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Piper SEMINOLE 2013 Pilot Operating Handbook

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REFERENCE ONLY

THIS ELECTRONIC VERSION

OF THE POH IS

NOT APPROVED TO

REPLACE ANY OPERATING

INFORMATION REQUIRED

BY THE REGULATIONS.

aiRplane

seRial no. ____________________

pa-44-180

RepoRT: vb-2307 faa appRoved bY: ___________________________

daTe of appRoval:

June 5, 2013

This handbook includes The maTerial required To be furnished To The

piloT by The federal aviaTion regulaTions and addiTional informaTion

provided by The manufacTurer and consTiTuTes The faa approved

airplane flighT manual. This handbook musT be carried in The airplane aT

all Times.

seminole

WiTH GaRmin G1000 sYsTem

aiRplane fliGHT manual

aiRplane

ReGisT. no. _________________

eRic a WRiGHT

o.d.a. 510620-ce

pipeR aiRcRafT, inc.

veRo beacH, floRida

pa-44-180

sn 4496331 and up

piloT's

opeRaTinG

Handbook

and

faa appRoved

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Page 1 RepoRT: vb-2307 faa appRoved bY: ___________________________ eRic a WRiGHT o.d.a. 510620-ce daTe of appRoval: pipeR aiRcRafT, inc. June 5, 2013 veRo beacH, floRida This handbook includes The maTerial required To be furnished To The piloT by The federal aviaTion regulaTions and addiTional informaTion provided by The manufacTurer and consTiTuTes The faa approved airplane flighT manual.
Page 2 PA-44-180, SEMINOLE Published by TECHNICAL PUBLICATIONS Piper Aircraft, Inc. Issued: June 5, 2013 © 2013, 2014 Piper Aircraft, Inc. All Rights Reserved. REPORT: VB-2307 ISSUED: June 5, 2013 REVISED: October 27, 2014...
Page 3 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 Extreme care must be exercised to limit the use of this handbook to applicable aircraft.
Page 4 PA-44-180, SEMINOLE REVISIONS The Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual, with the exception of the equipment list, is kept current by revisions which are distributed to the registered airplane owners. The equipment list was current at the time the airplane was certified by the manufacturer and thereafter must be maintained by the owner.
Page 5 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-2307 issued June 5, 2013 Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 1 Added EASA statement . (PR140611) Updated copyright.
Page 6 PA-44-180, SEMINOLE PILOT’S OPERATING hANDBOOk LOG Of REVISIONS Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 2 Revised T of C. (Continued) 3-iii Revised T of C. Revised Para. 3.1. Revised CAS messages. Revised CAS Advisory Table.
Page 7 PA-44-180, SEMINOLE PILOT’S OPERATING hANDBOOk LOG Of REVISIONS Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 2 4-20 Revised Para. 4.5j. (Continued) Relocated text to page 4-21. 4-21 Added text from page 4-20. 4-24 Revised Para.
Page 8 PA-44-180, SEMINOLE PILOT’S OPERATING hANDBOOk LOG Of REVISIONS Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 2 7-34 Revised Para. 7.9. (Continued) 7-36 Revised Para. 7.9. thru 7-38 7-39 Revised Para. 7.9. Added Para. 7.10. 7-39a Added pages.
Page 9 PA-44-180, SEMINOLE PILOT’S OPERATING hANDBOOk LOG Of REVISIONS Revision FAA Approved Number and Revised Description of Revisions Signature Code Pages and Date Rev. 2 9-16 Added text from page 9-15. (Continued) Relocated text to page 9-17. Revised footer. 9-17 Added text from page 9-16. Revised footer.
Page 10 PA-44-180, SEMINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 REVISED: October 27, 2014 vi-d...
Page 11 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 12 PA-44-180, SEMINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 viii...
Page 13: Table Of Contents
SECTION 1 PA-44-180, SEMINOLE GENERAL TABLE Of cONTENTS SEcTION 1 GENERAL Paragraph Page Introduction ................Engine ..................Propeller .................. Fuel ..................Oil ..................1.11 Maximum Weights ..............1.13 Standard Airplane Weights ............. 1.15 Baggage Space and Entry Dimensions ........1.17 Specific Loading ..............
Page 14 SECTION 1 GENERAL PA-44-180, SEMINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 1-ii...
Page 15: General
SECTION 1 PA-44-180, SEMINOLE GENERAL SEcTION 1 GENERAL 1.1 INTRODUcTION This Pilot’s Operating Handbook is designed as an operating guide for the pilot. It contains all of the information that must be provided in an Airplane Flight Manual (AFM) under Federal Aviation Regulation. Additional information is provided by the airplane manufacturer regarding the characteristics and operation of the airplane and its systems.
Page 16 SECTION 1 GENERAL PA-44-180, SEMINOLE ThREE VIEW Figure 1-1 REPORT: VB-2307 ISSUED: June 5, 2013...
Page 17: 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 18: 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 1.9 OIL (a) Oil Capacity (U.S. qts.) (per engine) (b) Oil Specification Refer to latest revision of Lycoming Service...
Page 19: 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.
Page 20: G1000 Gnss (Gps/Sbas) Navigation System Equipment Approvals
SEcTION 1 GENERAL PA-44-180, SEMINOLE 1.18 G1000 GNSS (GPS/SBAS) NAVIGATION SySTEM EqUIPMENT APPROVALS The Garmin G1000 Integrated Avionics GNSS navigation system installed in this aircraft is a GPS system with a Satellite Based Augmentation System (SBAS) comprised of two ETSO-145/TSO-C145a Class 3 approved Garmin GIA 63Ws, ETSO-146/TSO-C146a Class 3 approved Garmin GDU 1040 Display Units, two GA36 GPS antennas (one is a GA37 if optional GDL 69A is installed), and GPS software version 3.2 or later approved version.
Page 21 SEcTION 1 PA-44-180, SEMINOLE GENERAL 1.18 G1000 GNSS (GPS/SBAS) NAVIGATION SySTEM EqUIPMENT APPROVALS (continued) The Garmin GNSS navigation system complies with the equipment requirements of AC 90-100A for RNAV 2 and RNAV 1 operations. In accordance with AC 90-100A, Part 91 operators (except subpart K) following the aircraft and training guidance in AC 90-100A are authorized to fly RNAV 2 and RNAV 1 procedures.
Page 22: Symbols, Abbreviations And Terminology
SECTION 1 GENERAL PA-44-180, SEMINOLE 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 23 SECTION 1 PA-44-180, SEMINOLE GENERAL 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 24 SECTION 1 GENERAL PA-44-180, SEMINOLE 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 25 SEcTION 1 PA-44-180, SEMINOLE GENERAL 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 26 SECTION 1 GENERAL PA-44-180, SEMINOLE 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 27 SECTION 1 PA-44-180, SEMINOLE GENERAL 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 28 SECTION 1 GENERAL PA-44-180, SEMINOLE 1.19 SyMBOLS, ABBREVIATIONS AND TERMINOLOGy (continued) (g) Avionics Terminology Multifunction Display Primary Flight Display AHRS Attitude Heading Reference System Air Data Computer Garmin Integrated Avionics Unit Garmin Engine/Airframe Unit Global Positioning System REPORT: VB-2307 ISSUED: June 5, 2013 1-14...
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 ........... 2.10 Systems Limitations ..............2.11 Weight Limits ................2.13 Center of Gravity Limits ............
Page 30 SECTION 2 LIMITATIONS PA-44-180, SEMINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 2-ii...
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 operation of the airplane and its systems. This airplane must be operated as a normal or utility category airplane in compliance with the operating limitations stated in this section and the handbook.
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 Red Radial Line (One Engine Inoperative Air Minimum Control Speed) 56 KTS 2.7 POWER PLANT LIMITATIONS (a) Number of Engines (b) Engine Manufacturer Lycoming (c) Engine Model No. Left 0-360-A1H6 Right L0-360-A1H6...
Page 34: Powerplant Instrument Markings
SECTION 2 LIMITATIONS PA-44-180, SEMINOLE 2.9 POWERPLANT INSTRUMENT MARkINGS (a) Tachometer Green Arc (Normal Operating Range) 500 to 2700 RPM Red Line (Maximum) 2700 RPM (b) Oil Temperature Green Arc (Normal Operating Range) 75°F to 245°F Red Line ( Maximum) 245°F (c) Oil Pressure Green Arc (Normal Operating Range)
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 100...
Page 37: Garmin G1000 Avionics System Limitations
SEcTION 2 PA-44-180, SEMINOLE LIMITATIONS 2.25 GARMIN G1000 AVIONIcS SySTEM LIMITATIONS (a) cockpit Reference & Pilot’s Guide The Garmin G1000 Cockpit Reference Guide for the PA-44-180 Seminole (Garmin P/N 190-01462-01 latest appropriate revision) provides operating instructions on the major features of the G1000 Integrated Flight Deck. This Cockpit Reference Guide (CRG) must be immediately available to the pilot while operating the airplane.
Page 38 SEcTION 2 LIMITATIONS PA-44-180, SEMINOLE 2.25 GARMIN G1000 AVIONIcS SySTEM LIMITATIONS (continued) (c) Databases GPS/SBAS based IFR enroute, oceanic and terminal navigation predicated upon the Garmin G1000 GPS Receiver is prohibited unless the pilot uses a valid, compatible, and current Navigation database or verifies each selected waypoint for accuracy by reference to current data.
Page 39 SEcTION 2 PA-44-180, SEMINOLE LIMITATIONS 2.25 GARMIN G1000 AVIONIcS SySTEM LIMITATIONS (continued) (d) flight Planning (continued) For operations within European B-RNAV/RNAV-5 and P-RNAV airspace, if more than one satellite is scheduled to be out of service, then the availability of GPS RAIM shall be confirmed for the intended flight (route and time).
Page 40 SEcTION 2 LIMITATIONS PA-44-180, SEMINOLE 2.25 GARMIN G1000 AVIONIcS SySTEM LIMITATIONS (continued) (e) Enroute RNP and RNAV routes including Standard Instrument Departures (SIDs) and Obstacle Departure Procedures (ODPs) and Standard Terminal Arrival (STAR) must be loaded into the flight plan from the current database in their entirety, rather than loading route waypoints from the database into the flight plan individually.
Page 41 SEcTION 2 PA-44-180, SEMINOLE LIMITATIONS 2.25 GARMIN G1000 AVIONIcS SySTEM LIMITATIONS (continued) (f) Approaches (continued) (1) Vertical Guidance (continued) and EASA Airspace Systems. Approaches to airports in other airspace are not approved unless authorized by the appropriate governing authority. (2) GPS Approaches See Section 1, paragraph 1.18.
Page 42 SEcTION 2 LIMITATIONS PA-44-180, SEMINOLE 2.25 GARMIN G1000 AVIONIcS SySTEM LIMITATIONS (continued) (h) Terrain and Obstacle Display The G1000 terrain and obstacle information appears on the MFD display as red and yellow tiles or towers, and is depicted for advisory information only.
Page 43 SEcTION 2 PA-44-180, SEMINOLE LIMITATIONS 2.25 GARMIN G1000 AVIONIcS SySTEM LIMITATIONS (continued) (l) chartView and SafeTaxi® The G1000 Integrated Avionics System as installed in this aircraft supports approval of AC 20-173 Hardware Class 3, Software Type B Electronic Flight Bag (EFB) electronic aeronautical chart applications when using current FliteChart or ChartView data.
Page 44 SECTION 2 LIMITATIONS PA-44-180, SEMINOLE 2.25 GARMIN G1000 AVIONIcS SySTEM LIMITATIONS (continued) Minimum fully functional equipment required for flight operations: Equipment Number Installed AHRS (GRS) ADC (GDC) Magnetometer (GMU) Standby Instrument - Attitude Standby Instrument - Airspeed Standby Instrument - Altimeter Standby Instrument - Heading If the PFD is inoperative during DAY or NIGHT VFR, the MFD must be operative.
Page 45: Gfc 700 Automatic Flight Control System (Afcs)
SEcTION 2 PA-44-180, SEMINOLE LIMITATIONS 2.26 Gfc 700 AUTOMATIc fLIGhT cONTROL SySTEM (AfcS) The autopilot must be disengaged during takeoff and landing. Autopilot minimum engagement heights: 400 feet AGL during takeoff and subsequent climb operations. 1000 feet AGL during cruise and descent operations. 200 feet AGL during approach operations.
Page 46: Placards
SEcTION 2 LIMITATIONS PA-44-180, SEMINOLE 2.27 ASPEN STANDBy INSTRUMENT LIMITATIONS (continiued) 4. Use of the EFD1000 for IFR operations within 750 nautical miles of the magnetic North or South Pole, is NOT AUTHORIZED. NOTE See Section 2.25 for approved VFR and IFR operations when the EFD1000 has an invalid or failed function.
Page 47 SECTION 2 PA-44-180, SEMINOLE LIMITATIONS 2.29 PLAcARDS (continued) On instrument panel in full view of the pilot: Vo 135 AT 3800 LBS Vo 115 AT 2870 LBS VLo 140 DN, 109 UP VLE 140 MAX. DEMO. X-WIND 17 KTS In full view of the pilot and passengers: (S/N 4496014 and up) NO SMOKING In full view of the pilot when the oil cooler winterization kit is installed: OIL COOLER WINTERIZATION PLATE...
Page 48 SECTION 2 LIMITATIONS PA-44-180, SEMINOLE 2.29 PLAcARDS (continued) Near gear selector switch: GEAR UP 109 KIAS MAX. DOWN 140 KIAS MAX. Adjacent to upper door latch: ENGAGE LATCH BEFORE FLIGHT On inside of baggage compartment door: BAGGAGE MAX 200 LBS Adjacent to fuel tank filler caps: REPORT: VB-2307 ISSUED: June 5, 2013...
Page 49 SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES TABLE Of cONTENTS SEcTION 3 EMERGENcy PROcEDURES Paragraph Page General ..................Annunciations and Alerts ........... Crew Alerting System (CAS) Messages ......Terminology ............... Airspeeds for Safe Operations..........Emergency Procedures Checklist ..........3.5a Engine Inoperative Procedures ..........Engine Securing Procedure (Feathering Procedure) ..
Page 50: Paragraph Page
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE TABLE Of cONTENTS (continued) SEcTION 3 EMERGENcy PROcEDURES Paragraph Page 3.5c Air Starting Procedure ............. 3-18 Unfeathering Procedure Unfeathering Accumulator Functioning ......3-18 Unfeathering Procedure/Starter Assisted ......3-19 3.5d Engine Roughness ..............3-20 3.5e Engine Indicating System (EIS) ..........
Page 51 SEcTION 3 PA-44-180, SEMINOLE EMERGENcy PROcEDURES TABLE Of cONTENTS (continued) SEcTION 3 EMERGENcy PROcEDURES Paragraph Page 3.5k Avionics System Failures (Continued) Erroneous Indication or Loss of Engine and Fuel Displays ............... 3-35 Erroneous or Loss of Warning / Caution CAS Messages ............3-36 Communications (COM1 and COM2) Failure ....
Page 52 SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 3-iv...
Page 53: 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 are presented, along with those procedures that are necessary for operation of the airplane.
Page 54: Annunciations And Alerts
SEcTION 3 EMERGENcy PROcEDURES PA-44-180, SEMINOLE 3.1 GENERAL (continued) Annunciations and Alerts The G1000 System produces a number of annunciations and alerts by various means and methods. Some alerts are provided through visual indications, some are aural messages, and some are a combination of the two.
Page 55 SEcTION 3 PA-44-180, SEMINOLE EMERGENcy PROcEDURES GENERAL (continued) Crew Alerting System (CAS) Messages Warnings – Red checklist Event cAS Message Page cause* cAS Warnings with Text Messages High Cylinder Head 3-21 Left and/or right engine CHT L ENG CHT Temperature exceeds 500 °F R ENG CHT Low Fuel Quantity...
Page 56 SEcTION 3 EMERGENcy PROcEDURES PA-44-180, SEMINOLE GENERAL (continued) Crew Alerting System (CAS) Messages (Continued) Warnings – Red (continued) checklist Event cAS Message Page cause* cAS Warnings with EIS Indications Propeller None 3-42 Propeller speed is greater than Overspeed 2720 RPM for more than 5 seconds.
Page 57 SEcTION 3 PA-44-180, SEMINOLE EMERGENcy PROcEDURES GENERAL (continued) Crew Alerting System (CAS) Messages (Continued) cautions – Amber checklist cAS Event cAS Message Page cause* cAS cautions with Text Messages Low Fuel Quantity 3-22 Left or right fuel quantity is less L FUEL QTY than 10 GAL R FUEL QTY...
Page 58: Terminology
SEcTION 3 EMERGENcy PROcEDURES PA-44-180, SEMINOLE GENERAL (continued) Crew Alerting System (CAS) Messages (Continued) Advisories – White checklist cAS Event cAS Message Page cause* cAS Advisory with Text Message Emergency Power 3-29 Emergency battery is in use EMERG BATT ON In Use Fuel Imbalance Left and right fuel quantities...
Page 59: Airspeeds For Safe Operations
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 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 (115 KIAS @ 2870 LB) Never exceed ................202 KIAS 3.5 EMERGENcy PROcEDURES chEckLIST 3.5a Engine Inoperative Procedures...
Page 60: Engine Failure During Takeoff (Speed Below 75 Kias Or Gear Down)
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5a Engine Inoperative Procedures (continued) The engine securing procedure should always be accomplished in a sequential order on the inoperative engine. Move the throttle of the inoperative engine towards IDLE. If no changes are noted, the correct identification of the inoperative engine is confirmed.
Page 61: Engine Failure During Takeoff (Speed Above 75 Kias)
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5a Engine Inoperative Procedures (continued) Engine failure During Takeoff (Speed Above 75 kIAS If sufficient runway remains for a complete stop: GEAR ................VERIFY DOWN LAND ..............STRAIGHT AHEAD Directional Control ..............MAINTAIN THROTTLES ................CLOSE Brakes ................AS REQUIRED If GEAR is in transit or UP and the decision is made to continue: WARNING...
Page 62 SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5a Engine Inoperative Procedures (continued) If engine failure occurs after liftoff with the gear still down and 75 KIAS has been attained, the best course of action will depend on the runway remaining and aircraft configuration. Also the pilot’s decision must be based on a personal judgement, taking into consideration such factors as obstacles, the type of terrain beyond the runway, altitude and temperature, weight and loading, weather, airplane condition, and the pilot’s own proficiency and...
Page 63: Engine Failure During Climb
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5a Engine Inoperative Procedures (continued) Engine failure During climb Airspeed..............MAINTAIN 88 KIAS Directional Control ..............MAINTAIN MIXTURE ................FULL RICH PROPELLERS ............FULL INCREASE THROTTLES ............... FULL OPEN Inoperative Engine ..........IDENTIFY and VERIFY THROTTLE (Inop.
Page 64: Engine Failure During Flight (Speed Below Vmca )
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5a Engine Inoperative Procedures (continued) After the faulty engine has been identified and power loss has been verified, complete the Engine Securing Procedure. Continue a straight ahead climb until sufficient altitude (minimum of 1000 feet above ground elevation) is reached to execute the normal One Engine Inoperative Landing procedure at the nearest suitable airport.
Page 65: Engine Failure During Flight (Speed Above Vmca )
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5a Engine Inoperative Procedures (continued) In order to maximize control effectiveness during the recovery, bank the airplane 5° towards the operating engine. Engine failure During flight (Speed Above V Inoperative Engine ..............IDENTIFY Operating Engine......ADJUST POWER AS REQUIRED Airspeed............
Page 66: One Engine Inoperative Landing
SEcTION 3 EMERGENcy PROcEDURES PA-44-180, SEMINOLE 3.5a Engine Inoperative Procedures (continued) One Engine Inoperative Landing Inoperative Engine ......ENGINE SECURING PROCEDURE COMPLETE Seat Belts/Harnesses ..............SECURE FUEL Selector (Operating Engine) ............ON MIXTURE (Operating Engine)..........FULL RICH PROPELLER Control (Operating Engine) ....FULL INCREASE FUEL PUMP (Operating Engine) ............
Page 67: One Engine Inoperative Go-Around
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5a Engine Inoperative Procedures (continued) One Engine Inoperative Go-Around MIXTURE (Operating Engine)..........FULL RICH PROPELLER (Operating Engine) ......FULL INCREASE THROTTLES ..SMOOTHLY ADVANCE TO TAKEOFF POWER FLAPS ...........RETRACT INCREMENTALLY GEAR ....................UP Airspeed..................88 KIAS Trim .............ADJUST TO 2°...
Page 68: Summary Of Factors Affecting Single Engine Operations
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5a Engine Inoperative Procedures (continued) Summary of factors Affecting Single Engine Operations Significant climb performance penalties can result from landing gear, flap, or windmilling propeller drag. These penalties are approximated as follows: Landing gear extended/Flaps Up ..........- 250 ft./min. Flaps extended 25°/Gear Down ..........- 490 ft./min.
Page 69 SEcTION 3 PA-44-180, SEMINOLE EMERGENcy PROcEDURES ThIS PAGE INTENTIONALLy LEfT BLANk ISSUED: June 5, 2013 REPORT: VB-2307 REVISED: October 27, 2014 3-15...
Page 70 SEcTION 3 EMERGENcy PROcEDURES PA-44-180, SEMINOLE 3.5a Engine Inoperative Procedures (continued) The following general facts should be used as a guide if an engine failure occurs: Discontinuing a takeoff upon engine failure is advisable under most circumstances. Continuing the takeoff, if engine failure occurs prior to reaching obstacle speed and gear retraction, is not advisable.
Page 71: Cruising - One Engine Inoperative
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5b fuel Management - One Engine Inoperative cruising - One Engine Inoperative When using fuel from tank on the same side as the operating engine: FUEL Selector (Operating Engine) ............ON FUEL Selector (Inoperative Engine) ..........OFF FUEL PUMPS ..................OFF (except in case of engine driven pump failure when electric fuel pump on...
Page 72: Air Starting Procedure
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5c Air Starting Procedure Unfeathering Procedure / Unfeathering Accumulator functioning NOTE With the propeller unfeathering system installed, the propeller will usually windmill automatically when the propeller control is moved forward. FUEL Selector (Inoperative Engine) ........... ON MAG LEFT/RIGHT Switches (Inoperative Engine) ......
Page 73: Unfeathering Procedure/Starter Assisted
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5c Air Starting Procedure (continued) Unfeathering Procedure/ Starter Assisted FUEL Selector (Inoperative Engine) ........... ON MAG LEFT/RIGHT Switches (Inoperative Engine) ......ON FUEL PUMP (Inoperative Engine)............ON MIXTURE (Inoperative Engine) ......... FULL RICH THROTTLE (Inoperative Engine) ......Two full strokes and then open 1/4 inch PROPELLER (Inoperative Engine) ..
Page 74: Engine Roughness
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5d Engine Roughness Engine Roughness 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;...
Page 75: Engine Indicating System (Eis)
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5e Engine Indicating System (EIS) Oil Pressure OIL PSI ............... VERIFY LOSS & ENGINE AFFECTED Engine ............... SECURE per Engine Securing Procedure Loss of oil pressure may be either partial or complete. A partial loss of oil pressure usually indicates a malfunction in the oil pressure regulating system, and a landing should be made as soon as possible to investigate the cause and prevent engine damage.
Page 76: Loss Of Fuel Flow
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5e Engine Indicating System (EIS) (continued) Loss of fuel flow FUEL PUMP (Affected Engine) ............ON cAUTION If normal engine operation is not immediately re-established, the FUEL PUMP should be turned off. The lack of engine response could indicate a leak in the fuel system.
Page 77: Engine Fire
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5f Engine fire Engine fire During Start If engine has not started: MIXTURE ................. CUT-OFF THROTTLE ................. FULL OPEN ENG START ........CONTINUE to CRANK ENGINE If engine has already started and is running, continue operating to try pulling the fire into the engine.
Page 78: Electrical Fire
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5g Electrical fire Electrical fire EMERG BATT ..............VERIFY ARM BATT MASTR ..................OFF ALTR LEFT/RIGHT Switches ............OFF Vents ............... CLOSED (To avoid drafts) CABIN HEAT ..................OFF If fire persists, locate and, if practical, extinguish with portable fire extinguisher located on the console just aft of the 2 front seats.
Page 79: Landing Gear Malfunctions
SEcTION 3 PA-44-180, SEMINOLE EMERGENcy PROcEDURES 3.5h Landing Gear Unsafe (continued) The CHECK GEAR Caution is triggered when above ~400 feet AGL and the Warning below ~400 feet AGL. The CHECK GEAR aural that is triggered by low manifold pressure may be silenced by pressing the Master Warn Reset or Master Caution Reset switch as appropriate.
Page 80: Electrical Failures
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5j Electrical failures cAUTION The LEFT ALTR (Row 1, Column 15) and RIGHT ALTR (Row 1, Column 16) circuit breakers should not be opened manually when the alternators are functioning properly. NOTE Tripped circuit breakers should be reset only if the affected system/component is considered essential for safety of flight.
Page 81: Dual Alternator Failure
SEcTION 3 PA-44-180, SEMINOLE EMERGENcy PROcEDURES 3.5j Electrical failures (continued) Dual Alternator failure Indication: Master Warning, Triple chime, L ALTR FAIL R ALTR FAIL cAUTION Approximately 30 minutes of electrical power remains after a dual alternator failure. To ensure 30 minutes of battery power, complete the Load Shedding procedure below, within 3 minutes of dual alternator failure.
Page 82 SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5j Electrical failures (continued) To ensure 30-minutes of battery life: BATT AMPS............-20 AMPS Maximum PITOT HEAT ..........15 Minutes Usage Maximum Com Radio …………………………………3 Minutes Usage Maximum If neither alternator resets, the main battery becomes the primary source of electrical power.
Page 83: Complete Electrical Failure
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5j Electrical failures (continued) complete Electrical failure Indication: Single chime, EMERG BATT ON cAUTION The emergency battery is designed to provide electrical power to all items on the emergency bus for a minimum of 30 minutes. NOTE The VOLTS indication on the EIS window automatically changes to the emergency bus...
Page 84: Emergency Battery Voltage
SEcTION 3 EMERGENcy PROcEDURES PA-44-180, SEMINOLE 3.5j Electrical failures (continued) Emergency Battery Voltage Indication: Master Warning, Triple chime, flashing Red E VOLTS Indication. WARNING Complete electrical failure is imminent. Land as soon as possible. 3.5k Avionics System failures PfD failure Indication: PfD display goes blank.
Page 85 SEcTION 3 PA-44-180, SEMINOLE EMERGENcy PROcEDURES 3.5k Avionics System failures (continued) NOTE If the PFD failure occurs while operating on NAV1 DME, the NAV 1 DME information will still be available. If however, the pilot selects NAV2 DME, NAV1 DME may not be re-selected.
Page 86: Mfd Failure
SEcTION 3 EMERGENcy PROcEDURES PA-44-180, SEMINOLE 3.5k Avionics System failures (continued) MfD failure Indication: MfD display goes blank. DISPLAY BACKUP on audio panel..........PUSH (button extended) Exit and avoid IMC as soon as practical. NOTE The PFD will automatically revert to reversionary mode.
Page 87: Attitude Heading Reference System (Ahrs) Failures
SEcTION 3 PA-44-180, SEMINOLE EMERGENcy PROcEDURES 3.5k Avionics System failures (continued) Attitude heading Reference System (AhRS) failures AhRS Total failure On Ground: Indication: Sky/Ground presentation removed, course pointer straight up, red-x’s and amber text on all attitude and heading indications. PFD Message Advisories (MSG Softkey) ......CONSIDER AHRS Circuit Breaker (Row 2, Col.
Page 88: Air Data Computer (Adc) Failures
SEcTION 3 EMERGENcy PROcEDURES PA-44-180, SEMINOLE 3.5k Avionics System failures (continued) Air Data computer (ADc) failures ADC Total Failure On Ground: Indication: Red-x’s and amber text on all Air Data indications. PFD Message Advisories (MSG Softkey) ......CONSIDER ADC Circuit Breaker (Row 2, Col. 7) ...........RESET If ADC data still invalid: IFR operations not authorized.
Page 89: Avionics System Failures (Continued)
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5k Avionics System failures (continued) Erroneous Indication or Loss of Engine and fuel Displays Indication: Red-x over affected engine indication or fuel display NOTE Erroneous information should be suspected when indications do not agree with other system information.
Page 90: Erroneous Or Loss Of Warning/Caution Cas Messages
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5k Avionics System failures (continued) Erroneous or Loss of Warning/caution cAS Messages Indication: Red-x is shown over the cAS message window or cAS message present when not expected or cAS message not present when expected. 1.
Page 91: Communications (Com1 And Com2) Failure
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5k Avionics System failures (continued) communications (cOM1 and cOM2) failure Indication: Inability to communicate/receive on cOM1 and cOM2. NOTE No matter what the cause of a Com failure, removing power from the audio panel actuates a fail-safe connection between the pilot’s headset/ microphone and COM1.
Page 92 SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5k Avionics System failures (continued) WARNING TAWS is Inoperative. DR mode uses heading, airspeed and last known GPS position to estimate the airplanes current position. All maps with an airplane symbol show a ghosted airplane and a “DR” label. NOTE Traffic Information System (TIS) and Traffic Advisory System (TAS) are not dependent on GPS...
Page 93: Autopilot Malfunction
SEcTION 3 PA-44-180, SEMINOLE EMERGENcy PROcEDURES 3.5k Avionics System failures (continued) Autopilot Malfunction Indication: An unexpected roll or pitch deviation from the desired flight path, possible flight director command deviations from desired aircraft attitudes and possible autopilot disconnect with red AfcS annunciation, amber or red A/P annunciation on PfD.
Page 94: Electric Pitchtrim Failure
SEcTION 3 EMERGENcy PROcEDURES PA-44-180, SEMINOLE 3.5k Avionics System failures (continued) Electric PitchTrim failure Indication: Red boxed PTRM on PFD NOTE Loss of the electric pitch trim servo will not cause the autopilot to disconnect. Monitor pitch attitude for unusual behavior. Be alert to possible autopilot out-of-trim conditions (see AUTOPILOT OUT OF TRIM procedure this section) and expect residual control forces upon disconnect.
Page 95: Autopilot Overspeed Recovery
SEcTION 3 PA-44-180, SEMINOLE EMERGENcy PROcEDURES 3.5k Avionics System failures (continued) Autopilot Overspeed Recovery Indication: annunciation at the top of the PFD airspeed MAXSPD tape This autopilot mode is active whenever the aircraft actual or projected airspeed exceeds V THROTTLE ............REDUCE POWER as required Autopilot Pitch Reference .........RESET to slow the aircraft Autopilot ..............DISCONNECT if required NOTE...
Page 96: Autopilot Out-Of-Trim
SEcTION 3 EMERGENcy PROcEDURES PA-44-180, SEMINOLE 3.5k Avionics System failures (continued) Autopilot Out-Of-Trim á Indication: Amber AIL, AIL ELE, or ELE on PfD â cAUTION Do not attempt to overpower the autopilot in the event of a mistrim. The autopilot servos will oppose pilot input and will trim opposite the direction of pilot input (pitch axis only).
Page 97: Abnormal Flight Director Mode Transition
SEcTION 3 PA-44-180, SEMINOLE EMERGENcy PROcEDURES 3.5k Avionics System failures (continued) Abnormal flight Director Mode Transitions Indication: flashing lateral or vertical mode annunciations on PfD NOTE Upon loss of a selected mode, the system will revert to the default mode for the affected axis, either ROL or PIT.
Page 98: Loss Of Navigation Information
SEcTION 3 EMERGENcy PROcEDURES PA-44-180, SEMINOLE 3.5k Avionics System failures (continued) Loss Of Navigation Information Indication: Amber VOR, VAPP, GPS, Bc, LOc or GS flashing on NOTE If a navigation signal is lost while the autopilot is tracking it, the autopilot will roll the aircraft wings level and default to roll mode (ROL).
Page 99: Cooling Fan Failures
SEcTION 3 PA-44-180, SEMINOLE EMERGENcy PROcEDURES 3.5k Avionics System failures (continued) cooling fan failures Indication: cAS Advisory, Single chime, AV FAN FAIL PFD FAN FAIL MFD FAN FAIL If failure occurs on ground: Do not fly until issue is resolved. If failure occurs in flight: Fix issue prior to next flight.
Page 100: Hydraulic Pump Failures
SEcTION 3 EMERGENcy PROcEDURES PA-44-180, SEMINOLE 3.5l hydraulic Pump failures hydraulic Pump failures hydraulic pump will not deactivate: Indication: Master caution, Double chime, HYDR PUMP ON GEAR PUMP Circuit Breaker (Row 2, Col. 12) ..…………….PULL Prior to landing: GEAR PUMP Circuit Breaker (Row 2, Col. 12) ..………….…PUSH If GEAR PUMP Circuit Breaker Opens: Complete Manual Extension of Landing Gear checklist hydraulic pump will not activate:...
Page 101: Starter Engaged
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5m Starter Engaged Starter Engaged Indication: Master Warning, Triple chime, L START ENGD R START ENGD If on the ground: THROTTLE................REDUCE ENG START Circuit Breaker (Row 1, Col. 12).....PULL ENGINE................SHUTDOWN If in flight: THROTTLE..
Page 102: Open Door
SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE 3.5o Open Door Open Door To close the door in flight: Airspeed........... REDUCE to less than 82 KIAS Cabin Vents ................... CLOSE Storm Window ................OPEN Upper latch (if open) ............CLOSE latch Side latch (if open) ..........PULL on armrest while closing latch If both latches open ..
Page 103: Emergency Exit
SECTION 3 PA-44-180, SEMINOLE EMERGENCY PROCEDURES 3.5q Emergency Exit Emergency Exit Thermoplastic Cover ..............REMOVE Emergency Exit Handle ..........PULL FORWARD Window ..................PUSH OUT 3.5r heater Overheat heater Overheat Indication: Master Warning, Triple chime, HTR OVRHEAT CABIN HEAT ..................OFF An overheat switch in the heater unit deactivated the heater. See Section 7 for additional information.
Page 104 SECTION 3 EMERGENCY PROCEDURES PA-44-180, SEMINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 3-44...
Page 105 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 106 SEcTION 4 NORMAL PROcEDURES PA-44-180, SEMINOLE TABLE Of cONTENTS SEcTION 4 NORMAL PROcEDURES Paragraph Page 4.5m Go-Around Checklist .............. 4-24 4.5n After Landing Checklist ............4-25 4.5o Stopping Engine Checklist ............4-25 4.5p Mooring Checklist ..............4-26 4.5q Intentional One Engine Inoperative Speed ....4-26 4.5r - Air Minimum Control Speed ........
Page 107: 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 normal operating procedures required by FAA regulation, as well as those deemed necessary for normal operation of the airplane are presented.
Page 108 SEcTION 4 NORMAL PROcEDURES PA-44-180, SEMINOLE 4.3 AIRSPEEDS fOR SAfE OPERATIONS The following airspeeds 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 109: Normal Procedures Checklist
SEcTION 4 PA-44-180, SEMINOLE NORMAL PROcEDURES WALk-AROUND Figure 4-1 4.5 NORMAL PROcEDURES chEckLIST The airplane should be given a thorough preflight and walk-around check. The preflight should include a check of the airplane’s operational status, computation of weight and C.G. limits, takeoff distance and in-flight performance.
Page 110: Preflight Check
SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.5 NORMAL PROcEDURES chEckLIST (continued) 4.5a Preflight checklists cOckPIT Control Wheel ..............release restraints Flight Controls ............FREE AND CORRECT PARK BRAKE ..................SET Static System ................... DRAIN Alternate Static Source ..............CLOSED LEFT/RIGHT ENG MAG Switches ..........OFF LEFT/RIGHT FUEL PUMP Switches ..........
Page 111 SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.5 NORMAL PROcEDURES chEckLIST (continued) 4.5a Preflight checklists (continued) RIGhT WING Fuel Sump Drains ................DRAIN Surface Condition ....... CLEAR of ICE, FROST & SNOW Flap and Hinges ................CHECK Aileron, Hinges & Freedom of Movement ........CHECK Static Wicks ...................
Page 112 SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.5a Preflight checklists (continued) NOSE SEcTION 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 ................
Page 113 SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.5a Preflight checklists (continued) fUSELAGE (LEfT SIDE) General Condition ................CHECK Emergency Exit ................CHECK Antennas ..................CHECK Fresh Air Inlet .................CLEAR EMPENNAGE Surface Condition ....... CLEAR of ICE, FROST & SNOW Stabilator, Trim Tab & Freedom of Movement ......CHECK Rudder, Trim Tab &...
Page 114: Before Starting Engine
SECTION 4 NORMAL PROCEDURES PA-44-180, SEMINOLE 4.5b Before Starting Engine checklists BEfORE STARTING ENGINE Preflight Check ..............COMPLETED Flight Planning ..............COMPLETED Cabin Door ........CLOSE & LATCH (Upper and Lower) Seats ..............ADJUSTED & LOCKED Seatbelts and Harness ...........FASTEN/ADJUST CHECK INERTIA REEL PARK BRAKE ..................SET GEAR .....................
Page 115: Engine Start Checklists
SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.5c Engine Start checklists ENGINE START - GENERAL WARNING The L START ENGD or R START ENGD warning CAS message will illuminate after 30 seconds of continuous engine cranking. If the CAS message illuminates after the engine is running, stop the engine and determine the cause.
Page 116 SEcTION 4 NORMAL PROcEDURES PA-44-180, SEMINOLE 4.5c Engine Start checklists NORMAL START - cOLD ENGINE BATT MASTR Switch ................ON Gear Position Indications ............3 GREEN THROTTLES ..............1/4 inch OPEN PROPELLERS .............. FULL INCREASE MIXTURES ................FULL RICH *FUEL PUMP ..................ON *MAG LEFT/RIGHT Switches ............
Page 117 SEcTION 4 PA-44-180, SEMINOLE NORMAL PROcEDURES 4.5c Engine Start checklists (continued) NORMAL START - hOT ENGINE BATT MASTR Switch ................ON Gear Position Indications ............3 GREEN THROTTLES ..............1/2 inch OPEN PROPELLERS .............. FULL INCREASE *MIXTURE ................FULL RICH *FUEL PUMP ..................
Page 118 SEcTION 4 NORMAL PROcEDURES PA-44-180, SEMINOLE 4.5c Engine Start checklists (continued) ENGINE START - cOLD WEAThER (BELOW 10°f) (continued) *Propeller Area ................CLEAR *ENG START ................ENGAGE *OIL PSI ..................CHECK If engine does not start, add prime and repeat above. When engine fires, prime as required until engine is running smoothly.
Page 119 SEcTION 4 PA-44-180, SEMINOLE NORMAL PROcEDURES 4.5c Engine Start checklists (continued) ENGINE START WhEN fLOODED (continued) MIXTURES ................CUT-OFF *FUEL PUMP ..................OFF *MAG LEFT/RIGHT Switches ............ON *Propeller Area ................CLEAR *ENG START ................ENGAGE *MIXTURE ................ADVANCE *THROTTLE ................RETARD *OIL PSI ..................
Page 120: Before Taxiing Checklist
SEcTION 4 NORMAL PROcEDURES PA-44-180, SEMINOLE 4.5d Warm-Up checklist ENGINE START WITh EXTERNAL POWER SOURcE (continued) THROTTLES ..........LOWEST POSSIBLE RPM External Power Plug ....... DISCONNECT from RECEPTACLE BATT MASTR Switch ................ON ALTR LEFT/RIGHT Switches .............. ON VOLTS ................... CHECK ALTR AMP..................
Page 121: Taxiing Checklist
SEcTION 4 PA-44-180, SEMINOLE NORMAL PROcEDURES 4.5e Taxiing checklist TAXIING Taxi Area..................CLEAR THROTTLES ..............APPLY SLOWLY Brakes ..................... CHECK Steering ..................CHECK Instruments ..................CHECK NOTE During taxi, if the VOLTS indication decreases into the warning range, increase engine RPM (if possible) to retain adequate battery charging.
Page 122: Before Takeoff Checklist
SEcTION 4 NORMAL PROcEDURES PA-44-180, SEMINOLE 4.5f Ground check checklist (continued) Carburetor heat should also be checked prior to takeoff to be sure the control is operating properly and to purge any ice which may have formed during taxiing. Avoid prolonged ground operation with carburetor heat ON as the air is unfiltered.
Page 123 SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.5h Takeoff checklist (continued) NORMAL TAkEOff FLAPS ................... 0° to 10° Stabilator and Rudder Trim ........... CHECK SET Power............2700 RPM, FULL THROTTLE Rotate Speed ................. 75 KIAS Climb Speed .................. 88 KIAS GEAR ......................UP FLAPS .....................UP NOTE TAS aural alerts will be muted when GPS altitude...
Page 124: Climb Checklist
SEcTION 4 NORMAL PROcEDURES PA-44-180, SEMINOLE 4.5h Takeoff checklist (continued) 0° fLAP, ShORT fIELD PERfORMANcE TAkEOff (continued) When a short field effort is required, the safest technique is to use flaps up (0°). In the event of an engine failure, the airplane will be in the best configuration to maintain altitude immediately after the gear is raised.
Page 125: Cruise Checklist
SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.5i climb checklist (continued) cRUISE cLIMB (4.25b) MIXTURE ................FULL RICH Power ....................75% Climb Speed ................105 KIAS COWL FLAPS ...............As Required FUEL PUMPS..................ON After attaining an altitude for adequate terrain and obstacle clearance, a cruise climb speed of 105 KIAS or higher is recommended.
Page 126 SEcTION 4 NORMAL PROcEDURES PA-44-180, SEMINOLE 4.5j cruise checklist (continued) cRUISING (continued) Use of the mixture control in cruising flight reduces fuel consumption significantly, especially at higher altitudes. The mixture should be leaned during cruising operation above 5000 ft. altitude and at pilot’s discretion at lower altitudes when 75% power or less is being used.
Page 127: Descent Checklist
SEcTION 4 PA-44-180, SEMINOLE NORMAL PROcEDURES 4.5j cruise checklist (continued) cRUISING (continued) Since the Seminole has one fuel tank per engine, it is advisable to feed the engines symmetrically during cruise so that the same approximate amount of fuel will be left in each side for the landing. The crossfeed (XFEED) can be used to balance fUEL qTy, if necessary.
Page 128: Approach And Landing Checklist
SEcTION 4 NORMAL PROcEDURES PA-44-180, SEMINOLE 4.5l Approach and Landing checklist APPROAch AND LANDING Seat Backs ..................ERECT Seat Belts, Harnesses ...............ADJUSTED FUEL PUMPS..................ON FUEL Selectors ..................ON GEAR (Below 140 KIAS) .............. DOWN Gear Position Indications ............3 GREEN Nacelle Mirror ...........
Page 129 SECTION 4 PA-44-180, SEMINOLE NORMAL PROCEDURES 4.5l Approach and Landing checklist (continued) NORMAL LANDING FLAPS ................. 0° to FULL DOWN Airspeed (Flaps Up) ..............80-90 KIAS (Flaps Down) ............. 75-85 KIAS Trim ................... AS REQUIRED THROTTLES ..............AS REQUIRED Touchdown ...............MAIN WHEELS Braking ................
Page 130: Go-Around Checklist
SEcTION 4 NORMAL PROcEDURES PA-44-180, SEMINOLE 4.5l Approach and Landing checklist (continued) ShORT fIELD PERfORMANcE LANDING FLAPS (Below 111 KIAS) ..........FULL DOWN Airspeed (At Max. Weight) ............75 KIAS Trim ................... AS REQUIRED THROTTLES ..................IDLE Touchdown ...............MAIN WHEELS Braking ..........MAXIMUM without SKIDDING For landings on short runways or runways with adjacent obstructions, a short field landing technique should be used in accordance with the charts in Section 5.
Page 131: After Landing Checklist
SEcTION 4 PA-44-180, SEMINOLE NORMAL PROcEDURES 4.5n After Landing checklist AfTER LANDING Clear of runway. FLAPS ..................RETRACT COWL FLAPS ............... FULL OPEN CARB HEAT ..................OFF FUEL PUMPS..................OFF LIGHTS................AS REQUIRED PITOT HEAT ..................OFF A spongy pedal during braking, is often an indication that the brake fluid needs replenishing.
Page 132: Mooring Checklist
SEcTION 4 NORMAL PROcEDURES PA-44-180, SEMINOLE 4.5p Mooring checklist MOORING PARK BRAKE ..............AS REQUIRED Control Wheel ........... SECURED with seat belts FLAPS ..................FULL UP Wheel Chocks ................IN PLACE Tiedowns ..................SECURE If necessary, the airplane should be moved on the ground with the aid of the optional nose wheel tow bar.
Page 133: V Mca - Air Minimum Control Speed
SEcTION 4 PA-44-180, SEMINOLE NORMAL PROcEDURES 4.5r V - AIR MINIMUM cONTROL SPEED The V demonstration, may be required for the FAA flight test for the multi-engine rating. DEMONSTRATION (a) Landing Gear ..................UP (b) Flaps ....................UP (c) Altitude ............at or above 4000 ft. AGL (d) Airspeed ............
Page 134: Practice One Engine Inoperative Flight
SEcTION 4 NORMAL PROcEDURES PA-44-180, SEMINOLE 4.5s PRAcTIcE ONE ENGINE INOPERATIVE fLIGhT Simulated one engine inoperative flight can be practiced without actually shutting down one engine by setting the propeller rpm of an engine to approximate zero thrust. This is accomplished at typical training altitudes with the throttle adjusted to produce the appropriate engine speed shown below and the mixture full rich, or leaned as required for smooth low power operation.
Page 135: Stalls
SEcTION 4 PA-44-180, SEMINOLE NORMAL PROcEDURES 4.5u 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 Battery Master OFF ISSUED: June 5, 2013 REPORT: VB-2307 REVISED: October 27, 2014...
Page 136 SEcTION 4 NORMAL PROcEDURES PA-44-180, SEMINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 REVISED: October 27, 2014 4-30...
Page 137 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: June 5, 2013 REPORT: VB-2307...
Page 138 SECTION 5 pErfOrmaNCE pa-44-180, SEmINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 5-ii...
Page 139 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 in this section. Performance information associated with those optional systems and equipment which require handbook supplements is provided in Section 9 (Supplements).
Page 140 SECTION 5 pErfOrmaNCE pa-44-180, SEmINOLE 5.3 INTRODUcTION - PERfORMANcE AND fLIGhT PLANNING (continued) Paragraph 5.5 (Flight Planning Example) outlines a detailed, example flight plan, using the performance charts in this section. Each chart includes its own example to show how it is used. WARNING Performance should not be extrapolated beyond the limits shown on the charts.
Page 141 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 is entered in Figure 6-5.
Page 142 SECTION 5 pErfOrmaNCE pa-44-180, SEmINOLE 5.5 fLIGhT PLANNING EXAMPLE (continued) The existing conditions at the departure airport and the forecast conditions at the destination airport must be acquired and evaluated. Actual, versus forecast conditions at the destination airport should be monitored throughout the flight.
Page 143 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. First determine the Fuel, Time and Distance to Climb from sea level to the desired cruise altitude and OAT. Then determine the Fuel, Time and Distance to Climb from sea level to the departure field pressure altitude and OAT.
Page 144 SECTION 5 pErfOrmaNCE pa-44-180, SEmINOLE 5.5 fLIGhT PLANNING EXAMPLE (continued) (d) Descent Determine true descent time, fuel and distance similar to the method used for climb. First determine the Fuel, Time and Distance to Descend from cruise altitude and OAT to sea level. Then determine the Fuel, Time and Distance to Descend from the destination field altitude and OAT to sea level.
Page 145 SECTION 5 PA-44-180, SEMINOLE PErfOrMANCE 5.5 fLIGhT PLANNING EXAMPLE (continued) (e) Cruise Starting with the total flight distance, subtract the previously determined distance to climb and distance to descend to obtain 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 146 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. Keep in mind that the time values obtained from the climb and descent graphs are in minutes and must be converted to hours before adding them to the cruise time.
Page 147 SECTION 5 PA-44-180, SEMINOLE PErfOrMANCE 5.7 PERfORMANcE GRAPhS LIST Of fIGURES Figure Page Temperature Conversion ............5-11 Airspeed Calibration ..............5-12 Stall Speed Vs. Angle of Bank..........5-13 ISA Conversion ............... 5-14 Wind Components ..............5-15 5-10 Accelerate and Stop Distance - Short Field Effort ....5-16 5-11 Takeoff Ground Roll - Short Field Effort .......
Page 148 SECTION 5 pErfOrmaNCE pa-44-180, SEmINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 5-10...
Page 149 SECTION 5 PA-44-180, SEMINOLE PErfOrMANCE FAHRENHEIT CELSIUS DEGREES DEGREES TEMPERATURE cONVERSION Figure 5-1 ISSUED: June 5, 2013 REPORT: VB-2307 5-11...
Page 150 SECTION 5 pErfOrmaNCE pa-44-180, SEmINOLE AIRSPEED cALIBRATION Figure 5-3 REPORT: VB-2307 ISSUED: June 5, 2013 5-12...
Page 151 SECTION 5 PA-44-180, SEMINOLE PErfOrMANCE STALL SPEED VS. ANGLE Of BANk Figure 5-5 ISSUED: June 5, 2013 REPORT: VB-2307 5-13...
Page 152 SECTION 5 pErfOrmaNCE pa-44-180, SEmINOLE ISA cONVERSION Figure 5-7 REPORT: VB-2307 ISSUED: June 5, 2013 5-14...
Page 153 SECTION 5 PA-44-180, SEMINOLE PErfOrMANCE WIND cOMPONENTS Figure 5-9 ISSUED: June 5, 2013 REPORT: VB-2307 5-15...
Page 154 SECTION 5 pErfOrmaNCE pa-44-180, SEmINOLE AccELERATE AND STOP DISTANcE - ShORT fIELD EffORT Figure 5-10 REPORT: VB-2307 ISSUED: June 5, 2013 5-16...
Page 155 SECTION 5 PA-44-180, SEMINOLE PErfOrMANCE TAkEOff GROUND ROLL - ShORT fIELD EffORT Figure 5-11 ISSUED: June 5, 2013 REPORT: VB-2307 5-17...
Page 156 SECTION 5 pErfOrmaNCE pa-44-180, SEmINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 5-18...
Page 157 SECTION 5 PA-44-180, SEMINOLE PErfOrMANCE TAkEOff DISTANcE OVER 50 fT. OBSTAcLE - ShORT fIELD EffORT Figure 5-13 ISSUED: June 5, 2013 REPORT: VB-2307 5-19...
Page 158 SECTION 5 SEcTION 5 pErfOrmaNCE PERfORMANcE pa-44-180, SEmINOLE PA-44-180, SEMINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 5-20...
Page 159 SECTION 5 PA-44-180, SEMINOLE PErfOrMANCE cLIMB PERfORMANcE - BOTh ENGINES OPERATING - GEAR DOWN Figure 5-15 ISSUED: June 5, 2013 REPORT: VB-2307 5-21...
Page 160 SECTION 5 pErfOrmaNCE pa-44-180, SEmINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 5-22...
Page 161 SECTION 5 PA-44-180, SEMINOLE PErfOrMANCE cLIMB PERfORMANcE - BOTh ENGINES OPERATING - GEAR UP Figure 5-17 ISSUED: June 5, 2013 REPORT: VB-2307 5-23...
Page 162 SECTION 5 pErfOrmaNCE pa-44-180, SEmINOLE cLIMB PERfORMANcE - ONE ENGINE OPERATING - GEAR UP Figure 5-19 REPORT: VB-2307 ISSUED: June 5, 2013 5-24...
Page 163 SECTION 5 PA-44-180, SEMINOLE PErfOrMANCE fUEL, TIME AND DISTANcE TO cLIMB Figure 5-21 ISSUED: June 5, 2013 REPORT: VB-2307 5-25...
Page 164 SECTION 5 pErfOrmaNCE pa-44-180, SEmINOLE fUEL & POWER SETTING TABLE Figure 5-23 REPORT: VB-2307 ISSUED: June 5, 2013 5-26...
Page 165 SECTION 5 PA-44-180, SEMINOLE PErfOrMANCE SPEED POWER Figure 5-25 ISSUED: June 5, 2013 REPORT: VB-2307 5-27...
Page 166 SECTION 5 pErfOrmaNCE pa-44-180, SEmINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 5-28...
Page 167 SECTION 5 PA-44-180, SEMINOLE PErfOrMANCE STANDARD TEMPERATURE RANGE AND ENDURANcE - PERfORMANcE cRUISE Figure 5-27 ISSUED: June 5, 2013 REPORT: VB-2307 5-29...
Page 168 SECTION 5 pErfOrmaNCE pa-44-180, SEmINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 5-30...
Page 169 SECTION 5 PA-44-180, SEMINOLE PErfOrMANCE STANDARD TEMPERATURE RANGE AND ENDURANcE - EcONOMy cRUISE Figure 5-29 ISSUED: June 5, 2013 REPORT: VB-2307 5-31...
Page 170 SECTION 5 pErfOrmaNCE pa-44-180, SEmINOLE fUEL, TIME AND DISTANcE TO DEScEND Figure 5-31 REPORT: VB-2307 ISSUED: June 5, 2013 5-32...
Page 171 SECTION 5 PA-44-180, SEMINOLE PErfOrMANCE LANDING DISTANcE OVER 50 fT. OBSTAcLE - ShORT fIELD EffORT Figure 5-33 ISSUED: June 5, 2013 REPORT: VB-2307 5-33...
Page 172 SECTION 5 pErfOrmaNCE pa-44-180, SEmINOLE LANDING GROUND ROLL - ShORT fIELD EffORT Figure 5-35 REPORT: VB-2307 ISSUED: June 5, 2013 5-34...
Page 173 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 ......ISSUED: June 5, 2013 REPORT: VB-2307...
Page 174 SECTION 6 wEIghT aNd balaNCE Pa-44-180, SEMINOlE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 6-ii...
Page 175 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 176 6.3 AIRPLANE WEIGhING PROcEDURE Piper provides basic empty weight and center of gravity location for each airplane, when initial airworthiness is issued. This data is provided on a Weight and Balance Data form (figure 6-5) in Section 6 of the POh.
Page 177 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 178 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 179 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 180 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 181 SECTION 6 PA-44-180, SEMINOLE wEIghT ANd bALANCE WEIGhT AND BALANcE REcORD Figure 6-7 ISSUED: June 5, 2013 REPORT: VB-2307...
Page 182 SECTION 6 wEIghT aNd balaNCE Pa-44-180, SEMINOlE WEIGhT AND BALANcE REcORD (continued) Figure 6-7 (Continued) REPORT: VB-2307 ISSUED: June 5, 2013...
Page 183 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 184 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 185 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.
Page 186 SECTION 6 wEIghT aNd balaNCE Pa-44-180, SEMINOlE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 6-12...
Page 187 SECTION 6 PA-44-180, SEMINOLE wEIghT ANd bALANCE LOADING GRAPh Figure 6-13 ISSUED: June 5, 2013 REPORT: VB-2307 6-13...
Page 188 SECTION 6 wEIghT aNd balaNCE Pa-44-180, SEMINOlE c.G. RANGE AND WEIGhT Figure 6-15 REPORT: VB-2307 ISSUED: June 5, 2013 6-14...
Page 189 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 ................Garmin G1000 Avionics System ..........7.10 GFC700 Automatic Flight Control System (AFCS) ....7-39 7.11 Landing Gear ................
Page 190 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 7.31 Finish .................... 7-75 7.33 Stall Warning................7-75 7.35 Emergency Locator Transmitter ..........7-76 REPORT: VB-2307 ISSUED: June 5, 2013 7-ii...
Page 191: 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 192: 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, is mounted on top of the vertical fin, and incorporates an anti-servo tab which provides longitudinal stability and trim.
Page 193 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION 7.5 ENGINES AND PROPELLERS (continued) PROPELLERS Counter-rotating propellers provides balanced thrust during takeoff and climb which eliminates the critical engine factor in single-engine flight. Two blade, constant speed, controllable pitch and feathering Hartzell propellers are installed as standard equipment. The propellers mount directly to the engine crankshafts.
Page 194: Engine Controls
SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.5 ENGINES AND PROPELLERS (continued) Unfeathering Accumulators Unfeathering 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 out of the feathered position.
Page 195 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION 7.7 ENGINE cONTROLS (continued) cONTROL qUADRANT Figure 7-1 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 (cut-off) position.
Page 196 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.7 ENGINE cONTROLS (continued) The carburetor heat controls are located on the control quadrant just below the engine control levers. When a carburetor heat lever is in the up, or OFF, position the engine is operating on filtered air; when the lever is in the down, or ON, position the engine is operating on unfiltered, heated air.
Page 197: Garmin G1000 Avionics System
DEScR/OPERATION GARMIN G1000 AVIONIcS SySTEM NOTE Refer to the latest appropriate revision of the Garmin G1000 Pilot’s Guide for the Piper PA-44 Seminole, (Garmin P/N 190-01461-01) for complete descriptions of the G1000 integrated avionics system and operating procedures. The Garmin G1000 Integrated Avionics System consists of a Primary...
Page 198 SEcTION 7 DEScR/OPERATION PA-44-180, SEMINOLE GARMIN G1000 AVIONIcS SySTEM (continued) Primary flight Display (continued) The primary function of the PFDs is to provide attitude and heading data from the Attitude and Heading Reference System, air data from the Air Data Computer, and navigation and alerting information.
Page 199 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION Primary flight Display (continued) Attitude and Heading Reference System (AHRS) The AHRS uses rate sensors, air data, GPS data and magnetic variation, to calculate pitch, roll, heading and sideslip. The AHRS incorporates internal monitors to continually validate the information it sends to the flight displays. If a failure is detected, a red X will be displayed in place of the incorrect information.
Page 200 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE Primary flight Display (continued) Crew Alerting System (CAS) Messages The Crew Alerting System (CAS) consists of Master Warning and Master Caution indicators operating in conjunction with CAS text messages and aural alerts. The Master Warning and Caution indicators (labeled MASTER WARN RESET and MASTER CAUTION RESET) are illuminated push- button switches, above the PFD.
Page 201 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION Primary flight Display (continued) Crew Alerting System (CAS) Messages (continued) Caution (Amber) Messages Caution conditions are conveyed via a flashing (amber) Master Caution indicator, a non-repeating double chime and either an inverse (black on amber) text message or a flashing EIS gage indication. Cautions may be acknowledged by pressing the MASTER CAUTION RESET switch.
Page 202 SEcTION 7 DEScR/OPERATION PA-44-180, SEMINOLE Primary flight Display (continued) Aural Alerts The G1000 system generates the following aural alerts: • Master Warning - Repeating triple chime. • Master Caution - Non-repeating double chime. • Advisory - Non-repeating single chime. • Autopilot disconnect and preflight test complete (warble tone). •...
Page 203 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION Primary flight Display (continued) MfD & PfD Message Advisories The G1000 system generates several MFD and PFD Message Advisories. These messages are annunciated by flashing the PFD lower right softkey label, and are accessed/hidden by depressing that softkey. For a complete list of these messages, see the Garmin G1000 Cockpit Reference Guide.
Page 204 SEcTION 7 DEScR/OPERATION PA-44-180, SEMINOLE Primary flight Display (continued) Reversionary Mode - PfD If a failure is detected in the MFD, the G1000 automatically enters reversionary mode. In reversionary mode, critical flight instrumentation, autopilot annunciations, CAS display and the inset map are combined with engine instrumentation on a single display.
Page 205 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION Primary flight Display (continued) Synthetic Vision System (SVS) - Optional The Synthetic Vision System (SVS) is a visual enhancement to the G1000. Terrain-SVS is displayed on the PFD as a forward-looking depiction of the topography immediately in front of the aircraft. The depicted imagery is derived from the aircraft attitude, heading, GPS three-dimensional position, and a database of terrain, obstacles, and other relevant information.
Page 206 SEcTION 7 DEScR/OPERATION PA-44-180, SEMINOLE Multi-function Display The Multi-Function Display (MFD) is located in the center of the instrument panel, and displays the following: • Engine parameters • Aircraft system parameters • Various map and system status pages for Navigation, Traffic Map, Weather Datalink, and TAWS-B The MFD also displays waypoint information, auxiliary information, flight plan information, and nearest information.
Page 207 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION Multi-function Display (continued) ENGINE PAGE Figure 7-5 ISSUED: June 5, 2013 REPORT: VB-2307 7-17...
Page 208 SEcTION 7 DEScR/OPERATION PA-44-180, SEMINOLE Multi-function Display (continued) Reversionary Mode - MfD If the PFD becomes inoperative, the MFD will not automatically switch to reversionary mode. The pilot may elect to use the standby instrument for primary flight instruments, or may manually select the MFD to reversionary mode by pressing the red DISPLAY BACKUP button on the audio panel.
Page 209 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION Multi-function Display (continued) Traffic Information Service (TIS) NOTE If the G1000 system is configured to use the optional Traffic Advisory System (TAS), TIS will not be available for use. Traffic Information Service (TIS) provides a graphic display of traffic advisory information to the pilot.
Page 210 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE Multi-function Display (continued) Traffic Information Service (TIS) (continued) Traffic Map Page (Continued) Traffic is overlaid on the following pages: • Navigation Map Page • Traffic Map Page • Trip Planning Page • Nearest Pages • Active Flight Plan Page •...
Page 211 Additional details on the Traffic Information Service (TIS) are contained in the latest appropriate revisions of the Garmin Cockpit Reference Guide for the Piper PA-44 Seminole, Garmin P/N 190-01462-01 and/or the Garmin G1000 Pilot’s Guide for the PA-44 Seminole, Garmin P/N 190-01461-01.
Page 212 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE Multi-function Display (continued) Traffic Advisory System (TAS) – Optional (continued) Traffic Map Page The Traffic Map page, located in the Map Group on the MFD, is selectable from 2 nm to 12 nm. The GTS 800 is capable of tracking up to 45 intruding aircraft equipped with Mode A or C transponders, and up to 30 intruding aircraft equipped with Mode S transponders.
Page 213 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION Multi-function Display (continued) Traffic Advisory System (TAS) – Optional (continued) TAS Alerts: Traffic is displayed according to TCAS symbology using four different symbols. 1. Non-Threat Traffic – An open white diamond with black with black center indicates traffic is beyond a 6 nm range and greater than ±...
Page 214 Additional details on the Traffic Advisory System (TAS) are contained in the latest appropriate revisions of the Garmin Cockpit Reference Guide for the Piper PA-44 Seminole (Garmin P/N 190-01462-01) and/or the Garmin G1000 Pilot’s Guide for the Piper PA-44 Seminole (Garmin P/N 190- 01461-01). Terrain Proximity...
Page 215 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION Multi-function Display (continued) Terrain Proximity (continued) GPS altitude, is derived from satellite position and may differ from baro-cor- rected altitude read from the altimeter. It is converted to mean sea level (MSL) – based altitude (GPS-MSL altitude) and is used in conjunction with GPS position to calculate and predict the aircraft’s flight path in relation to the surrounding terrain and obstacles, whose altitudes are also referenced to MSL.
Page 216 SEcTION 7 DEScR/OPERATION PA-44-180, SEMINOLE Multi-function Display (continued) Terrain Proximity (continued) Terrain customization options are available by pressing the MENU key while on the Navigation Map page, and then selecting “Map Setup” then “Map” group. Options selected on the Navigation Map page will be used on other map pages (less the Terrain Proximity page itself) that display terrain information.
Page 217 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION Multi-function Display (continued) Terrain Awareness and Warning System (TAWS -B) – Optional NOTE If the G1000 system is configured to use the optional Terrain Awareness and Warning System (TAWS), Terrain Proximity will not be available for use.
Page 218 SEcTION 7 DEScR/OPERATION PA-44-180, SEMINOLE Multi-function Display (continued) Terrain Awareness and Warning System (TAWS-B) – Optional (continued) System Status (continued) TAWS-B requires the following to operate properly: • A valid terrain/obstacle/airport terrain database • A valid 3-D GPS position solution If a valid 3-D GPS position solution and vertical accuracy requirements are not attained or the aircraft is out of the database coverage area, a TAWS N/A annunciation will appear on the TAWS-B page and the aural...
Page 219 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION Multi-function Display (continued) Terrain Awareness and Warning System (TAWS-B) – Optional (continued) Operation of TAWS (continued) To inhibit the aural and visual Premature Descent Alert (PDA) and Forward Looking Terrain Awareness (FLTA) alerts (RTC, ITI, ROC and IOI), press the INHIBIT softkey on the TAWS-B page or depress the MENU key then select “Inhibit TAWS”...
Page 220 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE pfd/mfd alert response alert Type annunciation mfd pop-up alert aural message Technique excessive descent PULL-UP “pull up” Warning PULL-UP rate Warning (edr) reduced required “Terrain, Terrain; PULL-UP Terrain clearance Warning TERRAIN - PULL-UP pull up, pull up” Warning (rTc) imminent Terrain “Terrain ahead, pull up;...
Page 221 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION Multi-function Display (continued) Terrain Awareness and Warning System (TAWS-B) – Optional (continued) TAWS-B Page (continued) On all pages that display terrain data, the obstacles and terrain are depicted with the following colors: • Red - above or within 100 feet below the aircraft altitude. •...
Page 222 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE Multi-function Display (continued) Terrain Awareness and Warning System (TAWS-B) – Optional (continued) TAWS-B Alerts (continued) Response Technique - CAUTION: 1. Take positive corrective action until the alert ceases. 2. Based on analysis of all available instruments and information: •...
Page 223 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION Multi-function Display (continued) Garmin Datalink (GDL) – Optional SiriusXM Weather and SiriusXM Satellite Radio® entertainment services is provided through the optional GDL 69A, a remote-mounted data-link satellite receiver. SiriusXM Satellite Weather and SiriusXM Satellite Radio® services, available by subscription, have coded IDs unique to the installed GDL 69A.
Page 224 SEcTION 7 DEScR/OPERATION PA-44-180, SEMINOLE Multi-function Display (continued) Garmin Datalink (GDL) – Optional (continued) SiriusXM Satellite Weather (continued) NOTE Echo Tops and Cloud Tops are not selectable at the same time due to their color similarities. The following pages can display various portions of XM Weather data: •...
Page 225 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION Multi-function Display (continued) Garmin Datalink (GDL) – Optional (continued) SirusXM Satellite Weather (continued) expiration Time broadcast rate Weather product symbol (minutes) (minutes) 5 (u.s.) neXrad 10 (canada) cloud Top (cld Top) echo Top (echo Top) sirusXm lightning (Xm lTng) cell movement...
Page 226 XM Satellite Radio and their data vendors. Additional details on weather products are contained in the latest appropriate revisions of the Garmin Cockpit Reference Guide for the Piper PA-44 Seminole, (Garmin P/N 190-01462-01) and/or the Garmin G1000 Pilot’s Guide for the Piper PA-44 Seminole, (Garmin P/N 190-01461-01).
Page 227 Additional details on the XM Radio features are contained in the latest appropriate revisions of the Garmin Cockpit Reference Guide for the Piper PA-44 Seminole, (Garmin P/N 190-01462-01) and/or the Garmin G1000 Pilot’s Guide for the Piper PA-44 Seminole, (Garmin P/N 190-01461-01).
Page 228 SEcTION 7 DEScR/OPERATION PA-44-180, SEMINOLE Databases The G1000 utilizes several databases. Database titles display in yellow if they have expired. Database cycle information is displayed on the MFD at power up, but more detailed information is available on the AUX pages. Internal database validation prevents incorrect data from being displayed.
Page 229: Gfc700 Automatic Flight Control System (Afcs)
SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION Databases (continued) FliteCharts Database The Garmin FliteCharts database contains procedure charts for the purchased coverage area. This database is updated on a 28-day cycle. If not updated within 180 days of the expiration date, FliteCharts will no longer function.
Page 230 SEcTION 7 DEScR/OPERATION PA-44-180, SEMINOLE 7.10 Gfc 700 AUTOMATIc fLIGhT cONTROL SySTEM (AfcS) (continued) AUTOPILOT OPERATION When the AVION MASTER switch is selected ON, the GFC700 automatically conducts a self-test, as indicated by a white boxed PFT on the PFD. Successful completion of this self-test is indicated by extinguishing the PFT with no AP failure indications and an autopilot “warble”...
Page 231 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION 7.10 Gfc 700 AUTOMATIc fLIGhT cONTROL SySTEM (AfcS) (continued) Autopilot Disengagement Methods: The autopilot can be disengaged manually by the following “normal” methods which are indicated by a yellow flashing AP annunciation: • Pressing the A/P DISC / TRIM INTER switch on the control wheel •...
Page 232 SEcTION 7 DEScR/OPERATION PA-44-180, SEMINOLE AUTOPILOT fEATURES (continued) Overspeed Recovery Mode (continued) amber MAXSPD is displayed above the airspeed tape. Overspeed Recovery is not active in ALT or GS modes and the airspeed reference (FLC) cannot be adjusted while in Overspeed Recovery mode. Takeoff Mode (optional) Takeoff Mode allows the pilot to manually follow the flight director command bars after takeoff rotation.
Page 233 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION AUTOPILOT fEATURES (continued) Level Mode (Optional) Level Mode commands the airplane to wings level and zero vertical speed. It is activated by pressing the blue switch (labeled LVL) at the top center of the instrument panel. Level Mode may be activated at anytime with the autopilot engaged or disengaged.
Page 234 SEcTION 7 DEScR/OPERATION PA-44-180, SEMINOLE Audio Panel The audio panel contains traditional transmitter and receiver selectors, as well as an integral intercom and marker beacon system. The marker beacon lights appear on the PFD and the marker beacon audio can be heard over the headsets or cockpit speaker.
Page 235 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION 33ES (Extended Squitter) Transponder (Option) In addition to the capabilities of the GTX 33 transponder, the GTX 33ES with Extended Squitter Enabled provides Version 2 Automatic Dependent Surveillance-Broadcast (ADS-B) which meets the TSO C166b mandate for 2020.
Page 236: Landing Gear
SEcTION 7 DEScR/OPERATION PA-44-180, SEMINOLE Standby Instrument (continued): The Aspen Evolution EFD1000 is a fully digital, independent flight instrument display which provides attitude, barometric altitude, airspeed, heading, vertical speed, slip/skid and turn rate indications. The purpose of this flight instrument is to provide a reference to crosscheck the G1000 system information for system reliability and to display basic flight information during a G1000 system failure.
Page 237 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION 7.11 LANDING GEAR (continued) NORMAL OPERATION Hydraulic pressure for gear operation is furnished by an electrically powered, reversible hydraulic pump (refer to Figures 7-9 and 7-11). The pump is activated by a two-position gear selector switch located to the left of the control quadrant on the instrument panel (Figure 7-7).
Page 238 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE LANDING GEAR ELEcTRIcAL SySTEM SchEMATIc Figure 7-9 REPORT: VB-2307 ISSUED: June 5, 2013 7-44...
Page 239 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION LANDING GEAR hyDRAULIc SySTEM SchEMATIc Figure 7-11 ISSUED: June 5, 2013 REPORT: VB-2307 7-45...
Page 240 SEcTION 7 DEScR/OPERATION PA-44-180, SEMINOLE 7.11 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 241 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION Landing Gear Indications (continued) LANDING GEAR INDIcATIONS Figure 7-13 Gear Position Unsafe Should the throttle be placed in a low manifold pressure setting and/or the flaps extended while the gear is retracted, a CHECK GEAR CAS message alerts the pilot that the gear is retracted.
Page 242 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.11 LANDING GEAR (continued) SAFETY SWITCH If the gear selector is 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 when the master switch is turned on.
Page 243 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION NOTE If the emergency gear extension is used for training purposes the emergency gear extension knob may be pushed in again when desired, if there has not been any apparent malfunction of the landing gear system. HYDRAULIC RESERVOIR The hydraulic reservoir for landing gear operation is an integral part of the gear hydraulic pump.
Page 244: Brake System
SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.13 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 245 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION fLAP AND TRIM cONTROLS Figure 7-15 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 246: Fuel System
SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.17 fUEL SySTEM Fuel is stored in two 55 gallon fuel tanks, one in each nacelle (Figure 7-17). 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 247 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 operate at 14 VDC (a voltage converter steps main battery voltage from 28 to 14 volts).
Page 248 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE FUEL CONTROLS Fuel management controls are located on the console between the front seats (Figure 7-19). 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 tank on the same side as the engine.
Page 249: Electrical System
SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION 7.19 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 28 volt, 80 ampere alternators (Figure 7-21), one mounted on each engine.
Page 250 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.19 ELEcTRIcAL SySTEM (continued) EMERGENCY BATTERY (Continued) cAUTION The emergency battery will only provide 30 minutes of power if its voltage at the time of total electrical failure is greater than 23.3 volts. The emergency battery voltage must be verified prior to flight.
Page 251 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION SWITCHES (Continued) Engine Switches Left Switch Bank Right Switch Bank Dimmer Controls ELEcTRIcAL POWER SWITchES Figure 7-21 ISSUED: June 5, 2013 REPORT: VB-2307 REVISED: October 27, 2014 7-57...
Page 252 SEcTION 7 DEScR/OPERATION PA-44-180, SEMINOLE 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 7-23). The circuit breaker panel is provided with blank spaces to accommodate additional circuit breakers if extra electrical equipment is installed.
Page 253 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION POWER DISTRIBUTION A battery bus (Figure 7-25), located in the battery compartment, provides a continuous source of power to the clock, the engine Hobbs meter, the flight- time Hobbs meter and the heater Hobbs meter. Because the battery bus is connected directly to the battery, power is available even when the battery master switch is OFF.
Page 254 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE ELEcTRIcAL POWER DISTRIBUTION SySTEM Figure 7-25 Sheet 1 of 2 REPORT: VB-2307 ISSUED: June 5, 2013 7-60...
Page 255 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION ELEcTRIcAL POWER DISTRIBUTION SySTEM Figure 7-25 Sheet 2 of 2 ISSUED: June 5, 2013 REPORT: VB-2307 7-61...
Page 256 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE LIGHTING Interior lighting consists of a glareshield mounted light strip, internally lit placards and switches and back-lit avionics displays. Lighting intensities are controlled by three rotary switches located on the instrument panel below the PFD. A floodlight, mounted in the overhead panel, provides additional instrument and cockpit lighting for night flying.
Page 257: Pitot Static System
SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION 7.21 PITOT STATIc SySTEM Static and total pressure is sensed by a single pitot head installed on the bottom of the left wing. Independent pressure lines are plumbed from the pitot head to the Garmin air data computer and to the Aspen standby instrument (Figure 7-27).
Page 258 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE PITOT AND STATIc PRESSURE SySTEM Figure 7-27 REPORT: VB-2307 ISSUED: June 5, 2013 7-64...
Page 259: Heating, Ventilating And Defrosting System
SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION 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 7-29). Air from the heater is distributed by a manifold, through ducts along the cabin floor to outlets at each seat.
Page 260 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE ENVIRONMENTAL SySTEM Figure 7-29 REPORT: VB-2307 ISSUED: June 5, 2013 7-66...
Page 261 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION ENVIRONMENTAL cONTROLS AND ANNUNcIATORS Figure 7-31 ISSUED: June 5, 2013 REPORT: VB-2307 7-67...
Page 262 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE Safety Switches Two safety switches, activated by the intake valve, prevent both fan and heater operation when the air intake lever is in the closed position. When the landing gear is retracted, a micro switch turns off the ventilation blower so that in flight the cabin air is circulated by ram air pressure only.
Page 263 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION 7.25 INSTRUMENT PANEL The instrument panel (Figure 7-33) is designed to accommodate the Garmin G1000 avionics, the Aspen standby instrument, all avionics options and required switches. See Figure 7-33 for location of each item/ detail. ThIS SPAcE INTENTIONALLy LEfT BLANk ISSUED: June 5, 2013 REPORT: VB-2307...
Page 264: Instrument Panel
SEcTION 7 DEScR/OPERATION PA-44-180, SEMINOLE INSTRUMENT PANEL Figure 7-33 (Sheet 1 of 2) REPORT: VB-2307 ISSUED: June 5, 2013 REVISED: October 27, 2014 7-70...
Page 265 SEcTION 7 PA-44-180, SEMINOLE DEScR/OPERATION INSTRUMENT PANEL (continued) Figure 7-33 (Sheet 2 of 2) ISSUED: June 5, 2013 REPORT: VB-2307 REVISED: October 27, 2014 7-71...
Page 266: 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 7-35) down to the LATCHED position.
Page 267 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION EMERGENcy EXIT Figure 7-37 STANDARD FEATURES Standard front cabin features include cabin and baggage door locks, a pilot’s storm window, map pockets, and sun visors. An armrest is located on the side panel adjacent to each front seat. Additional standard cabin items are pockets on the front seat backs, a portable fire extinguisher, a special cabin sound-proofing package, a coat hanger support bar and baggage restraint straps in the aft baggage area.
Page 268 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 269: Baggage Area
7.31 fINISh 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..STALL aural alert which is activated between five and ten knots above stall speed.
Page 270 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.35 EMERGENcy LOcATOR TRANSMITTER The 406 MHz Emergency Locator Transmitter (ELT) meets the requirements of TSO-C126a. In the event of a crash, the unit activates automatically and transmits the standard tone on 121.5 MHz, lasting until the battery power is depleted.
Page 271 SECTION 7 PA-44-180, SEMINOLE DESCR/OPERATION 7.35 EMERGENcy LOcATOR TRANSMITTER (continued) ARTEX ME-406 ELT OPERATION The ELT unit has a two position switch placarded ARM and ON. A remote switch is located on the right side of the instrument panel, allowing the pilot to arm or test the transmitter from inside the cabin.
Page 272 SECTION 7 DESCR/OPERATION PA-44-180, SEMINOLE 7.35 EMERGENcy LOcATOR TRANSMITTER (continued) ARTEX ME-406 ELT OPERATION (Continued) The ELT should be checked after flight to make certain the unit has not been activated. Check by selecting 121.50 MHz on an operating receiver. If a downward sweeping audio tone is heard the ELT may have been activated.
Page 273 SECTION 8 PA-44-180, SEMINOLE HANDLING, SERV & MAINT TABLE Of cONTENTS SEcTION 8 AIRPLANE hANDLING, SERVIcING AND MAINTENANcE Paragraph Page General ..................Airplane Inspection Periods ............Preventive Maintenance ............... Airplane Alterations ..............Ground Handling ................8.11 Engine Induction Air Filter ............8.13 Brake Service ................
Page 274 SECTION 8 HAND / SERV / MAINT PA-44-180, SEMINOLE TABLE Of cONTENTS SEcTION 8 AIRPLANE hANDLING, SERVIcING AND MAINTENANcE Paragraph Page 8.33 Cleaning ..................8-18 8.35 Winterization ................8-21 REPORT: VB-2307 ISSUED: June 5, 2013 8-ii...
Page 275 WARNING Inspection, maintenance and parts requirements for all non-PIPER approved STC installations are not included in this handbook. When a non-PIPER approved STC installation is incorporated on the airplane, those portions of the airplane affected by the installation must be inspected in accordance with the inspection program published by the owner of the STC.
Page 276 HAND / SERV / MAINT PA-44-180, SEMINOLE 8.1 GENERAL (cONTINUED) WARNING Use only genuine PIPER parts or PIPER approved parts obtained from PIPER approved sources, in connection with the maintenance and repair of PIPER airplanes. Genuine PIPER parts are produced and inspected...
Page 277: General
HANDLING, SERV & MAINT 8.1 GENERAL (cONTINUED) Every owner should stay in close contact with an authorized Piper Service Center or Piper’s Customer Service Department to obtain the latest information pertaining to their airplane, and to avail themselves of Piper’s support systems.
Page 278: 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 aircraft...
Page 279: Preventive Maintenance
SECTION 8 PA-44-180, SEMINOLE HANDLING, SERV & MAINT 8.3 AIRPLANE INSPEcTION PERIODS (continued) In addition, but in conjunction with the above, the FAA requires periodic inspections on all aircraft to keep the Airworthiness Certificate in effect. The owner is responsible for assuring compliance with these inspection requirements and for maintaining proper documentation in logbooks and/or maintenance records.
Page 280: Airplane Alterations
SECTION 8 HAND / 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 281: 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 282 SECTION 8 HAND / 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 blades.
Page 283: 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 284: Brake Service
SECTION 8 HAND / 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 285 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: June 5, 2013 REPORT: VB-2307 8-11...
Page 286: Hydraulic System Service
SECTION 8 HAND / 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-PRF-5606 hydraulic fluid.
Page 287: 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 288: Fuel System
SECTION 8 HAND / 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 289 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 290 SECTION 8 HAND / 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 291: 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 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. 8.25 TIRE INfLATION For maximum service from the tires, keep them inflated to the proper pressures.
Page 292: Serial Number Plates
SECTION 8 HAND / SERV / MAINT PA-44-180, SEMINOLE 8.27 BATTERy SERVIcE (continued) The external power receptacle is located on the right side of the fuselage behind the wing. Refer to the Maintenance Manual for detailed procedures for servicing instructions. 8.29 SERIAL NUMBER PLATES The serial number plate is located on the bottom of the fuselage near the aft end of the tail cone.
Page 293 SECTION 8 PA-44-180, SEMINOLE HANDLING, SERV & MAINT 8.33 cLEANING (continued) (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 294 SECTION 8 HAND / 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 295 SECTION 8 PA-44-180, SEMINOLE HANDLING, SERV & MAINT 8.33 cLEANING (continued) (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.
Page 296 SECTION 8 HAND / SERV / MAINT PA-44-180, SEMINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 8-22...
Page 297 SECTION 9 PA-44-180, SEMINOLE SuPPLEMENTS TABLE Of cONTENTS SEcTION 9 SUPPLEMENTS Paragraph/Supplement Page General ..................Appareo Vision 1000 Unit ..........(4 pages) Flightcom Model 403 Intercom ........(4 pages) S-TEC System 55X Autopilot Two Axis -Automatic Flight Guidance System ..........(14 pages) 9-11 Bendix/King KR-87 Digital ADF With KI-227 Indicator..............(10 pages)
Page 298 SECTION 9 SupplEmENTS pA-44-180, SEmINOlE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 9-ii...
Page 299: 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 the various optional systems and equipment not approved with the standard airplane. All of the supplements provided in this section are FAA approved and consecutively numbered as a permanent part of this handbook.
Page 300 SECTION 9 SupplEmENTS pA-44-180, SEmINOlE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013...
Page 301: Appareo Vision 1000 Unit
This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when the optional Appareo Vision 1000 unit is installed in accordance with Piper Drawing 107422. This information supplements or supersedes the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein.
Page 302 SECTION 9 SupplEmENT 1 pA-44-180, SEmINOlE SEcTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Appareo Vision 1000 unit is installed. The information contained within this supplement is to be used in conjunction with the complete handbook.
Page 303 SEcTION 9 PA-44-180, SEMINOLE SUPPLEMENT 1 SEcTION 4 - NORMAL PROcEDURES (continued) Status Indicators: Table 1: LED Status Item LED Status Configuration Fault detected: Refer to ICA Blue Booting Green Operating Yellow SD card not inserted: insert SD card and verify Green LED SD card not formatted correctly: format SD to NTSF, verify Green LED GPS lock not received: Allow 15 minutes to clear, if problem...
Page 304 SEcTION 9 SUPPLEMENT 1 PA-44-180, SEMINOLE SEcTION 7- DEScRIPTION AND OPERATION The Vision 1000 system is a data acquisition and recording system. It records aircraft attitude, rate, acceleration, GPS position, and cockpit audio and video. The Vision 1000 system is protected via an in-line fuse located behind the instrument panel.
Page 305: Flightcom Model 403 Intercom
This supplement must be attached to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual when the optional Flightcom model 403 intercom is installed in accordance with Piper Drawing 107423. This information supplements or supersedes the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual only in those areas listed herein.
Page 306 SECTION 9 SupplEmENT 2 pA-44-180, SEmINOlE SEcTION 1 - GENERAL This supplement supplies the information necessary for operation of the airplane when the optional Flightcom model 403 intercom is installed. The information in this supplement is to be used in conjunction with the complete handbook.
Page 307 SEcTION 9 PA-44-180, SEMINOLE SUPPLEMENT 2 SEcTION 4 - NORMAL PROcEDURES (continued) Adjusting the Intercom and headsets (continued) NOTE Noise canceling microphones will not operate correctly if they are more than 1/8” from the mouth. 8. While speaking loudly, adjust the ICS volume controls on the Garmin audio panel to set the pilot and copilot volumes to a comfortable level.
Page 308 SEcTION 9 SUPPLEMENT 2 PA-44-180, SEMINOLE SEcTION 4 - NORMAL PROcEDURES (continued) Isolate Switch For normal intercom and transmit operations, place the Isolate switch in the ICS position. To isolate the passengers from transmitting and receiving radio communications, place the Flightcom 403 Isolate switch in the Isolate position. Placing the Isolate switch in this position will allow continued use of the intercom between copilot and passengers.
Page 309: Flight Guidance System
Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: _________________ Eric A. Wright ODA-510620-CE Piper Aircraft, Inc. Vero Beach, Florida DATE OF APPROVAL: June 5, 2013 ISSUED: June 5, 2013 REPORT: VB-2307...
Page 310 This supplement acquaints the pilot with the features and functions of the System 55X Two Axis Autopilot and provides operating instructions for the system when installed in the Piper Model PA-44-180 Seminole. The aircraft must be operated within the limitations provided herein when the autopilot is in use.
Page 311 SEcTION 9 PA-44-180, SEMINOLE SUPPLEMENT 3 SEcTION 3 - EMERGENcy PROcEDURES AUTOPILOT MALfUNcTION In the event of an autopilot malfunction, or anytime the autopilot is not performing as expected or commanded: Aircraft Control ....... Maintain by overpowering autopilot servos AP DISC/TRIM INTER Switch ............DEPRESS FD/AP MASTR Switch ................
Page 312 SEcTION 9 SUPPLEMENT 3 PA-44-180, SEMINOLE SEcTION 3 - EMERGENcy PROcEDURES (continued) PITch TRIM RUNAWAy Aircraft Control ......Maintain by overpowering the autopilot servos AP DISC/TRIM INTER Switch ........DEPRESS and HOLD ELEV TRIM Master Switch ..............Push OFF PITCH TRIM Circuit Breaker (Row 3, Col. 1)..........PULL Pitch Trim..............
Page 313 SEcTION 9 PA-44-180, SEMINOLE SUPPLEMENT 3 SEcTION 3 - EMERGENcy PROcEDURES (continued) G1000/AVIONIcS SySTEM fAILURES (continued) Cooling Fan Failures When any of these CAS messages illuminate, it is possible to exceed the manufacturer’s specified temperature limits for the affected equipment. The avionics fan (AV FAN FAIL advisory CAS message) supplies cooling air to the transponder, GIA, and autopilot.
Page 314 SEcTION 9 SUPPLEMENT 3 PA-44-180, SEMINOLE SEcTION 4 - NORMAL PROcEDURES (continued) PRE-fLIGhT PROcEDURES - AUTOPILOT (continued) Autopilot Self Test ................COMPLETE “RDY” is displayed NOTE If the autopilot system fails to initialize, it will annunciate “FAIL” and not allow any mode to function.
Page 315 SEcTION 9 PA-44-180, SEMINOLE SUPPLEMENT 3 SEcTION 4 - NORMAL PROcEDURES (continued) PRE-fLIGhT PROcEDURES - AUTOPILOT (continued) FD/AP MASTR Switch ................Select FD Verify FD bars appear Verify roll, pitch and yaw servos disengaged AP DISC/TRIM INTER Button on Control Wheel ....PRESS and HOLD Verify FD bars disappear PRE-fLIGhT PROcEDURES - MANUAL ELEcTRIc TRIM NOTE...
Page 316 SEcTION 9 SUPPLEMENT 3 PA-44-180, SEMINOLE SEcTION 4 - NORMAL PROcEDURES (continued) PRE-fLIGhT PROcEDURES - MANUAL ELEcTRIc TRIM (continued) NOTE If either the Manual Electric Trim or Autotrim fails any portion of the preflight test, push the ELEV TRIM (Master) switch OFF. DO NOT USE THE ELECTRIC TRIM UNTIL THE FAULT IS CORRECTED.
Page 317 SEcTION 9 PA-44-180, SEMINOLE SUPPLEMENT 3 SEcTION 4 - NORMAL PROcEDURES (continued) GLIDE SLOPE fLIGhT PROcEDURE - AUTOMATIc ARM/ cAPTURE (continued) With the GS mode armed, once the aircraft arrives at 5% needle deflection below the glideslope center line, the ALT annunciation will extinguish to indicate engagement/capture of the glideslope mode.
Page 318 SEcTION 9 SUPPLEMENT 3 PA-44-180, SEMINOLE SEcTION 4 - NORMAL PROcEDURES (continued) GPS APPROAch WITh VERTIcAL GUIDANcE Select and load the appropriate GPS WAAS approach (LPV, LNAV/VNAV or LNAV+V) into the MFD or PFD via the PROC button. Select GPSS or APR to allow the autopilot to execute the lateral approach sequence.
Page 319 SEcTION 9 PA-44-180, SEMINOLE SUPPLEMENT 3 SEcTION 7 - DEScRIPTION AND OPERATION This section contains system description and operation for the autopilot, and electric trim systems. for detailed normal operating procedures, including system description, pre-flight and in-flight procedures, refer to the S-TEc System fiftyfive X Pilot Operating handbook, P/N 87109, dated March 1, 2008 or later approved revision.
Page 320 SEcTION 9 SUPPLEMENT 3 PA-44-180, SEMINOLE SEcTION 7 - DEScRIPTION AND OPERATION (continued) AUTOPILOT and fLIGhT DIREcTOR SySTEMS - fLIGhT DIREcTOR (continued) Flight director only guidance is possible by selecting FD on the FD/AP MASTR switch. An audible alert will sound when switching from FD/AP to FD, thereby acknowledging that FD mode is engaged.
Page 321 SEcTION 9 PA-44-180, SEMINOLE SUPPLEMENT 3 SEcTION 7 - DEScRIPTION AND OPERATION (continued) ELEcTRIcAL SySTEM RIGhT SWITch BANk Figure 2 TyPIcAL cIRcUIT BREAkER PANEL Figure 3 ISSUED: June 5, 2013 REPORT: VB-2307 REVISED: October 27, 2014 13 of 16, 9-23...
Page 322 SEcTION 9 SUPPLEMENT 3 PA-44-180, SEMINOLE SEcTION 7 - DEScRIPTION AND OPERATION (continued) INSTRUMENT PANEL Figure 4 (Sheet 1 of 2) REPORT: VB-2307 ISSUED: June 5, 2013 REVISED: October 27, 2014 9-23a, 14 of 16...
Page 323 SEcTION 9 PA-44-180, SEMINOLE SUPPLEMENT 3 INSTRUMENT PANEL (cONTINUED) Figure 4 (Sheet 2 of 2) ISSUED: June 5, 2013 REPORT: VB-2307 REVISED: October 27, 2014 15 of 16, 9-23b...
Page 324 SEcTION 9 SUPPLEMENT 3 PA-44-180, SEMINOLE SEcTION 8 - hANDLING, SERVIcING, AND MAINTENANcE No change. ThIS SPAcE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 REVISED: October 27, 2014 9-24, 16 of 16...
Page 325: Bendix/King Kr-87 Digital Adf With
Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: Eric A. Wright DOA-510620-CE Piper Aircraft, Inc. Vero Beach, Florida DATE OF APPROVAL: June 5, 2013 ISSUED: June 5, 2013...
Page 326 SECTION 9 SupplEmENT 4 pA-44-180, SEmINOlE SEcTION 1 - GENERAL The Bendix/King Digital ADF is a panel mounted, digitally tuned, automatic direction finder. It is designed to provide continuous 1 kHz digital tuning in the frequency range of 200 kHz to 1799 kHz and eliminates the need for mechanical band switching.
Page 327 SEcTION 9 PA-44-180, SEMINOLE SUPPLEMENT 4 SEcTION 4 - NORMAL PROcEDURES To Operate as an Automatic Direction finder: 1. OFF/VOL Control - ON. 2. Frequency Selector Knobs - SELECT desired frequency in the standby frequency display. 3. FRQ Button - PRESS to move the desired frequency from the standby to the active position.
Page 328 SEcTION 9 SUPPLEMENT 4 PA-44-180, SEMINOLE SEcTION 4 - NORMAL PROcEDURES (continued) NOTE The Standby Frequency which is in memory while Flight Time or Elapsed Time modes are being displayed may be called back by pressing the FRQ button, then transferred to active use by pressing the FRQ button again.
Page 329 SEcTION 9 PA-44-180, SEMINOLE SUPPLEMENT 4 SEcTION 4 - NORMAL PROcEDURES (continued) ADf Operation NOTES: Erroneous ADF Bearing Due to Radio Frequency Phenomena: In the U.S., the FCC, which assigns AM radio frequencies, occasionally will assign the same frequency to more than one station in an area. Certain conditions, such as Night Effect, may cause signals from such stations to overlap.
Page 330 SEcTION 9 SUPPLEMENT 4 PA-44-180, SEMINOLE SEcTION 5 - PERfORMANcE No change. SEcTION 6 - WEIGhT AND BALANcE Factory installed optional equipment is included in the certified weight and balance data in Section 6 of the Pilot’s Operating Handbook and Airplane Flight Manual.
Page 331 SEcTION 9 PA-44-180, SEMINOLE SUPPLEMENT 4 SEcTION 7 - DEScRIPTION AND OPERATION kR-87 Digital ADf ADf Displays in Garmin PfD king Digital ADf Operating controls and Indicators Figure 1 ISSUED: June 5, 2013 REPORT: VB-2307 7 of 10, 9-31...
Page 332 SEcTION 9 SUPPLEMENT 4 PA-44-180, SEMINOLE SEcTION 7 - DEScRIPTION AND OPERATION (continued) Legend - figure 1 1. Mode Annunciation - Antenna (ANT) is selected by the “out” position of the ADF button. This mode improves the aural reception and is usually used for station identification.
Page 333 SEcTION 9 PA-44-180, SEMINOLE SUPPLEMENT 4 SEcTION 7 - DEScRIPTION AND OPERATION (continued) Legend - figure 1 (continued) 6. Timer Mode Annunciation - Either the elapsed time (ET) or flight time (FLT) mode is annunciated here. 7. Frequency Selector Knobs - Selects the standby frequency when FRO is displayed and directly selects the active frequency whenever either of the timer functions is selected.
Page 334 SEcTION 9 SUPPLEMENT 4 PA-44-180, SEMINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 9-34, 10 of 10...
Page 335: Bendix/King Kn-63 Dme
Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. FAA APPROVED: Eric A. Wright DOA-510620-CE Piper Aircraft, Inc. Vero Beach, Florida DATE OF APPROVAL: June 5, 2013 ISSUED: June 5, 2013 REPORT: VB-2307 1 of 4,...
Page 336 SECTION 9 SupplEmENT 5 pA-44-180, SEmINOlE SEcTION 1 - GENERAL The Bendix/King KN-63 DME supplies continuous slant range distance information from a fixed ground station to an aircraft in flight. The equipment consists of Garmin Primary Flight Display (PFD) which contains all the operating controls and displays, and a remotely mounted KN-63 Receiver-Transmitter.
Page 337 SEcTION 9 PA-44-180, SEMINOLE SUPPLEMENT 5 SEcTION 7 - DEScRIPTION AND OPERATION DME Display on Garmin PFD Figure 1 Legend - Figure 1 1. DME Information Window 2. DME MODE ANNUNCIATOR Displays the DME operating mode; NAV 1 or NAV 2 or HOLD as selected in the DME TUNING window. 3.
Page 338 SEcTION 9 SUPPLEMENT 5 PA-44-180, SEMINOLE SEcTION 7 - DEScRIPTION AND OPERATION (continued) Legend - figure 1 (continued) 5. DME TUNING Window (NAV1, NAV2, HOLD) Allows access to the DME operating mode as follows: NAV 1 Selects DME operation with No. 1 VHF naviga- tion set;...
Page 339 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: June 5, 2013 REPORT: VB-2307 10-i...
Page 340 SECTION 10 OPERATING TIPS PA-44-180, SEMINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 10-ii...
Page 341 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 342 SECTION 10 OPERATING TIPS PA-44-180, SEMINOLE 10.3 OPERATING TIPS (continued) (f) The rudder pedals are suspended from a torque tube which extends across the fuselage. The pilot should become familiar with the proper positioning of his feet on the rudder pedals so as to avoid interference with the torque tube when moving the rudder pedals or operating the toe brakes.
Page 343 SECTION 10 PA-44-180, SEMINOLE OPErATINg TIPS 10.3 OPERATING TIPS (continued) (l) Before starting either engine, check that all radio switches, light switches and the pitot heat switch are in the OFF position so as not to create an overloaded condition when the starter is engaged. (m) The airplane should not be flown in severe turbulence as damage to the airframe structure could result.
Page 344 SECTION 10 OPERATING TIPS PA-44-180, SEMINOLE ThIS PAGE INTENTIONALLy LEfT BLANk REPORT: VB-2307 ISSUED: June 5, 2013 10-4...

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