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Piper PA-46-350P Malibu Mirage Pilot's Manual And Operation Manual

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MALIBU MIRAGE

AIRPLANE

SERIAL NO. ___________________________

PA-46-350P

REPORT: VB-1710 FAA APPROVED BY:

DATE OF APPROVAL:

FEBRUARY 23, 1999

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.

PA-46-350P

SN 4636196 AND UP

OPERATING

HANDBOOK

AIRPLANE FLIGHT MANUAL

AIRPLANE

REGIST. NO. _______________________

PETER E. PECK

D.O.A. NO. SO-1

THE NEW PIPER AIRCRAFT, INC.

VERO BEACH, FLORIDA

PILOT'S

AND

FAA APPROVED

TM

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Page 1 REPORT: VB-1710 FAA APPROVED BY: PETER E. PECK D.O.A. NO. SO-1 DATE OF APPROVAL: THE NEW PIPER AIRCRAFT, INC. FEBRUARY 23, 1999 VERO BEACH, FLORIDA THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY THE FEDERAL AVIATION REGULATIONS AND ADDITIONAL INFORMATION PROVIDED BY THE MANUFACTURER AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT MANUAL.
Page 2 AIRPLANE IDENTIFIED ON THE FACE OF THE TITLE PAGE. SUBSEQUENT REVISIONS SUPPLIED BY PIPER MUST BE PROPERLY INSERTED. Published by PUBLICATIONS DEPARTMENT Issued: FEBRUARY 23, 1999 © 1997 THE NEW PIPER AIRCRAFT, INC. All Rights Reserved REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999...
Page 3 PA-46-350P, MALIBU APPLICABILITY Application of this handbook is limited to the specific Piper PA-46-350P 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-46-350P, MALIBU 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 PA-46-350P, MALIBU PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Current Revisions to the PA-46-350P Malibu Pilot's Operating Handbook, REPORT: VB-1710 issued FEBRUARY 23, 1999. Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 1 Added Rev. 1 to L of R pg. (PR990920) 3-11 Revised para.
Page 6 PA-46-350P, MALIBU PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 1 (continued) 9-115 Added Section 9 thru Supplement 15 Peter E. Peck 9-122 Sept. 10, 1999 Date Rev.
Page 7 PA-46-350P, MALIBU PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 3 9-133 Added pages (PR010910) thru and Supplement 18. continued 9-142 9-143 Added pages thru and Supplement 19. 9-150 9-151 Added pages...
Page 8 PA-46-350P, MALIBU PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 7 Added Warning and moved (PR021014) info. to page iv. Moved info. from page iii. vi-b Added Rev.
Page 9 PA-46-350P, MALIBU PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 10 vi-c Added page and Rev. 10 (PR040724) to L of R. vi-d Added page. 4-41 Revised para.
Page 10 PA-46-350P, MALIBU PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 vi-d REVISED: JULY 24, 2004...
Page 11 PA-46-350P, MALIBU TABLE OF CONTENTS SECTION 1 GENERAL SECTION 2 LIMITATIONS SECTION 3 EMERGENCY PROCEDURES SECTION 4 NORMAL PROCEDURES SECTION 5 PERFORMANCE SECTION 6 WEIGHT AND BALANCE SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS SECTION 8 AIRPLANE HANDLING, SERVICING AND MAINTENANCE SECTION 9...
Page 12 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 viii...
Page 13 SECTION PA-46-350P, MALIBU GENERAL TABLE OF CONTENTS SECTION 1 GENERAL Paragraph Page Introduction ................Engine..................Propeller ................... Fuel................... Oil ................... 1.11 Maximum Weights ..............1.13 Standard Airplane Weights............1.15 Cabin and Entry Dimensions............ 1.17 Baggage Space and Entry Dimensions........1.19 Specific Loading...............
Page 14 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 1-ii...
Page 15 SECTION 1 PA-46-350P, MALIBU GENERAL SECTION 1 GENERAL 1.1 INTRODUCTION This Pilot’s Operating Handbook is designed for maximum utilization as an operating guide for the pilot. It includes the material required to be furnished to the pilot by the Federal Aviation Regulations and additional information provided by the manufacturer and constitutes the FAA Approved Airplane Flight Manual.
Page 16 SECTION 1 GENERAL PA-46-350P, MALIBU THREE VIEW Figure 1-1 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999...
Page 17 SECTION 1 PA-46-350P, MALIBU GENERAL 1.3 ENGINE (a)Number of Engines (b) Engine Manufacturer Textron Lycoming (c) Engine Model Number TIO-540-AE2A (d) Rated Horsepower (e) Rated Speed (rpm) 2500 (f) Maximum Manifold Pressure (in. Hg.) 42.0 (g) Bore (inches) 5.125 (h) Stroke (inches) 4.375 (i) Displacement (cubic inches) 541.5...
Page 18 SECTION 1 GENERAL PA-46-350P, MALIBU 1.7 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, except alcohol is not approved for use in this airplane.
Page 19 SECTION 1 PA-46-350P, MALIBU GENERAL 1.11 MAXIMUM WEIGHTS (a) Maximum Ramp Weight (lb) 4358 (b) Maximum Takeoff Weight (lb) 4340 (c) Maximum Landing Weight (lb) 4123 (d) Maximum Zero Fuel Weight (lb) 4123 (e) Maximum Weights in Baggage Compartments (lb) (1) Forward (2) Aft 1.13 STANDARD AIRPLANE WEIGHTS...
Page 20 SECTION 1 GENERAL PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999...
Page 21 SECTION 1 PA-46-350P, MALIBU GENERAL 1.21 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY The following definitions are of symbols, abbreviations and terminology used throughout the handbook and those which may be of added operational significance to the pilot. (a) General Airspeed Terminology and Symbols Calibrated Airspeed means the indicated speed of an aircraft, corrected for position and instrument error.
Page 22 SECTION 1 GENERAL PA-46-350P, MALIBU 1.21 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) Maximum Landing Gear Extended Speed is the maximum speed at which an aircraft can be safely flown with the landing gear extended. Maximum Landing Gear Operating Speed is the maximum speed at which the landing gear can be safely extended or retracted.
Page 23 SECTION 1 PA-46-350P, MALIBU GENERAL 1.21 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) (b) Meteorological Terminology International Standard Atmosphere in which: (1) The air is a dry perfect gas; (2) The temperature at sea level is 15° Celsius (59° Fahrenheit); (3) The pressure at sea level is 29.92 inches hg.
Page 24 SECTION 1 GENERAL PA-46-350P, MALIBU 1.21 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) (c) Power Terminology Takeoff Power Maximum power permissible for takeoff. Maximum Con- Maximum power permissible contin- tinuous Power uously during flight. Maximum Climb Maximum power permissible during Power climb. Maximum Cruise Maximum power permissible during Power...
Page 25 SECTION 1 PA-46-350P, MALIBU GENERAL 1.21 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) (f) Weight and Balance Terminology Reference Datum An imaginary vertical plane from which all horizontal distances are measured for balance purposes. Station A location along the airplane fuselage usually given in terms of distance from the reference datum.
Page 26 SECTION 1 GENERAL PA-46-350P, MALIBU 1.21 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) Basic Empty Standard empty weight plus optional Weight equipment. Payload Weight of occupants, cargo and baggage. Useful Load Difference between takeoff weight, or ramp weight if applicable, and basic empty weight.
Page 27 SECTION 2 PA-46-350P, MALIBU LIMITATIONS TABLE OF CONTENTS SECTION 2 LIMITATIONS Paragraph Page General ..................Airspeed Limitations ..............Airspeed Indicator Markings............ Power Plant Limitations ............Leaning Limitations ..............2.11 Power Plant Instrument Markings ..........2.13 Weight Limits ................2.15 Center of Gravity Limits ............2.17 Maneuver Limits ..............
Page 28 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 2-ii...
Page 29 SECTION 2 PA-46-350P, MALIBU 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 30 SECTION 2 LIMITATIONS PA-46-350P, MALIBU AIRSPEED LIMITATIONS (CONTINUED) SPEED KIAS KCAS Maximum Speed for Pneumatic Boot Inflation. Maximum Flaps Extended Speed (V Do not exceed this speed at the given flap setting. 10° 20° 36° Maximum Landing Gear Extension Speed (V ) - Do not exceed this speed when extending the landing gear.
Page 31 SECTION 2 PA-46-350P, MALIBU LIMITATIONS POWER PLANT LIMITATIONS (a) Number of Engines (b) Engine Manufacturer Textron Lycoming (c) Engine Model No. TIO-540-AE2A (d) Engine Operating Limits Maximum Engine Speed 2500 RPM (2) Maximum Oil Temperature 245°F (3) Maximum Cylinder Head Temperature 500°F (4) Maximum Turbine Inlet Temperature...
Page 32 SECTION 2 LIMITATIONS PA-46-350P, MALIBU LEANING LIMITATIONS Mixture full RICH at all engine powers above high speed cruise power. 2.11 POWER PLANT INSTRUMENT MARKINGS (a) Tachometer Green Arc (Normal Operating Range) 600 to 2500 RPM Red Line (Maximum) 2500 RPM (b) Manifold Pressure Green Arc (Normal Operating Range) 10 to 42.0 in.
Page 33 SECTION 2 PA-46-350P, MALIBU LIMITATIONS 2.13 WEIGHT LIMITS (a) Maximum Ramp Weight 4358 LB (b) Maximum Takeoff Weight 4340 LB (c) Maximum Landing Weight 4123 LB (d) Maximum Zero Fuel Weight 4123 LB (e) Maximum Baggage (100 lb each compartment) 200 LB NOTE Refer to Section 5 (Performance) for maximum...
Page 34 SECTION 2 LIMITATIONS PA-46-350P, MALIBU 2.21 KINDS OF OPERATION EQUIPMENT LIST This airplane may be operated in day or night VFR, day or night IFR and known icing when the appropriate equipment is installed and operable. The following equipment list identifies the systems and equipment upon which type certification for each kind of operation was predicated and must be installed and operable for the particular kind of operation indicated.
Page 35 SECTION 2 PA-46-350P, MALIBU LIMITATIONS 2.21 KINDS OF OPERATION EQUIPMENT LIST (Continued) Types of Operation and Remarks Number (DAY, NIGHT, VFR, IFR and System Required ICING Conditions) 3. FLIGHT CONTROLS Flap Position Indicator DAY, NIGHT, VFR, IFR, ICING Elevator and Rudder Trim Position Indicator 1 ea.
Page 36 SECTION 2 LIMITATIONS PA-46-350P, MALIBU 2.21 KINDS OF OPERATION EQUIPMENT LIST (CONTINUED) Types of Operation and Remarks Number (DAY, NIGHT, VFR, IFR and System Required ICING Conditions) 5. ICE PROTECTION (Continued) Heated Stall Warning Transducer ICING Heated Pitot Head ICING Alternate Static Source ICING...
Page 37 SECTION 2 PA-46-350P, MALIBU LIMITATIONS 2.21 KINDS OF OPERATION EQUIPMENT LIST (CONTINUED) Types of Operation and Remarks Number (DAY, NIGHT, VFR, IFR and System Required ICING Conditions) 7. INSTRUMENTA- TION - FLIGHT Airspeed Indicator DAY, NIGHT, VFR, IFR, ICING Altimeter DAY, NIGHT, VFR, IFR, ICING Free Air Temperature Gauge...
Page 38 SECTION 2 LIMITATIONS PA-46-350P, MALIBU 2.21 KINDS OF OPERATION EQUIPMENT LIST (CONTINUED) Types of Operation and Remarks Number (DAY, NIGHT, VFR, IFR and System Required ICING Conditions) 9. LIGHTS - EXTERNAL Position Lights a. Left Wing - Red and White 1 ea.
Page 39 SECTION 2 PA-46-350P, MALIBU LIMITATIONS 2.21 KINDS OF OPERATION EQUIPMENT LIST (CONTINUED) Types of Operation and Remarks Number (DAY, NIGHT, VFR, IFR and System Required ICING Conditions) 12. PRESSURIZED FLIGHT Cabin Altimeter DAY, NIGHT, VFR, IFR, ICING Cabin Differential Pressure Indicator DAY, NIGHT, VFR, IFR ICING Cabin Vertical Speed Indicator...
Page 40 SECTION 2 LIMITATIONS PA-46-350P, MALIBU 2.23 FUEL LIMITATIONS (a) Minimum Aviation Fuel Grade..........100LL/100 (b) Total Capacity..............122 U.S. GAL. (c) Unusable Fuel..............2 U.S. GAL. The unusable fuel for this airplane has been determined as 1.0 gallon in each wing in critical flight attitudes. (d) Usable Fuel..............
Page 41 SECTION 2 PA-46-350P, MALIBU LIMITATIONS 2.33 MAXIMUM SEATING CONFIGURATION The maximum seating capacity is 6 (six) persons. 2.34 ICING INFORMATION "WARNING" Severe icing may result from environmental conditions outside of those for which the airplane is certified. Flight in freezing rain, freezing drizzle, or mixed icing conditions (supercooled liquid water and ice crystals) may result in ice build-up on protected surfaces exceeding the capability of the ice protection system, or may result in ice forming aft of the protected surfaces.
Page 42 SECTION 2 LIMITATIONS PA-46-350P, MALIBU 2.35 PLACARDS In full view of the pilot: T h e m a r k i n g s a n d p l a c a r d s i n s t a l l e d i n t h i s a i r p l a n e contain operating limitations which must be complied with when operating this airplane in the normal category.
Page 43 SECTION 2 PA-46-350P, MALIBU LIMITATIONS 2.35 PLACARDS (CONTINUED) Near the magnetic compass: CAUTION - COMPASS CAL. MAY BE IN E R RO R W I T H E L E C T. E Q U I P M E N T OTHER THAN AVIONICS ON.
Page 44 SECTION 2 LIMITATIONS PA-46-350P, MALIBU 2.35 PLACARDS (CONTINUED) Over emergency exit handle: EMERGENCY EXIT REMOVE GLASS PULL DOOR IN - LIFT UP On aft baggage closeout: MAXIMUM LOAD EACH COAT HOOK 8 LBS On aft close out panel, if required: Rear Passenger / Baggage Areas MAXIMUM ALLOWABLE WEIGHT MAXIMUM ALLOWABLE COMBINED WEIGHT IN AFT SEATS IS...
Page 45 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph Page General ..................Emergency Procedures Checklist ..........3.3a Engine Fire During Start (3.7) ..........3.3b Turbocharger Failure (3.8) ............3.3c Engine Power Loss During Takeoff (3.9) ........ 3.3d Engine Power Loss In Flight (3.11) ........
Page 46 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU TABLE OF CONTENTS SECTION 3 (cont) EMERGENCY PROCEDURES Paragraph Page 3.3w Hydraulic System Malfunction (3.49)........3-17 3.3x Flap System Malfunction (3.51)..........3-17 3.3y Fuel Tank Submerged Pump Failure (3.53) ......3-18 3.3z Stall Warning Failure (3.55) ............. 3-18 3.3aa Annunciator Light Panel Failure (3.57) ........
Page 47 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES TABLE OF CONTENTS SECTION 3 (cont) EMERGENCY PROCEDURES Paragraph Page 3.45 Inadvertent Icing Encounter (3.3v) ......... 3-35 3.49 Hydraulic System Malfunction (3.3w) ........3-36 3.51 Flap System Malfunction (3.3x) ..........3-36 3.53 Fuel Tank Submerged Pump Failure (3.3y) ......3-37 3.55 Stall Warning Failure (3.3z) ............
Page 48 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 3-iv...
Page 49 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES SECTION 3 EMERGENCY PROCEDURES GENERAL This section provides the recommended procedures for coping with various emergency or critical situations. All of the emergency procedures required by the FAA as well as those necessary for operation of the airplane, as determined by the operating and design features of the airplane, are presented.
Page 50 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU EMERGENCY PROCEDURES CHECKLIST 3.3a ENGINE FIRE DURING START (3.7) Starter (crank engine)..................PUSH Mixture ..................IDLE CUT-OFF Throttle .......................OPEN Fuel Selector ....................OFF Emergency (EMERG) Fuel Pump...........CHECK OFF Abandon if fire continues 3.3b TURBOCHARGER FAILURE (3.8) CAUTION: If a turbocharger failure is the result of loose, disconnected or burned through exhaust system components, a potentially serious fire hazard exists as...
Page 51 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 3.3b TURBOCHARGER FAILURE (3.8) (Cont’d) PARTIAL LOSS OF ENGINE POWER If the turbocharger wastegate fails in the OPEN position, a partial loss of engine power may result. The following procedure is recommended if a suspected turbocharger or turbocharger wastegate control failure results in a partial loss of engine power.
Page 52 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU 3.3c ENGINE POWER LOSS DURING TAKEOFF (3.9) (Cont’d) If sufficient altitude has been gained to attempt a restart: Maintain Safe Airspeed Emergency (EMERG) Fuel Pump............Check ON Fuel Selector ................SWITCH to tank containing fuel Mixture .....................FULL RICH Induction Air ..................ALTERNATE CAUTION If normal engine operation and fuel flow are...
Page 53 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 3.3d ENGINE POWER LOSS IN FLIGHT (3.11) (Cont’d) If power is restored: Induction Air ..................PRIMARY (Remain in ALTERNATE if induction ice is suspected) Emergency (EMERG) Fuel Pump (Except in case of engine driven pump failure)...............OFF Mixture..................AS REQUIRED Land as soon as practical and investigate cause of power loss.
Page 54 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU 3.3e POWER OFF LANDING (3.13) (Continued) When committed to landing: Landing Gear Selector ..............AS REQUIRED Throttle ....................CLOSED Mixture ..................IDLE CUT-OFF Flaps....................AS REQUIRED Fuel Selector ....................OFF ALTR Switches....................OFF Magneto Switches..................OFF Emergency (EMERG) Fuel Pump ..............OFF Battery Master Switch ...................OFF Seat Belt and Harness ................TIGHT Seats..............adjusted and locked in position...
Page 55 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 3.3f FIRE IN FLIGHT (3.15) (Continued) CAUTION The cabin pressure dump valve will remain open if the cabin pressure dump/normal switch is positioned to DUMP prior to turning the aircraft electrical system OFF. This provides maximum airflow through the cabin for smoke evacuation.
Page 56 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU 3.3h LOSS OF FUEL FLOW (3.19) (Continued) Emergency (EMERG) Fuel Pump..............ON Fuel Selector ................CHECK on tank containing usable fuel If power restored: Emergency (EMERG) Fuel Pump (except in case of engine driven pump failure)...............OFF Mixture..................AS REQUIRED If power not restored: Emergency (EMERG) Fuel Pump ..............OFF...
Page 57 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 3.3k TURBINE INLET TEMPERATURE (TIT) INDICATOR FAILURE (3.24) If failure occurs during takeoff, climb, or landing: Mixture....................Full Rich NOTE During cruise climb operations, a fuel flow of 32 gph may be used. If failure occurs prior to setting cruise power: Power ..............Set Power per POH Section 5 Power Setting Table Mixture ..............Lean to Approx.
Page 58 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU 3.3l HIGH CYLINDER HEAD TEMPERATURE (3.25) If indicated cylinder head temperature reaches 480°F: CHT Cycle Push Button ............CYCLE THRU ALL CYLINDERS Power ....................REDUCE Mixture ................ENRICH, if practical Airspeed .................INCREASE, if practical If condition is not corrected: Land at nearest airport and investigate problem.
Page 59 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 3.3m ELECTRICAL FAILURES (3.27) (Continued) Dual Alternator Failure (Zero amps both ammeters or ALTERNATOR #l and #2 INOP lights illuminated - annunciator panel). NOTE Anytime total tie bus voltage is below 25 Vdc, the LOW BUS VOLTAGE annunciator will illuminate.
Page 60 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU 3.3m ELECTRICAL FAILURES (3.27) (Continued) Supplemental Heater Control Circuit Failure (Heater Continues to Operate With AUX CBN HEAT and VENT/DEFOG switches OFF): VENT DEFOG Circuit Breaker ..............PULL If the heater still operates: BATT MASTER Switch ................OFF ALTR Switches .....................OFF Land as soon as practical.
Page 61 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 3.3p SPIN RECOVERY (3.33) Rudder .................FULL OPPOSITE to DIRECTION of ROTATION Control Wheel...............FULL FORWARD while NEUTRALIZING AILERONS Throttle ....................CLOSED Rudder (when rotation stops) .............NEUTRAL Control Wheel............AS REQUIRED to smoothly regain level flight attitude 3.3q ENGINE ROUGHNESS (3.35) Mixture ..............ADJUST FOR MAXIMUM SMOOTHNESS Induction Air ..................ALTERNATE...
Page 62 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU 3.3s PRESSURIZATION SYSTEM MALFUNCTION (3.39) Should the differential pressure rise above 5.5 psi maximum or a structural failure appear imminent, proceed as follows: NOTE If pressurized, the following procedure will result in an immediate loss of pressurization and the cabin altitude will rise at an uncontrollable rate.
Page 63 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 3.3t CABIN AIR CONTAMINATION/SMOKE EVACUATION (3.41) (Pressurized) NOTE If pressurized, the following procedure will result in an immediate loss of pressurization and the cabin altitude will rise at an uncontrollable rate. Cabin Pressure Dump/Normal Switch ............DUMP Cabin Pressurization Control ..........PULL to unpressurize Auxiliary Cabin Heat Switch ................OFF Vent/Defog Switch ..................ON...
Page 64 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU 3.3u VACUUM SYSTEM FAILURE (3.43) Single Vacuum System Failure (Reduced suction pressure and left or right Vacuum Inoperative Annunciators illuminated. Gyro Suction Gauge ......CHECK (within normal operating range) Operating Pump annuciator light ..........EXTINGUSHED Although either vacuum pump independently has sufficient capacity to operate the flight instruments and the deice boots in a normal manner, intentional or continued operation in icing conditions is not recommended.
Page 65 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 3.3v INADVERTENT ICING ENCOUNTER (3.45) (Continued) Vent/Defog Fan....................ON Electric Windshield Heat .............LOW or HIGH, as required Change heading and/or altitude to exit icing conditions. 3.3w HYDRAULIC SYSTEM MALFUNCTION (3.49) HYDRAULIC PUMP annunciator light illuminates continuously, or cycles on and off rapidly: HYDRAULIC PUMP POWER Circuit Breaker.........PULL Land as soon as practical and investigate the cause.
Page 66 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU 3.3y FUEL TANK SUBMERGED PUMP FAILURE (BOOST PUMP light illuminated - annunciator panel) (3.53) Fuel Selector ...................CHECK Boost Pump Circuit Breaker ...........CHECK - RESET if necessary BOOST PUMP Annunciator Light ........EXTINGUISHED If annunciator remains lit: Emergency (EMERG) Fuel Pump..............ON Fuel Flow ..................CHECK for fluctuation...
Page 67 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 3.3aa ANNUNCIATOR LIGHT PANEL FAILURE (ANNUNCIATOR INOP light illuminated - annunciator panel) (3.57) (Continued) If annunciator lights illuminate, annunciator panel is functioning properly. ANNUNCIATOR INOP will remain lit. If ANNUN circuit breaker does not remain closed, or lights fail to illuminate when tested, annunciator lights will be inoperative for remainder of flight.
Page 68 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 3-20...
Page 69 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 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 70 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU TURBOCHARGER FAILURE (3.3b)(CONT’D) COMPLETE LOSS OF ENGINE POWER: If a suspected turbocharger or turbocharger control system failure results in a complete loss of engine power, the following procedure is recommended. Retard the mixture control to the IDLE CUTOFF position. If necessary, reset the throttle to cruise power position and the propeller control to the full forward position.
Page 71 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES ENGINE POWER LOSS DURING TAKEOFF (3.3c) The proper action to be taken if loss of power occurs during takeoff will depend on the circumstances of the particular situation. If sufficient runway remains to complete a normal landing, leave the landing gear down and land straight ahead.
Page 72 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU 3.11 ENGINE POWER LOSS IN FLIGHT (3.3d) Complete engine power loss is usually caused by fuel flow interruption and power will be restored shortly after fuel flow is restored. The first step is to prepare for a power off landing (refer to paragraph 3.13). An airspeed of 90 KIAS (the power off glide speed) should be maintained.
Page 73 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 3.13 POWER OFF LANDING (3.3e) If loss of power occurs at altitude, trim the aircraft for best gliding angle, (90 KIAS) 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 74 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU 3.15 FIRE IN FLIGHT (3.3f) 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, character of smoke, or other indications since the action to be taken differs somewhat in each case.
Page 75 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 3.15 FIRE IN FLIGHT (3.3f) (Continued) all cases, the heater and defroster should be OFF. If radio communication is not required turn the battery master and alternator switches OFF. If the terrain permits, a landing should be made immediately (refer to Power Off Landing procedure paragraph 3.13).
Page 76 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU 3.19 LOSS OF FUEL FLOW (3.3h) (Continued) If power is restored, turn OFF the emergency (EMERG) fuel pump (except in the case of an engine driven fuel pump failure). Adjust the mixture control as necessary. If power is not restored, turn the emergency (EMERG) fuel pump and the fuel selector OFF, and proceed with Power Off Landing procedure (refer to paragraph 3.13).
Page 77 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 3.24 TURBINE INLET TEMP (TIT) INDICATOR FAILURE (3.3k) (CONT’D) If TIT failure occurs prior to setting cruise power, set power per the POH Section 5 power setting table and then lean to the approximate POH power setting table fuel flow +4 GPH.
Page 78 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU 3.27 ELECTRICAL FAILURES (3.3m) SINGLE ALTERNATOR FAILURE (Zero amps or ALTERNATOR #1 or #2 INOP light illuminated - annunciator panel) NOTE Anytime total tie bus voltage is below 25 Vdc, the LOW BUS VOLTAGE annunciator will illuminate.
Page 79 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 3.27 ELECTRICAL FAILURES (3.3m) (Continued) DUAL ALTERNATOR FAILURE (Zero amps both ammeters or ALTERNATOR #1 and #2 INOP light illuminated - annunciator panel) NOTE Anytime total tie bus voltage is below 25 Vdc, the LOW BUS VOLTAGE annunciator will illuminate.
Page 80 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU 3.27 ELECTRICAL FAILURES (3.3m) (Continued) SUPPLEMENTAL HEATER CONTROL CIRCUIT FAILURE (Heater Continues to Operate With AUX CBN HEAT and VENT/DEFOG Switches OFF) Pull the VENT DEFOG circuit breaker. If the heater still operates, turn the BATT MASTER and ALTR switches OFF.
Page 81 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 3.35 ENGINE ROUGHNESS (3.3q) Engine roughness may be caused by dirt in the injector nozzles, induction filter icing, ignition problems, or other causes. First adjust the mixture for maximum smoothness. The engine will run rough if the mixture is too rich or too lean.
Page 82 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU 3.39 PRESSURIZATION SYSTEM MALFUNCTION (3.3s) NOTE If pressurized, the following procedure will result in an immediate loss of pressurization and the cabin altitude will rise at an uncontrollable rate. Should the differential pressure rise above 5.5 psi maximum or a structural failure appear imminent, an immediate decrease in differential pressure is required.
Page 83 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 3.43 VACUUM SYSTEM FAILURE (3.3u) A failure of either vacuum pump is indicated by the illumination of a vacuum failure annunciator, “VACUUM NO. 1 INOP”.or “VACUUM NO. 2 INOP. In the event one vacuum pump fails, check that the suction gauge still indicates within the normal operating range, and that the operating pump’s vacuum failure annunciator is extinguished.
Page 84 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU 3.49 HYDRAULIC SYSTEM MALFUNCTION (3.3w) A hydraulic system malfunction, which causes the hydraulic pump to either run continuously (more than 15-20 seconds), or cycle on and off rapidly (more than 6-8 times), may be detected by the illumination of the HYDRAULIC PUMP amber annunciator light.
Page 85 SECTION 3 PA-46-350P, MALIBU EMERG PROCEDURES 3.53 FUEL TANK SUBMERGED PUMP FAILURE (BOOST PUMP light illuminated - annunciator panel) (3.3y) Illumination of the BOOST PUMP annunciator light indicates the selected fuel tank’s submerged fuel boost pump has failed. Immediately check that the fuel selector is in the proper position and check the appropriate FUEL PUMPS (L BOOST or R BOOST) circuit breaker located on the pilot’s forward breaker panel;...
Page 86 SECTION 3 EMERG PROCEDURES PA-46-350P, MALIBU 3.59 EMERGENCY EXIT (3.3ab) The second window aft of the windshield on the right side of the fuselage is an emergency exit. NOTE The cabin must be depressurized before attempting to open the emergency exit. To use the emergency exit, remove the plexiglas cover over the handle, pull the handle, and pull in on the exit window.
Page 87 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Paragraph Page GENERAL ................AIRSPEEDS FOR SAFE OPERATION........NORMAL PROCEDURES CHECKLIST....... 4.5a Preflight Checklists (4.9)............4.5b Before Starting Engine Checklist (4.11) ......... 4.5c Engine Start Checklist (4.13) ..........ENGINE START - GENERAL (4.13a).......
Page 88 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU TABLE OF CONTENTS SECTION 4 (cont) NORMAL PROCEDURES Paragraph Page 4.5i Climb Checklist (4.25) ............4-14 MAXIMUM CONTINUOUS POWER CLIMB (4.25a) ..............4-15 CRUISE CLIMB (4.25b)............. 4-14 4.5j Cruise Checklist (4.27)............4-15 4.5k Descent Checklist (4.29) ............4-15 NORMAL DESCENT (4.29) ..........
Page 89 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES TABLE OF CONTENTS SECTION 4 (cont) NORMAL PROCEDURES Paragraph Page 4.11 BEFORE STARTING ENGINE (4.5b)........4-22 4.13 ENGINE START (4.5c)............4-23 4.13a Engine Start - General (4.5c)..........4-23 4.13b Normal Start - Cold Engine (4.5c) ........4-24 4.13c Normal Start - Hot Engine (4.5c) .........
Page 90 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU TABLE OF CONTENTS SECTION 4 (cont) NORMAL PROCEDURES Paragraph Page 4.33 GO-AROUND (4.5n) .............. 4-35 4.35 AFTER LANDING (4.5o) ............4-35 4.37 STOPPING ENGINE (4.5p) ........... 4-35 4.39 MOORING (4.5q) ..............4-36 4.41 STALLS ................... 4-36 4.43 TURBULENT AIR OPERATION ..........
Page 91 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES SECTION 4 NORMAL PROCEDURES 4.1 GENERAL This section provides the normal operating procedures for the PA-46- 350P, Malibu airplane. All of the normal operating procedures required by the FAA are presented as well as those procedures which have been determined as necessary for the operation of the airplane, as determined by the operating and designed features of the airplane, are presented.
Page 92 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU AIRSPEEDS FOR SAFE OPERATIONS The following airspeeds are those which are significant to the safe operation of the airplane. These figures are for standard airplanes flown at gross weight under standard conditions at sea level. Performance for a specific airplane may vary from published figures depending upon the equipment installed, the condition of the engine, airplane and equipment, atmospheric conditions and piloting technique.
Page 93 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES WALK-AROUND Figure 4-1 NORMAL PROCEDURES CHECKLIST 4.5a Preflight Checklists (4.9) COCKPIT (4.9a) Control wheel ..............release restraints Parking Brake ..................SET Gear Handle..................DOWN All Switches....................OFF Magneto Switches...................OFF Radio Master Switch ................OFF Mixture ................IDLE CUT-OFF Battery Master Switch................ON CAUTION See fuel imbalance limitations, 2.23.
Page 94 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.5a Preflight Checklist (Continued) COCKPIT (4.9a) (Continued) Annunciator Panel ................CHECK Switch Panel ..................CHECK FUEL PRESS Annunciator ..............ON Oxygen Light (if installed) ..............CHECK Stall Warning System ................TEST Flaps ....................EXTEND Battery Master Switch ................OFF Primary Flight Controls ..........PROPER OPERATION Trim ....................NEUTRAL Static System ..................DRAIN Alternate Static System ......CHECK NORMAL POSITION...
Page 95 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.5a Preflight Checklist (4.9) (Continued) RIGHT WING (4.9C) (CONTINUED) Fuel Tank Vent .................CLEAR Tie Down and Chock ..............REMOVE Main Gear Strut ................PROPER INFLATION (3.44 +/- 0.25 in.) Tire ....................CHECK Brake Block and Disc ..............CHECK CAUTION When draining any amount of fuel, care should be taken to ensure that no fire hazard exists...
Page 96 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.5a Preflight Checklist (4.9) (Continued) LEFT WING (4.9) Surface Condition........CLEAR of ICE, FROST, SNOW CAUTION When draining any amount of fuel, care should be taken to ensure that no fire hazard exists before starting engine. Fuel Tank Sump ............DRAIN and CHECK for water, sediment Tie Down and Chock..............REMOVE...
Page 97 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.5a Preflight Checklist (4.9) (Continued) MISCELLANEOUS (4.9f) (Continued) Exterior Lighting Switches ..........ON and CHECK Pitot ..................CHECK - WARM Stall Warning Heat .............CHECK WARM All Lighting Switches ................OFF Pitot Heat Switch ...................OFF Stall Warning Heat Switch ..............OFF Battery Master Switch ................OFF Passengers ..................BOARD Door ................CLOSE and LATCH...
Page 98 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.5c Engine Start Checklist (4.13) ENGINE START - GENERAL (4.13a) CAUTION Do not attempt flight if there is no indication of alternator output. CAUTION The STARTER ENGAGE annunciator will illuminate during engine cranking. If the annunciator remains lit after the engine is running, stop the engine and determine the cause.
Page 99 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.5c Engine Start Checklist (4.13) (Continued) NORMAL START - COLD ENGINE (4.13b) (Continued) NOTE The amount of prime depends on engine temperature. Familiarity and practice will enable the operator to estimate the amount of prime required.
Page 100 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.5c Engine Start Checklist (4.13) (Continued) ENGINE START WITH EXTERNAL POWER SOURCE (4.13e) Battery Master Switch ................OFF Alternators ....................OFF All Electrical Equipment ................OFF External Power Plug ...........INSERT in receptacle Proceed with normal start. NOTE For all normal operations using an external power source, the battery master switch should be OFF, but it is possible to use the ship’s...
Page 101 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.5d Before Taxiing Checklist (4.15) BEFORE TAXIING (4.15) CAUTION Do not operate engine above 1200 RPM with cabin doors open. Throttle ................1000 to 1200 RPM Radio Master Switch ................ON Environmental System ............AS DESIRED Supplemental Electric Heater ..........AS DESIRED 4.5e Taxiing Checklist (4.17) TAXIING (4.17) Taxi Area...................CLEAR...
Page 102 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.5f Ground Check Checklist (4.19) (Continued) GROUND CHECK (4.19) (Continued) NOTE Refer to paragraph 4.50, Icing Information, prior to any flight operations. (Takeoff, cruise, landing, etc.) If flight into icing conditions (in visible moisture below +5°C) is anticipated, conduct a preflight check of the ice protection systems per Supplement No.
Page 103 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.5g Before Takeoff Checklist (4.21) (Continued) BEFORE TAKEOFF (4.21) (Continued) Seat Backs ..................ERECT Seats ..........ADJUSTED& LOCKED IN POSITION Armrests ..................STOWED Mixture ..................FULL RICH Propeller Control ............FULL INCREASE Belts/Harness ............FASTENED/ADJUSTED Empty Seats ........SEAT BELTS SNUGLY FASTENED Flaps .......................SET Trim ......................SET Controls ....................FREE...
Page 104 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.5h Takeoff Checklist (4.23) (Continued) ° FLAP TAKEOFF PERFORMANCE (4.23b) ° Flaps ......................0 Trim....................SET Brakes ...................APPLY Power..............SET TO MAXIMUM Brakes ..................RELEASE Liftoff..................78 KIAS Obstacle Clearance Speed............91 KIAS Landing Gear ..................UP SHORT FIELD TAKEOFF PERFORMANCE (4.23c) NOTE Gear warning will sound when the landing gear is retracted with the flaps extended more than...
Page 105 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.5i Climb Checklist (Continued) CRUISE CLIMB (4.25b) Manifold Pressure ..............35 IN. HG Propeller Speed................2500 RPM Mixture..................32 GPH Climb Speed................125 KIAS Pressurization Controls ..............SET Emergency (EMERG) Fuel Pump ..........OFF at safe altitude 4.5j Cruise Checklist (4.27) CRUISE (4.27) WARNING Operation above 25,000 ft is not approved.
Page 106 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.5k Descent Checklist (4.29) (Continued) REDUCED POWER DESCENT (4.29) Throttle..............AT or ABOVE 20 in. Hg. Mixture...............MAINTAIN 1350 TIT Propeller Speed ..............CRUISE SETTING Pressurization Controls ................SET Altimeter ....................SET Windshield Defrost ..............AS REQUIRED 4.5m Approach And Landing Checklist (4.31) APPROACH AND LANDING (4.31) Seat Backs ..................ERECT Seats ..........ADJUSTED &...
Page 107 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.5m Approach And Landing Checklist (4.31) (Continued) SHORT FIELD TECHNIQUE (4.31b) Flaps..................FULL DOWN Airspeed...................78 KIAS Throttle ................AS REQUIRED Over obstacle: Throttle ................REDUCE TO IDLE After touchdown: Brakes..................MAXIMUM 4.5n Go-around Checklist (4.33) GO-AROUND (4.33) Mixture ..................FULL RICH Propeller Control ............FULL INCREASE Throttle .................FULL POWER Control Wheel ..............back pressure to...
Page 108 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.5p Stopping Engine Checklist (4.37) STOPPING ENGINE (4.37) Radios and Electrical Equipment ............OFF External Lights ..................OFF Air Conditioner ..................OFF Propeller Control ............FULL INCREASE Throttle ................CLOSED until a decided decrease in CHT Throttle..................1000 RPM for approx.
Page 109 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.7 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. 4.9 PREFLIGHT CHECK (4.5a) The airplane should be given a thorough preflight and walk-around check. The preflight should include a check of the airplane's operational status, computation of weight and C.G.
Page 110 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU PREFLIGHT CHECK (4.5a) (Continued) 4.9b Empennage (4.5a) Begin the walk-around at the left side of the aft fuselage. Check the condition of any antennas located on the fuselage. All surfaces of the empennage must be clear of ice, frost, snow or other extraneous substances. Fairings and access covers should be attached properly.
Page 111 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES PREFLIGHT CHECK (4.5a) (Continued) 4.9d Nose Section (4.5a) Check the general condition of the nose section; look for oil or fluid leakage and that the cowling is secure. Drain the fuel filter sump located on the lower fuselage aft of the cowling.
Page 112 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.9 PREFLIGHT CHECK (4.5a) (Continued) 4.9f Miscellaneous (4.5a) Enter the cockpit and, if installed, check oxygen masks and hoses. Turn the battery master switch ON and retract the flaps. Check the interior lights by turning ON the necessary switches. After the interior lights are checked, turn ON the pitot heat, stall warning heat, and the exterior light switches.
Page 113 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.11 BEFORE STARTING ENGINE (4.5b) (Continued) If the flight is to be made unpressurized, the cabin pressurization control should be pulled out to dump bleed air overboard and the cabin pressure dump/normal switch should be in the DUMP position in order to provide maximum cabin airflow.
Page 114 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.13 ENGINE START (4.5c) (Continued) 4.13bNormal Start - Cold Engine (4.5c) Open the throttle lever approximately 1/2 inch. Turn the battery master switch ON, and check that the emergency (EMERG) fuel pump is OFF. Move the mixture control to full RICH for approximately four seconds then to idle cut-off.
Page 115 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.13 ENGINE START (4.5c) (Continued) 4.13e Engine Start With External Power Source (4.5c) An optional feature allows the operator to use an external power source to crank the engine without having to gain access to the airplane’s battery. Turn the battery master and alternator switches OFF and turn all electrical equipment OFF.
Page 116 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.15 BEFORE TAXIING (4.5d) CAUTION Do not operate engine above 1200 rpm with cabin doors open. Warm up the engine at 1000 to 1200 rpm. Avoid prolonged idling at low rpm, as this practice may result in fouled spark plugs. Turn the radio master switch ON, and set environmental system as desired.
Page 117 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.19 GROUND CHECK (4.5f) 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. NOTE If flight into icing conditions (in visible moisture below +5°C) is anticipated, conduct a preflight check of the icing systems per Supplement No.
Page 118 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.21 BEFORE TAKEOFF (4.5g) Ensure that the battery master, emergency fuel pump, and alternator switches are all ON. Check all of the flight instruments and set as required. Check all engine gauges to verify the engine indications are with the normal operating range.
Page 119 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.23 TAKEOFF (4.5h) (Continued) 4.23a Normal Technique (4.5h) When the available runway length is well in excess of that required and obstacle clearance is no factor, the normal takeoff technique may be used. The flaps should be in the 0°...
Page 120 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.25 CLIMB (4.5i) 4.25a Maximum Continuous Power Climb (4.5i) The best rate of climb at gross weight and maximum continuous power will be obtained at 110 KIAS. The best angle of climb may be obtained at 81 KIAS.
Page 121 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.27 CRUISE (4.5J) (CONTINUED) The cruising speed is determined by many factors, including power setting, altitude, temperature, loading, and equipment installed on the airplane. When leveling off at cruise altitude, the pilot may reduce to a cruise power setting in accordance with the *Power Setting Table in Section 5 of this manual.
Page 122 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.27 CRUISE (4.5j) (Continued) During cruise, use the following procedure to maintain lateral balance, and stay within the fuel imbalance limitations of 2.23: (a) When starting with a symmetrical fuel load, use the left tank first until 10 gallons are burned, then alternate tanks at approximately one hour intervals.
Page 123 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.29 DESCENT (4.5k) The recommended procedure for descent is to leave the engine controls at the cruise settings and increase the airspeed to give the desired rate of descent. Monitor the manifold pressure and adjust to maintain the cruise setting.
Page 124 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.31 APPROACH AND LANDING (4.5m) (Continued) NOTE During landing gear operation, it is normal for the HYDRAULIC PUMP annunciator light to illuminate until full system pressure is restored. The air conditioner should be OFF to ensure maximum rate of climb in the event of a go-around.
Page 125 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.33 GO-AROUND (4.5n) To initiate a go-around from a landing approach, the mixture should be set to full RICH, the propeller control should be at full INCREASE, and the throttle should be advanced to full power while the pitch attitude is increased to obtain the balked landing climb speed of 80 KIAS.
Page 126 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.39 MOORING (4.5q) If necessary, the airplane should be moved on the ground with the aid of the nose wheel tow bar. The parking brake should be set and the aileron and elevator controls should be secured by looping the safety belt through the control wheel and pulling it snug.
Page 127 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.45 CABIN PRESSURIZATION SYSTEM Cabin pressurization system controls, gauges and switches are located to the right of the pilots control wheel shaft. (Refer to Section 7, Figure 7-39.) The cabin pressurization system controls, gauges and switches are as follows: (a) Cabin Altitude Controller with Rate of Change Control (b) Cabin Pressure Altitude/Differential Pressure/Rate of Climb Gauge...
Page 128 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.45 CABIN PRESSURIZATION SYSTEM (Continued) For flight below an airplane altitude of 12,500 feet, the cabin altitude control should be left at the takeoff setting. For flight above 12,500 feet, at which point maximum differential will be achieved, smoother operation will result by setting the cabin altitude (outer scale) on the cabin altitude controller to 500 feet above field elevation for takeoff.
Page 129 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.47 SUPPLEMENTAL ELECTRIC HEATER AFTER ENGINE START BATT MASTER Switch .................ON Alternator Switches ..................OFF VENT DEFOG Switch ..................ON Airflow ....................CHECK Voltmeter ................LESS than 25 Vdc (increase electrical load as necessary to lower voltage) LOW BUS VOLTAGE Annunciator .........ILLUMINATED Electrical Switches ..................OFF VENT DEFOG Switch .................OFF Alternator Switches ..................ON...
Page 130 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU 4.49 NOISE LEVEL The corrected noise level of this aircraft with a two blade propeller is 74.7 dB(A). as measured per FAR 36 Appendix F. For the three blade propeller, the corrected noise level of this aircraft is 79.7 dB(A) as measured per FAR 36 Appendix G.
Page 131 SECTION 4 PA-46-350P, MALIBU NORMAL PROCEDURES 4.50 ICING INFORMATION "THE FOLLOWING WEATHER CONDITIONS MAY BE CONDUCIVE TO SEVERE IN-FLIGHT ICING" Visible rain at temperatures below 0 degrees Celsius ambient air temperature. Droplets that splash or splatter on impact at temperature below 0 degrees Celsius ambient air temperature.
Page 132 SECTION 4 NORMAL PROCEDURES PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 4-42...
Page 133 SECTION 5 PA-46-350P, MALIBU PERFORMANCE TABLE OF CONTENTS SECTION 5 PERFORMANCE Paragraph Page General ..................Aircraft Configuration.............. Introduction - Performance and Flight Planning...... Flight Planning Example ............Performance Graphs ..............List of Figures..............ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710...
Page 134 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 5-ii...
Page 135 SECTION 5 PA-46-350P, MALIBU PERFORMANCE SECTION 5 PERFORMANCE GENERAL All of the required (FAA regulations) and complementary performance information is provided by this section. Performance information associated with those optional systems and equipment which require handbook supplements is provided by Section 9 (Supplements).
Page 136 SECTION 5 PERFORMANCE PA-46-350P, MALIBU INTRODUCTION - PERFORMANCE AND FLIGHT PLANNING (CONT.) The information provided by paragraph 5.5 (Flight Planning Example) outlines a detailed flight plan using performance charts in this section. Each chart includes its own example to show how it is used. WARNING Performance information...
Page 137 SECTION 5 PA-46-350P, MALIBU 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. The basic empty weight for the airplane as licensed at the factory has been entered in Figure 6-5.
Page 138 SECTION 5 PERFORMANCE PA-46-350P, MALIBU FLIGHT PLANNING EXAMPLE (CONT) (b) Takeoff and Landing Now that the aircraft loading has been determined, 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 139 SECTION 5 PA-46-350P, MALIBU PERFORMANCE FLIGHT PLANNING EXAMPLE (CONT) 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 140 SECTION 5 PERFORMANCE PA-46-350P, MALIBU FLIGHT PLANNING EXAMPLE (cont) (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, time, and distance for descent (Figure 5-33).
Page 141 SECTION 5 PA-46-350P, MALIBU PERFORMANCE FLIGHT PLANNING EXAMPLE (cont) Calculate the cruise fuel consumption for the cruise power setting from the information provided by the Textron Lycoming Manual and the Cruise Performance Table (refer to page 5-26). 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.
Page 142 SECTION 5 PERFORMANCE PA-46-350P, MALIBU 5.5 FLIGHT PLANNING EXAMPLE (cont) The flight time required for the flight planning example is shown below: (1) Total Flight Time (c)(4) plus (d)(2) plus (e)(6), (0.235 hrs plus 0.395 hrs plus 1.33 hrs) (14.1 min. plus 23.7 min. plus 79.6 min.) 1.96 hrs/117.4 min. (g) Total Fuel Required Determine the total fuel required by adding the fuel for start, taxi, and runup (3.0 gal., calculated by allowing 5 minutes of fuel...
Page 143 SECTION 5 PA-46-350P, MALIBU PERFORMANCE PERFORMANCE GRAPHS LIST OF FIGURES Figure Page Airspeed Calibration ..............5-11 Angle of Bank Vs. Stall Speed..........5-12 Temperature Conversion ............5-13 Pressure Altitude Vs Outside Air Temperature......5-14 Temperature Rise Due To Ram Recovery ........ 5-15 5-11 Wind Components ..............
Page 144 SECTION 5 PERFORMANCE PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 5-10...
Page 145 SECTION 5 PA-46-350P, MALIBU PERFORMANCE AIRSPEED CALIBRATION Figure 5-1 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 5-11...
Page 146 SECTION 5 PERFORMANCE PA-46-350P, MALIBU ANGLE OF BANK VS. STALL SPEED Figure 5-3 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 5-12...
Page 147 SECTION 5 PA-46-350P, MALIBU PERFORMANCE TEMPERATURE CONVERSION Figure 5-5 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 5-13...
Page 148 SECTION 5 PERFORMANCE PA-46-350P, MALIBU PRESSURE ALTITUDE OUTSIDE AIR TEMPERATURE Figure 5-7 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 5-14...
Page 149 SECTION 5 PA-46-350P, MALIBU PERFORMANCE TEMPERATURE RISE DUE TO RAM RECOVERY Figure 5-9 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 5-15...
Page 150 SECTION 5 PERFORMANCE PA-46-350P, MALIBU WIND COMPONENTS Figure 5-11 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 5-16...
Page 151 SECTION 5 PA-46-350P, MALIBU PERFORMANCE TAKEOFF GROUND ROLL, 0° FLAPS Figure 5-13 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 5-17...
Page 152 SECTION 5 PERFORMANCE PA-46-350P, MALIBU TAKEOFF GROUND ROLL, 20° FLAPS Figure 5-15 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 5-18...
Page 153 SECTION 5 PA-46-350P, MALIBU PERFORMANCE TAKEOFF DISTANCE OVER 50 FT. OBSTACLE, 0° FLAPS Figure 5-17 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 5-19...
Page 154 SECTION 5 PERFORMANCE PA-46-350P, MALIBU TAKEOFF DISTANCE OVER 50 FT. OBSTACLE, 20° FLAPS Figure 5-19 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 5-20...
Page 155 SECTION 5 PA-46-350P, MALIBU PERFORMANCE RATE OF CLIMB Figure 5-21 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 5-21...
Page 156 SECTION 5 PERFORMANCE PA-46-350P, MALIBU MAXIMUM CONTINUOUS POWER TIME, FUEL, AND DISTANCE TO CLIMB (110 KIAS) Figure 5-23 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 5-22 REVISED: SEPTEMBER 20, 1999...
Page 157 SECTION 5 PA-46-350P, MALIBU PERFORMANCE MAXIMUM CONTINUOUS POWER TIME, FUEL, AND DISTANCE TO CLIMB (125 KIAS) Figure 5-24 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 REVISED: SEPTEMBER 20, 1999 5-23...
Page 158 SECTION 5 PERFORMANCE PA-46-350P, MALIBU CRUISE CLIMB TIME, FUEL, AND DISTANCE TO CLIMB Figure 5-25 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 5-24 REVISED: SEPTEMBER 20, 1999...
Page 159 SECTION 5 PA-46-350P, MALIBU PERFORMANCE MAXIMUM MANIFOLD PRESSURE Vs. PRESSURE ALTITUDE Figure 5-26 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 5-25...
Page 160 SECTION 5 PERFORMANCE PA-46-350P, MALIBU POWER SETTING TABLE REFERENCE FIG. 5-27 ASSOCIATED CONDITIONS Man. Approx. Press. Fuel Flow @ 20,000 ft High Speed Cruise 2500 32" Hg 20 GPH Lean to Peak Normal Cruise 2500 29” Hg 18 GPH Lean to Peak 2400 30"...
Page 161 SECTION 5 PA-46-350P, MALIBU PERFORMANCE CRUISE SPEED VS. ALTITUDE Figure 5-27 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 5-27...
Page 162 SECTION 5 PERFORMANCE PA-46-350P, MALIBU ISA RANGE Figure 5-29 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 5-28 REVISED: SEPTEMBER 20, 1999...
Page 163 SECTION 5 PA-46-350P, MALIBU PERFORMANCE ISA ENDURANCE Figure 5-31 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 5-29...
Page 164 SECTION 5 PERFORMANCE PA-46-350P, MALIBU FUEL, TIME, AND DISTANCE TO DESCEND Figure 5-33 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 5-30...
Page 165 SECTION 5 PA-46-350P, MALIBU PERFORMANCE GLIDE TIME AND DISTANCE Figure 5-35 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 5-31...
Page 166 SECTION 5 PERFORMANCE PA-46-350P, MALIBU BALKED LANDING CLIMB Figure 5-37 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 5-32...
Page 167 SECTION 5 PA-46-350P, MALIBU PERFORMANCE LANDING DISTANCE OVER 50 FT. OBSTACLE Figure 5-39 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 REVISED: SEPTEMBER 20, 1999 5-33...
Page 168 SECTION 5 PERFORMANCE PA-46-350P, MALIBU LANDING GROUND ROLL Figure 5-41 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 5-34 REVISED: SEPTEMBER 20, 1999...
Page 169 SECTION 6 PA-46-350P, MALIBU 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 ......6-10 Equipment List (Form 240-0127) ......
Page 170 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 6-ii...
Page 171 SECTION 6 PA-46-350P, MALIBU 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). Although the airplane offers flexibility of loading, it cannot be flown with the maximum number of adult passengers, full fuel tanks and maximum baggage.
Page 172 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 173 SECTION 6 PA-46-350P, MALIBU WEIGHT AND BALANCE AIRPLANE WEIGHING PROCEDURE (Continued) 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 ensure that no air exists in the fuel supply lines.
Page 174 SECTION 6 WEIGHT AND BALANCE PA-46-350P, MALIBU AIRPLANE WEIGHING PROCEDURE (Continued) Scale Scale Position 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 airplane when it is level.
Page 175 SECTION 6 PA-46-350P, MALIBU WEIGHT AND BALANCE AIRPLANE WEIGHING PROCEDURE (Continued) (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) inches Where:T = N + R + L WEIGHT AND BALANCE DATA AND RECORD...
Page 176 SECTION 6 WEIGHT AND BALANCE PA-46-350P, MALIBU WEIGHT AND BALANCE DATA AND RECORD (Continued) MODEL PA-46-350P MALIBU 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 177 SECTION 6 PA-46-350P, MALIBU WEIGHT AND BALANCE WEIGHT AND BALANCE DATA AND RECORD (Continued) WEIGHT AND BALANCE RECORD Figure 6-7 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710...
Page 178 SECTION 6 WEIGHT AND BALANCE PA-46-350P, MALIBU WEIGHT AND BALANCE DATA AND RECORD (Continued) WEIGHT AND BALANCE RECORD (cont) Figure 6-7 (cont) REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999...
Page 179 SECTION 6 PA-46-350P, MALIBU WEIGHT AND BALANCE GENERAL LOADING RECOMMENDATIONS For all airplane configurations, it is the responsibility of the pilot in command to make sure that the airplane always remains within the allowable weight vs. center of gravity while in flight. The following general loading recommendation is intended only as a guide.
Page 180 SECTION 6 WEIGHT AND BALANCE PA-46-350P, MALIBU WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (a) Add the weight of all items to be loaded, except fuel, to the basic empty weight to determine zero fuel weight. (b) Use the Loading Graph (Figure 6-13) to determine the moment of all items to be carried in the airplane.
Page 181 SECTION 6 PA-46-350P, MALIBU WEIGHT AND BALANCE WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (Continued) Arm Aft Weight of Datum Moment (Lb) (Inches) (In.-Lb) Basic Empty Weight 3156.5 135.33 427169 Pilot and Front Passenger 135.50 43360 Passengers (Center Seats) 177.00 60180 Passengers (Rear Seats) 218.75 30625...
Page 182 SECTION 6 WEIGHT AND BALANCE PA-46-350P, MALIBU WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (Continued) Arm Aft Weight of Datum Moment (Lb) (Inches) (In.-Lb) Basic Empty Weight Pilot and Front Passenger 135.50 Passengers (Center Seats) 177.00 Passengers (Rear Seats) 218.75 Baggage (Forward) (100 Lb Limit) 88.60 Baggage (Aft) (100 Lb Limit) 248.23...
Page 183 SECTION 6 PA-46-350P, MALIBU WEIGHT AND BALANCE WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (Continued) LOADING GRAPH Figure 6-13 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 6-13...
Page 184 SECTION 6 WEIGHT AND BALANCE PA-46-350P, MALIBU WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (Continued) C.G. Location (Inches aft of datum) C.G. RANGE AND WEIGHT GRAPH Figure 6-15 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 6-14 REVISED: SEPTEMBER 20, 1999...
Page 185 SECTION 7 PA-46-350P, MALIBU DESCR / OPERATION TABLE OF CONTENTS SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS Paragraph Page The Airplane................The Airframe ................Engine and Propeller ..............Air Induction System ............... Engine Controls................ Transicoil Engine Monitoring Inst. System (EMIS) ....7-10 Hydraulic System ..............
Page 186 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 7-ii...
Page 187 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS THE AIRPLANE The PA-46-350P Malibu is a single engine, all metal, retractable landing gear, low wing, turbocharged airplane. It has a pressurized cabin with seating for six occupants and two separate luggage compartments.
Page 188 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU THE AIRFRAME (Continued) The wing is in effect a three section structure. The center section built-up main spar extends through the lower fuselage and outboard of each main landing gear. This section has a forward spar and a rear spar which are pin jointed at the fuselage sides.
Page 189 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION ENGINE AND PROPELLER (Continued) manifold pressure. Accessories include a starter, two magnetos, a propeller governor, two belt driven alternators, two gear driven vacuum pumps, a belt driven air conditioner compressor, an oil filter, and an air/oil separator in the crankcase breather system.
Page 190 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU ENGINE AND PROPELLER (continued) TURBO-INDUCTION SYSTEM Figure 7-1 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999...
Page 191 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION ENGINE AND PROPELLER (continued) from overboost damage by limiting manifold pressure to 42.0 in. Hg. In the event of a controller malfunction, there is a pressure relief valve on the induction manifold which will relieve manifold pressure and prevent an overboost.
Page 192 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU ENGINE CONTROLS (Continued) ENGINE OIL SYSTEM SCHEMATIC Figure 7-3 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999...
Page 193 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION ENGINE AND PROPELLER (Continued) Oil temperature and pressure information is available from separate gauges located as part of the engine gauge stack. Engine crankcase gases are discharged to an air/oil separator behind the left rear cylinder, and then vented out the left exhaust stack.
Page 194 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU AIR INDUCTION SYSTEM (Continued) The engine air induction system receives ram air through forward facing ram air louvers located on the lower cowl below the propeller. Air enters these louvers and flows through a removable air filter mounted adjacent to the louvers.
Page 195 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION ENGINE CONTROLS (Continued) CONTROL PEDESTAL Figure 7-5 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710...
Page 196 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU ENGINE CONTROLS (Continued) The friction adjustment lever, located on the far left of the control quadrant, may be adjusted to increase or decrease the friction holding the throttle, propeller and mixture controls. The propeller control lever is used to adjust engine speed (rpm) at the propeller governor.
Page 197 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION Each analog indicator also has a red status light which illuminates when a red line limitation exceedance has occurred. Each fuel quantity indicator has an amber "low fuel" status light in place of red, which illuminates with 5 gallons or less of usable fuel indicated.
Page 198 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU TRANSICOIL ELECTRONIC MODULE INSTRUMENT SYSTEM (EMIS) (CONT'D) After the self-test is complete, the EDI will automatically display the MAP, RPM, TIT, FF and OAT in the LCD windows. NOTE: Any exceedances that have previously been recorded must be called up manually by the operator. To post the digital reading of a different analog instrument, momentarily press the select button adjacent to that analog indicator.
Page 199 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION FIGURE 7-7 Transicoil Electronic Module Instrument System (EMIS) ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 7-13...
Page 200 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU TRANSICOIL ELECTRONIC MODULE INSTRUMENT SYSTEM (EMIS) (CONT'D) Note: During fuel loading entry sequence, the three digits must display 120 gallons or less at all times to permit fuel load entry into the EDI. If the fuel tanks are filled to max capacity (120 gallons usable), the pre-set full fuel value can be entered by depressing the "E"...
Page 201 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION As percent power is changed, a suggested approximate value for manifold pressure and fuel flow will be displayed. If a different RPM is desired, the set button can be depressed to toggle the active parameter to the RPM display, and the up/down arrow buttons can be used to vary the RPM in 100 RPM increments.
Page 202 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU TRANSICOIL ELECTRONIC MODULE INSTRUMENT SYSTEM (EMIS) (CONT'D) CAUTION: When the memory for limitation exceedance recording is full, no new exceedancies will be recorded (the memory can accommodate a total of 238 exceedance events for all indicators). It will be necessary for the operator to have a qualified mechanic/technician reset the memory.
Page 203 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION The push button functions used to review the limitation exceedance events in the exceedance review mode "PEAK DISPLAY" are" 1. Down Arrow - This button will cause the EDI display to post all the exceedance events for the indicator under examination.
Page 204 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU TRANSICOIL ELECTRONIC MODULE INSTRUMENT SYSTEM (EMIS) (CONT'D) An example of a limitation exceedance review operation would consist of depressing the "E" and "N" buttons simultaneously to enter the review mode for the Peak Display. At this time, two possible display presentations will be posted based on the status of the EDI exceedance memory.
Page 205 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION Instrument Mode - Aircraft on the Ground Figure 7-9 Instrument Mode - Aircraft in Flight Figure 7-11 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 7-19...
Page 206 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU TRANSICOIL ELECTRONIC MODULE INSTRUMENT SYSTEM (EMIS) (CONT'D) Percent (%) power Mode Figure 7-13 Fuel Posting Mode Figure 7-15 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 7-20...
Page 207 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION Fuel Loading Mode Figure 7-17 Exceedance Review Mode Figure 7-19 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 7-21...
Page 208 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU TRANSICOIL ELECTRONIC MODULE INSTRUMENT SYSTEM (EMIS) (CONT'D) Exceedance Review Mode Figure 7-20 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 7-22...
Page 209 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 7-23...
Page 210 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU HYDRAULIC SYSTEM The hydraulic system (refer to Figure 7-21) provides the power to retract and extend the landing gear. The electric motor driven hydraulic pump assembly is located aft of the rear baggage compartment and is accessible through the baggage compartment aft closeout panel.
Page 211 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION HYDRAULIC SYSTEM (Continued) HYDRAULIC SYSTEM Figure 7-21 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 7-25...
Page 212 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.11 LANDING GEAR The aircraft is equipped with hydraulically operated, fully retractable, tricycle landing gear. Locking-type actuators are used for main and nose gears. The actuator assembly provides mechanical gear-down locking at the fully extended position and is hydraulically unlocked.
Page 213 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.11 LANDING GEAR (continued) The landing gear is held in the DOWN position by spring loaded mechanical locking mechanisms built into each of the three actuating cylinders. The individual gear safe light switches are also mechanically operated when each mechanism is in the LOCKED position.
Page 214 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.11 LANDING GEAR (Continued) LANDING GEAR ELECTRICAL DIAGRAM Figure 7-25 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 7-28...
Page 215 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.11 LANDING GEAR (Continued) CAUTION: When flying in extreme cold where the aircraft has been cold soaked for hours, the gear may not indicate down and locked for 10 to 15 seconds while aircraft temperatures are stabilizing. The annunciator panel contains two lights pertaining to landing gear operation.
Page 216 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.13 BRAKE SYSTEM (Continued) The parking brake knob is located just below the left control column. To set the parking brake, first depress and hold the toe brake pedals and then pull the parking brake knob. To release the parking brake, first depress and hold the toe brake pedals and then push in on the parking brake knob.
Page 217 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.17 FUEL SYSTEM Fuel is stored in two main integral wing tanks (see Figure 7-27), located outboard of the mid-wing splice. Fuel quantity held by each wing tank is 60 usable gallons with one gallon of unusable fuel, for a total of 122 gallons. The minimum fuel grade is 100 or 100LL aviation grade.
Page 218 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.17 FUEL SYSTEM (Continued) CAUTION For proper mid range accuracy, fuel quantity readings should be taken when the aircraft is in coordinated level flight at zero degrees bank angle. (Pitch, roll and yaw.) Failure to observe fuel quantity in this manner will result in erroneous readings due to wing cross section, low dihedral angle and fuel tank geometry.
Page 219 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.17 FUEL SYSTEM (Continued) FUEL SYSTEM SCHEMATIC Figure 7-27 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 7-33...
Page 220 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.17 FUEL SYSTEM (Continued) Should the fuel boost pump in the fuel tank being used fail to produce sufficient pressure, the BOOST PUMP light on the annunciator panel will illuminate. In this event, confirm that the fuel selector is properly seated in the detent for the selected tank.
Page 221 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.17 FUEL SYSTEM (Continued) When beginning flight operations with an equal amount of fuel in each tank, start, taxi, takeoff, and climb on the left tank. When beginning operations with unequal amounts of fuel in each tank, care must be taken not to exceed the fuel imbalance limitations specified in paragraph 2.23(e).
Page 222 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.19 ELECTRICAL SYSTEM (Continued) ELECTRICAL POWER DISTRIBUTION SYSTEM Figure 7-29 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 7-36...
Page 223 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.19 ELECTRICAL SYSTEM (Continued) When the Battery Master switch, located on the main switch panel, is turned ON, the battery solenoid contactor closes, enabling current to flow from the battery to both the starter solenoid contactor and the tie bus located on the lower left section of the pilot’s instrument panel (Figures 7-37b and 7- 39).
Page 224 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.19 ELECTRICAL SYSTEM (continued) Left Overhead Switch Panel Right Overhead Switch Panel MAIN ELECTRICAL SWITCH PANEL (Overhead) Figure 7-31 A main bus and a nonessential bus (Figure 7-35), with associated circuit breakers, are located on the pilot’s left side panels. Two avionics buses, with associated circuit breakers (Figure 7-37a), are located on the copilot’s right side panel.
Page 225 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.19 ELECTRICAL SYSTEM (Continued) AUXILIARY SWITCH PANELS ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 7-39...
Page 226 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.19 ELECTRICAL SYSTEM (Continued) FWD Panel AFT Panel MAIN AND NONESSENTIAL C/B PANELS Figure 7-35 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 7-40...
Page 227 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.19 ELECTRICAL SYSTEM (Continued) Avionics C/B Figure 7-37a Bus Tie Figure 7-37b AVIONICS & TIE BUS - C/B PANELS Figure 7-37 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 7-41...
Page 228 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.21 INSTRUMENT PANEL The instrument panel is designed to accommodate the customary advanced flight instruments and the normally required power plant instruments. The pilots artificial horizon is vacuum operated, while the directional gyro and turn coordinator are electrically operated. A switch panel located at the top of the right radio stack contains all switches for controlling cabin comfort and deice/anti-ice systems.
Page 229 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.21 INSTRUMENT PANEL (Continued) An annunciator panel, located at the top of the left radio stack. Monitored system includes: VACUUM NO. 1 INOP, VACUUM NO. 2 INOP, PRESSURE, HYDRAULIC PUMP, PITOT HEAT OFF/INOP, FUEL IMBALANCE, ALTERNATOR NO. 1 INOP, BOOST PUMP, FUEL PRESSURE, LOW BUS VOLTAGE, CABIN ALTITUDE, STALL WARN FAIL, ALTERNATOR NO.
Page 230 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU INSTRUMENT PANEL Figure 7-39 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 7-44...
Page 231 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.21 INSTRUMENT PANEL (Continued) 1. Gyro Slaving Control 22. Attitude Indicator 2. Digital Clock 23. Heading Indicator 3. Stall Test Switch 24. Altimeter 4. Airspeed Indicator 25. Rate of Climb 5. Turn and Bank Indicator 26.
Page 232 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.23 PITOT STATIC SYSTEM Pitot pressure for the airspeed indicator is sensed by a heated pitot head installed on the bottom of the left wing and is carried through lines within the wing and fuselage to the gauge on the instrument panel (refer to Figure 7-39). Static pressure for the altimeter, vertical speed and airspeed indicators is sensed by two static source pads, one on each side of the rear fuselage forward of the elevator.
Page 233 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.23 PITOT STATIC SYSTEM (Continued) PITOT AND STATIC PRESSURE SYSTEMS Figure 7-41 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 7-47...
Page 234 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.25 ENVIRONMENTAL SYSTEM (Refer to Figure 7-43) The environmental system consists of: (a) A compressor bleed air and conditioning system. (b) The ventilating air system. (c) A supplemental electric cabin heater. (d) An air conditioning system. (e) The cabin air distribution system.
Page 235 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION The supplemental electric heater consists of a resistance type heat element, a dual hermetically sealed bimetallic type overtemperature protection, a power relay, and a 35 amp in line current limiter fuse. Its function is to provide additional heat for maintaining desired cabin comfort during ground or flight operations under temperature conditions when fully heated bleed air or ventilating air is inadequate.
Page 236 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.25 ENVIRONMENTAL SYSTEM (Continued) The AIR COND and BLOWER HI & LO switches, located as part of the environmental switch panel in the center of the instrument panel, are used to control the air conditioning system. When the AIR COND switch is selected ON, the compressor belt drive is electrically clutched, the condenser blower motor relay is closed, and both recirculation blowers are activated.
Page 237 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.25 ENVIRONMENTAL SYSTEM (Continued) ENVIRONMENTAL SYSTEM Figure 7-43 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 7-51...
Page 238 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.27 BLEED AIR, CONDITIONING AND PRESSURIZATION SYSTEM Air for cabin pressure is obtained from the engine turbocharger induction air system through two sonic venturi tubes. Bleed air is routed through the bleed air heat exchanger for the temperature conditioning to provide the desired cabin comfort level.
Page 239 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.27 BLEED AIR, CONDITIONING AND PRESSURIZATION SYSTEM (Continued) PRESSURIZATION CONTROL SCHEMATIC Figure 7-45 Below the cabin pressure controller, a triple indicator simplifies monitoring the system’s operation. The triple indicator displays the cabin altitude, cabin rate of change and the differential pressure between the cabin and the outside atmosphere.
Page 240 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.27 BLEED AIR, CONDITIONING AND PRESSURIZATION SYSTEM (Continued) CABIN ALTITUDE VS. AIRPLANE ALTITUDE Figure 7-47 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 7-54...
Page 241 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.27 BLEED AIR, CONDITIONING AND PRESSURIZATION SYSTEM (Continued) For unpressurized flight the CABIN PRESS control should be pulled fully out. Setting the CABIN PRESS/DUMP/NORM switch to DUMP will provide maximum airflow through the cabin. Cabin temperature will continue to be controlled by the CABIN TEMP control.
Page 242 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.29 VACUUM SYSTEM (Continued) Upon completion of the flight, all system abnormalities or malfunctions should be checked by a mechanic, and necessary repairs made, prior to further pressurized flight or flight under IFR. Operators of airplanes equipped with wing and tail deicers should refer to Section 9, Supplement 3, for additional information concerning the vacuum system.
Page 243 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.29 VACUUM SYSTEM (Continued) VACUUM SYSTEM Figure 7-49 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 7-57...
Page 244 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.31 CABIN FEATURES The front seats are adjustable fore and aft and vertically. Pivoting armrests are provided on the inboard side of each seat. Shoulder harnesses with inertia reels are standard equipment for all seats. The inertia reel should be checked by tugging sharply on the strap. The reel will lock in place under this test and prevent the strap from extending.
Page 245 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.31 CABIN FEATURES (Continued) EMERGENCY EXIT Figure 7-51 Optional passenger oxygen generators and masks are available and, if installed, are located in a drawer under the right aft facing seat. Crew oxygen is located under the copilot’s seat, readily available to either crew member.
Page 246 All exterior surfaces are primed and finished with polyurethane. To keep the finish attractive looking, polyurethane touch-up paint is available from Piper Factory Authorized Service Centers. 7.37 STALL WARNING An approaching stall is indicated by a stall warning horn sounding a continuous tone, as opposed to the landing gear horn’s beeping tone.
Page 247 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.39 EMERGENCY LOCATOR TRANSMITTER The Emergency Locator Transmitter (ELT) meets the requirements of FAR 91.52. It operates on self-contained batteries and is located in the aft fuselage section. It is accessible through a cover on the bottom right side. A battery replacement date is marked on the transmitter.
Page 248 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU 7.39 EMERGENCY LOCATOR TRANSMITTER (Continued) ARTEX ELT OPERATION (Cont'd) The transmitter can be activated manually at any time by placing either the remote switch or the ELT switch to the ON position. NOTE: Three sweeps of the emergency tone and an illuminated warning light indicates a normally functioning unit.
Page 249 SECTION 7 PA-46-350P, MALIBU DESCR/OPERATION 7.43 RADAR* A weather radar system can be installed in the airplane. The basic components of this installation are a Receiver-Transmitter Antenna and a cockpit indicator. The function of the weather radar system is to detect weather conditions along the flight path and to visually display a continuous weather outline on the cockpit indicator.
Page 250 SECTION 7 DESCR/OPERATION PA-46-350P, MALIBU INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 7-64...
Page 251 SECTION 8 PA-46-350P, MALIBU HAND/SERV/MAINT TABLE OF CONTENTS SECTION 8 AIRPLANE HANDLING, SERVICING, AND MAINTNEANCE Paragraph Page General ..................Airplane Inspection Periods ............. Preventive Maintenance ............Airplane Alterations ..............Ground Handling..............8.11 Engine Induction Air Filter ............8.13 Brake Service ................8.15 Hydraulic System Service ............
Page 252 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 8-ii...
Page 253 STC installations. WARNING Modifications must be approved in writing by PIPER prior to installation. Any and all other installations, whatsoever, of any kind will void this warranty in it’s entirety.
Page 254 HAND/SERV/MAINT PA-46-350P, MALIBU 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 255 This information is provided to all authorized Piper Service Centers. Service Letters deal with product improvements and servicing techniques pertaining to the airplane. They are sent to Piper Service Centers and, if necessary, to the latest FAA-registered owners in the U.S. Owners should give careful attention to Service Letter information.
Page 256 Piper Service Center or a reputable repair shop. Piper cannot accept responsibility for the continued airworthiness of any aircraft not maintained to these standards, and/or not...
Page 257 SECTION 8 PA-46-350P, MALIBU HAND/SERV/MAINT 8.3 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 258 SECTION 8 HAND/SERV/MAINT PA-46-350P, MALIBU 8.7 AIRPLANE ALTERATIONS (CONTINUED) The owner or pilot is required to ascertain that the following aircraft papers are in order and in the aircraft. (a) To be displayed in the aircraft at all times: (1) Aircraft Airworthiness Certificate Form FAA-8100-2. (2) Aircraft Registration Certificate Form FAA-8050-3.
Page 259 SECTION 8 PA-46-350P, MALIBU HAND/SERV/MAINT 8.9 GROUND HANDLING (CONTINUED) by not less than fifteen feet, and a qualified person should ride in the pilot’s seat to maintain control by use of the brakes. (b) Taxiing CAUTION Do not operate engine above 1200 rpm with cabin doors open.
Page 260 SECTION 8 HAND/SERV/MAINT PA-46-350P, MALIBU 8.9 GROUND HANDLING (CONTINUED) CAUTION Care should be taken when setting brakes that are overheated or during cold weather when accumulated moisture may freeze a brake. (3) Aileron and elevator controls should be secured with the front seat belt and chocks used to properly block the wheels.
Page 261 SECTION 8 PA-46-350P, MALIBU HAND/SERV/MAINT 8.9 GROUND HANDLING (CONTINUED) (6) Install a pitot head cover if available. Be sure to remove the pitot head cover before flight. (7) Cabin and baggage door should be locked when the air- plane is unattended. 8.11 ENGINE INDUCTION AIR FILTER (a) Removing Induction Air Filter (1) Remove louvered induction air panel assembly at nose of...
Page 262 SECTION 8 HAND/SERV/MAINT PA-46-350P, MALIBU 8.13 BRAKE SERVICE (CONTINUED) BRAKE SYSTEM Figure 8-1 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999...
Page 263 SECTION 8 PA-46-350P, MALIBU HAND/SERV/MAINT 8.13 BRAKE SERVICE (CONTINUED) located behind the aft access panel in the forward baggage compartment. If the entire system must be refilled, fill with fluid under pressure from the brake end of the system. This will eliminate air from the system. No adjustment of the brake clearances is necessary.
Page 264 SECTION 8 HAND/SERV/MAINT PA-46-350P, MALIBU 8.17 LANDING GEAR SERVICE (CONTINUED) In jacking the aircraft for landing gear or other service, two hydraulic jacks and a tail stand should be used. At least 400 pounds of ballast should be placed on the base of the tail stand before the airplane is jacked up. The hydraulic jacks should be placed under the jack points on the bottom of the wing and the airplane jacked up until the tail skid is at the right height to attach the tail stand.
Page 265 SECTION 8 PA-46-350P, MALIBU HAND/SERV/MAINT 8.21 OIL REQUIREMENTS The oil capacity of the Textron Lycoming TI0-540-AE2A engine is 12 quarts with an inflight minimum quantity of approximately 2.75 quarts. Maximum endurance flights should begin with 12 quarts of oil. For all shorter flights, it is recommended that oil be added if the quantity falls to 10 quarts.
Page 266 SECTION 8 HAND/SERV/MAINT PA-46-350P, MALIBU 8.23 FUEL SYSTEM (a) Servicing Fuel System At every 100 hour inspection or after an extended downtime, the fuel filter strainer must be cleaned. The fuel filter strainer is located below the floor on the lower right side of the forward baggage compartment.
Page 267 SECTION 8 PA-46-350P, MALIBU HAND/SERV/MAINT 8.23 FUEL SYSTEM (CONTINUED) The operation of the aircraft is approved with an anti-icing additive in the fuel. When an anti-icing additive is used it must meet the specification MIL-1-27686, must be uniformly blended with the fuel while refueling, must not exceed .15% by volume of the refueled quantity, and to ensure its effectiveness should be blended at not less than .10% by volume.
Page 268 SECTION 8 HAND/SERV/MAINT PA-46-350P, MALIBU 8.23 FUEL SYSTEM (CONTINUED) Observe all safety precautions required when handling gasoline. Fill the fuel tanks through the filler located on the forward slope of the wing. Each wing holds a maximum of 60 U.S. gallons. When using less than the standard 120 gallon capacity, fuel should be distributed equally between each side.
Page 269 SECTION 8 PA-46-350P, MALIBU HAND/SERV/MAINT 8.23 FUEL SYSTEM (CONTINUED) FUEL TANK DRAIN Figure 8-3 (e) Emptying Fuel System Drain the bulk of fuel at sump tanks. Set fuel selector on left or right tank. Push in sump drain valves and twist turn to lock open. Remaining fuel may be drained through the filter drain.
Page 270 SECTION 8 HAND/SERV/MAINT PA-46-350P, MALIBU 8.25 TIRE INFLATION For maximum service, keep tires inflated to the proper pressure: 50 psi for the nose tire and 55 psi for the main tires. All wheels and tires are balanced before original installation, and the relationship of tire, tube, and wheel should be maintained upon reinstallation.
Page 271 SECTION 8 PA-46-350P, MALIBU HAND/SERV/MAINT 8.33 LUBRICATION For lubricating instructions, a chart showing lubrication points and types of lubricants to be used, and lubrication methods, refer to the PA-46-350P Maintenance Manual. 8.35 CLEANING (a) Cleaning Engine Compartment (1) Place a large pan under the engine to catch waste. (2) With the engine cowling removed, spray or brush the engine with solvent or a mixture of solvent and degreaser.
Page 272 SECTION 8 HAND/SERV/MAINT PA-46-350P, MALIBU 8.35 CLEANING (CONTINUED) (b) Cleaning Landing Gear Before cleaning the landing gear, place a plastic cover or similar material over the wheel and brake assembly. CAUTION Do not brush the micro switches. (1) Place a pan under the gear to catch waste. (2) Spray or brush the gear area with solvent or a mixture of solvent and degreaser, as desired.
Page 273 SECTION 8 PA-46-350P, MALIBU HAND/SERV/MAINT 8.35 CLEANING (CONTINUED) (d) Cleaning Windshield and Windows CAUTION Use only mild soap and water when cleaning the heated windshield. Use of ANY other cleaning agent or material may cause distortion or damage to windshield coatings. (1) Remove dirt, mud and other loose particles from exterior surfaces with clean water.
Page 274 SECTION 8 HAND/SERV/MAINT PA-46-350P, MALIBU 8.35 CLEANING (CONTINUED) (2) For simple stains (e.g. coffee, cola) clean headliner with a sponge and a common household suds detergent (e.g. Tide). Dirty grease stains should be first spot cleaned with a lighter fluid containing Naphtha to remove the solvent soluble matter.
Page 275 SECTION 8 PA-46-350P, MALIBU HAND/SERV/MAINT 8.35 CLEANING (CONTINUED) airplane. If difficulty is encountered with the water freezing on boots, direct a blast of warm air along the region being cleaned using a portable ground heater. Petroleum products are injurious to rubber and their use as cleaning agents should be avoided.
Page 276 SECTION 8 HAND/SERV/MAINT PA-46-350P, MALIBU 8.36 CLEANING AND MAINTENANCE OF RELIEF TUBE SYSTEM When the aircraft is equipped with a relief tube system, the corrosive effects of urine or other liquids poured through the system are extreme and require much attention to the cleanliness of this system both inside and outside of the aircraft.
Page 277 SECTION 8 PA-46-350P, MALIBU HAND/SERV/MAINT (b) Exterior Exterior bottom painted surfaces of the aircraft must be cleaned from the firewall to the tip of the tail including the bottom of the tail surfaces, at termination of each flight when the relief tube system has been used.
Page 278 SECTION 8 HAND/SERV/MAINT PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 8-24...
Page 279 SECTION 9 PA-46-350P, MALIBU SUPPLEMENTS TABLE OF CONTENTS SECTION 9 SUPPLEMENTS Paragraph/Supplement Page General ..................Emergency Oxygen System ........(6 Pages) Propeller Heat, Heated Windshield, and Wing Ice Detection Light ........(6 Pages) Ice Protection System ..........(16 Pages) 9-15 B.F. Goodrich Integrated Ice Detection System ..(4 Pages) 9-31 Bendix/King 150 Series Flight Control System ..............(1 Page)
Page 280 SECTION 9 SUPPLEMENTS PA-46-350P, MALIBU TABLE OF CONTENTS SECTION 9 SUPPLEMENTS (continued) Paragraph/Supplement Page Garmin GNS 430 VHF Comm/ Nav/GPS ...............(8 Pages) 9-115 S-TEC System 55 Autopilot ............. 9-123 Garmin GNS 530 VHF Comm/ Nav/GPS ...............(8 Pages) 9-125 Garmin GTX 327 Transponder........(10 pages) 9-133 Avidyne 5RR-MFC Series FlightMax Flight Situation Display ..........(8 pages)
Page 281 SECTION 9 PA-46-350P, MALIBU SUPPLEMENTS SECTION 9 SUPPLEMENTS GENERAL This section provides information in the form of supplements which are necessary for efficient operation of the airplane when it is equipped with one or more of the various optional systems and equipment not approved with the standard airplane.
Page 282 SECTION 9 SUPPLEMENTS PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999...
Page 283 This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when the Emergency Oxygen System is installed per Piper Drawing No. 83985-2. The information contained herein supplements or supersedes the information in the basic Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual...
Page 284 This supplement supplies information necessary for the operation of the airplane when the optional Emergency Oxygen System is installed in accordance with FAA Approved Piper Data. SECTION 2 - LIMITATIONS The following placard is installed on the right cabin side panel, immediately forward of the copilot’s air vent, and the right aft facing seat, aft...
Page 285 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 1 SECTION 3 - EMERGENCY PROCEDURES In the event that the emergency oxygen system is needed, proceed as follows: Mask compartment(s) .................OPEN Mask..............REMOVE and extend lanyard to full length; tug to activate generator. Unfold and don mask(s).
Page 286 SECTION 9 SUPPLEMENT 1 PA-46-350, MALIBU SECTION 4 - NORMAL PROCEDURES Prior to each flight, turn on the master switch and check that the amber OXYGEN annunciator light is not illuminated. If the annunciator is illuminated, one or more of the oxygen generators should be replaced. In addition, check the oxygen masks and hoses for accessibility and condition.
Page 287 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 1 The crew assembly is located under the copilot’s seat and contains one two-man oxygen generator and two masks mounted on a sliding tray. The tray is accessible from the aisle between the pilot’s and copilot’s seats and is pulled out from under the seat to expose the two masks.
Page 288 SECTION 9 SUPPLEMENT 1 PA-46-350P, MALIBU OXYGEN SYSTEM INSTALLATION Figure 7-1. REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-8, 6 of 6...
Page 289 This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when any or all of the following equipment is installed per the appropriate Piper Drawing: Prop Heat - Dwg. No. 89664, Heated Windshield - Dwg. No. 82288 and Wing Ice Detection Light - Dwg.
Page 290 This supplement supplies information necessary for the operation of the airplane when the optional propeller heat, heated windshield, and wing ice detection light are installed in accordance with FAA Approved Piper data. SECTION 2 - LIMITATIONS (a) This aircraft is not approved for flight in icing conditions. (See Supplement 3, Section 2 (a) Limitations.)
Page 291 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 2 When in visible moisture at temperatures at or below +5°C and icing conditions are anticipated, turn on the windshield heat LO switch. If low windshield heat is inadequate or if icing is encountered at temperatures at or below -15°C, turn on the windshield heat HI switch.
Page 292 SECTION 9 SUPPLEMENT 2 PA-46-350P, MALIBU PROPELLER HEAT Electrothermal propeller heat pads are bonded to a portion of the leading edges of the propeller blades. The system is controlled by an ON-OFF type PROP HEAT switch (Figure 2-1) situated in the switch panel located above the right radio stack.
Page 293 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 2 ELECTRIC HEATED WINDSHIELD WARNING Flight into known or forecast icing is not approved. If icing is encountered, take avoidance action immediately. The electrically heated left windshield is controlled by two switches in the switch panel. One switch controls low windshield heat and the other high heat, and are labled accordingly.
Page 294 SECTION 9 SUPPLEMENT 2 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-14, 6 of 6...
Page 295 This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when Ice Protection System, per Piper Drawing No. 89695-2, is installed. The information contained herein supplements or supersedes the information in the basic Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein.
Page 296 This supplement supplies information necessary for the operation of the airplane when the optional Ice Protection System is installed in accordance with FAA Approved Piper data. SECTION 2 - LIMITATIONS (a) The ice protection system was designed and tested for operation in the meteorological conditions of FAR 25, Appendix C, for continuous maximum and intermittent maximum icing conditions.
Page 297 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 3 SECTION 3 - EMERGENCY PROCEDURES WARNING The malfunction of any required deice equipment requires immediate action to exit icing conditions. Depending on the severity of the icing encounter, failure to take immediate positive action can lead to performance losses severe enough to make level flight impossible.
Page 298 SECTION 9 SUPPLEMENT 3 PA-46-350P, MALIBU SINGLE VACUUM PUMP FAILURE IN ICING CONDITIONS (Reduced suction pressure and left or right vacuum inoperative annunciator illuminate ) Gyro Suction Gauge.........Check (within normal operating range) Operative Pump vacuum inoperative annunciator ......extinguished Although either vacuum pump has sufficient capacity to operate the deice boots and flight instruments in a normal manner, immediate action should be taken to exit icing conditions.
Page 299 WSHLD HI or WSHLD LO switch to OFF. Take immediate action to exit icing conditions. SECTION 4 - NORMAL PROCEDURES The Piper Malibu is approved for flight into known icing conditions when equipped with the complete Piper Ice Protection System. Operating in icing conditions of Continuous Maximum and Intermittent Maximum as defined in FAR 25, Appendix C has been substantiated;...
Page 300 SECTION 9 SUPPLEMENT 3 PA-46-350P, MALIBU After 30 seconds, the flash rate is reduced, indicating the heater is in the “off” cycle. The green lamp will continue to flash at the slower flash rate as long as the aircraft is on the ground or until the pilot de- selects “prop heat”...
Page 301 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 3 IN FLIGHT Icing conditions of any kind should be avoided whenever possible, since any minor malfunction which may occur is potentially more serious in icing conditions. Continuous attention of the pilot is required to monitor the rate of ice build-up in order to effect the boot cycle at the optimum time.
Page 302 SECTION 9 SUPPLEMENT 3 PA-46-350P, MALIBU Both alternator ammeters should be monitored whenever the deice equipment is in use. An excessive indication shows an excessive electrical load, which may cause a battery discharging condition that could eventually lead to battery depletion. Nonessential electrical equipment should be turned off to correct or prevent this condition.
Page 303 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 3 SECTION 5 - PERFORMANCE Climb speed should be increased to 130 knots when icing conditions are encountered during climb. Cruise speeds are reduced approximately 5 knots when the surface boots are installed. CAUTION Ice accumulation on the unprotected surfaces can result in significant performance loss.
Page 304 SECTION 9 SUPPLEMENT 3 PA-46-350P, MALIBU SECTION 6 - WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in Section 6 of the Airplane Flight Manual. SECTION 7 - DESCRIPTION AND OPERATION OF THE ICE PRO- TECTION SYSTEM AND EQUIPMENT For flight into known icing conditions (FIKI), a complete ice protection system is required on the Malibu.
Page 305 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 3 deice flow valves for approximately six seconds. The boot solenoid valves are activated and air pressure is released to the boots, sequentially inflating the surface deicers. A SURFACE DE-ICE indicator light, located on the annunciator panel illuminates when the boots inflate.
Page 306 SECTION 9 SUPPLEMENT 3 PA-46-350P, MALIBU ELECTRICALLY HEATED WINDSHIELD The electrically heated left windshield is heated by current from the aircraft electrical system. It is controlled by WSHLD HI and WSHLD LO switches located on the switch panel. Circuit protection is provided by the windshield CONTROL and POWER circuit breakers in the ICE PROTECTION section of pilot’s aft circuit breaker panel.
Page 307 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 3 HEATED PITOT HEAD A heated AN type head is installed under the the wing. It is controlled by an ON-OFF type PITOT HEAT switch located on the switch panel and is protected by a PITOT HEAT circuit breaker located in the ICE PROTECTION section of the pilot's aft circuit breaker panel.
Page 308 SECTION 9 SUPPLEMENT 3 PA-46-350P, MALIBU DEICE SWITCH PANEL Figure 7-1 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-28, 14 of 16...
Page 309 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 3 MAIN SWITCH PANEL (OVERHEAD LEFT & RIGHT) Figure 7-2 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 15 of 16, 9-29...
Page 310 SECTION 9 SUPPLEMENT 3 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-30, 16 of 16...
Page 311 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED PETER E. PECK D.O.A. NO. SO.-1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL FEBRUARY 23, 1999____________________ ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710...
Page 312 This supplement supplies information necessary for the operation of the airplane when the B.F. Goodrich Integrated Ice Detection System is installed in accordance with FAA Approved Piper Data. SECTION 2 - LIMITATIONS The B.F. Goodrich Smartboot Ice Detection is an advisory system only.
Page 313 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 4 IN FLIGHT (Cont’d) If the ice is removed from the empennage following inflation, the “deice” annunciator will extinguish. If less than 90% of the ice cap located over the sensor within the right horizontal deicer has been removed, the select deice annunciator will remain illuminated.
Page 314 SECTION 9 SUPPLEMENT 4 PA-46-350P, MALIBU 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 Pilots Operating Handbook and Airplane Flight Manual.
Page 315 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 5 PILOT’S OPERATING HANDBOOK SUPPLEMENT NO. 5 KING 150 SERIES FLIGHT CONTROL SYSTEM This supplement has been DELETED as the FAA Approved Operational Supplement to the Bendix/King 150 Series Flight Control System as installed per STC SA1778CE-D. Bendix/King is responsible to supply and revise the operational supplement.
Page 316 SECTION 9 SUPPLEMENTS PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-36...
Page 317 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 6 PILOT’S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 6 KING KAS 297B VERTICAL SPEED AND ALTITUDE SELECTOR This supplement has been DELETED as the FAA Approved Operational Supplement to the Bendix/King KAS 297B Vertical Speed And Altitude Selector is installed per STC SA1778CE-D.
Page 318 SECTION 9 SUPPLEMENTS PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-38...
Page 319 This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when the optional WX- 1000/WX-1000+ Stormscope System is installed per Piper Dwg. CA-46-2- 046. The information contained herein supplements or supersedes the information in the basic Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein.
Page 320 This supplement supplies information necessary for the operation of the airplane when the optional WX-1000 or WX-1000+ Stormscope system is installed in accordance with FAA Approved Piper data. SECTION 2 - LIMITATIONS (a) The WX-1000/WX-1000+ Stormscope system signal displays are not intended for the purpose of penetrating thunderstorm areas or areas of severe turbulence;...
Page 321 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 7 SECTION 5 - PERFORMANCE No change. SECTION 6 - WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in the Equipment List attached to the Pilot’s Operating Handbook.
Page 322 SECTION 9 SUPPLEMENT 7 PA-46-350P, MALIBU WX-1000 STORMSCOPE Figure 7-1 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-42, 4 of 4...
Page 323 This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when the optional Bendix/King EHI 40 EHSI system is installed per approved Piper drawings. The information contained herein supplements or supersedes the information in the basic Pilot's Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein.
Page 324 SECTION 9 SUPPLEMENT 8 PA-46-350P, MALIBU SECTION 1 - GENERAL This supplement describes the components and operation of, and operational procedures for the Bendix/King EHI 40 Electronic Horizontal Situation Indicator (EHSI). The EHI 40 system utilizes the ED 461 display unit for display and control of navigation data and sensor selection.
Page 325 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 8 SECTION 1 - GENERAL (Continued) Navigation Nautical Miles RNAV Area Navigation STBY Standby Test Variation Very High Frequency Omni Range SECTION 2 - LIMITATIONS When installed in conjunction with navigation receivers (VOR, RNAV, GPS, ADF, compass systems, etc), display presentations and operations are subject to the identical limitations as identified for that same equipment if installed on aircraft.
Page 326 SECTION 9 SUPPLEMENT 8 PA-46-350P, MALIBU SECTION 3 - EMERGENCY PROCEDURES CAUTION Following failure of a red gun in a display tube, red warning flags will not be visible. SMALL RED SG ANNUNCIATION Small red SG annunciation indicates an internal self-test failure. Automatic built-in test and monitoring functions integral to the EHI 40 software detect component failures and present failure annunciations on the face of the EHSI display.
Page 327 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 8 SECTION 3 - EMERGENCY PROCEDURES (continued) RED HDG ANNUNCIATION Red HDG annunciation indicates a failure in the compass system by removing the lubber line and replacing it with a red HDG flag. Simultaneously, the course pointer head and tail will declutter leaving the d-bar. (The d-bar will reorient on the face of the instrument providing horizontal deviation in the manner of a CDI.) The autopilot will disengage, if engaged.
Page 328 SECTION 9 SUPPLEMENT 8 PA-46-350P, MALIBU SECTION 3 - EMERGENCY PROCEDURES (continued) HEADING OR COURSE KNOB FAILURE Red flags will appear on the heading bug, or on the head and tail of the course pointer as appropriate. Autopilot will not couple HDG, NAV, or APR, but can be used for attitude or altitude hold.
Page 329 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 8 SECTION 3 - EMERGENCY PROCEDURES (continued) YELLOW DU ANNUNCIATION Yellow DU annunciation indicates a failure of the EHSI cooling fan. If a fan failure occurs in flight, monitor the display presentation for an abnormal appearance which will indicate impending failure.
Page 330 SECTION 9 SUPPLEMENT 8 PA-46-350P, MALIBU SECTION 4 - NORMAL PROCEDURES (continued) INFLIGHT OPERATION CAUTION Make transition from HSI presentations to conventional CDI presentations (MAP format) with caution. CDI left-right deviation may appear reversed when traveling outbound on a TO indication or inbound on a FROM indication.
Page 331 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 8 SECTION 5 - PERFORMANCE No changes. 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. SECTION 7 - DESCRIPTION AND OPERATION SYSTEM CONFIGURATION (1) Various configurations of the EHI 40 system are currently available to fulfill the particular needs of the user.
Page 332 SECTION 9 SUPPLEMENT 8 PA-46-350P, MALIBU SECTION 7 - DESCRIPTION AND OPERATION (Continued) OPERATING CONTROLS Figures 7-1 illustrates all operating controls for the EHI 40 systems. This figure may be referred to as the controls are in the following paragraphs. 1-2 SYSTEM SELECT - The 1-2 button is used to cycle between primary navigation sensor system #1 and #2 for display.
Page 333 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 8 SECTION 7 - DESCRIPTION AND OPERATION (Continued) 3. NUMBER 1 SYSTEM BEARING POINTER SELECT - The bearing pointer select button works similar to the NAV sensor select button. A press of the bearing pointer button sequentially selects the next available sensor for display.
Page 334 SECTION 9 SUPPLEMENT 8 PA-46-350P, MALIBU SECTION 7 - DESCRIPTION AND OPERATION (Continued) 5. ARC SECTORED MODE SELECTION - The ARC mode provides the pilot a large scale view of the CDI by presenting an approximate 85 degree sector display of the compass. The EHI 40 has three possible ARC sectored display formats: standard HSI compass rose, ARC NAV MAP mode, and ARC NAV MAP mode with radar.
Page 335 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 8 SECTION 7 - DESCRIPTION AND OPERATION (Continued) 7. RANGE SELECTION RANGE DOWN - A press of the RANGE DOWN button selects the next lower range to be displayed while in the NAV MAP mode of operation.
Page 336 SECTION 9 SUPPLEMENT 8 PA-46-350P, MALIBU SECTION 7 - DESCRIPTION AND OPERATION (Continued) 10. HEADING SELECT KNOB - Rotation of the HEADING SELECT knob allows the heading bug on the EHSI to be rotated to the desired heading. The ED 461 provides a HEADING SYNC feature. Pushing the center of theHEADING SELECT knob will cause the heading bug on the EHSI to slew to the present aircraft heading (lubber line).
Page 337 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 8 ED 461 EHI CONTROLS Figure 7-1 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 15 of 26 9-57...
Page 338 SECTION 9 SUPPLEMENT 8 PA-46-350P, MALIBU SECTION 7 - DESCRIPTION AND OPERATION (Continued) EHSI DISPLAYS Standard EHI 40 displays, which may be referred to as key points of the display, are discussed in the following paragraphs (refer to figure 7-5): Normal Compass Card Display - A 360 degree rotating white compass scale indicates the aircraft heading referenced to the white triangular heading index (lubber line).
Page 339 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 8 SECTION 7 - DESCRIPTION AND OPERATION (Continued) 4. Heading Select Bug A notched orange heading bug is manually rotated around the compass scale by the heading select knob on the control panel. A digital readout of the selected heading is displayed in the lower right hand corner.
Page 340 SECTION 9 SUPPLEMENT 8 PA-46-350P, MALIBU SECTION 7 - DESCRIPTION AND OPERATION (Continued) Course Deviation Scale (continued) The following represents the deviation scale for different navigation sources: LATERAL DEVIATION SCALE (Continued) AIRCRAFT DISPLACEMENT MODE ANGULAR DEV (DEGREES) LINEAR DEV (MILES) 1 dot 5.0 deg 2 dots...
Page 341 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 8 SECTION 7 - DESCRIPTION AND OPERATION (Continued) 9. Distance and Ground Speed Display (continued) When the selected bearing pointer source has DME data associated with it, the distance information will be displayed below the bearing pointer source annunciator.
Page 342 SECTION 9 SUPPLEMENT 8 PA-46-350P, MALIBU SECTION 7 - DESCRIPTION AND OPERATION (Continued) 11. Bearing Pointer Display - The rotating blue single bar #1 RMI Pointer points in the direction of the selected sensor ground station or waypoint. The rotating magenta double bar #2 RMI Pointer points in the direction of the selected ground station.
Page 343 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 8 SECTION 7 - DESCRIPTION AND OPERATION (Continued) ED 461 DISPLAY UNIT Figure 7-5 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 21 of 26 9-63...
Page 344 SECTION 9 SUPPLEMENT 8 PA-46-350P, MALIBU SECTION 7 - DESCRIPTION AND OPERATION (Continued) ED 461 DISPLAY UNIT Figure 7-5 (cont) REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-64 22 of 26...
Page 345 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 8 SECTION 7 - DESCRIPTION AND OPERATION (Continued) MAP DISPLAY (refer to figure 7-7) The EHI 40 provides two basic types of map; a 360 degree map display about the aircraft and an approximately 85 degree sectored map display in front of the aircraft.
Page 346 SECTION 9 SUPPLEMENT 8 PA-46-350P, MALIBU SECTION 7 - DESCRIPTION AND OPERATION (Continued) 4. Course Deviation Display - The stationary white deviation scale along the bottom of display provides reference for the course deviation bar to indicate position of airplane in relation to selected navigation course.
Page 347 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 8 SECTION 7 - DESCRIPTION AND OPERATION (Continued) 9. MAP Weather Radar Information - Four data lines are reserved below the primary NAV sensor source annunciator to display radar informaion. First Line: Special performance features. Second Line: Standard Radar Modes (WX, WXA, or MAP).
Page 348 SECTION 9 SUPPLEMENT 8 PA-46-350P, MALIBU SECTION 7 - DESCRIPTION AND OPERATION (Continued) ARC (EXPANDED) EHSI DISPLAY (refer to figure 7-9) The expanded (ARC) format provides an enlarged display for increased resolution to NAV data due to the enlarged compass scale presentations. 1.
Page 349 Pilot’s Operating Handbook a n d FA A Approved Airplane Flight Manual. FAA APPROVED PETER E. PECK D.O.A. NO. SO-1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL FEBRUARY 23, 1999 ISSUED: FEBRUARY 23, 1999...
Page 350 This supplement supplies information necessary for the operation of the airplane when the optional Bendix/King RDR 2000 Vertical Profile Weather Radar System is installed in accordance with FAA Approved Piper data. SECTION 2 - LIMITATIONS Do not operate the radar during refueling operations or within 15 feet of trucks or containers accommodating flammables or explosives.
Page 351 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 9 SECTION 5 - PERFORMANCE When the radar pod is installed: The rate of climb is decreased approximately 50 fpm. The cruise speed is decreased approximately 2 knots. The cruise range is decreased approximately 1% due to the decrease in cruise speed.
Page 352 SECTION 9 SUPPLEMENT 9 PA-46-350P, MALIBU Operation and Controls RDR 2000 CONTROLS AND INDICATOR Figure 7-1 REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-72 4 of 10...
Page 353 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 9 Operation and Controls (cont.) CONTROL/ DISPLAY FUNCTION BRT Control Adjusts brightness of the display for varying cockpit light conditions. Wx/Wxa Button When pressed, alternately selects between the Wx (weather) and Wxa (weather alert) modes of operation. Wx or Wxa will appear in the lower left of the display.
Page 354 SECTION 9 SUPPLEMENT 9 PA-46-350P, MALIBU Operation and Controls (cont.) CONTROL/ DISPLAY FUNCTION GAIN Control Knob Manual gain control becomes active only when ground-mapping (MAP) is selected. Gain is internally set in all other modes. Radar Function 1. LOG position is used only when the Selector Switch Bendix/King IU 2023 series radar graphics unit is installedalong with a...
Page 355 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 9 Operation and Controls (cont.) CONTROL/ DISPLAY FUNCTION Radar Function 5. OFF position removes primary power Selector Switch (cont.) from the radar indicator and the sensor. The antenna is parked in the down position. Selector Button When pressed clears the display and advances the indicator to the next higher range.
Page 356 SECTION 9 SUPPLEMENT 9 PA-46-350P, MALIBU Operation and Controls (cont.) CONTROL/ DISPLAY FUNCTION 1. Prior to engaging VP, the appropriate button (left or right) is used to place the track line at the desired azimuth angle to be vertically scanned (sliced). When VP is engaged, the slice will be taken at the last position of the track line, whether it is visible or not.
Page 357 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 9 Operation and Controls (cont.) VERTICAL PROFILE MODE (RDR 2000 Figure 7-3 1. Vertical PROFILE mode annunciation 2. Left or right track annunciation. 3. Degrees of track left or right of aircraft nose. 4. Displays plus and minus thousands of feet from relative altitude. Will vary with selected range.
Page 358 SECTION 9 SUPPLEMENT 9 PA-46-350P, MALIBU Operation and Controls (cont.) TEST PATTERN Figure 7-5 Detail description on the function and use of the various controls and displays are outlined in the Bendix/King RDR 2000 Vertical Profile Weather Radar System Pilot's Guide, P/N 006-08755-0000, latest revision. REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-78,...
Page 359 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: PETER E. PECK D.O.A. NO. SO-1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: FEBRUARY 23, 1999 ISSUED: FEBRUARY 23, 1999...
Page 360 SECTION 9 SUPPLEMENT 10 PA-46-350P, MALIBU SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Argus 7000CE Moving Map Display is installed. The display must be operated within the limitations herein specified. The information contained within this supplement is to be used in conjunction with the complete handbook.
Page 361 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 10 conducting a precision approach to, or departure from, a landing facility. When using the ADF bearing pointer for navigation in the map and plan submode, the range must be limited to 40 nm or less, and the pointer must be discernible.
Page 362 SECTION 9 SUPPLEMENT 10 PA-46-350P, MALIBU SECTION 5 - PERFORMANCE No change. SECTION 6 - WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in the Equipment List attached to the Pilot's Operating Handbook.
Page 363 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 10 SECTION 7 - DESCRIPTION AND OPERATION (Continued) (2) In addition, the Software Program VERsion will appear on the Disclaimer Page, which will remain in view until any functional push button is depressed. The current VERsion is 5.0. (3) The intensity of the Argus 7000CE CRT and LED push buttons may be adjusted by rotating the PUSH-ON knob.
Page 364 SECTION 9 SUPPLEMENT 10 PA-46-350P, MALIBU SECTION 7 - DESCRIPTION AND OPERATION (Continued) 40 nm to 1 nm distance to the destination waypoint. All other navigation information is similar to that of the DEParture and ENRoute modes. Orientation and direction of flight of the moving arrow or symbolic aircraft is with respect to Gyroscopic Directional HSI heading, or GPS computed track.
Page 365 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 10 SECTION 7 - DESCRIPTION AND OPERATION (Continued) d. ADF Bearing Pointer and Digital ADF Bearing Procedures. (1) In the DEParture or ENRoute modes, when ADF is selected, the bearing pointer and/or tail will appear on the perimeter of the Compass Rose.
Page 366 SECTION 9 SUPPLEMENT 10 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-86, 8 of 8...
Page 367 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED PETER E. PECK D.O.A. NO. SO.-1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL_____________FEBRUARY 23, 1999 _______ ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710...
Page 368 SECTION 9 SUPPLEMENT 11 PA-46-350P, MALIBU SECTION 1 - GENERAL The KLN 90B GPS panel mounted unit contains the GPS sensor, the navigation computer, a CRT display, and all controls required to operate the unit. It also houses the data base cartridge which plugs directly into the back of the unit.
Page 369 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 11 SECTION 2 - LIMITATIONS The KLN 90B GPS Pilot’s Guide, P/N 006-08773-0000, dated December, 1994 (or later applicable revision) must be immediately available to the flight crew whenever navigation is predicated on the use of the system.
Page 370 SECTION 9 SUPPLEMENT 11 PA-46-350P, MALIBU SECTION 3 - EMERGENCY PROCEDURES ABNORMAL PROCEDURES If the KLN 90B GPS information is not available or invalid, utilize remaining operational navigation equipment as required. If a “RAIM NOT AVAILABLE” message is displayed while conducting an instrument approach, terminate the approach.
Page 371 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 11 SECTION 4 - NORMAL PROCEDURES (CONT'D) 3. Waypoint (WPT) annunciator - Prior to reaching a waypoint in the active flight plan, the KLN 90B GPS will provide navigation along a curved path segment to ensure a smooth transition between two adjacent legs in the flight plan.
Page 372 SECTION 9 SUPPLEMENT 11 PA-46-350P, MALIBU SECTION 4 - NORMAL PROCEDURES (CONT'D) NOTE Manual HSI course centering in OBS using the control knob can be difficult, especially at long distances. Centering the dbar can best be accomplished by pressing and then manually setting the HSI pointer to the course value prescribed in the KLN 90B displayed message.
Page 373 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 11 SECTION 4 - NORMAL PROCEDURES (CONT'D) APPROACH MODE SEQUENCING AND RAIM PREDICTION NOTE The special use airspace alert will automatically be disabled prior to flying an instrument approach to reduce the potential for message congestion. 1.
Page 374 SECTION 9 SUPPLEMENT 11 PA-46-350P, MALIBU SECTION 4 - NORMAL PROCEDURES (CONT'D) 4. Select Super NAV 5 page to fly the approach procedure. If receiving radar vectors, or need to fly a procedure turn or holding pattern, fly in OBS until inbound to the FAF. NOTE: OBS navigation is TO-FROM (like a VOR) without waypoint sequencing.
Page 375 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 11 SECTION 4 - NORMAL PROCEDURES (CONT'D) 8. Missed Approach: Climb Navigate to the MAP (in APR ARM if APR ACTV is not available). NOTE: There is no automatic LEG sequencing at the MAP. After climbing in accordance with the published missed approach procedure, press , verify or change the desired holding fix and press ENT.
Page 376 SECTION 9 SUPPLEMENT 11 PA-46-350P, MALIBU SECTION 4 - NORMAL PROCEDURES (CONT'D) • Waypoint suffixes in the flight plan: i - IAF f - FAF m - MAP h - missed approach holding fix. • The DME arc IAF (arc intercept waypoint) will be a) on your present position radial off the arc VOR when you load the IAF into the flight plan, or b) the beginning of...
Page 377 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 11 SECTION 4 - NORMAL PROCEDURES (CONT'D • APR ARM to APR ACTV is automatic provided: a. You are in APR ARM (normally automatic). b. You are in LEG model! c. The FAF is the active ; waypoint d.
Page 378 SECTION 9 SUPPLEMENT 11 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-98, 12 of 12...
Page 379 This supplement must be attached to the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual when the KX 155A Comm/Nav System is installed per the Piper Drawings. The information contained herein supplements or supersedes the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein.
Page 380 PA-46-350P, MALIBU SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the Bendix/King KX 155A Comm/Nav System is installed in accordance with FAA approved Piper data. SECTION 2 LIMITATIONS No change. SECTION 3- EMERGENCY PROCEDURES No change.
Page 381 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 12 SECTION 7 DESCRIPTION & OPERATION GENERAL All controls required to operate the KX 155A/165A are located on the unit front panel. (See Figure 3-1.) FIGURE 3-1 KX 155A CONTROL FUNCTIONS COMM TRANSCEIVER Rotate the VOL knob clockwise from the OFF position. Pull the VOL knob out and adjust for desired listening level.
Page 382 SECTION 9 SUPPLEMENT 12 PA-46-350P, MALIBU COMM TRANSCEIVER (CONT'D) The outer knob will change the MHz portion of the standby display. At one band-edge (118 or 136 MHz) the following 1 MHz change will wrap around to the other band-edge. The inner knob will change the kHz portion of the standby display.
Page 383 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 12 The KX 155A also has provision to program 32 channels. Pressing the CHAN button for 2 or more seconds will cause the unit to enter the channel program mode. Upon entering the channel program mode,”PG” is displayed next to the channel number and the channel number will flash indicating that it can be programmed.
Page 384 SECTION 9 SUPPLEMENT 12 PA-46-350P, MALIBU NAV RECEIVER (CONT'D) The inner knob operates in 50 kHz steps. The NAV receiver’s lower and upper frequency limits are 108.00 MHz and 117.95 MHz. Exceeding the upper limit of frequency band will automatically return to the lower limit and vice versa. Depressing the NAV frequency transfer button for 2 seconds or more will cause the display to go in to the ACTIVE ENTRY mode.
Page 385 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 12 FIGURE 3-3 NAV DISPLAY; ACTIVE LOCALIZER FREQUENCY/CDI FORMAT When the received signal is too weak to ensure accuracy the display will “flag”. See Figure 3-4. FIGURE 3-4 VOR FLAG DISPLAY ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 7 of 12, 9-105...
Page 386 SECTION 9 SUPPLEMENT 12 PA-46-350P, MALIBU NAV RECEIVER (CONT'D) Depressing the mode button will cause the NAV display to go from the ACTIVE/CDI format to the ACTIVE/BEARING format. In the BEARING mode, the increment/decrement knob channels the ACTIVE frequency window and depressing the frequency transfer button will cause the ACTIVE frequency to be placed in blind storage and the STANDBY frequency (in blind storage) to be displayed in the ACTIVE window display.
Page 387 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 12 Another push of the mode button will cause the NAV display to go from the ACTIVE/BEARING format to the ACTIVE/RADIAL format as shown in Figure 3-7. In the RADIAL mode, the increment/decrement knob channels the ACTIVE frequency window and depressing the frequency transfer button will cause the ACTIVE frequency to be placed in blind storage and the STANDBY frequency (in blind storage) to be displayed in the ACTIVE window display.
Page 388 SECTION 9 SUPPLEMENT 12 PA-46-350P, MALIBU NAV RECEIVER (CONT'D) Another push of the mode button will cause the unit to go into the TIMER mode. See Figure 3-9. When the unit is turned on the elapsed timer begins counting upwards from zero. The timer can be stopped and reset to zero by pushing the NAV frequency transfer button for 2 seconds or more causing the ET on the display to flash.
Page 389 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 12 PILOT CONFIGURATION This mode can be accessed by pressing and holding the Nav Mode Button for more than 2 seconds and then pressing the Nav Frequency Transfer Button for an additional 2 seconds, while continuing to hold the Nav Mode Button. When the Pilot Config Mode is entered the unit will show the “SWRV”...
Page 390 SECTION 9 SUPPLEMENT 12 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-110, 12 of 12...
Page 391 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 13 PILOT’S OPERATING HANDBOOK SUPPLEMENT NO. 13 PRECISE FLIGHT SPEEDBRAKE 2000 This supplement has been DELETED as the FAA Approved Operational Supplement to the Precise Flight SPEEDBRAKE2000 System as installed in this aircraft per STC SA00520SE. Precise Flight Inc. is responsible to supply and revise the operational supplement.
Page 392 SECTION 9 SUPPLEMENTS PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-112...
Page 393 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 14 PILOT’S OPERATING HANDBOOK SUPPLEMENT NO. 14 BENDIX/KING KFC 225 FLIGHT CONTROL SYSTEM This supplement has been DELETED as the FAA Approved Operational Supplement to the Bendix/King KFC 225 Series Flight Control System as installed per STC SA00656WI-D. Bendix/King is responsible to supply and revise the operational supplement.
Page 394 SECTION 9 SUPPLEMENTS PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-114...
Page 395 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: PETER E. PECK D.O.A. NO. SO- I THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: September 20,1999 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 REVISED: NOVEMBER 12, 1999...
Page 396 SECTION 9 SUPPLEMENT 15 PA-46-350P, MALIBU SECTION 1 - GENERAL The GNS 430 System is a fully integrated, panel mounted instrument, which contains a VHF Communications Transceiver, a VOR/ILS receiver, and a Global Positioning System (GPS) Navigation computer. The system consists of a GPS antenna, GPS receiver, VHF VOR/LOC/GS antenna, VOR/lLS receiver, VHF COMM antenna and a VHF Communications transceiver.
Page 397 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 15 SECTION 2 - LIMITATIONS A. The GARMIN GNS 430 Pilot’s Guide, p/n 190-00140-00, Rev. A, dated October 1998, or later appropriate revision, must be immediately available to the flight crew whenever navigation is predicated on the use of the system.
Page 398 SECTION 9 SUPPLEMENT 15 PA-46-350P, MALIBU SECTION 2 - LIMITATIONS (continued) 2. Accomplishment of ILS, LOC, LOC-BC, LDA, SDF, MLS or any other type of approach not approved for GPS overlay with the GNS 430’s GPS receiver is not authorized. Use of the GNS 430 VOR/ILS receiver to fly approaches not approved for GPS require VOR/ILS navigation data to be present on the external indicator.
Page 399 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 15 SECTION 3 - EMERGENCY PROCEDURES ABNORMAL PROCEDURES A. If GARMIN GNS 430 navigation information is not available or invalid, utilize remaining operational navigation equipment as required. B. If “RAIM POSITION WARNING” message is displayed the system will flag and no longer provide GPS based navigational guidance.
Page 400 SECTION 9 SUPPLEMENT 15 PA-46-350P, MALIBU SECTION 4 - NORMAL PROCEDURES WARNING Familiarity with the enroute operation of the GNS 430 does not constitute proficiency in approach operations. Do not attempt approach operations in IMC prior to attaining proficiency in the use of the GNS 430 approach feature. A.
Page 401 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 15 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 basic Pilot’s Operating Handbook. SECTION 7 - DESCRIPTION AND OPERATION See GNS 430 Pilot’s Guide for a complete description of the GNS 430 system.
Page 402 SECTION 9 SUPPLEMENT 15 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-122 8 of 8 REVISED: NOVEMBER 12, 1999...
Page 403 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 16 PILOT'S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 16 S-TEC SYSTEM 55 TWO AXIS AUTOMATIC FLIGHT GUIDANCE SYSTEM WITH TRIM MONITOR (Serial numbers 4636248 and up) The FAA approved operational supplement for the S-TEC System 55 Autopilot, installed in accordance with STC SA09402AC-D, is required for operation of this system.
Page 404 SECTION 9 SUPPLEMENT 16 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-124 REVISED: NOVEMBER 12, 1999...
Page 405 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: PETER E. PECK D.O.A. NO. SO- 1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: September 10, 2001 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710...
Page 406 SECTION 9 SUPPLEMENT 17 PA-46-350P, MALIBU SECTION 1 - GENERAL The GNS 530 System is a fully integrated, panel mounted instrument, which contains a VHF Communications Transceiver, a VOR/ILS Receiver, and a Global Positioning System (GPS) Navigation computer. The system consists of a GPS Antenna, GPS Receiver, VHF VOR/LOC/GS Antenna, VOR/ILS Receiver, VHF COMM Antenna and a VHF Communications Transceiver.
Page 407 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 17 SECTION 2 - LIMITATIONS A. The GARMIN GNS 530 Pilot’s Guide, p/n 190-00181-00, Rev. A, dated November 1999, or later appropriate revision, must be immediately available to the flight crew whenever navigation is predicated on the use of the system.
Page 408 SECTION 9 SUPPLEMENT 17 PA-46-350P, MALIBU SECTION 2 - LIMITATIONS (continued) 2. Accomplishment of ILS, LOC, LOC-BC, LDA, SDF, MLS or any other type of approach not approved for GPS overlay with the GNS 530’s GPS receiver is not authorized. Use of the GNS 530 VOR/ILS receiver to fly approaches not approved for GPS require VOR/ILS navigation data to be present on the external indicator.
Page 409 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 17 SECTION 3 - EMERGENCY PROCEDURES ABNORMAL PROCEDURES A. If GARMIN GNS 530 navigation information is not available or invalid, utilize remaining operational navigation equipment as required. B. If “RAIM POSITION WARNING” message is displayed the system will flag and no longer provide GPS based navigational guidance.
Page 410 SECTION 9 SUPPLEMENT 17 PA-46-350P, MALIBU SECTION 4 - NORMAL PROCEDURES WARNING Familiarity with the enroute operation of the GNS 530 does not constitute proficiency in approach operations. Do not attempt approach operations in IMC prior to attaining proficiency in the use of the GNS 530 approach features. A.
Page 411 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 17 SECTION 4 - NORMAL PROCEDURES (continued) E. AUTOMATIC LOCALIZER COURSE CAPTURE By default, the GNS 530 automatic localizer course capture feature is enabled. This feature provides a method for system navigation data present on the external indicators to be switched automatically from GPS guidance to localizer/glide slope guidance at the point of course intercept on a localizer at which GPS derived course deviation equals localizer derived course deviation.
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Page 413 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: PETER E. PECK D.O.A. NO. SO- 1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: September 10, 2001 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710...
Page 414 SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the Garmin GTX 327 Transponder is installed in accordance with FAA approved Piper data. SECTION 2 - LIMITATIONS No change. SECTION 3 - EMERGENCY PROCEDURES To transmit an emergency signal: •...
Page 415 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 18 SECTION 4 - NORMAL PROCEDURES BEFORE TAKEOFF: • To transmit Mode C (Altitude Reporting) code in flight: • Mode Selection Key - ALT • Code Selector Keys - SELECT assigned code. To transmit Mode A (Aircraft Identification) code in flight: •...
Page 416 SECTION 9 SUPPLEMENT 18 PA-46-350P, MALIBU SECTION 7 - DESCRIPTION AND OPERATION The GTX 327 transponder is powered on by pressing the STBY, ALT or ON keys, or by a remote avionics master switch (if applicable). After power on, a start-up page will be displayed while the unit performs a self test.
Page 417 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 18 SECTION 7 - DESCRIPTION AND OPERATION (continued) GTX 327 Configuration Mode (continued) To use the GTX 327 Configuration Mode: 1. Press and hold the FUNC key while powering on the unit using the STBY, ON, or ALT key (or using an avionics master switch). 2.
Page 418 SECTION 9 SUPPLEMENT 18 PA-46-350P, MALIBU SECTION 7 - DESCRIPTION AND OPERATION (continued) Code Selection (continued) Important Codes: 1200 - The VFR code for any altitude in the US (Refer to ICAO standards elsewhere) 7000 - The VFR code commonly used in Europe (Refer to ICAO standards) 7500 - Hijack code (Aircraft is subject to unlawful interference) 7600 - Loss of communications 7700 - Emergency...
Page 419 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 18 SECTION 7 - DESCRIPTION AND OPERATION (continued) Keys for Other GTX 327 Functions (continued) PRESSURE ALT: Displays the altitude data supplied to the GTX 327 in feet, hundreds of feet (i.e., flight level), or meters, depending on configuration.
Page 420 SECTION 9 SUPPLEMENT 18 PA-46-350P, MALIBU SECTION 7 - DESCRIPTION AND OPERATION (continued) Altitude Trend Indicator When the “PRESSURE ALT” page is displayed, an arrow may be displayed to the right of the altitude, indicating that the altitude is increasing or decreasing. One of two sizes of arrows may be displayed depending on the rate of climb/descent.
Page 421 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 18 SECTION 7 - DESCRIPTION AND OPERATION (continued) Automatic ALT/STBY Mode Switching If the GTX 327 is configured for automatic standby switching, the mode will automatically change to ALT when a squat switch senses that the aircraft has become airborne.
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Page 423 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: PETER E. PECK D.O.A. NO. SO- 1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: September 10, 2001 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710...
Page 424 This supplement provides information necessary for the operation of the aircraft with the Avidyne FlightMax 700/750 FSD installed (5RR-MFC Series FlightMax Flight Situation Display installed in accordance with FAA approved Piper data). SECTION 2 - LIMITATIONS 1. Use of Avidyne charts during IFR flight requires an IFR approved GPS receiver and installation, operated in accordance with its applicable limitations.
Page 425 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 19 SECTION 3 - EMERGENCY PROCEDURES There is no change to the aircraft emergency procedures with this equipment installed. SECTION 4 - NORMAL PROCEDURES Normal operating procedures for all FSD functions are shown in the FlightMax 700/750 Series User’s Manual, 600-0032.
Page 426 SECTION 9 SUPPLEMENT 19 PA-46-350P, MALIBU SECTION 7 - DESCRIPTION AND OPERATION (CONTINUED) AVIDYNE NAVIGATOR (FlightMax 750 FSD only) (continued) Navigator displays real-time navigation data such as distance and bearing to waypoints and nearby airports, cross-track error against a planned route of flight, and estimated time of arrival at a destination.
Page 427 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 19 SECTION 7 - DESCRIPTION AND OPERATION (CONTINUED) AVIDYNE LIGHTNING (FlightMax 750 FSD only) Avidyne Lightning displays weather avoidance data gathered by an airborne thunderstorm sensor, the BF Goodrich Avionics Systems Stormscope® WX-500 Weather Mapping System. Proper use of Avidyne Lightning and the WX-500 can improve the pilot’s ability to maintain a safe distance from thunderstorms.
Page 428 SECTION 9 SUPPLEMENT 19 PA-46-350P, MALIBU SECTION 7 - DESCRIPTION AND OPERATION (CONTINUED) AVIDYNE CHARTS (FlightMax 750 FSD only) Avidyne Charts is a moving map display. Interfacing with an onboard, external GPS, Avidyne Charts shows aircraft position on the 3 by 4 inch display. Avidyne Charts gives access to digitized versions of VFR and IFR ENROUTE charts.
Page 429 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 19 SECTION 7 - DESCRIPTION AND OPERATION (CONTINUED) DATABASE UPDATES Avidyne Navigator is intended for use as an enhanced human interface to a variety of certified GPS receivers. As with certified receivers, the database of Avidyne Navigator is a critical component and must be kept current.
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Page 431 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: PETER E. PECK D.O.A. NO. SO- I THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: September 10, 2001 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710...
Page 432 SECTION 9 SUPPLEMENT 20 PA-46-350P, MALIBU SECTION 1 - GENERAL The SKYWATCH system is an on-board traffic advisory system which monitors a radius of nominally 6 nautical miles about the aircraft by interrogating any “intruding” aircraft transponder, and determines if a potential conflict exists with other aircraft.
Page 433 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 20 SECTION 2 - LIMITATIONS Information shown on the display is provided to the pilot as an aid to visually acquiring traffic. Pilot’s should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic. Maneuver should be consistent with ATC instructions.
Page 434 SECTION 9 SUPPLEMENT 20 PA-46-350P, MALIBU SECTION 4 - NORMAL PROCEDURES (continued) SELF TEST (continued) If “TRAFFIC ADVISORY SYSTEM TEST FAILED” is heard or the SKY497 FAILED screen appears, the SKYWATCH system should be turned OFF. NOTE The SELF TEST is inhibited when the aircraft is airborne.
Page 435 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 20 SECTION 4 - NORMAL PROCEDURES (continued) ABNORMAL PROCEDURES If “TRAFFIC ADVISORY SYSTEM TEST FAILED” is heard or the SKY497 FAILED screen appears, the SKYWATCH system should be turned OFF. If the barometric altimeter fails in flight and is the altitude source for the transponder, turn SKYWATCH OFF.
Page 436 SECTION 9 SUPPLEMENT 20 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-156, 6 of 6 REVISED: SEPTEMBER 10, 2001...
Page 437 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: PETER E. PECK D.O.A. NO. SO- I THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: September 10, 2001 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710...
Page 438 SECTION 9 SUPPLEMENT 21 PA-46-350P, MALIBU SECTION 1 - GENERAL This supplement provides information necessary for the operation of the aircraft with the BF Goodrich WX-500 Stormscope. WARNING Never use your Stormscope system to attempt to penetrate a thunderstorm. The FAA Advisory Circular, Subject: Thunderstorms, and the Airman’s Information Manual (AIM) recom- mend that a pilot “avoid by at least 20...
Page 439 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 21 SECTION 4 - NORMAL PROCEDURES Normal operating procedures are described in the BF Goodrich Aerospace WX-500 Stormscope Users Guide, p/n 009-11501-001, Rev. A, dated September 10, 1997, or later appropriate revision. SECTION 5 - PERFORMANCE No change.
Page 440 SECTION 9 SUPPLEMENT 21 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-160, 4 of 4 REVISED: SEPTEMBER 10, 2001...
Page 441 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 22 MEGGITT ELECTRONIC FLIGHT DISPLAY SYSTEM (EFIS) INSTALLED ON A PIPER PA-46-350P (PILOT SIDE ONLY) The FAA approved operational supplement for the Meggitt Electronic Flight Display System (Pilot Side Only), installed in accordance with STC SA09557AC, is required for operation of this system.
Page 442 SECTION 9 SUPPLEMENT 22 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-162 REVISED: APRIL 19, 2002...
Page 443 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 23 PILOT’S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 23 BENDIX/KING KMH 880 MULTI-HAZARD AWARENESS SYSTEM The FAA approved operational supplement for the Bendix/King KMH 880 Multi-Hazard Awareness System, installed in accordance with STC SA01006WI-D, is required for operation of this system.
Page 444 SECTION 9 SUPPLEMENT 23 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 9-164 REVISED: NOVEMBER 8, 2002...
Page 445 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: ALBERT J. MILL D.O.A. NO. SO - 1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: January 20, 2004 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710...
Page 446 This supplement supplies information necessary for the operation of the airplane when the Garmin GTX 330 Transponder is installed in accordance with FAA approved Piper data. SECTION 2 - LIMITATIONS A. Display of TIS traffic information is advisory only and does not relieve the pilot responsibility to “see and avoid”...
Page 447 SECTION 9 PA-46-350P, MALIBU SUPPLEMENT 24 SECTION 4 - NORMAL PROCEDURES BEFORE TAKEOFF: To transmit Mode C (Altitude Reporting) code in flight: • Mode Selection Key - ALT • Code Selector Keys - SELECT assigned code. To transmit Mode A (Aircraft Identification) code in flight: •...
Page 448 SECTION 9 SUPPLEMENT 24 PA-46-350P, MALIBU 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 Airplane Flight Manual. SECTION 7 - DESCRIPTION AND OPERATION See the 400/500 Series Garmin Display Interfaces (Pilot’s Guide Addendum), P/N 190-00140-13, and GTX 330 Pilot’s Guide, P/N 190-00207-00, for a complete description of the GTX 330 system.
Page 449 SECTION 10 PA-46-350P , MALIBU OPERATING TIPS TABLE OF CONTENTS SECTION 10 OPERATING TIPS Paragraph Page 10.1 General ..................10-1 10.3 Operating Tips ................10-1 ISSUED: FEBRUARY 23, 1999 REPORT: VB-1710 10-i...
Page 450 PA-46-350P, MALIBU THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1710 ISSUED: FEBRUARY 23, 1999 10-ii...
Page 451 SECTION 10 PA-46-350P, MALIBU OPERATING TIPS SECTION 10 OPERATING TIPS 10.1 GENERAL This section provides operating tips of particular value in the operation of the Malibu. 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 (b) The best speed for takeoff is 80 to 85 KIAS under normal conditions.
Page 452 SECTION 10 OPERATING TIPS PA-46-350P, MALIBU 10.3 OPERATING TIPS (continued) (g) In an effort to avoid accidents, pilots should obtain and study the safety related information made available in FAA publications, such as regulations, advisory circulars, Aviation News, AIM and safety aids.

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