Page 1 WARNING This Information Manual may be used for general information purposes only. This Information Manual is not kept current. It must not be used as a substitute for the official FAA approved Pilot’s Operating Handbook required for operation of the airplane.
Page 2 SEMINOLE PA-44-180 SN 4496001 AND UP INFORMATION MANUAL MANUAL PART NUMBER 761-873...
Page 5 PA-44-180, SEMINOLE APPLICABILITY Application of this handbook is limited to the specific Piper PA-44-180 model airplane designated by serial number and registration number on the face of the title page of this handbook. WARNING This handbook cannot be used for operational purposes unless kept in a current status.
Page 6 PA-44-180, SEMINOLE II. Revision Procedure Revisions will be distributed whenever necessary as complete page replacements or additions and shall be inserted into the handbook in accordance with the instructions given below. 1. Revision pages will replace only pages with the same page number.
Page 7 PA-44-180, SEMINOLE PILOT'S OPERATING HANDBOOK LOG OF REVISIONS Current Revisions to the PA-44-180, Seminole Pilot's Operating Handbook, REPORT: VB-1616 issued July 12, 1995. Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 1 Revised Table of Contents. (PR951025) 9-31 Added Supplement 3...
Page 8: Table Of Contents
PA-44-180, SEMINOLE PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 4 Added Rev. 4 to Log of Revs. (PR960604) Revised Para. 2.25 Revised Para. 2.27 3-ii Revised Table of Contents 3-iii Revised Table of Contents...
Page 9 PA-44-180, SEMINOLE PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 7 vi-a Added page & Rev. 7 to L of R. (PR981105) vi-b Added page. Revised Table of Contents. Revised Supplement 1.
Page 10: Revised Para
PA-44-180, SEMINOLE PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 10 9-93 Added pages (PR010112) thru and Supplement 11. continued 9-94 9-95 Added pages thru and Supplement 12. 9-100 9-101 Added pages...
Page 12: Report: Vb
PA-44-180, SEMINOLE PILOT'S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date REPORT: VB-1616 ISSUED: JULY 12, 1995 vi-d REVISED: NOVEMBER 30, 2001...
Page 13 PA-44-180, SEMINOLE 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 14: Issued: July
PA-44-180, SEMINOLE THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1616 ISSUED: JULY 12, 1995 viii...
Page 15 SECTION 1 PA-44-180, SEMINOLE GENERAL TABLE OF CONTENTS SECTION 1 GENERAL Paragraph Page Introduction ................... Engine ................... Propeller ..................Fuel ......................................1.11 Maximum Weights ................ 1.13 Standard Airplane Weights ............1.15 Baggage Space and Entry Dimensions ......... 1.17 Specific Loading ................1.19 Symbols, Abbreviations and Terminology........
Page 16 SECTION 1 GENERAL PA-44-180, SEMINOLE THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1616 ISSUED: JULY 12, 1995 1-ii...
Page 17: Introduction
SECTION 1 PA-44-180, SEMINOLE 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 18 SECTION 1 GENERAL PA-44-180, SEMINOLE THREE VIEW Figure 1-1 REPORT: VB-1616 ISSUED: JULY 12, 1995...
Page 19: Engine
SECTION 1 PA-44-180, SEMINOLE GENERAL 1.3 ENGINE (a) Number of Engines (b) Engine Manufacturer Lycoming (c) Engine Model Number Left 0-360-A1H6 Right L0-360-A1H6 (d) Rated Horsepower (e) Rated Speed (rpm) 2700 (f) Bore (in.) 5.125 (g) Stroke (in.) 4.375 (h) Displacement (cu. in.) (i) Compression Ratio 8.5:1 (j) Engine Type...
Page 20: Fuel
SECTION 1 GENERAL PA-44-180, SEMINOLE 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 21: Maximum Weights
SECTION 1 PA-44-180, SEMINOLE GENERAL 1.11 MAXIMUM WEIGHTS (a) Maximum Ramp Weight (lb) 3816 (b) Maximum Takeoff Weight (lb) 3800 (c) Maximum Landing Weight (lb) 3800 (d) Maximum Weights in Baggage Compartment (lb) 1.13 STANDARD AIRPLANE WEIGHTS Refer to Figure 6-5 for the Standard Empty Weight and the Useful Load. 1.15 BAGGAGE SPACE AND ENTRY DIMENSIONS (a) Compartment Volume (cu.
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Page 23: Symbols, Abbreviations And Terminology
SECTION 1 PA-44-180, SEMINOLE GENERAL 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY The following definitions are of symbols, abbreviations and terminology used throughout the handbook and those which may be of added operational significance to the pilot. (a) General Airspeed Terminology and Symbols Calibrated Airspeed means the indicated speed of an airplane, corrected for position and instrument error.
Page 24 SECTION 1 GENERAL PA-44-180, SEMINOLE 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. Maximum Landing Gear Extended Speed is the maximum speed at which an airplane can be safely flown with the landing gear extended.
Page 25 SECTION 1 PA-44-180, SEMINOLE GENERAL 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) Intentional One Engine Inoperative Speed is a minimum speed selected by the manu- facturer for intentionally rendering one engine inoperative in flight for pilot training. Best Angle-of-Climb Speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance.
Page 26 SECTION 1 GENERAL PA-44-180, SEMINOLE 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) Pressure Altitude Altitude measured from standard sea-level pressure (29.92 in. Hg) by a pressure or barometric altimeter. It is the indicated pressure altitude corrected for position and instrument error. In this handbook, altimeter instrument errors are assumed to be zero.
Page 27 SECTION 1 PA-44-180, SEMINOLE GENERAL 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) Demonstrated The demonstrated crosswind velocity is the Crosswind velocity of the crosswind component for Velocity which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests. Accelerate-stop The distance required to accelerate an air- Distance...
Page 28 SECTION 1 GENERAL PA-44-180, SEMINOLE 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY (Continued) C.G. Arm The arm obtained by adding the airplane's individual moments and dividing the sum by the total weight. C.G. Limits The extreme center of gravity locations within which the airplane must be operated at a given weight.
Page 29 SECTION 2 PA-44-180, SEMINOLE LIMITATIONS TABLE OF CONTENTS SECTION 2 LIMITATIONS Paragraph Page General ..................Airspeed Limitations..............Airspeed Indicator Markings ............Power Plant Limitations ..............Power Plant Instrument Markings..........2.11 Weight Limits................2.13 Center of Gravity Limits ............... 2.15 Maneuver Limits ................2.17 Flight Load Factors ...............
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Page 31: General
SECTION 2 PA-44-180, SEMINOLE LIMITATIONS SECTION 2 LIMITATIONS 2.1 GENERAL This section provides the FAA Approved operating limitations, instrument markings, color coding and basic placards necessary for the safe 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 32: Airspeed Indicator Markings
SECTION 2 LIMITATIONS PA-44-180, SEMINOLE 2.3 AIRSPEED LIMITATIONS (Continued) SPEED KIAS KCAS Maximum Landing Gear Extended Speed (V ) -Do not exceed this speed with landing gear extended. Maximum Landing Gear Extension Speed (V ) - Do not exceed this speed when extending the landing gear.
Page 33: Power Plant Limitations
SECTION 2 PA-44-180, SEMINOLE LIMITATIONS 2.5 AIRSPEED INDICATOR MARKINGS (Continued) MARKING White Arc (Flap Down) 55 KTS to 111 KTS Blue Radial Line (One Engine Inoperative Best Rate of Climb Speed) 88 KTS Red Radial Line (One Engine Inoperative Air Minimum Control Speed) 56 KTS 2.7 POWER PLANT LIMITATIONS (a) Number of Engines...
Page 34: Power Plant Instrument Markings
SECTION 2 LIMITATIONS PA-44-180, SEMINOLE 2.7 POWER PLANT LIMITATIONS (Continued) (j) Propeller Hub and Blade Models Left HC-C2Y(K,R)-2CEUF/ FC7666A-2R Right HC-C2Y(K,R)-2CLEUF/ FJC7666A-2R (k) Propeller Diameter (inches) Maximum 74 IN. Minimum 72 IN. 2.9 POWER PLANT INSTRUMENT MARKINGS (a) Tachometer Green Arc (Normal Operating Range) 500 to 2700 RPM Red Line (Maximum) 2700 RPM...
Page 35: Weight Limits
SECTION 2 PA-44-180, SEMINOLE LIMITATIONS 2.11 WEIGHT LIMITS (a) Maximum Ramp Weight 3816 lb (b) Maximum Takeoff Weight 3800 lb (c) Maximum Landing Weight 3800 lb (d) Maximum Weight in Baggage Compartment 200 lb NOTE Refer to Section 5 (Performance) for maximum weight as limited by performance.
Page 36: Types Of Operation
SECTION 2 LIMITATIONS PA-44-180, SEMINOLE 2.19 TYPES OF OPERATION The airplane is approved for the following operations when equipped in accordance with FAR 91 or FAR 135. (a) Day V.F.R. (b) Night V.F.R. (c) Day I.F.R. (d) Night I.F.R. (e) Non Icing 2.21 FUEL LIMITATIONS (a) Minimum Aviation Fuel Grade 100LL or...
Page 37: Placards
SECTION 2 PA-44-180, SEMINOLE LIMITATIONS 2.27 PLACARDS In full view of the pilot: The markings and placards installed in this airplane contain operating limitations which must be complied with when operating this airplane in the normal category. Other operating limitations which must be complied with when operating this airplane in this category are contained in the airplane flight manual.
Page 38: February
SECTION 2 LIMITATIONS PA-44-180, SEMINOLE 2.27 PLACARDS (Continued) In full view of the pilot: ONE ENGINE INOPERATIVE AIR MINIMUM CONTROL SPEED 56 KIAS In full view of the pilot: ONE ENGINE INOPERATIVE STALLS NOT RECOMMENDED. CAN CAUSE 300 FT. LOSS OF ALTITUDE AND 30Þ PITCH ANGLE.
Page 39 SECTION 2 PA-44-180, SEMINOLE LIMITATIONS 2.27 PLACARDS (Continued) On the landing gear warning mute switch: GEAR WARN MUTE In full view of the pilot when the oil cooler winterization kit is installed: OIL COOLER WINTERIZATION PLATE TO BE REMOVED WHEN AMBIENT TEMPERATURE EXCEEDS 50°F.
Page 40 SECTION 2 LIMITATIONS PA-44-180, SEMINOLE REPORT: VB-1616 ISSUED: JULY 12, 1995 2-10 REVISED: JUNE 15, 2001...
Page 41 SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph Page General ..................Airspeeds for Safe Operations ............Emergency Procedures Checklist..........3.5a Engine Inoperative Procedures (3.9)..........Identifying Dead Engine and Verifying Power Loss (3.9a)............. Engine Securing Procedure (Feathering Procedure) (3.9b) ..........
Page 42: Emergency Procedures
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph Page 3.5b Air Starting Procedure (3.11)............Unfeathering Procedure/ Unfeathering Accumulator Functioning (3.11a) ....Unfeathering Procedure/ Starter Assisted (3.11b) ............3.5c Engine Roughness (3.13) .............. 3-10 3.5d Engine Overheat (3.15) ..............3-10 3.5e Loss of Oil Pressure (3.17)............
Page 43 SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph Page 3.5n Electrical Failures (3.33)............... 3-16 Single Alternator Failure (3.33a) ..........3-16 Dual Alternator Failure (3.33b)............. 3-17 3.5o Spin Recovery (3.35) ..............3-18 3.5p Open Door (3.37) ................3-19 3.5q Propeller Overspeed (3.39) ............
Page 44 SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph Page 3.9g Engine Failure During Flight (Speed Above Vmca) (3.5a) ............. 3-25 3.9h One Engine Inoperative Landing (3.5a)........3-26 3.9i One Engine Inoperative Go-Around (3.5a)........3-26 3.9j Summary of Factors Affecting Single Engine Operations....
Page 45 SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph Page 3.33 Electrical Failures (3.5n)............... 3-36 3.35 Spin Recovery (Intentional Spins Prohibited) (3.5o) ....3-37 3.37 Open Door (Entry Door Only) (3.5p) ........... 3-37 3.39 Propeller Overspeed (3.5q) ............3-38 3.41 Emergency Exit (3.5r) ..............
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Page 47: General
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES 3.1 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 its operating and design features, are presented.
Page 48: Engine Inoperative Procedures (3.9)
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.3 AIRSPEEDS FOR SAFE OPERATIONS One engine inoperative air minimum control ........56 KIAS One engine inoperative best rate of climb ........88 KIAS One engine inoperative best angle of climb ........82 KIAS Maneuvering (3800 lb) ..............135 KIAS Never exceed..................202 KIAS 3.5 EMERGENCY PROCEDURES CHECKLIST 3.5a Engine Inoperative Procedures (3.9)
Page 49: Engine Failure During Takeoff (Speed Above 75 Kias) (3.9D)
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5a Engine Inoperative Procedures (Continued) ENGINE FAILURE DURING TAKEOFF (SPEED BELOW 75 KIAS OR GEAR DOWN) (3.9c) Throttles ..............IMMEDIATELY CLOSE Brakes (or land and brake)...........AS REQUIRED Stop straight ahead If insufficient runway remains for a complete stop: Mixtures................IDLE CUTOFF Fuel Selectors ..................OFF Magneto Switches...................OFF...
Page 51: Engine Failure During Climb (3.9E)
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5a Engine Inoperative Procedures (Continued) ENGINE FAILURE DURING CLIMB (3.9e) Airspeed..............MAINTAIN 88 KIAS Directional Control ..............MAINTAIN Power ................MAX. CONTINUOUS Inoperative Engine ..........IDENTIFY and VERIFY Inoperative Engine .............Complete Engine Securing Procedure Trim ..............ADJUST TO 2° to 3° BANK TOWARD OPERATIVE ENGINE WITH APPROXIMATELY 1/2 BALL SLIP INDICATED ON...
Page 52 SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5a Engine Inoperative Procedures (Continued) ENGINE FAILURE DURING FLIGHT (SPEED ABOVE V (3.9g) Inoperative Engine...............IDENTIFY Operative Engine........ADJUST POWER AS REQUIRED Airspeed ............ATTAIN AND MAINTAIN AT LEAST 88 KIAS Before securing inop. engine: Electric Fuel Pump...................ON Fuel Quantity...................
Page 53: One Engine Inoperative Landing (3.9H)
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5a Engine Inoperative Procedures (Continued) ONE ENGINE INOPERATIVE LANDING (3.9h) Inoperative Engine......ENGINE SECURING PROCEDURE COMPLETE Seat Belts/Harnesses...............SECURE Fuel Selector (Operative Engine) .............ON Mixture (Operative Engine) ............FULL RICH Propeller Control (Operative Engine)......FULL FORWARD Electric Fuel Pump (Operative Engine) ...........ON Cowl Flap (Operative Engine) ..........AS REQUIRED Altitude &...
Page 55: Air Starting Procedure (3.11)
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5b Air Starting Procedure (3.11) (Continued) Prop Control ..............FULL FORWARD Throttle ................Reduce power until engine is warm Alternator ....................ON NOTE Starter assist is required if the propeller is not windmilling freely within 5-7 seconds after the propeller control has been moved forward.
Page 56: Engine Roughness (3.13)
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5c Engine Roughness (3.13) NOTE Partial carburetor heat may be worse than no heat at all, since it may melt part of the ice which will refreeze in the intake system. Therefore, when using carburetor heat always use full heat; and, when ice is removed, return the control to the full cold position.
Page 57: Engine Fire (3.19)
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5f Engine Fire (3.19) ENGINE FIRE DURING START (3.19a) If engine has not started: Mixture ................IDLE CUT-OFF Throttle ..................FULL OPEN Starter .............CONTINUE to Crank Engine If engine has already started and is running, continue operating to try pulling the fire into the engine.
Page 58: Electrical Fire (3.21)
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5g Electrical Fire (3.21) (Continued) Flashlight (at night) ................LOCATE Battery Master ..................OFF Alternator Switches ................OFF All Electrical Switches ................OFF Radio Master Switch ................OFF Vents ..............CLOSED (To avoid drafts) Cabin Heat ....................OFF If fire persists, locate and, if practical, extinguish with portable fire extinguisher locate on the console just aft of the 2 front seats.
Page 59 SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5g Electrical Fire (3.21) (Continued) NOTE Refer to Power Distribution paragraph on page 7- 22 and Figure 7-23 on page 7-23 for electrical power distribution information. One (1) Main Bus Tie Circuit Breaker Battery Master..................ON L.
Page 60: Engine-Driven Fuel Pump Failure (3.25)
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5h Fuel Management During One Engine Inoperative Operation (3.23) CRUISING (3.23a) When using fuel from tank on the same side as the operating engine: Fuel Selector (Operative Engine) .............ON Fuel Selector (Inoperative Engine) ............OFF Electric Fuel Pumps................OFF (except in case of engine driven pump failure when electric fuel pump on...
Page 61: Landing Gear Malfunctions (3.29)
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5k Landing Gear Malfunctions (3.29) MANUAL EXTENSION OF LANDING GEAR Check following before extending gear manually: Navigation Lights (Daytime)..............OFF Day/Night Dimmer Switch (Daytime)...........DAY Circuit Breakers................CHECK Master Switch...................ON Alternators ..................CHECK To extend, proceed as follows: Airspeed ............REDUCE (100 KIAS max.) Gear Selector .................GEAR DOWN LOCKED position...
Page 62 SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE REPORT: VB-1616 ISSUED: JULY 12, 1995 3-16...
Page 63 SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5n Electrical Failures (3.33) (Continued) DUAL ALTERNATOR FAILURE (Zero Amps Both Ammeters or Alternator Inop. Light Illuminated - Annunciator Panel). (3.33b) NOTE Anytime total tie bus voltage is below approx- imately 12.5 Vdc, the LO BUS voltage annun- ciator will illuminate.
Page 64 SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5n Electrical Failures (3.33) (Continued) WARNING Compass error may exceed 10 degrees with both alternators inoperative. NOTE If the battery is depleted, the landing gear must be lowered using the emergency gear extension procedure. The gear position lights will be inoperative.
Page 65 SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5p Open Door (Entry door only) (3.37) If both top and side latches are open, the door will trail slightly open and airspeeds will be reduced slightly. To close the door in flight: Airspeed ................Slow to 82 KIAS. Cabin Vents ..................CLOSE Storm Window..................OPEN If Top Latch is Open .................LATCH...
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Page 67 SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.7 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 68 SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.9c Engine Failure During Takeoff (Speed Below 75 KIAS or Gear Down) (3.5a) Determination of runway length, single engine climb rate, and accelerate/stop distance will aid in determining the best course of action in the event of an engine failure during takeoff.
Page 70 SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.9e Engine Failure During Climb (3.5a) If engine failure occurs during climb, a minimum airspeed of 88 KIAS ) should be maintained. Since one engine will be inoperative and the other will be at maximum power, the airplane will have a tendency to turn in the direction of the inoperative engine.
Page 71 SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.9f Engine Failure During Flight (Speed Below V )(3.5a) Should an engine fail during flight at an airspeed below V (56 KIAS) apply rudder towards the operative engine to minimize the yawing motion. The throttles should be retarded to stop the yaw towards the inoperative engine.
Page 73: Summary Of Factors Affecting Single Engine Operations
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.9j Summary of Factors Affecting Single Engine Operations. Significant climb performance penalties can result from landing gear, flap, or windmilling propeller drag. These penalties are approximately as listed below: Landing gear extended/Flaps Up ........- 250 ft./min. Flaps extended 25°/Gear Down .........- 490 ft./min.
Page 74: Air Starting Procedure (3.5B)
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.9j Summary of Factors Affecting Single Engine Operations. (Continued) If the requirement for an immediate climb is not present, allow the airplane to accelerate to the single-engine best rate-of-climb airspeed since this speed will always provide the best chance of climb or least altitude loss in a given time.
Page 75: Engine Roughness (3.5C)
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.11 AIR STARTING PROCEDURE (3.5c) (Continued) 3.11b Unfeathering Procedure/ Starter Assisted Move the fuel selector for the inoperative engine to the ON position and check to make sure the electric fuel pump for that engine is ON. Push the propeller control forward to the cruise RPM position and the mixture should be set RICH.
Page 76: Engine Overheat (3.5D)
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.15 ENGINE OVERHEAT (3.5d) A steady, rapid rise in oil temperature is a sign of trouble. An abnormally high oil temperature indication may be caused by a low oil level, an obstruction in the oil cooler, damaged or improper baffle seals, a defective gauge, or other causes.
Page 77: Electrical Fire (3.5G)
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.19 ENGINE FIRE (3.5f) (Continued) 3.19a Engine Fire During Start (3.5f) (Continued) In either case (above), if the fire continues longer than a few seconds the fire should be extinguished by the best available external means. If an external fire extinguishing method is to be applied move the fuel selector valves to OFF and the mixture to idle cut-off.
Page 78 SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.21 ELECTRICAL FIRE (3.5g) (Continued) If electrical power is required for safe continuation of flight, proceed as follows: WARNING The following procedure may reenergize the faulty system. Reset the circuit breakers one at a time.
Page 79: Fuel Management During
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.23 FUEL MANAGEMENT DURING ONE ENGINE INOPERATIVE OPERATION (3.5h) A crossfeed is provided to increase range during one engine inoperative operation. Use crossfeed in level flight only. 3.23a Cruising When using fuel from the fuel tank on the same side as the operating engine, the fuel selector of the operating engine should be ON and the fuel selector for the inoperative engine should be OFF.
Page 80: Engine Driven Fuel Pump Failure (3.5I)
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.25 ENGINE DRIVEN FUEL PUMP FAILURE (3.5i ) Loss of fuel pressure and engine power can be an indication of failure of the engine-driven fuel pump. Should these occur and engine-driven fuel pump failure is suspected, turn ON the electric fuel pump. CAUTION If normal engine operation and fuel pressure are not immediately re-established, the electric fuel...
Page 81: Landing Gear Malfunctions (3.5K)
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.29 LANDING GEAR MALFUNCTIONS (3.5k) Manual Extension of Landing Gear Several items should be checked prior to extending the landing gear manually. Check for popped circuit breakers and ensure the master switch is ON. Then check the alternators. If it is daytime, turn OFF the navigation lights or select DAY on the day/night dimmer switch, whichever applies to your aircraft.
Page 82: Electrical Failures (3.5N)
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.33 ELECTRICAL FAILURES (3.5n) WARNING Compass error may exceed 10 degrees with both alternators inoperative. NOTE If the battery is depleted, the landing gear must be lowered using the emergency extension procedure. The green position lights will be inoperative.
Page 83: Spin Recovery (Intentional Spins Prohibited) (3.5O)
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.35 SPIN RECOVERY (INTENTIONAL SPINS PROHIBITED) (3.5o) NOTE Federal Aviation Administration Regulations do not require spin demonstration of multi-engine airplanes; therefore, spin tests have not been conducted. The recovery technique presented is based on the best available information. Intentional spins are prohibited in this airplane.
Page 84: Propeller Overspeed (3.5Q)
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.39 PROPELLER OVERSPEED (3.5q) Propeller overspeed is usually caused by a malfunction in the propeller governor which allows the propeller blades to rotate to full low pitch. If propeller overspeed should occur. retard the throttle. The propeller control should be moved to full DECREASE rpm and then set if any control is available.
Page 85 SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Paragraph Page General ..................Airspeed for Safe Operation............Normal Procedures Check List ............. 4.5a Preflight Check................. 4.5b Before Starting Engine ............. 4.5c Engine Start Checklists ............4.5d Before Taxiing Checklist............
Page 86 SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Paragraph Page 4.5n Go-Around Checklist ............... 4-17 4.5o After Landing Checklist ............4-17 4.5p Stopping Engine Checklist ............4-17 4.5q Mooring Checklist..............4-18 Amplified Normal Procedures (General) ........4-19 Preflight Check ................
Page 87 SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Paragraph Page 4.33 Go-Around ..................4-38 4.35 After Landing ................4-38 4.37 Stopping Engine ................4-38 4.39 Mooring..................4-38 4.41 Stalls ..................... 4-39 4.43 Turbulent Air Operation..............4-39 4.45 V - Intentional One Engine Inoperative Speed ......
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Page 89: General
SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES SECTION 4 NORMAL PROCEDURES 4.1 GENERAL This section provides the normal operating procedures for the PA-44-180, Seminole airplane. All of the normal operating procedures required by the FAA 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 90: Airspeed For Safe Operation
SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.3 AIRSPEEDS FOR SAFE OPERATIONS The following airspeeds are those which are significant to the safe operation of the airplane. These figures are for standard airplanes flown at gross weight under standard conditions at sea level. 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 91: Normal Procedures Checklist
SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES WALK-AROUND Figure 4-1 4.5 NORMAL PROCEDURES CHECKLIST 4.5a Preflight Checklists (4.9) COCKPIT (4.9a) Control Wheel ..............release restraints Static System ..................DRAIN Alternate Static Source ..............NORMAL Magneto Switches...................OFF Parking Brake ..................SET Fuel Pump Switches ................OFF Gear Selector ..................DOWN Throttles ....................IDLE Mixture Controls ..............IDLE CUT-OFF Cowl Flaps...................OPEN...
Page 92 SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.5a Preflight Checklists (4.9) (Continued) COCKPIT (4.9a) Battery Master Switch................ON Fuel Gauges ..............CHECK QUANTITY Annunciator Panel .............PRESS TO TEST Landing Gear Lights..............3 GREEN Battery Master Switch ................OFF Emergency Exit ................CHECK Flaps....................EXTEND Windows.................check CLEAN Required Papers ..............check ON BOARD POH.................check ON BOARD Baggage ............STOW PROPERLY - SECURE RIGHT WING (4.9b)
Page 93 SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.5a Preflight Checklists (4.9) (Continued) NOSE SECTION (4.9c) General Condition ................CHECK Windshield..................CLEAN Battery Vents..................CLEAR Landing Lights .................CHECK Heater Air Inlet .................CLEAR Chock ....................REMOVE Nose Gear Strut............PROPER INFLATION (2.70 +/- 0.25 in.) Nose Wheel Tire................CHECK LEFT WING (4.9d) Surface Condition ........CLEAR of ICE, FROST &...
Page 94 SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.5a Preflight Checklists (4.9) (Continued) FUSELAGE (LEFT SIDE) (4.9e) General Condition ................CHECK Emergency Exit ................CHECK Antennas...................CHECK Fresh Air Inlet...................CLEAR EMPENNAGE (4.9f) Surface Condition ........CLEAR of ICE, FROST & SNOW Stabilator, Trim Tab & Freedom of Movement ........CHECK Rudder, Trim Tab &...
Page 95: Preflight Check
SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.5b Before Starting Engine Checklists (4.11) BEFORE STARTING ENGINE (4.11) Preflight Check ..............COMPLETED Flight Planning...............COMPLETED Cabin Door..............CLOSE & SECURE Seats..............ADJUSTED & LOCKED Seatbelts and Harness............FASTEN/ADJUST CHECK INERTIA REEL Alternators....................ON Parking Brake ..................SET Gear Selector .................GEAR DOWN Throttles ....................IDLE Propeller Controls............FULL FORWARD Mixture ................IDLE CUT-OFF...
Page 96: Throttles
SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.5c Engine Start Checklists (4.13) (Continued) NORMAL START - COLD ENGINE (4.13a) Battery Master Switch................ON Gear Lights ..................3 GREEN Throttles.................1/4 inch OPEN Propeller Controls............FULL FORWARD Mixtures..................FULL RICH *Electric Fuel Pump.................ON *Primer ................AS REQUIRED *Propeller Area .................CLEAR *Magneto Switches ..................ON *Starter...................ENGAGE *Throttle ............ADJUST WHEN ENGINE...
Page 97 SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.5c Engine Start Checklists (4.13) (Continued) ENGINE START - COLD WEATHER (BELOW 10°F) (4.13c) CAUTION Ensure magneto and master switches are OFF and mixture controls are in idle cut-off before turning propeller manually. If available, preheat should be considered. Rotate each propeller through 10 blades manually during preflight inspection.
Page 98 SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.5c Engine Start Checklists (4.13) (Continued) Ammeter (Operating Engine)............CHECK Right Engine...............NORMAL RESTART Gyro Vacuum..................CHECK ENGINE START WHEN FLOODED (4.13d) Mixture ................IDLE CUT-OFF Propeller Control .............FULL FORWARD Throttle ..................OPEN FULL Electric Fuel Pump .................OFF Battery Master Switch................ON Propeller Area ...................CLEAR Magneto Switches ..................ON Starter.....................ENGAGE...
Page 99: Fuel Selectors
SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.5c Engine Start Checklists (4.13) (Continued) Battery Master Switch................ON Alternators....................ON Ammeter (Operating Engine)............CHECK Right Engine .................RESTART Gyro Vacuum..................CHECK 4.5d Warm-Up Checklist (4.15) WARM-UP (4.15a) Throttles................1000 to 1200 RPM BEFORE TAXIING (4.15b) External Power Source Unit ............REMOVE Battery Master Switch................ON Gyros.......................SET Altimeter and Clock................SET...
Page 100: Ground Check Checklist
SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.5f Ground Check Checklist (4.19) GROUND CHECK (4.19) Parking Brake ..................SET Mixtures..................FULL RICH Propeller Controls............FULL FORWARD Engine Instruments................CHECK Throttles..................1500 RPM Propeller Controls (Max. Drop - 500 RPM)....FEATHER - CHECK Throttles..................2000 RPM Magnetos (Max. Drop - 175 RPM: Max.
Page 101 SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.5g Before Takeoff Checklist (4.21) (Continued) Cowl Flaps...................OPEN Transponder .................AS REQUIRED Flaps ..................CHECK & SET Warning Lights .................CHECK Door .....................LATCHED Parking Brake ................RELEASE 4.5h Takeoff Checklist (4.23) CAUTION Fast taxi turns immediately prior to takeoff should be avoided to prevent unporting fuel feed lines.
Page 102 SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.5h Takeoff Checklist (4.23) (Continued) 0° FLAP, SHORT FIELD PERFORMANCE TAKEOFF (4.23b) Flaps......................UP Stabilator and Rudder Trim............CHECK SET Brakes ....................HOLD Power............2700 RPM, FULL THROTTLE Mixture..........FULL RICH (or SET for ALTITUDE) Brakes...................RELEASE Rotate Speed ..................70 KIAS Obstacle Clearance Speed ...............82 KIAS Gear......................UP Climb Speed (past obstacles)............88 KIAS...
Page 103: Climb Checklist
SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.5i Climb Checklist (4.25) MAXIMUM PERFORMANCE CLIMB (4.25a) Best Rate (Flaps Up)................88 KIAS Best Angle (Flaps Up) ..............82 KIAS Cowl Flaps...................OPEN Electric Fuel Pump............OFF at desired altitude CRUISE CLIMB (4.25b) Mixture ..................FULL RICH Power ......................75% Climb Speed ..................105 KIAS Cowl Flaps .................As Required Electric Fuel Pump............OFF at desired altitude...
Page 104: Approach And Landing Checklist
SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.5m Approach and Landing Checklist (4.31) APPROACH AND LANDING (4.31) Seat Backs ..................ERECT Seat Belts, Harnesses ..............ADJUSTED Fuel Pumps....................ON Fuel Selectors ...................ON Landing Gear (Below 140 KIAS)............DOWN Landing Gear Lights..............3 GREEN Nacelle Mirror ............NOSE GEAR DOWN Mixture Controls ...............FULL RICH Propeller Controls............FULL FORWARD Carburetor Heat Controls.............AS REQUIRED...
Page 106: Mooring Checklist
SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.5q Mooring Checklist (4.39) MOORING (4.39) Parking Brake ..................SET Control Wheel .............SECURED with belts Flaps....................FULL UP Wheel Chocks ................IN PLACE Tiedowns..................SECURE REPORT: VB-1616 ISSUED: JULY 12, 1995 4-18...
Page 107: Amplified Normal Procedures (General)
SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.7 AMPLIFIED NORMAL PROCEDURES (GENERAL) The following paragraphs are provided to supply detailed information and the explanations of the normal procedures necessary for the safe operation of the airplane. 4.9 PREFLIGHT CHECK (4.5a) The airplane should be given a thorough preflight and walk-around inspection.
Page 108 SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.9a Cockpit (4.5a) (Continued) CAUTION If the emergency exit is unlatched in flight, it may separate and damage the exterior of the airplane. Check that the emergency exit is in place and securely latched. Extend the flaps for the walk-around inspection.
Page 109 SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.9b Right Wing (4.5a) (Continued) Next, complete a check of the landing gear. Check the main gear strut for proper inflation. There should be 2.60 +/- 0.25 inches of strut exposure under a normal static load. Check for hydraulic leaks. Check the tire for cuts, wear, and proper inflation.
Page 110 SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.9d Left Wing (4.5a) (Continued) Proceed along the leading edge of the wing to the stall warning vanes. Check both vanes for damage and freedom of movement. A squat switch in the stall warning system does not allow the unit to be activated on the ground. Check the pitot/ static head.
Page 111: Before Starting Engine
SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.9h Miscellaneous (4.5a) Enter the cockpit and retract the flaps. Turn the battery master switch ON. Check the interior lights by turning ON the necessary switches. After the interior lights are checked, turn ON the pitot heat, and the exterior light switches.
Page 112: Engine Start
SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.11 BEFORE STARTING ENGINE (4.5b) (Continued) Verify that the carburetor heat for each engine is off and the cowl flaps are open. Verify that both stabilator and rudder trim is set to neutral and that the fuel selectors are on.
Page 113 SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.13 ENGINE START(4.5c) (Continued) NOTE To prevent starter damage, limit starter cranking to 30-second periods. If the engine does not start within that time, allow a cooling period of several minutes before engaging starter again. Do not engage the starter immediately after releasing it.
Page 114 SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.13c Engine Start - Cold Weather (Below 10°F) (4.5c) (Continued) Turn the battery master switch and alternator switches OFF. Verify the magneto switches are OFF and connect the external power. Turn ON the electric fuel pump, move the mixture control full rich, the propeller control full forward and open the throttle 1/4 inch.
Page 115 A feature called the Piper External Power (PEP) allows the operator to use an external battery to crank the engines without having to gain access to the airplane's battery.
Page 116: Before Taxiing
SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.13e Engine Start With External Power Source (4.5c) (Continued) WARNING Shut down the right engine when it is warmed prior to disconnecting the external power plug. After the engines have started, check the oil pressure, reduce power on the left engine to the lowest possible RPM to reduce sparking, and shut down the right engine.
Page 117: Taxiing
SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.17 TAXIING (4.5e) Check to make sure the taxi area is clear. Always apply the throttles slowly. While taxiing, apply the brakes to determine their effectiveness. Make slight turns to check steering. During the taxi, check the instruments (turn indicator, directional gyro, coordination ball &...
Page 118: Before Takeoff
SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.21 BEFORE TAKEOFF (4.5g) Ensure proper flight control movement and response. Check that flight instruments are set and operational, and that all engine instruments are reading within limits. Check that the fuel quantity is sufficient for the intended flight. Turn the electric fuel pumps ON for takeoff.
Page 119 SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.23 TAKEOFF (4.5h) (Continued) Avoid fast turns onto the runway followed by immediate takeoff, especially with a low fuel supply. As power is applied at the start of the takeoff roll, look at the engine instruments to see that the engines are operating properly and putting out normal power and at the airspeed indicator to see that it is functioning.
Page 120: Climb
SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.23b 0° Flap, Short Field Performance Takeoff (4.5h) (Continued) NOTE Gear warning horn will sound when landing gear is retracted with flaps extended beyond first notch. When the shortest possible ground roll and the greatest clearance distance over a 50-foot obstacle is needed, a flap setting up to a maximum of 25°...
Page 121: Cruise
SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.25b Cruise Climb (4.5i) At this point, engine power should be reduced to approximately 75% power for cruise climb. A cruise climb speed of 105 KIAS or higher is also recommended. This combination of reduced power and increased climb speed provides better engine cooling, less engine wear, reduced fuel consumption, lower cabin noise level, and better forward visibility.
Page 122 SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.27 CRUISE (4.5j) (Continued) WARNING Flight in icing conditions is prohibited. If icing is encountered, immediate action should be taken to fly out of icing conditions. Icing is hazardous due to greatly reduced performance, loss of forward visibility, possible longitudinal control difficulties due to increased control sensitivity, and impaired power plant and fuel...
Page 123: Descent
SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.27 CRUISE (4.5j) (Continued) During flight, keep account of time and fuel used in connection with power settings to determine how the fuel flow and fuel quantity gauging systems are operating. There are no mechanical uplocks in the landing gear system. In the event of a hydraulic system malfunction, the landing gear will free-fall to the gear down position.
Page 124 SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.31 APPROACH AND LANDING (4.5m) (Continued) Prior to entering the traffic pattern, the aircraft should be slowed to approximately 100 KIAS, and this speed should be maintained on the downwind leg. The landing check should be made on the downwind leg. The seat backs should be erect, and the seat belts and shoulder harnesses should be fastened.
Page 125 SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.31 APPROACH AND LANDING (4.5m) (Continued) 4.31a Normal Landing (4.5m) Landing may be made with any flap setting. Normally full flaps are used. Full flaps will reduce stall speed during final approach and will permit contact with the runway at a slower speed.
Page 127: Turbulent Air Operation
SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.41 STALLS The loss of altitude during a power off stall with the gear and flaps retracted may be as much as 300 feet. NOTE The stall warning system is inoperative with the master switch OFF. During preflight, the stall warning system should be checked by turning the battery switch on and lightly lifting up on the stall warning vanes on the left wing to determine if the horn is actuated.
Page 128: Vmca - Air Minimum Control Speed
SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.47 V - AIR MINIMUM CONTROL SPEED is the minimum flight speed at which a twin-engine airplane is directionally and/or laterally controllable as determined in accordance with Federal Aviation Regulations. Airplane certification conditions include one engine becoming inoperative and windmilling;...
Page 129: Practice One Engine Inoperative Flight
SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.47 V - AIR MINIMUM CONTROL SPEED (Continued) CAUTION Use rudder to maintain directional control (heading) and ailerons to maintain 5° bank towards the operative engine (lateral attitude). At the first sign of either V (airspeed indicator redline) or stall warning (which may be evidenced by: inability to maintain heading or...
Page 130: Noise Level
SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.51 NOISE LEVEL The corrected noise level of this aircraft is 74. 7 d B(A) with the two blade propeller. No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or unacceptable for operation at, into, or out of, any airport.
Page 131 SECTION 5 PA-44-180, SEMINOLE PERFORMANCE TABLE OF CONTENTS SECTION 5 PERFORMANCE Paragraph Page General ..................Introduction - Performance and Flight Planning......Flight Planning Example............... Performance Graphs..............List of Figures..............ISSUED: JULY 12, 1995 REPORT: VB-1616...
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Page 133 SECTION 5 PA-44-180, SEMINOLE PERFORMANCE SECTION 5 PERFORMANCE 5.1 GENERAL All of the required (FAA regulations) and complementary performance information applicable to this aircraft 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 134 SECTION 5 PERFORMANCE PA-44-180, SEMINOLE 5.3 INTRODUCTION - PERFORMANCE AND FLIGHT PLANNING (Continued) The information provided by paragraph 5.5 (Flight Planning Example) outlines a detailed flight plan using the performance charts in this section. Each chart includes its own example to show how it is used. WARNING Performance information...
Page 135 SECTION 5 PA-44-180, SEMINOLE PERFORMANCE 5.5 FLIGHT PLANNING EXAMPLE (a) Aircraft Loading The first step in planning a 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 delivered from the factory has been entered in Figure 6-5.
Page 136 SECTION 5 PERFORMANCE PA-44-180, SEMINOLE 5.5 FLIGHT PLANNING EXAMPLE (Continued) All of the existing conditions at the departure and destination airport must be acquired, evaluated and maintained throughout the flight. Apply the departure airport conditions and takeoff weight to the appropriate Takeoff performance graphs (Figures 5-11 and 5-13) to determine the length of runway necessary for the takeoff and/or the obstacle distance.
Page 137 SECTION 5 PA-44-180, SEMINOLE PERFORMANCE 5.5 FLIGHT PLANNING EXAMPLE (Continued) (c) Climb The next step in the flight plan is to determine the necessary climb segment components. The desired cruise pressure altitude and corresponding cruise outside air temperature values are the first variables to be considered in determining the climb components from the Fuel, Time and Distance to Climb graph (Figure 5-21).
Page 138 SECTION 5 PERFORMANCE PA-44-180, SEMINOLE 5.5 FLIGHT PLANNING EXAMPLE (Continued) (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 5-31).
Page 139 SECTION 5 PA-44-180, SEMINOLE PERFORMANCE 5.5 FLIGHT PLANNING EXAMPLE (Continued) (e) Cruise Using the total distance to be traveled during the flight, subtract the previously calculated distance to climb and distance to descend to establish the total cruise distance. Refer to the appropriate Lycoming Operator's Manual and the Fuel and Power Setting Tables when selecting the cruise power setting.
Page 140 SECTION 5 PERFORMANCE PA-44-180, SEMINOLE 5.5 FLIGHT PLANNING EXAMPLE (Continued) (f) Total Flight Time The total flight time is determined by adding the time to climb, the time to descend and the cruise time. Remember! The time values taken from the climb and descent graphs are in minutes and must be converted to hours before adding them to the cruise time.
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Page 143 SECTION 5 PA-44-180, SEMINOLE PERFORMANCE TEMPERATURE CONVERSION Figure 5-1 ISSUED: JULY 12, 1995 REPORT: VB-1616 5-11...
Page 144 SECTION 5 PERFORMANCE PA-44-180, SEMINOLE AIRSPEED CALIBRATION Figure 5-3 REPORT: VB-1616 ISSUED: JULY 12, 1995 5-12...
Page 145 SECTION 5 PA-44-180, SEMINOLE PERFORMANCE STALL SPEED VS. ANGLE OF BANK Figure 5-5 ISSUED: JULY 12, 1995 REPORT: VB-1616 5-13...
Page 146 SECTION 5 PERFORMANCE PA-44-180, SEMINOLE ISA CONVERSION Figure 5-7 REPORT: VB-1616 ISSUED: JULY 12, 1995 5-14...
Page 147 SECTION 5 PA-44-180, SEMINOLE PERFORMANCE WIND COMPONENTS Figure 5-9 ISSUED: JULY 12, 1995 REPORT: VB-1616 5-15...
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Page 158 SECTION 5 PERFORMANCE PA-44-180, SEMINOLE FUEL & POWER SETTING TABLE Figure 5-23 REPORT: VB-1616 ISSUED: JULY 12, 1995 5-26 REVISED: NOVEMBER 1, 2001...
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Page 161 SECTION 5 PA-44-180, SEMINOLE PERFORMANCE STANDARD TEMPERATURE RANGE AND ENDURANCE - PERFORMANCE CRUISE Figure 5-27 ISSUED: JULY 12, 1995 REPORT: VB-1616 REVISED: NOVEMBER 1, 2001 5-29...
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Page 163 SECTION 5 PA-44-180, SEMINOLE PERFORMANCE STANDARD TEMPERATURE RANGE AND ENDURANCE - ECONOMY CRUISE Figure 5-29 ISSUED: JULY 12, 1995 REPORT: VB-1616 REVISED: NOVEMBER 1, 2001 5-31...
Page 167 SECTION 6 PA-44-180, SEMINOLE WEIGHT AND BALANCE TABLE OF CONTENTS SECTION 6 WEIGHT AND BALANCE Paragraph Page General ..................Airplane Weighing Procedure ............Weight and Balance Data Record ..........Weight and Balance Determination for Flight ......Instructions for Using the Weight and Balance Plotter ....6-15 ISSUED: JULY 12, 1995 REPORT: VB-1616...
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Page 169: General
SECTION 6 PA-44-180, SEMINOLE WEIGHT AND BALANCE SECTION 6 WEIGHT AND BALANCE 6.1 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 170: Airplane Weighing Procedure
SECTION 6 WEIGHT AND BALANCE PA-44-180, SEMINOLE 6.1 GENERAL (Continued) The basic empty weight and C.G. location are recorded in the Weight and Balance Data Form (Figure 6-5) and the Weight and Balance Record (Figure 6-7). The current values should always be used. Whenever new equipment is added or any modification work is done, the mechanic responsible for the work is required to compute a new basic empty weight and C.G.
Page 171 SECTION 6 PA-44-180, SEMINOLE WEIGHT AND BALANCE 6.3 AIRPLANE WEIGHING PROCEDURE (Continued) CAUTION Whenever the fuel system is completely drained and fuel is replenished it will be necessary to run the engines for a minimum of 3 minutes at 1000 RPM on each tank to ensure no air exists in the fuel supply lines.
Page 172 SECTION 6 WEIGHT AND BALANCE PA-44-180, SEMINOLE 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 Nacelle (Top View) W.S. 106 Fairing (Outboard of Nacelle) 78.4"...
Page 173: Weight And Balance Data Record
SECTION 6 PA-44-180, SEMINOLE WEIGHT AND BALANCE 6.3 AIRPLANE WEIGHING PROCEDURE (Continued) (d) Basic Empty Weight Center of Gravity (1) The Leveling Diagram geometry (Figure 6-3) applies to the PA-44-180 airplane when it is level. Refer to Leveling paragraph 6.3 (b). (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:...
Page 174 SECTION 6 WEIGHT AND BALANCE PA-44-180, SEMINOLE MODEL PA-44-180, SEMINOLE 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 Standard Empty Weight* Computed Optional Equipment Basic Empty Weight *The standard empty weight includes full oil capacity and 2.0 gallons of...
Page 175 SECTION 6 PA-44-180, SEMINOLE WEIGHT AND BALANCE WEIGHT AND BALANCE RECORD Figure 6-7 ISSUED: JULY 12, 1995 REPORT: VB-1616...
Page 176 SECTION 6 WEIGHT AND BALANCE PA-44-180, SEMINOLE WEIGHT AND BALANCE RECORD (Continued) Figure 6-7 (Continued) REPORT: VB-1616 ISSUED: JULY 12, 1995...
Page 177: Weight And Balance Determination For Flight
SECTION 6 PA-44-180, SEMINOLE WEIGHT AND BALANCE 6.7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (a) Add the weight of all items to be loaded to the basic empty weight. (b) Use the Loading Graph (Figure 6-13) to determine the moment of all items to be carried in the airplane.
Page 178 SECTION 6 WEIGHT AND BALANCE PA-44-180, SEMINOLE 6.7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (Continued) Arm Aft Weight Datum Moment (Lbs) (Inches) (In-Lbs) Basic Empty Weight Pilot and Front Passenger 340.0 80.5 27370 Passengers (Rear Seats) 340.0 118.1 40154 Fuel (108 Gallon Maximum Usable) 95.0 Baggage (200 Lb.
Page 179 SECTION 6 PA-44-180, SEMINOLE WEIGHT AND BALANCE 6.7 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT (Continued) Arm Aft Weight Datum Moment (Lbs) (Inches) (In-Lbs) Basic Empty Weight Pilot and Front Passenger 80.5 Passengers (Rear Seats) 118.1 Fuel (108 Gallon Maximum Usable) 95.0 Baggage (200 Lb.
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Page 181 SECTION 6 PA-44-180, SEMINOLE WEIGHT AND BALANCE LOADING GRAPH Figure 6-13 ISSUED: JULY 12, 1995 REPORT: VB-1616 6-13...
Page 182 SECTION 6 WEIGHT AND BALANCE PA-44-180, SEMINOLE C.G. RANGE AND WEIGHT Figure 6-15 REPORT: VB-1616 ISSUED: JULY 12, 1995 6-14...
Page 183: Instructions For Using The Weight And Balance Plotter
Heat can warp or ruin the plotter if it is left in the sunlight. Replacement plotters may be purchased from Piper dealers and distributors. When the airplane is delivered, the basic weight and basic C.G. will be recorded on the computer. These should be changed any time the basic weight or C.G.
Page 184 SECTION 6 WEIGHT AND BALANCE PA-44-180, SEMINOLE SAMPLE PROBLEM A sample problem (Figure 6-17) will demonstrate the use of the weight and balance plotter. Assume a basic weight and C.G. location of 2364 pounds at 86.14 inches respectively. We wish to carry a pilot and 3 passengers. Two men weighing 180 and 200 pounds will occupy the front seats, and two children weighing 80 and 100 pounds will ride in the rear.
Page 185 SECTION 6 PA-44-180, SEMINOLE WEIGHT AND BALANCE SAMPLE PROBLEM Figure 6-17 ISSUED: JULY 12, 1995 REPORT: VB-1616 6-17...
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Page 187 SECTION 7 PA-44-180, SEMINOLE DESCR/ OPERATION TABLE OF CONTENTS SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND IT'S SYSTEMS Paragraph Page The Airplane ................. Airframe ..................Engines and Propellers..............Engine Controls................Landing Gear................. 7.11 Brake System ................7-14 7.13 Flight Control System ..............7-14 7.15 Fuel System...................
Page 188 SECTION 7 DESCR/ OPERATION PA-44-180, SEMINOLE TABLE OF CONTENTS SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND IT'S SYSTEMS Paragraph Page 7.33 Stall Warning................. 7-42 7.35 Emergency Locator Transmitter............ 7-43 REPORT: VB-1616 ISSUED: JULY 12, 1995 7-ii...
Page 189: The Airplane
SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS 7.1 THE AIRPLANE The Seminole is a twin-engine, all metal, retractable landing gear, airplane. It has seating for up to four occupants and has a two hundred pound capacity luggage compartment.
Page 190: Engines And Propellers
SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.3 AIRFRAME (Continued) A vertical stabilizer, an all-movable horizontal stabilator, and a rudder make up the empennage. The stabilator, which is mounted on top of the fin incorporates an anti-servo tab which provides longitudinal stability and trim. This tab moves in the same direction as the stabilator, but with increased travel.
Page 191 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION 7.5 ENGINES AND PROPELLERS (Continued) PROPELLERS Counter-rotation of the propellers provides balanced thrust during takeoff and climb and eliminates the critical engine factor in single-engine flight. Two blade, constant speed, controllable pitch and feathering Hartzell propellers are installed as standard equipment.
Page 192 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.5 ENGINES AND PROPELLERS (Continued) Unfeathering Accumulators The propeller unfeathering system consists of increased capacity governors and gas charged accumulators. The feathering governors are designed to operate in the conventional manner in addition to their accumulator unfeathering capability. The accumulators store engine oil under pressure from the governors which is released back to the governors for propeller unfeathering when the propeller control lever is moved forward from the feathered position.
Page 193: Engine Controls
SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION 7.7 ENGINE CONTROLS Engine controls consist of a throttle, a propeller control and a mixture control lever for each engine. These controls are located on the control quadrant on the lower center of the instrument panel where they are accessible to both the pilot and the copilot (Figure 7-1).
Page 194 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.7 ENGINE CONTROLS (Continued) The propeller control levers are used to adjust the propeller speed from high RPM (low pitch) to feather (high pitch). The mixture control levers are used to adjust the air to fuel ratio. An engine is shut down by the placing of the mixture control lever in the full lean (idle cut-off) position.
Page 195: Landing Gear
SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION 7.9 LANDING GEAR The Seminole is equipped with hydraulically operated, fully retractable, tricycle landing gear. On takeoff, the gear should be retracted before an airspeed of 109 KIAS is exceeded. The landing gear may be lowered at any speed up to 140 KIAS.
Page 196 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE LANDING GEAR ELECTRICAL SYSTEM SCHEMATIC Figure 7-7 REPORT: VB-1616 ISSUED: JULY 12, 1995...
Page 197 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION LANDING GEAR HYDRAULIC SYSTEM SCHEMATIC Figure 7-9 ISSUED: JULY 12, 1995 REPORT: VB-1616...
Page 198 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.9 LANDING GEAR (Continued) When the gear is fully extended or fully retracted and the gear selector is in the corresponding position, electrical limit switches stop the flow of current to the motor of the hydraulic pump. When the landing gear is retracted, the main wheels retract inboard into the wings and the nose wheel retracts aft into the nose section.
Page 199 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION ANNUNCIATOR LIGHTS (Continued) If one or two of the three green lights do not illuminate when the gear DOWN position has been selected, any of the following conditions could exist for each light that is out: (a) The gear is not locked down.
Page 200 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.9 LANDING GEAR (Continued) SAFETY SWITCH To prevent inadvertent gear retraction should the gear selector be placed in the UP position when the airplane is on the ground, a squat switch located on the left main gear will prevent the hydraulic pump from actuating if the master switch is turned on.
Page 201 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION NOTE If the airplane is being used for training purposes or a pilot check-out mission, and the emergency gear extension knob has been pulled out, it may be pushed in again when desired if there has not been any apparent malfunction of the landing gear system.
Page 202: Brake System
SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.11 BRAKE SYSTEM NORMAL OPERATION The brake system is designed to meet all normal braking needs. Two single-disc, double puck brake assemblies, one on each main gear, are actuated by toe brake pedals mounted on both the pilot's and copilot's rudder pedals. A brake system hydraulic reservoir, independent of the landing gear hydraulic reservoir, is located on the upper right side of the bulkhead in the nose compartment.
Page 203 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION STABILATOR TRIM RUDDER TRIM FLAP CONTROL LEVER FLAP AND TRIM CONTROLS Figure 7-13 To extend the flaps, pull the handle up to the desired setting - 10, 25 or 40 degrees. To retract, depress the button on the end of the handle and lower the control.
Page 204: Fuel System
SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.15 FUEL SYSTEM Fuel is stored in two 55 gallon fuel tanks, one in each nacelle (Figure 7-15). One gallon of fuel in each nacelle is unusable, giving a total of 108 usable gallons. The minimum fuel grade is 100 octane. The fuel tank vents, one installed under each wing, feature an anti-icing design to prevent ice formation from blocking the fuel tank vent lines.
Page 205 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION FUEL PUMPS Normally, fuel is supplied to the engines through engine-driven fuel pumps. Auxiliary electric fuel pumps serve as a back-up feature. The electric fuel pumps are controlled by rocker switches on the switch panel below and to the right of the pilot's control column.
Page 206 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE FUEL CONTROLS Fuel management controls are located on the console between the front seats (Figure 7-17). There is a control lever for each engine, and each is placarded ON - OFF - X-FEED. During normal operation, the levers are in the ON position, and each engine draws fuel from the tanks on the same side as the engine.
Page 207: Electrical System
SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION 7.17 ELECTRICAL SYSTEM The electrical system is a negative-ground, dual-fed, split-bus system capable of supplying sufficient current for complete night IFR equipment. ALTERNATORS The primary electrical power is supplied by two belt-driven 14 volt, 70 ampere alternators (Figure 7-19), one mounted on each engine.
Page 208 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE SWITCHES The engine switches, including the Battery Master, left and right Alternators, left and right Magnetos, left and right Starters and left and right Fuel Pumps are located on the lower panel (Figure 7-19) in front of the pilot. The light switches, the Radio Master switch, and the Day/Night Dimmer switch (if installed) are located to the left of the copilot control column.
Page 209 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION CIRCUIT BREAKERS The electrical system and equipment are protected by circuit breakers located on a circuit breaker panel on the lower right side of the instrument panel (Figure 7-21). The circuit breaker panel is provided with blank spaces to accommodate additional circuit breakers if extra electrical equipment is installed.
Page 210 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE POWER DISTRIBUTION A battery bus (Figure 7-23), located in the battery compartment, provides a continuous source of power to the clock, the engine hourmeter, the flight- time hourmeter and the heater hourmeter. Because the battery bus is connected directly to the battery, power is available even when the Battery Master switch is OFF.
Page 211 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION ELECTRICAL POWER DISTRIBUTION SYSTEM Figure 7-23 ISSUED: JULY 12, 1995 REPORT: VB-1616 7-23...
Page 212 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE SYSTEM MONITORS Dual ammeters and two annunciator lights provide a means of monitoring electrical system operation. Two ammeters, located to the left of the pilot's control column, indicate the individual electrical load of each alternator. Should an overvoltage condition occur in either alternator, its voltage regulator will shut off the voltage of that alternator.
Page 213 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION LIGHTS Interior lighting consists of post lights and internally lighted avionics and switches. Radio, panel, and switch lights are controlled by rheostat switches located below the pilot's control column. A floodlight, mounted in the overhead panel, provides additional instrument and cockpit lighting for night flying.
Page 214 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE EXTERNAL POWER RECEPTACLE (Continued) Turn the Battery Master switch and all electrical equipment OFF. Connect the power connector plug assembly to an appropriate external battery. Insert the plug into the external power receptacle. This completes a circuit which permits current to flow from the external power source directly to the starter contactors and the tie bus.
Page 215: Vacuum System
SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION A vacuum regulator is provided in the system to protect the gyros. The valve is set so the normal vacuum reads 4.8 to 5.2 inches of mercury, a setting which provides sufficient vacuum to operate all the gyros at their rated RPM. Higher settings will damage the gyros and with a low setting the gyros will be unreliable.
Page 216: Pitot Static System
SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.21 PITOT STATIC SYSTEM The pitot static system (Figure 7-29) supplies both pitot and static pressure for the airspeed indicator and static pressure for the altimeter, vertical speed indicator, blind encoder and autopilot. Pitot and static pressure are picked up by the pitot head on the bottom of the left wing.
Page 217 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION PITOT AND STATIC PRESSURE SYSTEM Figure 7-29 ISSUED: JULY 12, 1995 REPORT: VB-1616 7-29...
Page 218: Heating, Ventilating And Defrosting System
SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.23 HEATING, VENTILATING AND DEFROSTING SYSTEM HEAT Heated air for cabin heat and windshield defrosting is provided by a Janitrol combustion heater located in the forward fuselage (Figure 7-31). Air from the heater is distributed by a manifold down through ducts along the cabin floor to outlets at each seat.
Page 219 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION ENVIRONMENTAL SYSTEM Figure 7-31 ISSUED: JULY 12, 1995 REPORT: VB-1616 7-31...
Page 220 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE ENVIRONMENTAL CONTROLS AND ANNUNCIATORS Figure 7-33 REPORT: VB-1616 ISSUED: JULY 12, 1995 7-32...
Page 221 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION Safety Switches Two safety switches activated by the intake valve and located aft of the heater unit prevent both fan and heater operation when the air intake lever is in the closed position. A micro switch, which actuates when the landing gear is retracted, turns off the ventilation blower so that in flight the cabin air is circulated by ram air pressure only.
Page 222: Instrument Panel
SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.25 INSTRUMENT PANEL The instrument panel (Figure 7-35) is designed to accommodate the customary advanced flight instruments and the normally required power plant instruments. The artificial horizon is vacuum operated and located in the center of the left instrument panel, above the pilot's control column. The vacuum gauge is located on the right side of the instrument panel.
Page 223 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION 7.25 INSTRUMENT PANEL (Continued) Instrument panel lighting is provided by post lights and internally lighted avionics and switches. Lighting can be adjusted by two rheostat switches, labeled SWITCH LIGHTS and PANEL LIGHTS, located below the pilot's control column.
Page 224 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE INSTRUMENT PANEL Figure 7-35 REPORT: VB-1616 ISSUED: JULY 12, 1995 7-36 REVISED: NOVEMBER 1, 2001...
Page 225 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION INSTRUMENT PANEL (Continued) Figure 7-35 (Continued) ISSUED: JULY 12, 1995 REPORT: VB-1616 REVISED: NOVEMBER 1, 2001 7-37...
Page 226: Cabin Features
SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.27 CABIN FEATURES Cabin entry is made through the cabin door on the right side. The cabin door is double latched. To close the cabin door, hold the door closed with the armrest while moving the side door latch (Figure 7-37) down to the LATCHED position.
Page 227 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION EMERGENCY EXIT Figure 7-39 STANDARD FEATURES Standard front cabin features include cabin and baggage door locks, a pilot's storm window, map pockets, ashtrays, and sun visors. The left sun visor contains Takeoff/ Landing Checklist and the right sun visor includes the Power Setting Table.
Page 228 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE SEATS All seat backs have three positions: normal, intermediate and recline. An adjusment lever is located at the base of each seat back on the outboard side. The two front seats are adjustable fore, aft and vertically. The seats are adjustable fore and aft by lifting the bar below the seat front and moving to the desired position.
Page 229 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION FIRE EXTINGUISHER A portable, handheld, fire extinguisher, containing Halon 1211, is mounted between the pilot and copilot seats, behind the fuel selector console. Read the instructions on the nameplate and become familiar with the unit before an emergency situation.
Page 230: Baggage Area
The standard exterior finish is painted with acrylic enamel. To keep the finish attractive, economy size spray cans of touch-up paint are available from Piper Dealers. 7.33 STALL WARNING An approaching stall is indicated by a stall warning horn which is activated between five and ten knots above stall speed.
Page 231 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION 7.35 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 rectangular cover on the right hand side. A number 2 Phillips screwdriver is required to remove the cover.
Page 232 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.35 EMERGENCY LOCATOR TRANSMITTER (Continued) In the event the transmitter is activated by an impact, it can only be turned off by moving the switch on the ELT unit to OFF. Normal operation can then be restored by pressing the small clear plastic reset button located on the top of the front face of the ELT and then moving the switch to ARM.
Page 233 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION 7.35 EMERGENCY LOCATOR TRANSMITTER (Continued) NOTE The warning light will not blink if the ELT is activated by an incident that also results in severance of the airplane's power supply lines. Should the ELT be activated inadvertently it can be reset by either positioning the remote switch to the ON position for two seconds, and then relocating it to the ARM position, or by setting the switch on the ELT to OFF and then back to ARM.
Page 234 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.35 EMERGENCY LOCATOR TRANSMITTER (Continued) ARTEX 110-4 ELT OPERATION Should the ELT be activated inadvertently it can be reset by either positioning the remote switch to the ON then immediately relocating it to the ARM position, or by setting the switch on the ELT to ON and then back to OFF.
Page 235 SECTION 8 PA-44-180, SEMINOLE HAND / SERV / MAINT TABLE OF CONTENTS SECTION 8 AIRPLANE HANDLING, SERVICING AND MAINTENANCE Paragraph Page General ..................Airplane Inspection Periods ............Preventive Maintenance ..............Airplane Alterations ..............Ground Handling................8.11 Engine Induction Air Filter ............8.13 Brake Service ................
Page 236: Paragraph Page
SECTION 8 HAND / SERV / MAINT PA-44-180, SEMINOLE TABLE OF CONTENTS SECTION 8 AIRPLANE HANDLING, SERVICING AND MAINTENANCE Paragraph Page 8.33 Cleaning ..................8-16 8.35 Winterization................. 8-19 REPORT: VB-1616 ISSUED: JULY 12, 1995 8-ii...
Page 237: General
This information is provided to all authorized 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 latest FAA-registered owners in the U.S. Owners should give careful attention to Service Letter information.
Page 238: Airplane Inspection Periods
Piper Service/Maintenance Manual, and should be complied with by a properly trained, knowledgeable, and qualified mechanic at a Piper Authorized Service Center or a reputable repair shop. Piper cannot accept responsibility for the continued airworthiness of any...
Page 239: Preventive Maintenance
SECTION 8 PA-44-180, SEMINOLE HANDLING, SERV & MAINT 8.3 AIRPLANE INSPECTION PERIODS (Continued) A spectographic 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 240: Airplane Alterations
SECTION 8 HANDLING, SERV & MAINT PA-44-180, SEMINOLE 8.7 AIRPLANE ALTERATIONS If the owner desires to have his aircraft modified, he must obtain FAA approval for the alteration. Major alterations accomplished in accordance with Advisory Circular 43.13-2, when performed by an A & P mechanic, may be approved by the local FAA office.
Page 241: Ground Handling
SECTION 8 PA-44-180, SEMINOLE HANDLING, SERV & MAINT 8.9 GROUND HANDLING (a) Towing The airplane may be moved on the ground by the use of the nose wheel steering bar that is stowed in the baggage compartment or by power equipment that will not damage or excessively strain the nose gear steering assembly.
Page 242 SECTION 8 HANDLING, SERV & MAINT PA-44-180, SEMINOLE 8.9 GROUND HANDLING (Continued) (4) Observe wing clearance when taxiing near buildings or other stationary objects. If possible, station an observer outside the airplane. (5) When taxiing over uneven ground, avoid holes and ruts. (6) Do not operate the engine at high RPM when running up or taxiing over ground containing loose stones, gravel, or any loose material that may cause damage to the propeller...
Page 243: Engine Induction Air Filter
SECTION 8 PA-44-180, SEMINOLE HANDLING, SERV & MAINT (5) Secure tie-down ropes to the wing tie-down rings and to the tail skid at approximately 45 degree angles to the ground. When using rope of non-synthetic material, leave sufficient slack to avoid damage to the airplane should the ropes contract.
Page 244: Brake Service
SECTION 8 HANDLING, SERV & MAINT PA-44-180, SEMINOLE 8.11 ENGINE INDUCTION AIR FILTERS (Continued) To clean the filter: (1) Tap filter gently to remove dirt particles. Do not use compressed air or cleaning solvents. (2) Inspect filter. If paper element is torn or ruptured or gasket is damaged, the filter should be replaced.
Page 245 SECTION 8 PA-44-180, SEMINOLE HANDLING, SERV & MAINT 1. BRAKE FLUID RESERVOIR 2. PARKING BRAKE HANDLE 3. BRAKE CYLINDERS 4. BRAKE LINES 5. PARKING BRAKE VALVE 6. BRAKE ASSEMBLY BRAKE SYSTEM Figure 8-1 ISSUED: JULY 12, 1995 REPORT: VB-1616...
Page 246: Hydraulic System Service
SECTION 8 HANDLING, SERV & MAINT PA-44-180, SEMINOLE 8.17 HYDRAULIC SYSTEM SERVICE The hydraulic landing gear system reservoir is an integral part of the electric hydraulic pump assembly. The combination pump and reservoir is accessible through a panel in the baggage compartment. Fill the reservoir with MIL-H-5606 hydraulic fluid.
Page 247: Oil Requirements
SECTION 8 PA-44-180, SEMINOLE HANDLING, SERV & MAINT 8.19 PROPELLER SERVICE (Continued) The spinner and backing plate should be cleaned and inspected for cracks frequently. Before each flight the propeller should be inspected for nicks, scratches, or corrosion. If found, they should be repaired as soon as possible by a rated mechanic, since a nick or scratch causes an area of increased stress which can lead to serious cracks or the loss of a propeller tip.
Page 248: Fuel System
SECTION 8 HANDLING, SERV & MAINT PA-44-180, SEMINOLE 8.23 FUEL SYSTEM (a) Servicing Fuel System The fuel screens in the strainers require cleaning at 50 hour or 90 day intervals, whichever occurs first. The fuel gascolator strainers are located in the fuselage under the rear seats. The fuel selector valves and the auxiliary pumps are in the wings adjacent to the nacelles.
Page 249 SECTION 8 PA-44-180, SEMINOLE HANDLING, SERV & MAINT 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 0.15% by volume of the refueled quantity, and to ensure its effectiveness should be blended at not less than 0.10% by volume.
Page 250 SECTION 8 HANDLING, SERV & MAINT PA-44-180, SEMINOLE 8.23 FUEL SYSTEM (Continued) (d) Draining Fuel Strainers, Sumps and Lines The aircraft is equipped with single point drains (Figure 8-3) which should be drained before the first flight of the day and after refueling, to check for fuel contamination.
Page 251: Tire Inflation
SECTION 8 PA-44-180, SEMINOLE HANDLING, SERV & MAINT (e) Draining Fuel System The fuel may be drained by opening the valves at the right hand side of the fuselage just forward of the entrance step or by siphoning. The remaining fuel in the lines may be drained through the gascolators.
Page 252: Serial Number Plates
SECTION 8 HANDLING, SERV & MAINT PA-44-180, SEMINOLE 8.27 BATTERY SERVICE (Continued) The external power receptacle is located on the right side of the nose section. Be sure the Battery Master switch is OFF while inserting or removing a plug at this receptacle. Refer to the Maintenance Manual for detailed procedures for cleaning and servicing the battery.
Page 253 SECTION 8 PA-44-180, SEMINOLE HANDLING, SERV & MAINT (3) Allow the solvent to remain on the engine from five to ten minutes. Then rinse the engine clean with additional solvent and allow it to dry. CAUTION Do not operate the engine until excess solvent has evaporated or otherwise been removed.
Page 254 SECTION 8 HANDLING, SERV & MAINT PA-44-180, SEMINOLE 8.33 CLEANING (Continued) (3) To remove exhaust stains, allow the solution to remain on the surface longer. (4) To remove stubborn oil and grease, use a cloth dampened with naphtha. (5) Rinse all surfaces thoroughly. (6) Any good automotive wax may be used to preserve painted surfaces.
Page 255 SECTION 8 PA-44-180, SEMINOLE HANDLING, SERV & MAINT (e) Cleaning Headliner, Side Panels and Seats (1) Clean headliner, side panels, and seats with a stiff brush, and vacuum where necessary. (2) Soiled upholstery, except leather, may be cleaned with a good upholstery cleaner suitable for the material.
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Page 257 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENTS TABLE OF CONTENTS SECTION 9 SUPPLEMENTS Paragraph/Supplement Page General ..................King KFC 150 Series Flight Control System ........(1 Page) (Pages 9-4 thru 9-24 DELETED) King KNS-81 Area Navigation System......(6 Pages) 9-25 Bendix/King KLN 89B GPS Navigation System..........(12 Pages) 9-31 Bendix/King KLN 90B GPS...
Page 258 THIS PAGE INTENTIONALLY LEFT BLANK...
Page 259: General
SECTION 9 PA-44-180, SEMINOLE SUPPLEMENTS SECTION 9 SUPPLEMENTS 9.1 GENERAL This section provides information in the form of Supplements which are necessary for efficient operation of the airplane when equipped with one or more of the various optional systems and equipment not approved with the standard airplane.
Page 260 SECTION 9 SUPPLEMENTS PA-44-180, SEMINOLE THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1616 ISSUED: JULY 12, 1995...
Page 261: King Kfc 150 Series Flight Control System
SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 1 PILOT'S OPERATING HANDBOOK SUPPLEMENT NO. 1 KING KFC 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 SA2321CE-D.
Page 262 SECTION 9 SUPPLEMENT 1 PA-44-180, SEMINOLE THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1616 ISSUED: JULY 12, 1995...
Page 263 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: JULY 12, 1995 ___________________ ISSUED: JULY 12, 1995...
Page 264 This supplement supplies information necessary for the operation of the airplane when the optional King KNS 81 Digital Area Navigation System is installed in accordance with FAA Approved Piper data. SECTION 2 - LIMITATIONS No changes to the basic limitations provided by Section 2 of this Pilot's Operating Handbook are necessary for this supplement.
Page 265 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 2 (b) CONTROLS (1) USE BUTTON Momentary pushbutton. Causes displayed waypoint to become active waypoint and carrot display to go to FRQ mode. (2) RTN BUTTON Momentary pushbutton. When pushed causes waypoint in use to be displayed and carrot display to go to FRQ mode.
Page 266 SECTION 9 SUPPLEMENT 2 PA-44-180, SEMINOLE SECTION 4- NORMAL PROCEDURES (Continued) (7) DATA INPUT CONTROL Dual concentric knobs, right side of panel - Center knob has in and out positions. Frequency Data Outer knob varies 1 MHz digit. A carry occurs from units to tens position. Rollover occurs from 117 to 108.
Page 267 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT NAV FREQ DISPLAY MODE SELECTOR KNOB WAYPOINT DISTANCE M O D E ı WAYPOINT RADIAL ANNUNCIATOR DATA BUTTON U S E R T N R A D C H K D A T A RADIAL BUTTON WAYPOINTı...
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Page 269: Bendix/King Kln 89B Gps Navigation System
Pilot's O p erating 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: October 25, 1995 ISSUED: OCTOBER 25, 1995 REPORT: VB-1616...
Page 270 SECTION 9 SUPPLEMENT 3 PA-44-180, SEMINOLE SECTION 1 GENERAL The KLN 89B 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 card which plugs directly into the front of the unit.
Page 271 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 3 SECTION 2- LIMITATIONS The KLN 89B GPS Pilot’s Guide, P/N 006-08786-0000, dated May, 1995 (or later applicable revision) must be immediately available to the flight crew whenever navigation is predicated on the use of the system. The Operational Revision Status (ORS) of the Pilot’s Guide must match the ORS level annunciated on the Self Test page.
Page 272 SECTION 9 SUPPLEMENT 3 PA-44-180, SEMINOLE SECTION 3- EMERGENCY PROCEDURES ABNORMAL PROCEDURES If the KLN 89B 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 273 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 3 NORMAL PROCEDURES Message (MSG) annunciator - Will flash to alert the pilot of a situation that requires attention. Press the MSG button on the KLN 89B GPS to view the message. (Appendix B of the KLN 89B Pilot’s Guide contains a list of all of the message page messages and their meanings).
Page 274 SECTION 9 SUPPLEMENT 3 PA-44-180, SEMINOLE NORMAL PROCEDURES GPS approach (GPS APR ARM/ACTV) switch/annunciator - Used to (a) manually select or deselect approach ARM (or deselect approach ACTV) and (b) annunciate the stage of approach operation either armed (ARM) or activated (ACTV). Sequential button pushes if in ACTV would first result in approach ARM and then approach arm canceled.
Page 275 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 3 NORMAL PROCEDURES ALTITUDE ALERT AURAL TONES r 1000 feet prior to reaching the selected altitude - three short tones. Upon reaching the selected altitude - two short tones. Deviating above or below the selected altitude by more than the warn altitude - four short tones.
Page 276 SECTION 9 SUPPLEMENT 3 PA-44-180, SEMINOLE NORMAL PROCEDURES At 30 nm from the airport: Verify automatic annunciation of APR ARM. Note automatic dbar scaling change from ± 5.0 nm to ±1.0 nm over the next 30 seconds. Update the KLN 89B altimeter baro setting as required. Internally the KLN 89B will transition from en route to terminal integrity monitoring.
Page 277 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 3 NORMAL PROCEDURES Approaching the FAF inbound (within 2 nm.): Verify APR ACTV. Note automatic dbar scaling change from ±1.0 nm to ± 0.3 nm over the 2 nm inbound to the FAF. Internally the KLN 89B will transition from terminal to approach integrity monitoring.
Page 278 SECTION 9 SUPPLEMENT 3 PA-44-180, SEMINOLE NORMAL PROCEDURES • 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 the arc if...
Page 279 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 3 NORMAL PROCEDURES APR ARM to APR ACTV is automatic provided: a. You are in APR ARM (normally automatic). b. You are in LEG mode! c. The FAF is the active waypoint! d. Within 2 n.m. of the FAF. e.
Page 280 SECTION 9 SUPPLEMENT 3 PA-44-180, SEMINOLE THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1616 ISSUED: OCTOBER 25, 1995 9-42...
Page 281: Bendix/King Kln 90B Gps Navigation System
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_____________JANUARY 9, 1996 __________ ISSUED: JULY 12, 1995 REPORT: VB-1616...
Page 282 SECTION 9 SUPPLEMENT 4 PA-44-180, SEMINOLE 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 283 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 4 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 284 SECTION 9 SUPPLEMENT 4 PA-44-180, SEMINOLE 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 285 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 4 SECTION 4 - NORMAL PROCEDURES (CONT'D) 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 286 SECTION 9 SUPPLEMENT 4 PA-44-180, SEMINOLE 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 287 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 4 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 288 SECTION 9 SUPPLEMENT 4 PA-44-180, SEMINOLE SECTION 4 - NORMAL PROCEDURES (CONT'D) 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 289 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 4 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 290 SECTION 9 SUPPLEMENT 4 PA-44-180, SEMINOLE 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 291 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 4 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 mode! c. The FAF is the active ; waypoint d.
Page 292 SECTION 9 SUPPLEMENT 4 PA-44-180, SEMINOLE THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1616 ISSUED: JULY 12, 1995 9-54 12 of 12...
Page 293: Bendix/King Kx 155A Comm/Nav System
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 294 PA-44-180, SEMINOLE 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 295 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 5 SECTION 7 DESCRIPTION & OPERATION GENERAL All controls required to operate the KX 155A 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 296 SECTION 9 SUPPLEMENT 5 PA-44-180, SEMINOLE 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 297 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 5 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 298 SECTION 9 SUPPLEMENT 5 PA-44-180, SEMINOLE 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 299 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 5 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: JULY 12, 1995 REPORT: VB-1616 REVISED: JUNE 20, 1998 7 of 12...
Page 300 SECTION 9 SUPPLEMENT 5 PA-44-180, SEMINOLE 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 301 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 5 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 302 SECTION 9 SUPPLEMENT 5 PA-44-180, SEMINOLE 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 303 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 5 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 304 SECTION 9 SUPPLEMENT 5 PA-44-180, SEMINOLE THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1616 ISSUED: JULY 12, 1995 9-66 12 of 12 REVISED: JUNE 20, 1998...
Page 305 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: CHRISTINA L. MARSH D.O.A. NO. SO-1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: NOVEMBER 30, 1999 ISSUED: JULY 12, 1995 REPORT: VB-1616...
Page 306 SECTION 9 SUPPLEMENT 6 PA-44-180, SEMINOLE 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/ILS receiver, VHF COMM antenna and a VHF Communications transceiver.
Page 307 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 6 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 308 SECTION 9 SUPPLEMENT 6 PA-44-180, SEMINOLE 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 309 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 6 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 310 SECTION 9 SUPPLEMENT 6 PA-44-180, SEMINOLE 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 311 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 6 SECTION 4 - NORMAL PROCEDURES (continued) D. AUTOMATIC LOCALIZER COURSE CAPTURE By default, the GNS 430 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.
Page 312 SECTION 9 SUPPLEMENT 6 PA-44-180, SEMINOLE THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1616 ISSUED: JULY 12, 1995 9-74 8 of 8 REVISED: NOVEMBER 30, 1999...
Page 313: S-Tec System 55 Autopilot
SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 7 PILOT'S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 7 S-TEC SYSTEM 55 TWO AXIS AUTOMATIC FLIGHT GUIDANCE SYSTEM WITH TRIM MONITOR (Serial numbers 4496031 and up) The FAA approved operational supplement for the S-TEC System 55 Autopilot, installed in accordance with STC SA09131AC-D, is required for operation of this system.
Page 314 SECTION 9 SUPPLEMENT 7 PA-44-180, SEMINOLE THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1616 ISSUED: JULY 12, 1995 9-76 REVISED: NOVEMBER 30, 1999...
Page 315: S-Tec Manual Electric Trim System
SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 8 PILOT'S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 8 S-TEC MANUAL ELECTRIC TRIM SYSTEM WITH TRIM MONITOR (Serial numbers 4496012 and up) The FAA approved operational supplement for the S-TEC Manual Electric Trim System, installed in accordance with STC SA09139AC-D, is required for operation of this system.
Page 316 SECTION 9 SUPPLEMENT 8 PA-44-180, SEMINOLE THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1616 ISSUED: JULY 12, 1995 9-78 REVISED: NOVEMBER 30, 1999...
Page 317: March
Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: CHRISTINA L. MARSH D.O.A. NO. SO-1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA ISSUED: JULY 12, 1995 REPORT: VB-1616 REVISED: MARCH 10, 2000...
Page 318: March
SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Battery Master Hourmeter is installed in accordance with FAA approved Piper data. SECTION 2 - LIMITATIONS No change. SECTION 3 - EMERGENCY PROCEDURES No change.
Page 319: Issued: July
SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 9 SECTION 7 - DESCRIPTION AND OPERATION INSTRUMENT PANEL Figure 7-1 ISSUED: JULY 12, 1995 REPORT: VB-1616 REVISED: MARCH 10, 2000 3 of 4, 9-81...
Page 320 SECTION 9 SUPPLEMENT 9 PA-44-180, SEMINOLE INSTRUMENT PANEL Figure 7-1 (continued) REPORT: VB-1616 ISSUED: JULY 12, 1995 9-82, 4 of 4 REVISED: MARCH 10, 2000...
Page 321: Garmin Gtx 327 Transponder
Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: CHRISTINA L. MARSH D.O.A. NO. SO- 1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: January 12, 2001 ISSUED: JULY 12, 1995 REPORT: VB-1616...
Page 322 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 323 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 10 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 324 SECTION 9 SUPPLEMENT 10 PA-44-180, SEMINOLE 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 325 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 10 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 326 SECTION 9 SUPPLEMENT 10 PA-44-180, SEMINOLE 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 327 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 10 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 328 SECTION 9 SUPPLEMENT 10 PA-44-180, SEMINOLE 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 329 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 10 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.
Page 330 SECTION 9 SUPPLEMENT 10 PA-44-180, SEMINOLE THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1616 ISSUED: JULY 12, 1995 9-92, 10 of 10 REVISED: JANUARY 12, 2001...
Page 331 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 11 PILOT'S OPERATING HANDBOOK FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. 11 S-TEC SYSTEM 55X TWO AXIS AUTOMATIC FLIGHT GUIDANCE SYSTEM The FAA approved operational supplement for the S-TEC System 55X Autopilot, installed in accordance with STC SA09131AC-D, is required for operation of this system.
Page 332 SECTION 9 SUPPLEMENT 11 PA-44-180, SEMINOLE THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1616 ISSUED: JULY 12, 1995 9-94 REVISED: JANUARY 12, 2001...
Page 333: S-Tec Adf 650A System
Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: CHRISTINA L. MARSH D.O.A. NO. SO- 1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: January 12, 2001 ISSUED: JULY 12, 1995 REPORT: VB-1616...
Page 334 SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the S-TEC ADF-650A System is installed in accordance with FAA approved Piper data. SECTION 2 - LIMITATIONS No change. SECTION 3 - EMERGENCY PROCEDURES No change.
Page 335 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 12 SECTION 4 - NORMAL PROCEDURES To operate as an Automatic Direction Finder: • OFF/VOL Control - ON • Frequency Selector Knobs - SELECT desired frequency. • ADF SPEAKER/PHONE Selector Switch (on audio control panel) - SELECT as desired.
Page 336 SECTION 9 SUPPLEMENT 12 PA-44-180, SEMINOLE SECTION 7 - DESCRIPTION AND OPERATION The S-TEC ADF-650A System operates over a frequency range of 200 through 1799 kHz in 1-kHz increments. Three operating modes are included as part of the ADF-650 System. •...
Page 337 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 12 SECTION 7 - DESCRIPTION AND OPERATION (continued) ANT (Antenna) Mode The ANT (antenna) mode cannot be used for navigation; this mode enhances audio reception clarity and is normally used for station identification. ADF Mode Automatic Direction Finder (ADF) mode is used for navigation.
Page 338 SECTION 9 SUPPLEMENT 12 PA-44-180, SEMINOLE THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1616 ISSUED: JULY 12, 1995 9-100 6 of 6 REVISED: JANUARY 12, 2001...
Page 339: Garmin Gma 340 Audio Panel
Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED CHRISTINA L. MARSH D.O.A. NO. SO-1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL January 12, 2001 ISSUED: JULY 12, 1995...
Page 340 SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the Garmin GMA 340 audio panel is installed in accordance with FAA approved Piper data. SECTION 2 - LIMITATIONS No change. SECTION 3 - EMERGENCY PROCEDURES No change.
Page 341 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 13 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 1.
Page 342 SECTION 9 SUPPLEMENT 13 PA-44-180, SEMINOLE SECTION 7 - DESCRIPTION AND OPERATION (continued) ON/OFF, Pilot Intercom System (ICS) Volume Control The GMA 340 is powered OFF when the left small knob (5) is rotated fully CCW into the detent. To turn the unit ON, rotate the knob clockwise past the click.
Page 343 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 13 SECTION 7 - DESCRIPTION AND OPERATION (continued) Aircraft Radios and Navigation Pressing NAV1, NAV2, DME, ADF (16) or MRK (2) selects each audio source. A second button press deselects the audio. Speaker Output Pressing the SPKR button (12) selects the aircraft radios over the cabin speaker.
Page 344 SECTION 9 SUPPLEMENT 13 PA-44-180, SEMINOLE SECTION 7 - DESCRIPTION AND OPERATION (continued) Marker Beacon Receiver The GMA 340’s marker beacon receiver controls are located on the left side of the front panel (1 - 4). The SENS button selects either high or low sensitivity as indicated by the HI or LO LED being lit.
Page 345 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: CHRISTINA L. MARSH D.O.A. NO. SO- 1 THE NEW PIPER AIRCRAFT, INC. VERO BEACH, FLORIDA DATE OF APPROVAL: January 12, 2001 ISSUED: JULY 12, 1995 REPORT: VB-1616...
Page 346 SECTION 9 SUPPLEMENT 14 PA-44-180, SEMINOLE SECTION 1 - GENERAL The S-TEC DME-450 system is a full feature, solid state, remote mounted system with full 200 channel capability. For long distance operation, it provides a full 100 watts maximum pulse power transmitter output. The IND-450 indicator (see figure 1) provides selectable read-out of distance to/from the station, ground speed, and time to/from the station.
Page 347 SECTION 9 PA-44-180, SEMINOLE SUPPLEMENT 14 SECTION 6 - WEIGHT AND BALANCE Factory installed optional equipment is included in the licensed weight and balance data in Section 6 of the Pilot’s Operating Handbook and Airplane Flight Manual. SECTION 7 - DESCRIPTION AND OPERATION IND-450 Figure 1 1.
Page 348 SECTION 9 SUPPLEMENT 14 PA-44-180, SEMINOLE 7 - DESCRIPTION AND OPERATION (continued) 4. DME ON/OFF SWITCH - Turns DME power on or off. Mode Selector Switch Figure 2 5. DME MODE SELECTOR SWITCH (NAV 1, HOLD, NAV 2) - Selects DME operating mode as follows: NAV 1 - Selects DME operation with NO.
Page 349 SECTION 10 PA-44-180, SEMINOLE OPERATING TIPS TABLE OF CONTENTS SECTION 10 OPERATING TIPS Paragraph Page 10.1 General ..................10-1 10.3 Operation Tips................10-1 ISSUED: JULY 12, 1995 REPORT: VB-1616 REVISED: NOVEMBER 29, 1995 10-i...
Page 350 SECTION 10 OPERATING TIPS PA-44-180, SEMINOLE THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1616 ISSUED: JULY 12, 1995 10-ii REVISED: NOVEMBER 29, 1995...
Page 351 OPERATING TIPS 10.1 GENERAL This section provides operating tips of particular value in the operation of the Piper Seminole. 10.3 OPERATING TIPS (a) Learn to trim for takeoff so that only a very light back pressure on the wheel is required to lift the airplane off the ground.
Page 352 SECTION 10 OPERATING TIPS PA-44-180, SEMINOLE 10.3 OPERATING TIPS (Continued) Extreme running turning takeoffs should be avoided. Prolonged slips and skids which result in excess of 2000 feet of altitude loss, or other radical or extreme maneuvers which could cause uncovering of the fuel outlet must be avoided as fuel flow interruption may occur when the tank being used is not full.
Page 353 SECTION 10 PA-44-180, SEMINOLE OPERATING TIPS 10.3 OPERATING TIPS (Continued) (k) Sluggish RPM control and propeller overspeed with poor RPM recovery after rapid throttle application are indications that nitrogen pressure in the propeller dome is low. (l) Experience has shown that the training advantage gained by pulling a mixture control or turning off the fuel to simulate engine failure at low altitude is not worth the risk assumed, therefore it is recommended that instead of using either of these procedures to simulate loss of...
Page 354 SECTION 10 OPERATING TIPS PA-44-180, SEMINOLE THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-1616 ISSUED: JULY 12, 1995 10-4...

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