
Page 222 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC LANDING GEAR LANDING GEAR CONTROLS Figure 7-3 The airplane is equipped with a retractable tricycle landing gear, which is hydraulically actuated by an electrically powered reversible pump. The pump is controlled by a wheel-shaped selector switch on the instrument panel to the left of the control quadrant (Figure 7-3).
Page 223 SECTION 7 PA-32R-301T, SARATOGA II TC DESCRIPTION & OPERATION Gear down and locked positions are indicated by three green lights located above the gear selector, and a red GEAR WARN light is located just above the three green lights. An all lights out condition indicates the gear is up.
Page 224 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC The standard brake system includes toe brakes on the left and right set of rudder pedals and a hand brake located below and near the center of the instrument panel. The toe brakes and the hand brake have individual brake cylinders, but all cylinders use a common reservoir.
Page 225 SECTION 7 PA-32R-301T, SARATOGA II TC DESCRIPTION & OPERATION LANDING GEAR ELECTRICAL SCHEMATIC Figure 7-5 ISSUED: April 9, 2007 REPORT: VB-1975...
Page 226 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC LANDING GEAR HYDRAULIC SYSTEM SCHEMATIC Figure 7-7 REPORT: VB-1975 ISSUED: April 9, 2007 7-10...
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Page 228 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC 7.11 FLIGHT CONTROLS Dual flight controls are provided as standard equipment. A cable system provides actuation of the control surfaces when the flight controls are moved in their respective directions. The horizontal surface (stabilator) features a trim tab/servo mounted on the trailing edge.
Page 229 SECTION 7 PA-32R-301T, SARATOGA II TC DESCRIPTION & OPERATION The wing flaps are electrically controlled (Figure 7-11) by a selector lever (Figure 7-1) mounted on the instrument panel to the right of the control pedestal. Selection of a new flap position activates the flap motor and, after the flaps reach the desired position, the flap motor is automatically switched off.
Page 231 DESCRIPTION & OPERATION 7.13 FUEL SYSTEM The standard fuel capacity of the Saratoga II TC is 107 gallons, of which 102 gallons are usable. The inboard tank is attached to the wing structure with screws and nut plates and can be removed for service or inspection.
Page 232 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC FLOW DIVIDER FUEL NOZZLES FUEL INJECTOR TRANSDUCER ENGINE DRIVEN FUEL PUMP FUEL FLOW GEA-71 ELECTRIC FUEL PUMP FUEL SELECTOR VALVE FUEL FUEL FUEL FUEL CELL CELL CELL CELL VENT VENT GEA-71...
Page 233 SECTION 7 PA-32R-301T, SARATOGA II TC DESCRIPTION & OPERATION FUEL DRAIN LEVER Figure 7-15 After using the underseat quick drain, check from the outside to make sure that it has closed completely and is not leaking. Fuel flow and fuel quantity indications are presented on the Multi- Function Display.
Page 234 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC 7.15 ELECTRICAL SYSTEM The 28-volt electrical system is comprised of four power supplies and four power distribution busses. The power supplies consist of a main battery, main alternator, standby alternator and emergency battery. The power distribution busses consist of an essential bus, main bus, avionics bus and emergency bus.
Page 235 SECTION 7 PA-32R-301T, SARATOGA II TC DESCRIPTION & OPERATION Standby Alternator A 20-amp standby alternator is installed to automatically provide electrical power to the electrical system any time the essential bus voltage drops below 27 volts. The standby alternator is tied directly to the essential bus. During normal operations the standby alternator will not produce power.
Page 236 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC Emergency Battery A 3.5 amp-hour rechargeable emergency battery is installed to provide 30 minutes of electrical power should the main alternator and standby alternator fail. The emergency battery is tied directly to the emergency bus, which after...
Page 237 EMER EMER STBY STBY STBY STBY BATT BATT ALTERNATOR ALTERNATOR ALTNR ALTNR SWITCH SWITCH FIELD FIELD VOLT REG VOLT REG TO GEA FOR ALTERNATOR CURRENT TO GEA FOR ALTERNATOR CURRENT ALTERNATOR ALTERNATOR STANDBY STANDBY MAIN MAIN STBY STBY SHUNT SHUNT ALTERNATOR ALTERNATOR ALTERNATOR...
Page 238 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC The electrical system is divided into four power busses as follows: Essential Bus The Essential bus is tied directly to the main aircraft battery via the battery master switch. When the battery master switch is turned on, power is immediately supplied to the Essential bus.
Page 239 SECTION 7 PA-32R-301T, SARATOGA II TC DESCRIPTION & OPERATION All powerplant and exterior light switches are grouped in the overhead switch panel and all avionics switches are grouped in a switch panel located just above the throttle quadrant (see Figure 7-19 for switch details). The circuit breaker panel is located on the lower right side of the instrument panel (Figure 7-21).
Page 240 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC START FUEL BATT STBY LEFT PUMP RIGHT ALTR ALTR MASTR Overhead Switch Panel - Left Side STROBE LANDING LIGHTS LIGHTS TAXI PULSE LIGHT STROBE LIGHT Overhead Switch Panel - Right Side...
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Page 243 7.17 GARMIN G1000 AVIONICS SYSTEM NOTE Refer to the Garmin G1000 Cockpit Reference Guide for the Piper PA32, p/n 190-00416-01, latest revision, for complete descriptions of the G1000 system and operating procedures. The Garmin G1000 Integrated Avionics System consists of a Primary...
Page 244 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC Primary Flight Display The Primary Flight Display (PFD) typically displays airspeed, attitude, altitude, and heading information in a traditional format. Slip information is shown as a trapezoid under the bank pointer. One width of the trapezoid is equal to a one ball width slip.
Page 245 SECTION 7 PA-32R-301T, SARATOGA II TC DESCRIPTION & OPERATION Primary Flight Display (continued) The primary function of the VHF Communication portion of the Garmin G1000 is to enable external radio communications. The primary function of the VOR/ILS Receiver portion of the equipment is to receive VOR, Localizer, and Glide Slope signals.
Page 246 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC Autopilot Integration The Entegra PFD is fully integrated with the S-TEC System 55X Autopilot. Reference bugs for Heading and Altitude are provided on the PFD to control the autopilot and aid pilot situational awareness. Vertical Speed is set using the VS knob on the autopilot computer.
Page 247 SECTION 7 PA-32R-301T, SARATOGA II TC DESCRIPTION & OPERATION Autopilot Integration (continued) The following autopilot modes are supported by the PFD: Lateral Modes: 1. HDG (Heading, using the heading bug) 2. NAV (Nav, using the course pointer and course deviation indicator) 3.
Page 248 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC Multi-Function Display The Multi-Function Display (MFD) typically displays engine data, maps, terrain, traffic, and topography displays, and flight planning and progress information. The display unit is identical to the PFD and contains the same controls as previously listed.
Page 249 SECTION 7 PA-32R-301T, SARATOGA II TC DESCRIPTION & OPERATION Audio Panel The audio panel contains traditional transmitter and receiver selectors, as well as an integral intercom and marker beacon system. The marker beacon lights appear on the PFD. In addition, a clearance recorder records the last 2½ minutes of received audio.
Page 250 G1000 Integrated Cockpit. All Communications, Navigation, Engine Instruments, and System Annunciations have been integrated into a custom design package specifically for the PA-32R-301T Saratoga II TC. Engine, electrical, and exterior light switches are located in an overhead switch panel. The row of switches on the left side of the overhead switch panel includes the Starter, Battery Master, Alternator, Standby Alternator, Electric Fuel Pump, and Left and Right Magnetos.
Page 252 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC 7.21 PITOT-STATIC SYSTEM The pitot static system (Figure 7-25) supplies both pitot and static pressure for the primary and standby airspeed indicators and static pressure for the primary and standby altimeter and vertical speed indicator. Pitot pressure for the...
Page 253 SECTION 7 PA-32R-301T, SARATOGA II TC DESCRIPTION & OPERATION PITOT AND STATIC PRESSURE SYSTEM Figure 7-25 ISSUED: April 9, 2007 REPORT: VB-1975 7-37...
Page 254 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC 7.23 CABIN FEATURES For ease of entry and exit and for pilot and passenger comfort, the front seats are adjustable fore and aft. All seats recline and have optional head and arm rests.
Page 255 SECTION 7 PA-32R-301T, SARATOGA II TC DESCRIPTION & OPERATION 7.25 BAGGAGE AREA The airplane has two separate baggage areas, each with a 100 pound capacity. A 7 cubic foot forward luggage compartment, located just aft of the fire wall, is accessible through a 16 x 22 inch door on the right side of the fuselage.
Page 256 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC 7.27 HEATING AND VENTILATING SYSTEM Fresh air is ducted from a vent in the forward left lower cowling to the heater shroud by a flexible hose. Hot air from the heater shroud is then routed down the right side of the engine compartment to the air box mounted on the firewall.
Page 258 All exterior surfaces are primed with etching primer and finished with acrylic lacquer. To keep the finish attractive looking, economy size spray cans of touch-up paint are available from Piper Dealers. An optional polyurethane enamel finish is available. 7.33 AIR CONDITIONING (optional) The air conditioning system is a recirculating air system.
Page 259 SECTION 7 PA-32R-301T, SARATOGA II TC DESCRIPTION & OPERATION The switches and temperature control are located on the lower right side of the instrument panel in the climate control center panel. The temperature control regulates the temperature of the cabin. Turning the control clockwise increases cooling;...
Page 260 SECTION 7 DESCRIPTION & OPERATION PA-32R-301T, SARATOGA II TC 7.35 EXTERNAL POWER A nominal 24-volt external power source can be used to start the engine when the main battery is not sufficiently charged. The external power receptacle is tied directly to the essential bus in a similar fashion to that of the main battery. The procedures in Section 4 should be followed for external power engine starts.
Page 261 SECTION 7 PA-32R-301T, SARATOGA II TC DESCRIPTION & OPERATION ARTEX 110-4 ELT OPERATION On the ELT unit itself is a two position switch placarded ON and OFF. The OFF position is selected when the transmitter is installed at the factory and the switch should remain in that position whenever the unit is installed in the airplane.
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Page 263 SECTION 8 PA-32R-301T, SARATOGA II TC HANDLING, SERV & MAINT TABLE OF CONTENTS SECTION 8 AIRPLANE HANDLING, SERVICING AND MAINTENANCE Paragraph Page General ..................Airplane Inspection Periods............Preventive Maintenance ..............Airplane Alterations ..............Ground Handling ................8.11 Engine Air Filter ................
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Page 265 AIRPLANE HANDLING, SERVICING, AND MAINTENANCE GENERAL This section provides guidelines relating to the handling, servicing, and maintenance of the Saratoga II TC. For complete maintenance instructions, refer to the latest revision of the appropriate Maintenance Manual. WARNING Inspection, maintenance and parts requirements for all non-PIPER approved STC installations are not included in this handbook.
Page 266 PA-32R-301T, SARATOGA II TC 8.1 GENERAL (CONTINUED) WARNING Use only genuine PIPER parts or PIPER approved parts obtained from PIPER approved sources, in connection with the maintenance and repair of PIPER airplanes. Genuine PIPER parts are produced and inspected under rigorous procedures to insure airworthiness and suitability for use in PIPER airplane applications.
Page 267 Piper’s support systems. Piper takes a continuing interest in having owners get the most efficient use from their airplane and keeping it in the best mechanical condition. Consequently, Piper, from time to time, issues service releases including Service Bulletins, Service Letters, Service Spares Letters, and others relating to the airplane.
Page 268 Piper Authorized Service Center or a reputable repair shop. Piper cannot accept responsibility for the continued airworthiness of any aircraft not maintained to these standards,...
Page 269 SECTION 8 PA-32R-301T, SARATOGA II TC HANDLING, SERV & MAINT AIRPLANE INSPECTION PERIODS (CONTINUED) A spectrographic analysis of the engine oil is available from several sources. This inspection, if performed properly, provides a good check of the internal condition of the engine. To be accurate, induction air filters must be cleaned or changed regularly, and oil samples must be taken and sent in at regular intervals.
Page 270 SECTION 8 HANDLING, SERV & MAINT PA-32R-301T, SARATOGA II TC AIRPLANE ALTERATIONS If the owner desires to have his aircraft modified, he must obtain FAA approval for the alteration. Major alterations accomplished in accordance with Advisory Circular 43.13-2, when performed by an A & P mechanic, may be approved by the local FAA office.
Page 271 SECTION 8 PA-32R-301T, SARATOGA II TC HANDLING, SERV & MAINT GROUND HANDLING (a) Towing The airplane may be moved on the ground by the use of the nose wheel steering bar that is stowed in the rear baggage compartment or by power equipment that will not damage or excessively strain the nose gear steering assembly.
Page 272 SECTION 8 HANDLING, SERV & MAINT PA-32R-301T, SARATOGA II TC (4) Observe wing clearance when taxiing near buildings or other stationary objects. If possible, station an observer outside the airplane. (5) When taxiing over uneven ground, avoid holes and ruts.
Page 273 SECTION 8 PA-32R-301T, SARATOGA II TC HANDLING, SERV & MAINT (5) Secure tie-down ropes to the wing tie-down rings and to the tail ring at approximately 45 degree angles to the ground, When using rope of non-synthetic material, leave sufficient slack to avoid damage to the airplane should the ropes contract.
Page 274 SECTION 8 HANDLING, SERV & MAINT PA-32R-301T, SARATOGA II TC (b) Cleaning the Engine Air Filter (1) Tap gently to remove dirt particles. Do not blow out with compressed air. (2) Flush excessively dirty filter with running water (less than 40 psi) and soak it in a solution of Donaldson D-1400 compound and water.
Page 276 SECTION 8 HANDLING, SERV & MAINT PA-32R-301T, SARATOGA II TC 8.15 LANDING GEAR SERVICE The main landing gear uses Cleveland Aircraft Products 6.00 x 6 wheels with 6.00 x 6, eight-ply rating tires and tubes. The nose wheel uses a Cleveland Aircraft Products 5.00 x 5 wheel with a 5.00 x 5 six-ply rating, type III tire and...
Page 277 SECTION 8 PA-32R-301T, SARATOGA II TC HANDLING, SERV & MAINT 8.17 PROPELLER SERVICE The spinner and backing plate should be cleaned and inspected for cracks frequently. Before each flight the propeller should be inspected for nicks, scratches, and corrosion. If found, they should be repaired as soon as possible by a rated mechanic, since a nick or scratch causes an area of increased stress which can lead to serious cracks or the loss of a propeller tip.
Page 278 SECTION 8 HANDLING, SERV & MAINT PA-32R-301T, SARATOGA II TC (b) Fuel Requirements (AVGAS ONLY) The minimum aviation grade fuel is 100. Since the use of lower grades can cause serious engine damage in a short period of time, the engine warranty is invalidated by the use of lower octanes.
Page 279 SECTION 8 PA-32R-301T, SARATOGA II TC HANDLING, SERV & MAINT CAUTIONS Assure that the additive is directed into the flowing fuel stream. The additive flow should start after and stop before the fuel flow. Do not permit the concentrated additive to come in contact with the aircraft painted surfaces or the interior surfaces of the fuel tanks.
Page 280 SECTION 8 HANDLING, SERV & MAINT PA-32R-301T, SARATOGA II TC FUEL TANK DRAIN Figure 8-3 CAUTION When draining fuel, be sure that no fire hazard exists before starting engine. After using the fuel system quick drain, check from outside the airplane to be sure that it has closed completely and is not leaking.
Page 281 SECTION 8 PA-32R-301T, SARATOGA II TC HANDLING, SERV & MAINT 8.23 TIRE INFLATION For maximum service from the tires, keep them inflated to the proper pressures - 35 psi for the nose gear and 38 psi for the main gear. All wheels and tires are balanced before original installation, and the relationship of tire, tube, and wheel should be maintained upon reinstallation.
Page 282 SECTION 8 HANDLING, SERV & MAINT PA-32R-301T, SARATOGA II TC 8.27 CLEANING (a) Cleaning Engine Compartment Before cleaning the engine compartment, place a strip of tape on the magneto vents to prevent any solvent from entering these units. (1) Place a large pan under the engine to catch waste.
Page 283 SECTION 8 PA-32R-301T, SARATOGA II TC HANDLING, SERV & MAINT (b) Cleaning Landing Gear Before cleaning the landing gear, place a plastic cover or similar material over the wheel and brake assembly. (1) Place a pan under the gear to catch waste.
Page 284 SECTION 8 HANDLING, SERV & MAINT PA-32R-301T, SARATOGA II TC (d) Cleaning Windshield and Windows (1) Remove dirt, mud and other loose particles from exterior surfaces with clean water. (2) Wash with mild soap and warm water or with aircraft plastic cleaner.
Page 285 SECTION 8 PA-32R-301T, SARATOGA II TC HANDLING, SERV & MAINT 8.29 CLEANING GARMIN PFD AND MFD DISPLAYS The Garmin Primary Flight Display (PFD) and Multi-Function Display (MFD) use a lens coated with a special anti-reflective coating that is very sensitive to skin oils, waxes and abrasive cleaners.
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Page 287 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENTS TABLE OF CONTENTS SECTION 9 SUPPLEMENTS Paragraph/Supplement Page General ..................Air Conditioning Installation .........(4 pages) Scott Fixed Oxygen System...........(4 pages) S-TEC System 55X Two Axis Automatic Flight Guidance System with Trim Monitor......... 9-11 TKS Ice Protection System..........(28 pages)
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Page 289 Information pertaining to the operation of these systems is contained in the Garmin G1000 Cockpit Reference Guide for the Piper PA32, p/n 190-00416-01, latest revision and/or the Garmin G1000 Pilot’s Guide for the Piper PA32, Garmin p/n 190-00692-00, latest revision.
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Page 291 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 1 PILOT’S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT 1 AIR CONDITIONING INSTALLATION This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when optional air conditioning is installed.
Page 292 SECTION 9 SUPPLEMENT 1 PA-32R-301T, SARATOGA II TC SECTION 1 - GENERAL This supplement supplies information necessary for the efficient operation of the airplane when the optional air conditioning system is installed. The information contained within this supplement is to be used in conjunction with the complete handbook.
Page 293 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 1 SECTION 4 - NORMAL PROCEDURES Prior to takeoff, the air conditioner should be checked for proper operation as follows: (a) Check aircraft master switch ON. (b) Turn the air conditioner control switch to ON and the fan switch to...
Page 294 SECTION 9 SUPPLEMENT 1 PA-32R-301T, SARATOGA II TC SECTION 5 - PERFORMANCE Operation of the air conditioner will cause slight decreases in cruise speed and range. Power from the engine is required to run the compressor, and the condenser door, when extended, causes a slight increase in drag. When the air conditioner is turned off there is normally no measurable difference in climb, cruise or range performance of the airplane.
Page 295 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 2 PILOT'S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 2 FIXED OXYGEN SYSTEM INSTALLATION SCOTT AVIATION PRODUCTS AMBASSADOR MARK III This supplement must be attached to the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual when the optional fixed oxygen system is installed per the Equipment List.
Page 296 SECTION 9 SUPPLEMENT 2 PA-32R-301T, SARATOGA II TC SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the optional fixed oxygen system is installed in accordance with FAA Approved Piper data. This fixed oxygen system provides supplementary oxygen for the crew and passengers during high altitude flights (above 10,000 feet).
Page 297 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 2 When not in use, masks may be stowed in the storage pockets behind the front and center seats. Always remove fittings from the oxygen receptacles and stow the mask when they are not in use. If the control knob is pulled on and the fitting is in the receptacle, oxygen will flow through the mask continuously.
Page 298 SECTION 9 SUPPLEMENT 2 PA-32R-301T, SARATOGA II TC SECTION 3 - EMERGENCY PROCEDURES (a) Time of useful consciousness at 20,000 feet is approximately 10 minutes. (b) If oxygen flow is interrupted as evidenced by the flow indicators or hypoxic indications: (1) Install another mask unit.
Page 299 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 3 PILOT'S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 3 S-TEC SYSTEM 55X TWO AXIS AUTOMATIC FLIGHT GUIDANCE SYSTEM WITH TRIM MONITOR The FAA approved operational supplement for the S-TEC System 55X Autopilot, installed in accordance with STC SA8396SW-D, is required for operation of this system.
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Page 301 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 4 PILOT’S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 4 TKS ICE PROTECTION SYSTEM (NON-FIKI INSTALLATION) This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when the optional TKS Ice Protection System (Non-FIKI Installation) is installed per the Equipment List.
Page 302 SECTION 9 SUPPLEMENT 4 PA-32R-301T, SARATOGA II TC SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the TKS Ice Protection System is installed in accordance with FAA approved Piper data. WARNING This system is not approved for Flight Into Known Icing (FIKI) conditions.
Page 303 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 4 SECTION 2 - LIMITATIONS There is no change to the basic airplane limitations when the TKS Ice Protection System is installed. INTENTIONAL FLIGHT INTO KNOWN ICING IS PROHIBITED Ice Protection Fluid CAUTION Under no circumstances are fluids other than those listed below to be used in the TKS system.
Page 304 SECTION 9 SUPPLEMENT 4 PA-32R-301T, SARATOGA II TC SECTION 2 - LIMITATIONS (continued) Placards Placard specifying fluid to be attached adjacent to the de-icing fluid tank filler cap: T.K.S. ICE PROTECTION TANK USE ONLY THE FOLLOWING FLUIDS TKS 80; AL-5(DTD 406B); TKS R328...
Page 305 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 4 SECTION 2 - LIMITATIONS (continued) Placards (continued) Placard prohibiting flight into known icing conditions fitted on the upper control panel in front of the pilot: FLIGHT INTO KNOWN ICING CONDITIONS IS PROHIBITED...
Page 306 SECTION 9 SUPPLEMENT 4 PA-32R-301T, SARATOGA II TC SECTION 3 - EMERGENCY PROCEDURES In Flight If unexpected icing conditions are encountered, the following procedure is recommended: Exit the icing condition. If exiting the icing condition is not possible, then proceed with the following:...
Page 307 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 4 SECTION 3 - EMERGENCY PROCEDURES (continued) In Flight (continued) Exit the icing condition (continued). NOTE Loss of flow to the airframe and propeller may occur due to air entering the pump in turbulent conditions with low tank contents.
Page 308 SECTION 9 SUPPLEMENT 4 PA-32R-301T, SARATOGA II TC SECTION 3 - EMERGENCY PROCEDURES (continued) Inadvertent Icing Encounter CAUTION Flight into known icing conditions is prohibited. If icing is inadvertently encountered: NOTE Accumulation of fluid mist from the propeller may obstruct vision through the windshield.
Page 309 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 4 SECTION 3 - EMERGENCY PROCEDURES (continued) Descent / Landing Select system as required. NOTE Accumulation of fluid mist from the propeller may obstruct vision through the windshield. Final Approach If icing conditions have been encountered or are anticipated: Maximum Flap Deflection ..........Approach setting or less...
Page 310 SECTION 9 SUPPLEMENT 4 PA-32R-301T, SARATOGA II TC SECTION 4 - NORMAL PROCEDURES Preflight Inspection Battery Switch ....................ON Fluid Quantity Indicator........Check quantity (See Limitations for weight and balance) TKS System ....................MAX Airframe Inspection Fluid Tank ................Check quantity - Check cap secure Porous Panels..........Check condition and security -...
Page 311 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 4 SECTION 6 - WEIGHT AND BALANCE The fluid density is 9.2 pounds per U. S. gallon. There are no changes in the weight and balance limits with the system fitted. The contents indicator provides an estimate of the quantity of fluid on board. For the purposes of weight and balance, determine the true weight of fluid from the table below.
Page 312 SECTION 9 SUPPLEMENT 4 PA-32R-301T, SARATOGA II TC SECTION 7 - DESCRIPTION AND OPERATION Ice protection with a TKS system is achieved by mounting laser drilled titanium panels to the leading edges of the wings and horizontal stabilizer. The propeller is protected with a fluid slinger ring.
Page 313 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 4 SECTION 7 - DESCRIPTION AND OPERATION (continued) Magnified View of Holes Laser Drilled Through Titanium Figure 7-2 TKS Porous Panel Cross Section Figure 7-3 ISSUED: April 9, 2007 REPORT: VB-1975 13 of 28,...
Page 314 SECTION 9 SUPPLEMENT 4 PA-32R-301T, SARATOGA II TC SECTION 7 - DESCRIPTION AND OPERATION (continued) The porous panels are bonded to the leading edges of the protected surfaces with a two-part adhesive. Porous panels cover a majority of the leading edges of the wings.
Page 315 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 4 SECTION 7 - DESCRIPTION AND OPERATION (continued) PA-32 TKS System Fluid Schematic Figure 7-4 Maximum Fluid Endurance: NORM selected ....approximately 1 hour and 40 minutes MAX selected ....approximately 50 minutes ISSUED: April 9, 2007...
Page 316 SECTION 9 SUPPLEMENT 4 PA-32R-301T, SARATOGA II TC SECTION 7 - DESCRIPTION AND OPERATION (continued) PA-32 TKS System Fluid Endurance (Quantity vs. Time) Figure 7-5 REPORT: VB-1975 ISSUED: April 9, 2007 9-28, 16 of 28...
Page 317 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 4 SECTION 7 - DESCRIPTION AND OPERATION (continued) The Contents Indicator Gauge is an analog gauge, located on the instrument panel below the primary flight display. This display dims for night operation. Contents Indicator Gauge...
Page 318 SECTION 9 SUPPLEMENT 4 PA-32R-301T, SARATOGA II TC SECTION 7 - DESCRIPTION AND OPERATION (continued) Fluid pressure for airframe/propeller ice protection is provided by a two-speed electrically driven pump. The low speed provides the required flow when NORM is selected, and the high speed provides the required flow when MAX is selected.
Page 319 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 4 SECTION 7 - DESCRIPTION AND OPERATION (continued) TKS System Electrical Controls Figure 7-8 ISSUED: April 9, 2007 REPORT: VB-1975 19 of 28, 9-31...
Page 320 SECTION 9 SUPPLEMENT 4 PA-32R-301T, SARATOGA II TC SECTION 7 - DESCRIPTION AND OPERATION (continued) Inactive TKS System A common occurrence with all TKS porous ice protection panels is “leaking” when not in use. Specifically, panels will stream very small quantities in flight or drip while parked.
Page 321 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 4 SECTION 7 - DESCRIPTION AND OPERATION (continued) Inactive TKS System (continued) This type of fluid loss from the panel is very low volume, but it can be deceptive to the user. In flight the weeping can look very similar to normal operation on the inboard section of a panel.
Page 322 SECTION 9 SUPPLEMENT 4 PA-32R-301T, SARATOGA II TC SECTION 8 - HANDLING, SERVICING AND MAINTENANCE Prolonged Out-of-Service Care During Flyable Storage Ensure that the de-icing fluid tank contains at least the minimum takeoff quantity of fluid (refer to Section 7 of this supplement), and that all system components are filled with fluid.
Page 323 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 4 SECTION 8 - HANDLING, SERVICING AND MAINTENANCE (continued) Servicing (continued) De-icing Fluid Tank (continued) In the event that the fluid tank must be drained, this may be accomplished using the TKS system drain. The valve is located on the lower, right inboard surface of the wing, ahead of the landing gear area.
Page 324 SECTION 9 SUPPLEMENT 4 PA-32R-301T, SARATOGA II TC SECTION 8 - HANDLING, SERVICING AND MAINTENANCE (continued) Servicing (continued) De-icing Fluid Strainer The de-icing fluid strainer in the fluid tank outlet should not require cleaning unless there is a definite indication of foreign matter in the tank.
Page 325 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 4 SECTION 8 - HANDLING, SERVICING AND MAINTENANCE (continued) Servicing (continued) Porous Leading Edge Panels CAUTION Porous panels contain a plastic membrane which may be damaged by certain solvents, particularly Methyl Ethyl Ketone (MEK), lacquer thinner, and other types of thinners and solvents.
Page 326 SECTION 9 SUPPLEMENT 4 PA-32R-301T, SARATOGA II TC SECTION 8 - HANDLING, SERVICING AND MAINTENANCE (continued) Component Overhaul or Replace Airframe/Propeller Pump On condition Motor Brushes, Airframe/Propeller Pump Every 2,000 aircraft hours Filter (subject to element Every three years replacement detailed in Servicing)
Page 327 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 4 SECTION 9 - SUPPLEMENTS Not applicable SECTION 10 - OPERATING TIPS Flight in Unexpected Icing Conditions 1. The airframe ice protection system is not intended to remove ice from the aircraft on the ground. Do not attempt to takeoff with frost, ice or snow on flying surfaces.
Page 328 SECTION 9 SUPPLEMENT 4 PA-32R-301T, SARATOGA II TC SECTION 10 - OPERATING TIPS (continued) Flight in Unexpected Icing Conditions (continued) 4. Stall warning indications should not be relied upon during or following icing conditions, as operation of the wing mounted sensors is likely to be impaired.
Page 329 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 5 PILOT’S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 5 BENDIX/KING KR-87 DIGITAL ADF This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when the Bendix/King KR-87 Digital ADF is installed per the Equipment List.
Page 330 SECTION 9 SUPPLEMENT 5 PA-32R-301T, SARATOGA II TC SECTION 1 - GENERAL The Bendix/King Digital ADF is a panel mounted, digitally tuned, automatic direction finder. It is designed to provide continuous 1 kHz digital tuning in the frequency range of 200 kHz to 1799 kHz and eliminates the need for mechanical band switching.
Page 331 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 5 SECTION 4 - NORMAL PROCEDURES To Operate as an Automatic Direction Finder: 1. OFF/VOL Control - ON. 2. Frequency Selector Knobs - SELECT desired frequency in the standby frequency display. 3. FRQ Button - PRESS to move the desired frequency from the standby to the active position.
Page 332 SECTION 9 SUPPLEMENT 5 PA-32R-301T, SARATOGA II TC SECTION 4 - NORMAL PROCEDURES (continued) NOTE The Standby Frequency which is in memory while Flight Time or Elapsed Time modes are being displayed may be called back by pressing the FRQ button, then transferred to active use by pressing the FRQ button again.
Page 333 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 5 SECTION 4 - NORMAL PROCEDURES (continued) ADF Operation NOTES: Erroneous ADF Bearing Due to Radio Frequency Phenomena: In the U.S., the FCC, which assigns AM radio frequencies, occasionally will assign the same frequency to more than one station in an area. Certain conditions, such as Night Effect, may cause signals from such stations to overlap.
Page 334 SECTION 9 SUPPLEMENT 5 PA-32R-301T, SARATOGA II TC SECTION 5 - PERFORMANCE No change. SECTION 6 - WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in Section 6 of the Pilot’s Operating Handbook and Airplane Flight Manual.
Page 335 SECTION 9 PA-32R-301T, SARATOGA II TC SUPPLEMENT 5 SECTION 7 - DESCRIPTION AND OPERATION (continued) Legend - Figure 1 1. Mode Annunciation - Antenna (ANT) is selected by the “out” position of the ADF button. This mode improves the aural reception and is usually used for station identification.
Page 336 SECTION 9 SUPPLEMENT 5 PA-32R-301T, SARATOGA II TC SECTION 7 - DESCRIPTION AND OPERATION (continued) Legend - Figure 1 (continued) 6. Timer Mode Annunciation - Either the elapsed time (ET) or flight time (FLT) mode is annunciated here. 7. Frequency Selector Knobs - Selects the standby frequency when FRO is displayed and directly selects the active frequency whenever either of the timer functions is selected.
Page 337 SECTION 10 PA-32R-301T, SARATOGA II TC OPERATING TIPS TABLE OF CONTENTS SECTION 10 OPERATING TIPS Paragraph Page 10.1 General ..................10-1 10.3 Operating Tips................10-1 ISSUED: April 9, 2007 REPORT: VB-1975 10-i...
Page 338 SECTION 10 OPERATING TIPS PA-32R-301T, SARATOGA II TC THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1975 ISSUED: April 9, 2007 10-ii...
Page 339 SECTION 10 PA-32R-301T, SARATOGA II TC OPERATING TIPS SECTION 10 OPERATING TIPS 10.1 GENERAL This section provides operating tips of particular value in the operation of the airplane. 10.3 OPERATING TIPS (a) Learn to trim for takeoff so that only a very light back pressure on the control wheel is required to lift the airplane off the ground.
Page 340 SECTION 10 OPERATING TIPS PA-32R-301T, SARATOGA II TC (g) The rudder pedals are suspended from a torque tube which extends across the fuselage. The pilot should become familiar with the proper positioning of his feet on the rudder pedals so as to avoid interference with the torque tube when moving the rudder pedals or operating the toe brakes.

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