Piper CHEROKEE WARRIOR II Pilot Operating Handbook Download | Manualshive

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Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000

Revision 4 Issue:

9/19/17

Page 22 of 27

Document Number L3-76AK-AFMS1

FAA Approved

Table 3-1: Troubleshooting for the Panel Mount NGT-9000

Symptom

Screen

Cause/Corrective Actions

No TIS-B Coverage
Indicator

It is located on the traffic
screen next to the Zoom Out
button.

NOTE

: The indicator is

suppressed when
TAS/TCAS is operational
(i.e. installed, not failed, not
in standby).

Traffic

The No Coverage Indicator is shown on the traffic
display for the following reasons:

1. No TIS-B / ADS-R data available in the area
2. Aircraft is not within range of an ADS-B ground

station. Move aircraft in location where information
can be received.

3. UAT-In test failed (indicator seen after 60 seconds

of test failure)

4. 1090 Receiver failed

•

Try clearing the failure by cycling power to the

unit.

•

Check the L-Band antenna or cables for possible

errors.

•

If the problem continues, replacement of the L-

Band antenna or the unit may be required.

Contact L3 Field Service before removal.

Display indicator ON-GND
showing on transponder
screen.

Transponder

Transponder is operating in the on-ground mode.

1. This is a normal condition when the aircraft is on

ground.

2. If the indication is seen during flight. Contact L3

Field Service.

•

Display indicator XPDR

FAIL (Amber text)
showing on transponder
screen.

•

MSG button on screen.

Transponder

Transponder data is invalid. This indication is shown on
the transponder screen and alternate traffic screen.

1.  Possible problem with internal hardware.
2.  Cycle power to the unit.
3.  Check System Status Messages.
4.  Check the Lynx MAT fault log.
Contact L3 Field Service before removal of unit.

Pressure Altitude digits
replaced with amber
dashes.

Transponder

Invalid Pressure Altitude.
Note: Some altitude encoders may not provide pressure
altitude until after 1-3 minutes of operation.

1.  Cycle power to the unit.
2.  Check System Status Messages.
3.  Check the Lynx MAT fault log.
4.  Check the wiring between the unit and the

secondary equipment supplying the pressure
altitude.

5. Check the secondary equipment for problems.
Contact L3 Field Service before removal of unit.

•

No data on the weather

display.

•

ADS-B Out Fail lamp is

OFF.

Weather

The FIS-B data is not being transmitted to the weather
display.
Note: NEXRAD data is only transmitted every 5 minutes.
CONUS data is only transmitted every 15 minutes.

1. No ground station is in range.
2. The ground station may not provide FIS-B service.

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Summary of Contents for CHEROKEE WARRIOR II

Page 1: ...E FLIGHT MANUAL AND MUST BE CARRIED IN THE AIRPLANE AT ALL TIMES AIRPLANE SERIAL NO _____________________________ AIRPLANE REGISTRATION NO ______________________ PA 28 161 REPORT VB 880 FAA APPROVED BY _______________________________ WARD EVANS D O A NO SO 1 PIPER AIRCRAFT CORPORATION VERO BEACH FLORIDA DATE OF APPROVAL DECEMBER 16 1976 28 7916159 N3067D REFERENCE ONLY THIS ELECTRONIC VERSION OF T...

Page 2: ...R SUBSEQUENTLY REVISED IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED ON THE FACE OF THE TITLE PAGE WHEN OFFICIALLY APPROVED SUBSEQUENT REVISIONS SUPPLIED BY PIPER AIRCRAFT CORPORATION MUST BE PROPERLY INSERTED MODEL PA 28 161 CHEROKEE WARRIOR II PILOT S OPERATING HANDBOOK REPORT VB 880 REVISION_________________________________ PIPER AIRCRAFT CORPORATION APPROVAL SIGNATURE AND STAMP _______________...

Page 3: ... to cover added airplane equipment I Revisions Revisions will be distributed whenever necessary as complete page replacements or additions and shall be inserted into the handbook in accordance with the instructions given below 1 Revision pages will replace only pages with the same page number 2 Insert all additional pages in proper numerical order within each section 3 Page numbers followed by a s...

Page 4: ...6 Added air cond directions to Stopping Engine 4 11 Added air cond check to 4 19 Ground Check 4 12 Added air cond directions to 4 21 Before Takeoff 4 14 Added air cond directions to 4 29 Approach and Landing and 4 31 Stopping Engine 5 3 Revised Fig nos in item b 5 4 Revised Fig nos in footnote 5 5 Revised Fig nos in item e 5 9 Revised Fig Nos revised Page Nos revised titles added pages added figur...

Page 5: ...0 Added page chart relocated from 5 23 5 31 Added page chart relocated from 5 24 5 32 Added page chart relocated from 5 25 6 33 Added items 67 and 69 6 45 Revised item nos added item 213 6 46 Revised item nos added items 229 through 235 relocated items to following page added footnote 6 47 Revised item nos added items 237 and 253 added relocated items relocated items to following page removed foot...

Page 6: ... pages Supplement 4 Air Conditioning Ward Evans 9 13 9 14 Installation July 11 1977 Rev 3 761 649 1 4 Revised items 1 13 and 1 17 PR780630 2 7 Added new takeoff checklist revised lead sentence 3 3 3 7 Added info to Engine Power Loss During Takeoff 4 5 Added info to Before Takeoff 4 9 Revised items 4 13 a b and c 4 12 Added info to Before Takeoff 4 13 Corrected info under 4 23 Takeoff 5 5 Revised i...

Page 7: ...ed para 1 21 6 1 Revised para 6 1 6 19 Revised item 9 6 33 Added items 71 and 73 6 37 Revised item 113 6 41 Added item 170 7 12 Added Warning to para 7 15 7 13 Revised para 7 15 Ward Evans 7 23 Revised para 7 35 Feb 26 1979 Rev 5 761 649 6 49 Revised item 277 added item 278 PR790413 7 23 Revised para 7 35 7 24 Revised para 7 35 relocated para 7 37 to pg 7 25 Ward Evans 7 25 Added info from pg 7 24...

Page 8: ...1 Revised para 6 1 6 3 Added Caution to item 6 3 a 3 6 11 Revised Figure 6 9 6 12 Revised Figure 6 11 6 14 Revised Figure 6 15 6 17 Revised para 6 9 added item 3 revised item 1 6 19 Revised items 5 7 and 9 added new items 6 21 Revised item nos added new items 6 23 Added new items 6 25 Revised item nos added new items 6 27 Revised items added new items 6 29 6 33 Revised items 6 35 6 36 6 37 Revised...

Page 9: ...g 6 35 6 39 Added item 145 renumbered items 6 40 Added items 151 thru 159 6 42 Added item 176 relocated item 177 from pg 6 43 6 43 Added item 178 moved item 177 to pg 6 42 6 44 Added items 196 and 198 renumbered items 6 45 Added item 199 new item 201 renumbered items moved item 213 to pg 6 46 6 46 Relocated item 213 from pg 6 45 6 53 Added item 342 6 54 Added new items 344 and 345 renumbered items...

Page 10: ...3 27 3 28 and 3 29 from pg 3 11 6 17 Added item 4 6 23 Added item 25 6 25 Renumbered items 6 35 Revised items 90 91 and 93 6 38 Added item 132 6 42 Relocated revised item 178 from pg 6 43 6 43 Moved item 178 to pg 6 42 renumbered item added new item 181 revised item 182 6 49 Added item 276 moved items 281 283 and 285 to pg 6 50 6 50 Relocated items 281 283 and 285 from pg 6 49 7 10 Revised para 7 ...

Page 11: ...1 4 i Amended pg number 4 1 Revised para 4 1 and 4 3 4 3 4 5 Revised para 4 5 4 6 4 8 Added Note to para 4 9 4 12 Added Note to para 4 21 moved info to pg 413 4 13 Relocated info from pg 4 12 moved info to pg 4 14 4 14 Relocated info from pg 4 13 added Note to para 4 29 moved info to pg 4 15 4 15 Relocated info from pg 4 14 moved para 4 35 to pg 4 16 4 16 Relocated para 4 35 from pg 4 15 6 17 Revi...

Page 12: ...sed para 6 8 7 22 Revised para 7 31 8 1 Revised para 8 1 8 3 Revised para 8 3 8 4 Revised para 8 5 D H Trompler 8 11 Revised para 8 19 and 8 21 b 9 5 Revised Section 3 a Aug 23 1989 9 9 Revised Section 3 a Date Rev 13 761 649 1 3 Revised para 1 5 c PR900913 2 2 Revised para s 2 7 j and l Added para 2 7 m and Notes 7 3 Revised para 7 5 D H Trompler 8 4 Revised para 8 5 October 9 1990 Rev 14 761 649...

Page 13: ...NCY PROCEDURES SECTION 4 NORMAL PROCEDURES SECTION 5 PERFORMANCE SECTION 6 WEIGHT AND BALANCE SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS SECTION 8 AIRPLANE HANDLING SERVICING AND MAINTENANCE SECTION 9 SUPPLEMENTS SECTION 10 SAFETY TIPS REPORT VB 880 v ...

Page 14: ...ion 1 1 1 3 Engines 1 3 1 5 Propellers 1 3 1 7 Fuel 1 3 1 9 Oil 1 3 1 11 Maximum Weights 1 4 1 13 Standard Airplane Weights 1 4 1 15 Baggage Space 1 4 1 17 Specific Loadings 1 4 1 19 Symbols Abbreviations and Terminology 1 5 1 21 Conversion Factors 1 11 REPORT VB 880 1 i ...

Page 15: ...is also responsible for remaining within the operating limitations as outlined by instrument markings placards and this handbook Although the arrangement of this handbook is intended to increase its in flight capabilities it should not be used solely as an occasional operating reference The pilot should study the entire handbook to familiarize himself with the limitations performance procedures an...

Page 16: ...THREE VIEW Figure 1 1 REPORT VB 880 ISSUED DECEMBER 16 1976 1 2 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA 28 161 CHEROKEE WARRIOR II ...

Page 17: ... Fixed Pitch 1 7 FUEL a Fuel Capacity U S gal total 50 b Usable Fuel U S gal total 48 c Fuel 1 Minimum Octane 100 Green or 100 LL Blue Aviation Grade 2 Alternate Fuel Refer to Fuel Requirements Section 8 Handling Servicing and Maintenance paragraph 8 1 item b 1 9 OIL a Oil Capacity U S quarts 8 b Oil Specification Refer to latest issue of Lycoming Service Instruction 1014 c Oil Viscosity per Avera...

Page 18: ...er to Figure 6 5 for the Standard Empty Weight and the Useful Load 1 15 BAGGAGE SPACE a Compartment Volume cubic feet 24 b Entry Width inches 22 c Entry Height inches 20 1 17 SPECIFIC LOADINGS a Wing Loading lbs per sq ft 13 7 b Power Loading lbs per hp 14 5 REPORT VB 880 ISSUED DECEMBER 16 1976 1 4 REVISED JUNE 29 1981 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA 28 161 CHEROKEE WARRIOR II ...

Page 19: ...ir which is the CAS corrected for altitude temperature and compressability VA Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstress the airplane VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position VNE MNE Never Exceed Speed or Mach Number is the speed limit that may not be...

Page 20: ...dicated Pressure The number actually read from an altimeter when the barometric Altitude subscale has been set to 29 92 inches of mercury 1013 millibars 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 a...

Page 21: ...Crosswind The demonstrated crosswind velocity is the velocity of the Velocity crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during WIND certification tests Accelerate Stop Distance The distance required to accelerate an airplane to a specified speed and assuming failure of an engine at the instant that speed is attained to bring...

Page 22: ...s The extreme center of gravity locations within which the airplane must be operated at a given weight Usable Fuel Fuel available for flight planning Unusable Fuel Fuel remaining after a runout test has been completed in accordance with governmental regulations Standard Empty Weight Weight of a standard airplane including unusable fuel full operating fluids and full oil Basic Empty Weight Standard...

Page 23: ...THIS PAGE INTENTIONALLY LEFT BLANK ISSUED DECEMBER 16 1976 REPORT VB 880 1 9 PIPER AIRCRAFT CORPORATION SECTION 1 PA 28 161 CHEROKEE WARRIOR II GENERAL ...

Page 24: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 1 10 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA 28 161 CHEROKEE WARRIOR II ...

Page 25: ... degrees arc 0 01745 radians mercury at 0 C 0 3937 in Hg cm Hg 0 1934 lb sq in degrees per second 0 01745 radians sec 27 85 lb sq ft deg sec 135 95 kg m2 drams fluid dr fl 0 125 fl oz centimeters per 0 032808 ft sec second cm sec 1 9685 ft min drams avdp 0 0625 oz avdp 0 02237 mph dr avdp cubic centimeters 0 03381 fl oz feet ft 30 48 cm cm3 0 06102 cu in 0 3048 m 3 531 x 10 5 cu ft 12 in 0 001 1 0...

Page 26: ... gallons U S dry 268 8 cu in inches of mercury 0 033421 atm U S gal dry 1 556 x 10 1 cu ft at 0 C in Hg 0 4912 lb sq in 1 164 U S gal 70 73 lb sq ft 4 405 1 345 3 kg m2 2 540 cm Hg gallons U S Iiquid 231 cu in 25 40 mm Hg U S gal 0 1337 cu ft 4 951 x 10 3 cu yd inch pounds in lb 0 011521 m kg 3785 4 cm3 3 785 x 10 3 m3 kilograms kg 2 204622 lb 3 785 1 35 27 oz avdp 0 83268 Imperial gal 1000 g 128 ...

Page 27: ...s per hour 44 7041 cm sec knots kt 1 nautical mph mph 4 470 x 10 1 m sec 1 689 ft sec 1 467 ft sec 1 1516 statute mph 88 ft min 1 852 km hr 1 6093 km hr 51 48 m sec 0 8684 kt liters 1 1000 cm3 miles per hour 2 151 ft sec sq 61 02 cu in square m hr sq 0 03531 cu ft 33 814 fl oz millibars 2 953 x 10 2 in Hg 0 264172 U S gal 0 2200 Imperial gal millimeters mm 0 03937 in 1 05669 qt millimeters of 0 03...

Page 28: ... 27 68 g cm3 square inches 6 4516 cm2 sq in 6 944 x 10 3 sq ft pounds per square 0 1414 in Hg foot lb sq ft 4 88243 kg m2 square kilometers 0 3861 sq mi 4 725 x 10 4 atm km 2 pounds per square 5 1715 cm Hg square meters m2 10 76391 sq ft inch psi or 2 036 in Hg 1 196 sq yd lb sq in 0 06804 atm 0 0001 ha 0 0689476 bar 703 1 kg m2 square miles sq mi 2 590 km2 640 acres quart U S qt 0 94635 1 57 749 ...

Page 29: ... Indicator Markings 2 2 2 7 Power Plant Limitations 2 2 2 9 Power Plant Instrument Markings 2 3 2 11 Weight Limits 2 3 2 13 Center of Gravity Limits 2 4 2 15 Maneuver Limits 2 4 2 17 Flight Load Factors 2 4 2 19 Types of Operations 2 5 2 21 Fuel Limitations 2 5 2 23 Noise Levels 2 5 2 25 Placards 2 7 REPORT VB 880 2 i ...

Page 30: ...d in Section 9 Supplements 2 3 AIRSPEED LIMITATIONS SPEED KIAS KCAS Never Exceed Speed VNE Do not exceed this speed in any operation 160 153 Maximum Structural Cruising Speed VNO Do not exceed this speed except in smooth air and then only with caution 126 122 Design Maneuvering Speed VA Do not make full or abrupt control movements above this speed At 2325 LBS G W 111 108 At 1531 LBS G W 88 89 CAUT...

Page 31: ...ion Grade h Number of Propellers 1 i Propeller Manufacturer Sensenich j Propeller Model 74DM6 0 60 or 74DM6 0 58 k Propeller Diameter Minimum 72 IN Maximum 74 IN l 74DM6 0 60 Propeller Tolerance static rpm at maximum permissible throttle setting Sea Level ISA Not above 2430 RPM Not below 2330 RPM NOTE Refer to the airplane maintenance manual for test procedure to determine approved static rpm unde...

Page 32: ...0 PSI Yellow Arc Ground Warm Up 90 PSI to 100 PSI Red Line Minimum 25 PSI Red Line Maximum 100 PSI d Fuel Pressure Green Arc Normal Operating Range 5 PSI to 8 PSI Red Line Minimum 5 PSI Red Line Maximum 8 PSI 2 1 WEIGHT LIMITS NORMAL UTILITY a Maximum Weight 2325 LBS 2020 LBS b Maximum Baggage 200 LBS 0 LBS NOTE Refer to Section 5 Performance for maximum weight as limited by performance ISSUED DEC...

Page 33: ...It is the responsibility of the airplane owner and the pilot to insure that the airplane is properly loaded See Section 6 Weight and Balance for proper loading instructions 2 15 MANEUVER LIMITS a Normal Category All acrobatic maneuvers including spins prohibited b Utility Category Approved maneuvers for bank angles exceeding 60 Entry Speed Steep Turns 111 KIAS Lazy Eights 111 KIAS Chandelles 111 K...

Page 34: ... this aircraft is 72dBA No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or unacceptable for operation at into or out of any airport The above statement not withstanding the noise level stated above has been verified by and approved by the Federal Aviation Administration in noise level test flights conducted in...

Page 35: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 2 6 SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA 28 161 CHEROKEE WARRIOR II ...

Page 36: ... pump on Seat backs erect Trim tab set Engine gauges checked Controls free Flaps set Door latched Carb heat off Air conditioner off TAKEOFF CHECK LIST Fuel on proper tank Mixture set Fasten belts harness Electric fuel pump on Primer locked Trim tab set Engine gages checked Seat backs erect Controls free Flaps set Door latched Carb heat off Air conditioner off LANDING CHECK LIST Fuel on proper tank...

Page 37: ...AT 2325 SEE P O H UTILITY CATEGORY OPERATION NO AFT PASSENGERS ALLOWED DEMONSTRATED CROSS WIND COMPONENT 17 KTS or DEMO X WIND 17 KTS In full view of the pilot when the oil cooler winterization kit is installed OIL COOLER WINTERIZATION PLATE TO BE REMOVED WHEN AMBIENT TEMPERATURE EXCEEDS 50 F In full view of the pilot UTILITY CATEGORY OPERATION ONLY 1 NO AFT PASSENGERS ALLOWED 2 ACROBATIC MANEUVER...

Page 38: ...LL AVIATION GRADE OR FUEL 100 AVIATION GRADE MIN USABLE CAPACITY 24 GAL USABLE CAPACITY TO BOTTOM OF FILLER NECK INDICATOR 17 GAL ISSUED MAY 30 1980 REPORT VB 880 2 9 PIPER AIRCRAFT CORPORATION SECTION 2 PA 28 161 CHEROKEE WARRIOR II LIMITATIONS ...

Page 39: ...trical Overload 3 4 Spin Recovery 3 4 Open Door 3 5 Engine Roughness 3 5 Carburetor Icing 3 5 3 5 Amplified Emergency Procedures General 3 7 3 7 Engine Fire During Start 3 7 3 9 Engine Power Loss During Takeoff 3 7 3 11 Engine Power Loss In Flight 3 8 3 13 Power Off Landing 3 8 3 15 Fire In Flight 3 9 3 17 Loss of Oil Pressure 3 9 3 19 Loss of Fuel Pressure 3 10 3 21 High Oil Temperature 3 10 3 23...

Page 40: ...ion provides amplified emergency procedures corresponding to the emergency procedures checklist items These amplified emergency procedures contain additional information to provide the pilot with a more complete description of the procedures so they may be more easily understood Pilots must familiarize themselves with the procedures given in this section and must be prepared to take the appropriat...

Page 41: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 3 2 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA 28 161 CHEROKEE WARRIOR II ...

Page 42: ...wer loss Primer check locked If no fuel pressure is indicated check tank selector position to be sure it is on a tank containing fuel When power is restored Carburetor heat OFF Electric fuel pump OFF If power is not restored prepare for power off landing Trim for 73 KIAS POWER OFF LANDING Locate suitable field Establish spiral pattern 1000 ft above field at downwind position for normal landing app...

Page 43: ...load Reduce If alternator loads are reduced ALT switch OFF Land as soon as practical Battery is the only re maining source of power Anticipate complete electrical failure ELECTRICAL OVERLOAD Alternator over 20 amps above known electrical load FOR AIRPLANES WITH SEPARATE BAT AND ALT SWITCH OPERATION ALT switch ON BATT switch OFF If alternator loads are reduced Electrical load Reduce to Minimum Land...

Page 44: ...to latched position If both latches are open latch side latch then top latch ENGINE ROUGHNESS Carburetor heat ON If roughness continues after one min Carburetor heat OFF Mixture adjust for max smoothness Electric fuel pump ON Fuel selector switch tanks Engine gauges check Magneto switch L then R then BOTH If operation is satisfactory on either one continue on that magneto at reduced power and full...

Page 45: ...SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA 28 161 CHEROKEE WARRIOR II THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 3 6 ...

Page 46: ...s should be OFF and the mixture at idle cut off if an external fire extinguishing method is to be used 3 9 ENGINE POWER LOSS DURING TAKEOFF The proper action to be taken if loss of power occurs during takeoff will depend on the circumstances of the particular situation If sufficient runway remains to complete a normal landing land straight ahead If insufficient runway remains maintain a safe airsp...

Page 47: ... If power loss is due to water fuel pressure indications will be normal If engine failure was caused by fuel exhaustion power will not be restored after switching fuel tanks until the empty fuel lines are filled This may require up to ten seconds If power is not regained proceed with the Power Off Landing procedure refer to the emergency check list and paragraph 3 13 3 13 POWER OFF LANDING If loss...

Page 48: ...The procedure given is general and pilot judgment should be the determining factor for action in such an emergency 3 17 LOSS OF OIL PRESSURE Loss of oil pressure may be either partial or complete A partial loss of oil pressure usually indicates a malfunction in the oil pressure regulating system and a landing should be made as soon as possible to investigate the cause and prevent engine damage A c...

Page 49: ...uced as much as possible Check the alternator circuit breakers for a popped circuit The next step is to attempt to reset the overvoltage relay This is accomplished by moving the ALT switch to OFF for one second and then to ON If the trouble was caused by a momentary overvoltage condition 16 5 volts and up this procedure should return the ammeter to a normal reading If the ammeter continues to indi...

Page 50: ... to higher voltage and radio frequency noise operation with the ALT switch ON and the BATT switch OFF should be made only when required by an electrical failure 3 25 SPIN RECOVERY Intentional spins are prohibited in this airplane If a spin is inadvertently entered immediately move the throttle to idle and the ailerons to neutral Full rudder should then be applied opposite to the direction of rotat...

Page 51: ...ce is encountered Adjust mixture for maximum smoothness 3 29 ENGINE ROUGHNESS Engine roughness is usually due to carburetor icing which is indicated by a drop in RPM and may be accompanied by a slight loss of airspeed or altitude If too much ice is allowed to accumulate restoration of full power may not be possible therefore prompt action is required Turn carburetor heat on See Note RPM will decre...

Page 52: ...emal Power Source 4 4 Warm Up 4 4 Taxiing 4 4 Ground Check 4 4 Before Takeoff 4 5 Takeoff 4 5 Climb 4 5 Cruising 4 5 Descent 4 5 Approach and Landing 4 6 Stopping Engine 4 6 Parking 4 6 4 7 Amplified Nomnal Procedures General 4 7 4 9 Preflight Check 4 7 4 11 Before Starting Engine 4 8 4 13 StartingEngine 4 9 4 15 Warm Up 4 11 4 17 Taxiing 4 11 4 19 Ground Check 4 11 4 21 Before Takeoff 4 12 4 23 T...

Page 53: ...CONTENTS SECTION 4 NORMAL PROCEDURES Continued Paragraph Page No No 4 31 Stopping Engine 4 15 4 33 Parking 4 15 4 35 Stalls 4 16 4 37 Turbulent Air Operation 4 16 4 39 Weight and Balance 4 16 REPORT VB 880 4 ii ...

Page 54: ...quence for normal operations with little emphasis on the operation of the systems The remainder of the section is devoted to amplified normal procedures which provide detailed information and explanations of the procedures and how to perform them This portion of the section is not intended for use as an in flight reference due to the lengthly explanations The short form check list should be used f...

Page 55: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 4 2 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA 28 161 CHEROKEE WARRIOR II ...

Page 56: ...k Pitot head remove cover holes clear Windshield clean Propeller and spinner check Fuel and oil check for leaks Oil check level Dipstick properly seated Cowling secure Inspection covers secure Nose wheel tire check Nose gear strut proper inflation 3 25 in Air inlets clear Alternator belt check tension Tow bar and control locks stow Baggage stowed properly secure Baggage door close and secure Fuel ...

Page 57: ...POWER SOURCE Master switch OFF All electrical equipment OFF Terminals connect External power plug insert in fuselage Proceed with normal start Throttle lowest possible RPM External power plug disconnect from fuselage Master switch ON check ammeter Oil pressure check WARM UP Throttle 800 to 1200 RPM TAXIING Chocks removed Taxi area clear Throttle apply slowly Brakes check Steering check GROUND CHEC...

Page 58: ...climb speed 79 KIAS SOFT FIELD OBSTACLE CLEARANCE Flaps 25 second notch Accelerate and lift off nose gear as soon as possible Lift off at lowest possible airspeed Accelerate just above ground to 52 KIAS to climb past obstacle height Continue climbing while accelerating to best rate of climb speed 79 KIAS Flaps slowly retract SOFT FIELD NO OBSTACLE Flaps 25 second notch Accelerate and lift off nose...

Page 59: ... max Air conditioner OFF Trim to 70 KIAS Final approach speed flaps 40 63 KIAS STOPPING ENGINE Flaps retract Electric fuel pump OFF Air conditioner OFF Radios OFF Throttle full aft Mixture idle cut off Magnetos OFF Master switch OFF PARKING Parking brake set Control wheel secured with belts Flaps full up Wheel chocks in place Tie downs secure REPORT VB 880 ISSUED DECEMBER 16 1976 4 6 REVISED NOVEM...

Page 60: ...d now be made Turn the master switch ON Lift the detector while checking to determine if the horn is actuated and check that the navigation lights are illuminated The master switch should be returned to the OFF position after the checks are complete A visual check of the fuel tank quantity should be performed Remove the filler cap from each tank and visually check the supply and color Be sure to s...

Page 61: ...r storage and security The baggage compartment doors should be closed and secure Upon entering the aircraft ascertain that all prirnary flight controls operate properly Close and secure the cabin door and check that all the required papers are in order and in the airplane Fasten the seat belts and shoulder harness and check the function of the inertia reel by pulling sharply on the strap Fasten se...

Page 62: ...ottle d Starting Engine With External Power Source An optional feature called the Piper External Power PEP allows the operator to use an external battery to crank the engine without having to gain access to the airplane s battery Turn the master switch OFF and turn all electrical equipment OFF Connect the RED lead of the PEP kit jumper cable to the POSITIVE terminal of an external 12 volt battery ...

Page 63: ...M If oil pressure is not indicated within thirty seconds stop the engine and determine the trouble In cold weather it will take a few seconds longer to get an oil pressure indication If the engine has failed to start refer to the Lycoming Operating Handbook Engine Troubles and Their Remedies Starter manufacturers recommend that cranking periods be limited to thirty seconds with a two minute rest b...

Page 64: ...ning up or taxiing over ground containing loose stones gravel or any loose material that may cause damage to the propeller blades 4 19 GROUND CHECK The magnetos should be checked at 2000 RPM Drop off on either magneto should not exceed 175 RPM and the difference between the magnetos should not exceed 50 RPM Operation on one magneto should not exceed 10 seconds Check the vacuum gauge the indicator ...

Page 65: ...the flaps and trim tab Insure proper flight control movement and response All doors should be properly secured and latched On air conditioned models the air conditioner must be OFF to insure normal takeoff performance 4 23 TAKEOFF The normal takeoff technique is conventional The tab should be set slightly aft of neutral with the exact setting determined by the loading of the airplane Allow the air...

Page 66: ...ment installed in the airplane The normal maximum cruising power is 75 of the rated horsepower of the engine Airspeeds which may be obtained at various altitudes and power settings can be determined from the performance graphs provided by Section 5 Use of the mixture control in cruising flight reduces fuel consumption significantly especially at higher altitudes and reduces lead deposits when the ...

Page 67: ...y every 30 seconds by partially opening and then closing the throttle clearing the engine When leveling off enrichen mixture set power as required and select carburetor heat off unless carburetor icing conditions are suspected 4 29 APPROACH AND LANDING Check to insure the fuel selector is on the proper fullest tank and that the seat backs are erect The seat belts and shoulder harness should be fas...

Page 68: ...itions particularly in strong crosswinds it may be desirable to approach the ground at higher than normal speeds with partial or no flaps 4 31 STOPPING ENGINE At the pilot s discretion the flaps should be raised and the electric fuel pump turned OFF The air conditioner and radios should be turned OFF and the engine stopped by disengaging the friction adjustment lever and pulling the mixture contro...

Page 69: ...The master switch should be returned to the OFF position after the check is complete 4 37 TURBULENT AIR OPERATION In keeping with good operating practice used in all aircraft it is recommended that when turbulent air is encountered or expected the airspeed be reduced to maneuvering speed to reduce the structural loads caused by gusts and to allow for inadvertent speed build ups which may occur as ...

Page 70: ...NTS SECTION 5 PERFORMANCE Paragraph Page No No 5 1 General 5 1 5 3 Introduction to Performance and Flight Planning 5 1 5 5 Flight Planning Example 5 3 5 7 Performance Graphs 5 9 List of Figures 5 9 REPORT VB 880 5 i ...

Page 71: ...cy or mechanical deterioration of the aircraft This performance however can be duplicated by following the stated procedures in a properly maintained airplane Effects of conditions not considered on the charts must be evaluated by the pilot such as the effect of soft or grass runway surface on takeoff and landing performance or the effect of winds aloft on cruise and range performance Endurance ca...

Page 72: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 5 2 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 73: ...lished refer to item g 1 1 Basic Empty Weight 1391 lbs 2 Occupants 4 x 170 lbs 680 lbs 3 Baggage and Cargo 50 lbs 4 Fuel 6 lb gal x 30 180 lbs 5 Takeoff Weight 2316 lbs 6 Landing Weight a 5 minus g 1 2316 lbs minus 134 4 lbs 2181 6 lbs Our takeoff weight is below the maximum of 2325 lbs and our weight and balance calculations have determined our C G position within the approved limits b Takeoff an...

Page 74: ...e climb components from the Time Distance and Fuel to Climb graph Figure 5 13 After the time distance and fuel for the cruise pressure altitude and outside air temperature values have been established apply the existing conditions at the departure field to graph Figure 5 13 Now subtract the values obtained from the graph for the field of departure conditions from those for the cruise pressure alti...

Page 75: ...imb and distance to descend to establish the total cruise distance Refer to the appropriate Avco Lycoming Operator s Manual when selecting the cruise power setting The established pressure altitude and temperature values and the selected cruise power should now be utilized to determine the true airspeed from the Cruise Performance graph Figures 5 15 through 5 18 Calculate the cruise fuel consumpti...

Page 76: ... 40 hrs 2 58 hrs g Total Fuel Required Determine the total fuel required by adding the fuel to climb the fuel to descend and the cruise fuel When the total fuel in gallons is determined multiply this value by 6 lb gal to determine the total fuel weight used for the flight The total fuel calculations for our example flight plan are shown below 1 Total Fuel Required c 5 plus d 3 plus e 7 1 5 gal plu...

Page 77: ...THIS PAGE INTENTIONALLY LEFT BLANK ISSUED DECEMBER 16 1976 REPORT VB 880 5 7 PIPER AIRCRAFT CORPORATION SECTION 5 PA 28 161 CHEROKEE WARRIOR II PERFORMANCE ...

Page 78: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 5 8 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 79: ...28 7716001 through 7716323 5 21 5 16 Best Power Cruise Performance Serial Nos 28 7816001 and up 5 22 5 17 Best Economy Cruise Performance Serial Nos 28 7716001 through 7716323 5 23 5 18 Best Economy Cruise Performance Serial Nos 28 7816001 and up 5 24 5 19 Best Power Mixture Range Serial Nos 28 7716001 through 7716323 5 25 5 20 Best Power Mixture Range Serial Nos 28 7816001 and up 5 26 5 21 Best E...

Page 80: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 5 10 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 81: ...AIRSPEED SYSTEM CALIBRATION Figure 5 1 ISSUED DECEMBER 16 1976 REPORT VB 880 5 11 PIPER AIRCRAFT CORPORATION SECTION 5 PA 28 161 CHEROKEE WARRIOR II PERFORMANCE ...

Page 82: ...ht 2170 lbs Angle of bank 20 Flap position 40 Stall speed indicated 44 KTS STALL SPEED Figure 5 3 REPORT VB 880 ISSUED DECEMBER 16 1976 5 12 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 83: ...F Weight 2325 lbs Wind 15 KTS headwind Ground roll 1150 ft Lift off speed 50 KIAS NORMAL SHORT FIELD GROUND ROLL DISTANCE NO OBSTACLE Figure 5 5 ISSUED DECEMBER 16 1976 REPORT VB 880 REVISED JULY 11 1977 5 13 PIPER AIRCRAFT CORPORATION SECTION 5 PA 28 161 CHEROKEE WARRIOR II PERFORMANCE ...

Page 84: ... Wind 15 KTS headwind Distance over 50 ft barrier 2100 ft Lift off speed 50 KIAS Barrier speed 55 KIAS NORMAL SHORT FIELD TAKEOFF DISTANCE NO OBSTACLE Figure 5 6 REPORT VB 880 ISSUED DECEMBER 16 1976 5 14 REVISED JULY 11 1977 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 85: ...F Weight 2175 lbs Wind 15 KTS headwind Ground roll 975 ft Lift off speed 48 KIAS OBSTACLE CLEARANCE SHORT FIELD GROUND ROLL DISTANCE Figure 5 7 ISSUED DECEMBER 16 1976 REPORT VB 880 REVISED JULY 11 1977 5 15 PIPER AIRCRAFT CORPORATION SECTION 5 PA 28 161 CHEROKEE WARRIOR II PERFORMANCE ...

Page 86: ... Wind 15 KTS headwind Distance over 50 ft barrier 1600 ft Lift off speed 48 KIAS Barrier speed 53 KIAS OBSTACLE CLEARANCE SHORT FIELD TAKEOFF DISTANCE Figure 5 8 REPORT VB 880 ISSUED DECEMBER 16 1976 5 16 REVISED JULY 11 1977 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 87: ...AT 60 F Cruise power 75 Engine RPM 2645 ENGINE PERFORMANCE SERIAL NOS 28 7716001 THROUGH 7716323 Figure 5 9 ISSUED DECEMBER 16 1976 REPORT VB 880 REVISED JULY 11 1977 5 17 PIPER AIRCRAFT CORPORATION SECTION 5 PA 28 161 CHEROKEE WARRIOR II PERFORMANCE ...

Page 88: ...se OAT 60 F Cruise power 75 Engine RPM 2620 ENGINE PERFORMANCE SERIAL NOS 28 7816001 AND UP Figure 5 10 REPORT VB 880 ISSUED DECEMBER 16 1976 5 18 REVISED JULY 11 1977 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 89: ...N SECTION 5 PA 28 161 CHEROKEE WARRIOR II PERFORMANCE Example Climb pressure altitude 5000 ft Climb OAT 60 F Rate of climb 420 ft min CLIMB PERFORMANCE Figure 5 11 ISSUED DECEMBER 16 1976 REPORT VB 880 REVISED JUNE 30 1978 5 19 ...

Page 90: ... F 16 C Time to climb 10 min minus 2 5 min 7 5 min Distance to climb 13 5 miles minus 3 5 miles 10 nautical miles Fuel to climb 2 gal minus 5 gal 1 5 gal FUEL TIME AND DISTANCE TO CLIMB Figure 5 13 REPORT VB 880 ISSUED DECEMBER 16 1976 5 20 REVISED JULY 3 1979 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 91: ...FORMANCE Example Cruise pressure altitude 5000 ft Cruise OAT 60 F Cruise power 75 best power mixture Cruise speed 116 5 KTS TAS BEST POWER CRUISE PERFORMANCE SERIAL NOS 28 7716001 THROUGH 7716323 Figure 5 15 ISSUED DECEMBER 16 1976 REPORT VB 880 REVISED JULY 11 1977 5 21 ...

Page 92: ...ower 75 best power mixture Cruise speed 122 5 KTS TAS BEST POWER CRUISE PERFORMANCE SERIAL NOS 28 7816001 AND UP Figure 5 16 REPORT VB 880 ISSUED DECEMBER 16 1976 5 22 REVISED JULY 11 1977 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 93: ... best economy mixture Cruise speed 112 5 KTS TAS BEST ECONOMY CRUISE PERFORMANCE SERIAL NOS 28 7716001 THROUGH 7716323 Figure 5 17 ISSUED DECEMBER 16 1976 REPORT VB 880 REVISED JULY 11 1977 5 23 PIPER AIRCRAFT CORPORATION SECTION 5 PA 28 161 CHEROKEE WARRIOR II PERFORMANCE ...

Page 94: ...ower 75 best power mixture Cruise speed 118 KTS TAS BEST ECONOMY CRUISE PERFORMANCE SERIAL NOS 28 7816001 AND UP Figure 5 18 REPORT VB 880 ISSUED DECEMBER 16 1976 5 24 REVISED JULY 11 1977 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 95: ...5 min reserve 55 power 476 6 x 11 482 6 nautical miles Range w no reserve 533 6 x 11 539 6 nautical miles BEST POWER MIXTURE RANGE SERIAL NOS 28 7716001 THROUGH 7716323 Figure 5 19 ISSUED DECEMBER 16 1976 REPORT VB 880 REVISED JULY 3 1979 5 25 PIPER AIRCRAFT CORPORATION SECTION 5 PA 28 161 CHEROKEE WARRIOR II PERFORMANCE ...

Page 96: ...e w 45 min reserve 55 power 501 6 x 11 507 6 nautical miles Range w no reserve 561 6 x 11 567 6 nautical miles BEST POWER MIXTURE RANGE SERIAL NOS 28 7816001 AND UP Figure 5 20 REPORT VB 880 ISSUED DECEMBER 16 1976 5 26 REVISED MAY 30 1980 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 97: ... 45 min reserve 55 power 540 7 x 11 547 7 nautical miles Range w no reserve 602 7 x 11 609 7 nautical miles BEST ECONOMY MIXTURE RANGE SERIAL NOS 28 7716001 THROUGH 7716323 Figure 5 21 ISSUED JULY 11 1977 REPORT VB 880 REVISED JULY 3 1979 5 27 PIPER AIRCRAFT CORPORATION SECTION 5 PA 28 161 CHEROKEE WARRIOR II PERFORMANCE ...

Page 98: ...nge w 45 min reserve 55 power 567 7 x 11 574 7 nautical miles Range w no reserve 635 7 x 11 642 7 nautical miles BEST ECONOMY MIXTURE RANGE SERIAL NOS 28 7816001 AND UP Figure 5 22 REPORT VB 880 ISSUED JULY 11 1977 5 28 REVISED JULY 3 1979 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 99: ... best economy mixture Endurance w 45 min reserve 55 power 4 85 hrs Endurance w no reserve 5 45 hrs ENDURANCE Figure 5 23 ISSUED JULY 11 1977 REPORT VB 880 REVISED JULY 3 1979 5 29 PIPER AIRCRAFT CORPORATION SECTION 5 PA 28 161 CHEROKEE WARRIOR II PERFORMANCE ...

Page 100: ...60 F 16 C Time to descend 6 5 min minus 3 5 min 3 min Distance to descend 14 miles minus 7 5 miles 6 5 nautical miles Fuel to descend 1 gal minus 5 gal 5 gal FUEL TIME AND DISTANCE TO DESCEND Figure 5 25 REPORT VB 880 ISSUED JULY 11 1977 5 30 REVISED JULY 3 1979 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 101: ...ressure altitude 2000 ft Glide distance 9 5 miles minus 3 8 miles 5 7 nautical miles GLIDE PERFORMANCE Figure 5 27 ISSUED JULY 11 1977 REPORT VB 880 REVISED JULY 3 1979 5 31 PIPER AIRCRAFT CORPORATION SECTION 5 PA 28 161 CHEROKEE WARRIOR II PERFORMANCE ...

Page 102: ...ion airport temperature 75 F Destination airport wind 0 KTS Ground roll 660 ft Distance over 50 ft barrier 1190 ft LANDING PERFORMANCE Figure 5 29 REPORT VB 880 ISSUED JULY 11 1977 5 32 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 103: ...Accessories 6 19 c Landing Gear and Brakes 6 21 d Electrical Equipment 6 23 e Instruments 6 25 f Miscellaneous 6 27 g Engine and Engine Accessories Optional Equipment 6 29 h Propeller and Propeller Accessories Optional Equipment 6 31 i Landing Gear and Brakes Optional Equipment 6 33 j Electrical Equipment Optional Equipment 6 35 k Instruments Optional Equipment 6 37 i Autopilots Optional Equipment...

Page 104: ...ly loaded airplane however will perform as intended Before the airplane is delivered it is weighed and a basic empty weight and C G location is computed basic empty weight consists of the standard empty weight of the airplane plus the optional equipment Using the basic empty weight and C G location the pilot can easily determine the weight and C G position for the loaded airplane by computing the ...

Page 105: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 6 2 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 106: ...nd engine stops Then add the unusable fuel 2 0 gallons total 1 0 gallons each wing CAUTION Whenever the fuel system is completely drained and fuel is re plenished it will be necessary to run the engine for a minimum of three minutes at 1000 RPM on each tank to insure no air exists in the fuel supply lines 4 Fill with oil to full capacity 5 Place pilot and copilot seats in fourth 4th notch aft of f...

Page 107: ...s Weighed T WEIGHING FORM Figure 6 1 d Basic Empty Weight Center of Gravity 1 The following geometry applies to the PA 28 161 airplane when it is level Refer to Leveling paragraph 6 3 b The datum is 78 4 inches ahead of the wing leading edge at the intersection of the straight and A 30 9 tapered section B 109 7 LEVELING DIAGRAM Figure 6 3 REPORT VB 880 ISSUED DECEMBER 16 1976 6 4 REVISED FEBRUARY ...

Page 108: ...ding optional equipment full oil and unusable fuel can be determined by the following formula C G Arm N A R L B inches T Where T N R L ISSUED DECEMBER 16 1976 REPORT VB 880 6 5 PIPER AIRCRAFT CORPORATION SECTION 6 PA 28 161 CHEROKEE WARRIOR II WEIGHT AND BALANCE ...

Page 109: ...plane as delivered from the factory has been entered in the Weight and Balance Record Figure 6 7 This form is provided to present the current status of the airplane basic empty weight and a complete history of previous modifications Any change to the permanently installed equipment or modification which affects weight or moment must be entered in the Weight and Balance Record REPORT VB 880 ISSUED ...

Page 110: ...uel AIRPLANE USEFUL LOAD NORMAL CATEGORY OPERATION Gross Weight Basic Empty Weight Useful Load Normal Category 2325 lbs lbs lbs Utility Category 2020 lbs lbs lbs THIS BASIC EMPTY WEIGHT C G AND USEFUL LOAD ARE FOR THE AIRPLANE AS LICENSED AT THE FACTORY REFER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE WEIGHT AND BALANCE DATA FORM Figure 6 5 ISSUED DECEMBER 16 1976 REPORT VB 880...

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Page 112: ...8 7916159 N3067D 3 13 79 10 19 80 10 22 81 2 21 82 6 6 86 10 18 93 8 28 03 11 2 05 1 6 20 5 6 20 X X X X X X ELT Removal ELT install and collins SB 1 IFR avionics package installation Piper SB 631B kit installation KN64 DME installation Nose fairing removal Avionics retrofit Transponder swap TDR950 to KT76C Transponder swap KT76C to NGT9000 Avionics retrofit 1 7 236 2 402 1462 4 126168 3 5 236 2 8...

Page 113: ...A 28 161 CHEROKEE WARRIOR II PA 28 161 Serial Number Registration Number Page Number Item No Weight Change Running Basic Added Removed Empty Weight Date Description of Article or Modification In Out Wt Arm Moment Wt Arm Moment Wt Moment Lb In 100 Lb In 100 Lb 100 As Delivered WEIGHT AND BALANCE RECORD cont Figure 6 7 cont ...

Page 114: ... Weight Pilot and Front Passenger 340 0 80 5 27370 Passengers Rear Seats 340 0 118 1 40154 Fuel 48 Gallon Maximum 95 0 Baggage 200 Lbs Maximum 142 8 Total Loaded Airplane The center of gravity C G of this sample loading problem is at inches aft of the datum line Locate this point on the C G range and weight graph Since this point falls within the weight C G envelope this loading meets the weight a...

Page 115: ...owner and the pilot to insure that the airplane is loaded properly The Basic Empty Weight C G is noted on the Weight and Balance Data Form Figure 6 5 If the airplane has been altered refer to the Weight and Balance Record for this information Utility Category Operation No baggage or aft passengers allowed WEIGHT AND BALANCE LOADING FORM Figure 6 11 REPORT VB 880 ISSUED DECEMBER 16 1976 6 12 REVISE...

Page 116: ...LOADING GRAPH Figure 6 13 ISSUED DECEMBER 16 1976 REPORT VB 880 6 13 PIPER AIRCRAFT CORPORATION SECTION 6 PA 28 161 CHEROKEE WARRIOR II WEIGHT AND BALANCE ...

Page 117: ...C G RANGE AND WEIGHT Figure 6 15 REPORT VB 880 ISSUED DECEMBER 16 1976 6 14 REVISED MAY 30 1980 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 118: ...To use it first plot a point on the grid to locate the basic weight and C G location This can be put on more or less permanently because it will not change until the airplane is modified Next position the zero weight end of any one of the loading slots over this point Using a pencil draw a line along the slot to the weight which will be carried in that location Then position the zero weight end of...

Page 119: ...SAMPLE PROBLEM REPORT VB 880 ISSUED DECEMBER 16 1976 6 16 REVISED MAY 30 1980 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 120: ...85 00 inches to represent the basic airplane See illustration b Slide the slotted plastic into position so that the dot is under the slot for the forward seats at zero weight c Draw a line up the slot to the 380 pound position 180 200 and put a dot d Continue moving the plastic and plotting points to account for weight in the rear seats 80 100 baggage compartment 45 and fuel tanks 288 e As can be ...

Page 121: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED MAY 30 1980 6 16b SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 122: ... unless replaced by an optional equivalent item C denotes an optional item which replaces a required item of standard equipment Where no letter precedes an item that item is not required equipment Unless otherwise indicated the installation certification basis for the equipment included in this list is the aircraft s approved type design PIPER AIRCRAFT CORPORATION PA 28 161 WARRIOR II SERIAL NO __...

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Page 124: ...mp Bendix P N 478360 1 8 36 8 66 11 A Fuel Valve Piper Dwg 66945 or Allen Aircraft Prod Inc No 6S122 ______ 0 4 61 9 25 12 A Oil Coolers Piper Dwg 18622 Harrison No C8526250 1 9 41 3 78 13 A Air Filter Piper Dwg 35477 0 9 29 5 27 14 A Starter Prestolite MZ4218 Cert Basis TC E274 17 0 14 5 247 15 A Oil Filter LW 13743 Champion No CH48110 or Lyc No 75528 AC No OF5578770 Cert Basis TC E274 2 5 35 3 8...

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Page 126: ...o D 30500 Cert Basis TSO C26b ______ 3 6 30 8 111 c 5 00 5 Type III 4 Ply Rating Tire with Regular Tube Cert Basis TSO C62 ______ 5 8 30 8 179 18 A Hand Brake Master Cylinder Piper Dwg 65842 Cleveland Aircraft Products P N 10 22 ______ 0 6 60 9 37 19 A Toe Brake Cylinders a Cleveland Aircraft Products No 10 27 ______ 0 7 53 0 37 b Gar Kenyon Instrument No 17000 ______ 0 4 53 0 21 Item Mark if Weig...

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Page 128: ... Relay Piper Dwg 35544 Wico X16799 0 5 55 4 28 24 A Stall Warning Device Piper Dwg 35544 Safe Flight P N C52207 4 0 2 80 2 16 25 A Stall Warning Horn Piper Dwg 35544 Safe Flight P N 35214 ______ 0 2 58 8 12 Item Mark if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In ISSUED DECEMBER 16 1976 REPORT VB 880 REVISED DECEMBER 18 1980 6 23 PIPER AIRCRAFT CORPORATION SECTION 6 PA 28 161 CHEROKE...

Page 129: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 6 24 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 130: ... Compass Piper Dwg 67462 Cert Basis TSO C7c 0 9 59 9 54 29 A Tachometer Piper Dwg 62177 3 0 7 61 2 43 30 A Engine Cluster Piper Dwg 95241 17 0 8 62 4 50 Item Mark if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In ISSUED DECEMBER 16 1976 REPORT V 880 REVISED DECEMBER 18 1980 6 25 PIPER AIRCRAFT CORPORATION SECTION 6 PA 28 161 CHEROKEE WARRIOR II WEIGHT AND BALANCE ...

Page 131: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 6 26 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 132: ...______ 15 5 84 0 1302 38 Rear Seat Piper Dwg 35131 27 0 124 1 3351 39 A a Shoulder Harness 2 Front Seats Only Piper PS50039 4 20 Pacific Scientific P N 110747 13 ______ 1 4 119 5 167 B b Shoulder Harness Fixed Front 2 Piper Dwg PS50039 4 23 American Safety Eqpt Corp 501385 407 Davis Acft Prod Inc FDC 7275 16 4 Black ______ 1 1 119 5 131 40 A Baggage Straps Piper Dwg 66804 and 66805 1 3 142 8 186 I...

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Page 134: ...1 2 50 0 60 47 Carburetor Ice Detector Piper Dwg 39684 2 ______ 0 5 59 7 30 Item Mark if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In ISSUED DECEMBER 16 1976 REPORT VB 880 REVISED MAY 30 1980 6 29 PIPER AIRCRAFT CORPORATION SECTION 6 PA 28 161 CHEROKEE WARRIOR II WEIGHT AND BALANCE ...

Page 135: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 6 30 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 136: ...ccessories Optional Equipment Item Mark if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In ISSUED DECEMBER 16 1976 REPORT VB 880 6 31 PIPER AIRCRAFT CORPORATION SECTION 6 PA 28 161 CHEROKEE WARRIOR II WEIGHT AND BALANCE ...

Page 137: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 6 32 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 138: ...6 3 374 69 Main Wheel Fairings Piper Dwg 37885 2 3 ______ 20 6 113 6 2340 71 Nose Wheel Fairing Piper Dwg 37896 2 ______ 3 5 36 3 127 73 Main Wheel Fairings Piper Dwg 79893 2 3 ______ 17 0 113 6 1931 Item Mark if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In ISSUED DECEMBER 16 1976 REPORT VB 880 REVISED MAY 30 1980 6 33 PIPER AIRCRAFT CORPORATION SECTION 6 PA 28 161 CHEROKEE WARRIOR II...

Page 139: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 6 34 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 140: ...______ 0 5 106 6 53 90 Navigation Lights Wing 2 Red White Green White with White Strobe Wing Whelen Model A600 ______ 5 8 157 9 916 Fin Strobe A 470 ______ 1 1 216 0 238 91 Navigation Lights Wing 2 Red White Green White with Red Strobe Wing ______ 5 8 157 9 916 Fin Strobe A 470 ______ 1 1 216 0 238 92 Rotating Beacon Whelen Eng Co WRMI 12 Piper Dwg 63892 or 63518 ______ 1 5 263 4 395 93 Anti Colli...

Page 141: ...C Battery 12V 35 A H Rebat R35 Wt 27 2 lbs ______ 5 3 114 9 609 103 Auxiliary Power Receptacle Piper Dwg 35298 ______ 2 7 178 5 482 105 External Power Cable Piper Dwg 62355 11 ______ 4 6 142 8 657 107 Lighter 200462 12 Volt Universal ______ 0 2 62 9 13 Weight and moment difference between standard and optional equipment Item Mark if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In REPORT ...

Page 142: ... PS50008 6 or 7 Cert Basis TSO C10b C88 ______ 0 9 60 3 54 122 Altitude Digitizer United Instruments P N 5125 P3 Cert Basis TSO C88 ______ 1 0 51 5 52 123 Vertical Speed Piper Dwg 99010 2 4 or 5 Cert Basis TSO C8b ______ 1 0 60 9 61 125 Alternate Static Source Piper Dwg 35493 ______ 0 4 61 0 24 127 Turn and Slip Indicator Piper PS50030 2 or 3 Cert Basis TSO C3b ______ 2 6 59 7 155 Weight and momen...

Page 143: ...eel Digital Clock Piper Dwg 87347 3 ______ 0 3 71 9 22 133 Air Temperature Gauge Piper Dwg 99479 0 or 2 ______ 0 2 72 6 15 Item Mark if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In REPORT VB 880 ISSUED DECEMBER 16 1976 6 38 REVISED JUNE 29 1981 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 144: ... 388 ______ 1 0 59 3 59 Piper Dwg 79221 Cert Basis STC SA3065SW D 145 AutoPilot Century 21 Piper Dwg 39726 Cert Basis STC SA3352SW ______ 12 0 69 0 828 Item Mark if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In ISSUED DECEMBER 16 1976 REPORT VB 880 REVISED MAY 30 1980 6 39 PIPER AIRCRAFT CORPORATION SECTION 6 PA 28 161 CHEROKEE WARRIOR II WEIGHT AND BALANCE ...

Page 145: ..._____ 6 0 105 0 630 156 Bendix TR2060 Transponder ______ 2 8 63 6 178 Cert Basis TSO C74c 157 Bendix CN2011 Dual Com Nav Cert Basis TSO C34c C35d C36c C37b C40a ______ 16 8 66 8 1122 158 Bendix IN2014B Indicator a Single ______ 1 9 63 4 121 b Dual ______ 3 8 63 4 241 Cert Basis TSO C34c C 36c C40a C66c 159 Bendix DME 2030 Cert Basis TSO C66a ______ 10 3 185 0 1906 Weight includes antenna and cable...

Page 146: ...r Cert Basis TSO C40a C36c ______ 1 3 60 2 78 165 Collins GLS 350 Glide Slope Receiver Cert Basis TSO C34c ______ 2 0 183 4 367 167 Collins DCE 400 Distance Computing Equipment Cert Basis TSO C40a ______ 2 1 58 9 124 168 Collins RCR 650 ADF Receiver and Antenna and IND 650 Indicator Cert Basis TSO C41c ______ 6 6 104 8 692 169 Collins RCR 650A ADF Receiver and Antenna and IND 650A Indicator Cert B...

Page 147: ...198 b Dual ______ 6 2 63 8 396 175 King KX 155 VHF Nav Comm Transceiver a With Audio Amplifier ______ 5 0 58 1 291 b With Glide Slope Receiver ______ 5 3 58 1 308 c Without Glide Slope Receiver ______ 4 8 58 1 279 Cert Basis TSO C37b C38b C40a C36a 176 King KX 165 VHF Nav Comm Transceiver a With Glide Slope Receiver ______ 5 7 58 0 331 b Without Glide Slope Receiver ______ 5 1 58 1 296 Cert Basis ...

Page 148: ..._ 4 2 183 6 771 d King KI 203 VOR ILS Indicator ______ 1 6 60 5 97 e King KNI 520 VOR ILS Indicator ______ 1 7 60 5 103 Cert Basis TSO C36c C37b C38b C40a 180 King KY 196E Transceiver with RB 125 Power Booster a Single ________ 5 7 77 0 439 b Dual ________ 11 4 77 0 878 Cert Basis TSO C37b C38b 181 King KY 197 Transceiver a Single ________ 4 2 58 7 246 b Dual ________ 8 4 58 7 492 Cert Basis TSO C...

Page 149: ...ng KN 62A DME ______ 3 3 58 3 193 193 King KN 65A DME Cert Basis TSO C66a ______ 13 0 174 9 2274 194 King KRA 10 Radio Altimeter ______ 4 3 162 6 699 195 King KR 85 Digital ADF ______ 8 6 85 2 733 a Audio Amplifier ______ 0 8 51 0 41 Cert Basis TSO C41b 196 King KR 85 ADF with KA 42B Loop and Sense Antenna ______ 9 5 85 2 809 a Audio Amplifier ______ 0 8 51 0 41 Cert Basis TSO C41b 197 King KR 86 ...

Page 150: ...__ 3 7 70 8 262 201 King KMA 24 Audio Panel ______ 1 7 65 3 111 Cert Basis TSO C35d C50b 203 King KT 76 78 Transponder Cert Basis TSO C74b ______ 3 1 58 1 180 204 Narco Comm 10A VHF Transceiver ______ 3 9 57 4 224 205 Narco Comm 11A VHF Transceiver a Single ______ 3 6 57 4 207 b Dual ______ 7 1 57 4 408 207 Narco Comm 11B VHF Transceiver a Single ______ 3 9 57 4 224 b Dual ______ 7 8 57 4 448 Weig...

Page 151: ...eiver a Single ______ 2 8 58 6 164 b Dual ______ 5 6 58 6 328 219 Narco Nav 12 VHF Receiver ______ 3 4 58 6 199 221 Narco Nav 14 VHF Receiver ______ 2 5 57 4 144 223 Narco Nav 111 Cert Basis TSO C36c C40a C66a ______ 2 5 58 6 147 225 Narco Nav 112 Receiver Cert Basis TSO C36c C40a C66c C34c ______ 3 3 58 6 193 227 Narco Nav 114 VHF Receiver Cert Basis TSO C38b C40a C36c C34c C66a ______ 2 5 57 4 1...

Page 152: ...1 Cert Basis TSO C35d C36c C40a C66a 237 Narco ID 124 VOR LOC GS Indicator a Single ______ 1 2 60 5 73 b Dual ______ 2 4 60 5 145 Cert Basis TSO C34c C35d C36c C40c 239 Narco UGR 2A Glide Slope a Single ______ 4 2 154 0 647 b Dual ______ 8 4 220 0 1848 Cert Basis TSO C34b 241 Narco UGR 3 Glide Slope ______ 4 2 154 0 647 243 Narco MBT 12 R Marker Beacon ______ 3 1 69 1 214 245 Narco CP 125 Audio Se...

Page 153: ...F 141 a Single ______ 6 0 91 2 547 b Dual ______ 17 9 107 6 1926 Cert Basis TSO C41c 261 Narco AT50A Transponder Cert Basis TSO C74b ______ 3 0 57 3 172 a Narco AR 500 Altitude Encoder Cert Basis TSO C88 ______ 1 0 51 5 52 263 Narco AT150 Transponder Cert Basis TSO C74c ______ 3 0 57 3 172 a Narco AR 500 Altitude Encoder Cert Basis TSO C88 ______ 1 0 51 5 52 Weight includes marker antenna and cabl...

Page 154: ...luded as part of marker beacon installation 277 Marker Beacon Antenna Comant CI 102 Piper Dwg 39737 4 ______ 1 2 175 0 210 278 Emergency Locator Transmitter C C C Model CIR 11 2 ______ 1 7 236 2 402 a Antenna and Coax ______ 0 2 224 4 45 b Shelf and Access Hole ______ 0 5 235 4 118 Cert Basis TSO C91 279 Emergency Locator Transmitter Narco Model ELT 10 ______ 3 5 236 2 827 a Antenna and Coax _____...

Page 155: ... Speaker Piper Dwg 99220 ______ 1 1 99 0 109 285 Headset Piper Dwg 68856 10 ______ 0 5 60 0 30 Item Mark if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In REPORT VB 880 ISSUED DECEMBER 16 1976 6 50 REVISED DECEMBER 18 1980 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 156: ...THIS PAGE INTENTIONALLY LEFT BLANK ISSUED DECEMBER 16 1976 REPORT VB 880 6 51 PIPER AIRCRAFT CORPORATION SECTION 6 PA 28 161 CHEROKEE WARRIOR II WEIGHT AND BALANCE ...

Page 157: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 6 52 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 158: ...ist Step Piper Dwg 65384 ______ 1 8 156 0 281 335 Super Cabin Sound Proofing Piper Dwg 79030 2 ______ 18 1 86 8 1571 337 C Adjustable Front Seat Left Piper Dwg 79591 0 79591 2 ______ 6 6 80 3 530 339 Adjustable Front Seat Right Piper Dwg 79591 1 79591 3 ______ 6 6 79 6 525 341 Headrests 2 Front Piper Dwg 79337 18 ______ 2 2 94 5 208 342 Shoulder Harness Inertia Front 2 Piper Dwg PS50039 4 20 Pacif...

Page 159: ...8 347 Assist Strap Piper Dwg 79455 ______ 0 2 109 5 22 349 Curtain and Rod Installation Piper Dwg 67955 2 ______ 4 2 124 0 521 351 Luxurious Interior Piper Dwg 67952 4 ______ 14 5 98 3 1425 352 Deluxe Carpeting Piper Dwg 66801 ______ 2 6 97 8 254 355 Fire Extinguisher a Piper Dwg 76167 2 Scott 42211 00 ______ 4 6 71 0 327 b Piper Dwg 37872 2 Graviner HA 1014 01 ______ 5 6 57 9 324 357 Tow Bar Pipe...

Page 160: ...between standard and optional equipment TOTAL OPTIONAL EQUIPMENT ______ ______ ______ Item Mark if Weight Arm In Moment No Item Instl Pounds Aft Datum Lb In ISSUED DECEMBER 16 1976 REPORT VB 880 REVISED NOVEMBER 20 1981 6 55 PIPER AIRCRAFT CORPORATION SECTION 6 PA 28 161 CHEROKEE WARRIOR II WEIGHT AND BALANCE 124 1 97 6 12108 ...

Page 161: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 6 56 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA 28 161 CHEROKEE WARRIOR II ...

Page 162: ...Controls 7 8 7 13 Fuel System 7 10 7 15 Electrical System 7 12 7 17 Vacuum System 7 15 7 19 Instrument Panel 7 16 7 21 Pitot Static System 7 18 7 23 Heating and Ventilating System 7 21 7 25 Cabin Features 7 21 7 27 Baggage Area 7 22 7 29 Stall Warning 7 22 7 31 Finish 7 22 7 33 Piper External Power 7 23 7 35 Emergency Locator Transmitter 7 23 7 37 Air Conditioning 7 25 7 39 Carburetor Ice Dectecti...

Page 163: ...etc and in nonstructural components throughout the airplane The fuselage is a conventional semi monocoque structure On the right side of the airplane is a cabin door for entrance and exit and a baggage door to provide loading into the 24 cubic foot compartment The wing is a conventional semi tapered design incorporating a laminar flow NACA 652415 airfoil section The cantilever wings are attached t...

Page 164: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 7 2 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA 28 161 CHEROKEE WARRIOR II ...

Page 165: ...on the left side for the oil cooler A winterization plate is provided to restrict air during winter operation refer to paragraph 8 29 Engine air enters on either side of the propeller through openings in a nose cowling and is carried through the engine baffling around the engine and oil cooler Air for the muffler shroud is also picked up from the nose cowling and carried through a duct to the shro...

Page 166: ...MAIN WHEEL ASSEMBLY Figure 7 1 REPORT VB 880 ISSUED DECEMBER 16 1976 7 4 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA 28 161 CHEROKEE WARRIOR II ...

Page 167: ...mechanism also incorporates a shimmy dampener The three struts are of the air oil type with the normal static load extension being 3 25 inches for the nose gear and 4 50 inches for the main gear The brakes are actuated by toe brake pedals which are attached to the rudder pedals or by a hand lever and master cylinder located below and behind the center of the instrument sub panel Hydraulic cylinder...

Page 168: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 7 6 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA 28 161 CHEROKEE WARRIOR II ...

Page 169: ...cated on the control console between the front seats Figure 7 3 Forward rotation of the wheel gives nose down trim and aft rotation gives nose up trim The rudder is conventional in design and incorporates a rudder trim The trim mechanism is a spring loaded recentering device The trim control is located on the right side of the pedestal below the throttle quadrant refer to Figure 7 5 Turning the tr...

Page 170: ... Engine controls consist of a throttle control and a mixture control lever These controls are located on the control quadrant on the lower center of the instrument panel Figure 7 5 where they are accessible to both the pilot and the copilot The controls utilize teflon lined control cables to reduce friction and binding The throttle lever is used to adjust engine RPM The mixture control lever is us...

Page 171: ...CONTROL QUADRANT AND CONSOLE Figure 7 5 ISSUED DECEMBER 16 1976 REPORT VB 880 7 9 PIPER AIRCRAFT CORPORATION SECTION 7 PA 28 161 CHEROKEE WARRIOR II DESCRIPTION AND OPERATION ...

Page 172: ...ON position An auxiliary electric fuel pump is provided in case of the failure of the engine driven pump The electric pump should be ON for all takeoffs and landings and when switching tanks The fuel pump switch is located in the switch panel above the throttle quadrant The fuel drains should be opened daily prior to first flight to check for water or sediment Each tank has an individual drain at ...

Page 173: ...FUEL SYSTEM SCHEMATIC Figure 7 9 ISSUED DECEMBER 16 1976 REPORT VB 880 7 11 PIPER AIRCRAFT CORPORATION SECTION 7 PA 28 161 CHEROKEE WARRIOR II DESCRIPTION AND OPERATION ...

Page 174: ...ressure indicator lights When the optional gyro system is installed the annunciator panel also includes a low vacuum indicator light The annunciator panel lights are provided only as a warning to the pilot that a system may not be operating properly and that he should check and monitor the applicable system gauge to determine when or if any necessary action is required Optional electrical accessor...

Page 175: ...ad for night flight with radios on is about 30 amperes This 30 ampere value plus approximately 2 amperes for a fully charged battery will appear continuously under these flight conditions The amount of current shown on the ammeter will tell immediately if the alternator system is operating normally as the amount of current shown should equal the total amperage drawn by the electrical equipment whi...

Page 176: ...TERNATOR AND STARTER SCHEMATIC Figure 7 11 REPORT VB 880 ISSUED DECEMBER 16 1976 7 14 REVISED DECEMBER 18 1980 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA 28 161 CHEROKEE WARRIOR II ...

Page 177: ...cate a sheared pump drive defective pump possibly a defective gauge or collapsed line In the event of any gauge variation from the norm the pilot should have a mechanic check the system to prevent possible damage to the system components or eventual failure of the system A vacuum regulator is provided in the system to protect the gyros The valve is set so the normal vacuum reads 5 0 1 inches of me...

Page 178: ...ft main fuel quantity gauge an oil temperature gauge and an oil pressure gauge Standard instruments include a compass an airspeed indicator a tachometer an altimeter an ammeter an engine cluster and an annunciator panel The compass is mounted on the windshield bow in clear view of the pilot The annunciator panel is mounted in the upper instrument panel to warn the pilot of a possible malfunction i...

Page 179: ...INSTRUMENT PANEL Figure 7 15 ISSUED DECEMBER 16 1976 REPORT VB 880 REVISED JULY 3 1979 7 17 PIPER AIRCRAFT CORPORATION SECTION 7 PA 28 161 CHEROKEE WARRIOR II DESCRIPTION AND OPERATION ...

Page 180: ... defroster must be on during alternate static source operation The altimeter error is less than 50 feet unless otherwise placarded Both the pitot and static lines can be drained through separate drain valves located on the left lower side of the fuselage interior A heated pitot head which alleviates problems with icing and heavy rain is available as optional equipment The switch for the heated pit...

Page 181: ...PITOT STATIC SYSTEM Figure 7 17 ISSUED DECEMBER 16 1976 REPORT VB 880 7 19 PIPER AIRCRAFT CORPORATION SECTION 7 PA 28 161 CHEROKEE WARRIOR II DESCRIPTION AND OPERATION ...

Page 182: ...HEATING AND VENTILATING SYSTEM Figure 7 19 REPORT VB 880 ISSUED DECEMBER 16 1976 7 20 REVISED JULY 3 1979 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA 28 161 CHEROKEE WARRIOR II ...

Page 183: ...l with the heater and defroster controls 7 25 CABIN FEATURES For ease of entry and exit and for pilot passenger comfort the front seats are adjustable fore and aft The right front seat tilts forward to allow easy entry to the rear seats The cabin interior includes a pilot storm window ash trays and armrests on each front seat two map pockets and pockets on the backs of the front seats The front se...

Page 184: ...G range See Weight and Balance Section 7 29 STALL WARNING An approaching stall is indicated by an audible alarm located behind the instrument panel The indicator activates at between five and ten knots above stall speed 7 31 FINISH All exterior surfaces are primed with etching primer and finished with acrylic lacquer To keep the finish attractive economy size spray cans of touch up paint are avail...

Page 185: ...ld be conducted only in the first five minutes of any hour and limited to three audio sweeps If the tests must be made at any other time the tests should be coordinated with the nearest FAA tower or flight service station NARCO ELT 10 OPERATION On the ELT unit itself is a three position switch placarded ON OFF and ARM The ARM position sets the ELT so that it will transmit after impact and will con...

Page 186: ...or to discontinue transmission NOTE If the switch has been placed in the ON position for any reason the OFF position has to be selected before selecting ARM If ARM is selected directly from the ON position the unit will continue to transmit in the ARM position A pilot s remote switch located on the left side panel is provided to allow the transmitter to be controlled from inside the cabin The pilo...

Page 187: ...n can be operated independently of the air conditioning However it must be on for air conditioner operation Turning either switch off will disengage the compressor clutch and retract the condenser door Cooling air should be felt within one minute after the air conditioner is turned on NOTE If the system is not operating in 5 minutes turn the system OFF until the fault is corrected The FAN switch a...

Page 188: ...em for critical ice detection first turn on the airplanes master switch and then turn on the ice detection unit Turn the sensitivity knob fully counter clockwise causing the carb ice light to come on Now rotate the sensitivity knob back clockwise until the ice light just goes out This establishes the critical setting WARNING This instrument is approved as optional equipment only and Flight Operati...

Page 189: ...entive Maintenance 8 4 8 7 Airplane Alterations 8 5 8 9 Ground Handling 8 6 8 11 Engine Air Filter 8 8 8 13 Brake Service 8 8 8 15 Landing Gear Service 8 10 8 17 Propeller Service 8 11 8 19 Oil Requirements 8 11 8 21 Fuel System 8 11 8 23 Tire Inflation 8 14 8 25 Battery Service 8 14 8 27 Cleaning 8 14 8 29 Cold Weather Operation 8 16 REPORT VB 880 8 i ...

Page 190: ...r PIPER approved parts obtained from PIPER approved sources in connection with the maintenance and repair of PIPER airplanes Genuine PIPER parts are produced and inspected under rigorous procedures to insure airworthiness and suitability for use in PIPER airplane applications Parts purchased from sources other than PIPER even though identical in appearance may not have had the required tests and i...

Page 191: ...rs deal with product improvements and servicing techniques pertaining to the airplane They are sent to Piper Service Centers and if necessary to the latest FAA registered owners in the U S Owners should give careful attention to Service Letter information Service Spares Letters offer improved parts kits and optional equipment which were not available originally and which may be of interest to the ...

Page 192: ...lity for the continued airworthiness of any aircraft not maintained to these standards and or not brought into compliance with applicable Service Bulletins issued by Piper instructions issued by the engine propeller or accessory manufacturers or Airworthiness Directives issued by the FAA A Progressive Inspection approved by the Federal Aviation Administration FAA is also available to the owner Thi...

Page 193: ... person or facility appropriately certificated by the Federal Aviation Administration FAA to perform that work Anytime maintenance is accomplished an entry must be made in the appropriate aircraft maintenance records The entry shall include a The date the work was accomplished b Description of the work c Number of hours on the aircraft d The certificate number of pilot performing the work e Signat...

Page 194: ...Certificate Form FAA 8100 2 2 Aircraft Registration Certificate Form FAA 8050 3 3 Aircraft Radio Station License if transmitters are installed b To be carried in the aircraft at all times 1 Pilot s Operating Handbook 2 Weight and Balance data plus a copy of the latest Repair and Alteration Form FAA 337 if applicable 3 Aircraft equipment list Although the aircraft and engine logbooks are not requir...

Page 195: ...e brakes b Taxiing Before attempting to taxi the airplane ground personnel should be instructed and approved by a qualified person authorized by the owner Engine starting and shut down procedures as well as taxi techniques should be covered When it is ascertained that the propeller back blast and taxi areas are clear power should be applied to start the taxi roll and the following checks should be...

Page 196: ...y and protection The following procedures should be used for the proper mooring of the airplane 1 Head the airplane into the wind if possible 2 Retract the flaps 3 Immobilize the ailerons and stabilator by looping the seat belt through the control wheel and pulling it snug 4 Block the wheels 5 Secure tie down ropes to the wing tie down rings and to the tail skid at approximately 45 degree angles t...

Page 197: ...y or shows any damage replace it immediately b Installation Of Engine Air Filter When replacing the filter install the filter in the reverse order of removal 8 13 BRAKE SERVICE The brake system is filled with MIL H 5606 petroleum base hydraulic brake fluid The fluid level should be checked periodically or at every 50 hour inspection and replenished when necessary The brake reservoir is located on ...

Page 198: ...BRAKE SYSTEM Figure 8 1 ISSUED DECEMBER 16 1976 REPORT VB 880 8 9 PIPER AIRCRAFT CORPORATION SECTION 8 PA 28 161 CHEROKEE WARRIOR II HANDLING SERVICING AND MAINTENANCE ...

Page 199: ...not allow the strut to extend more than 12 inches When air bubbles cease to flow through the hose compress the strut fully and again check fluid level Reinstall the valve core and filler plug and the main gear torque links if disconnected With fluid in the strut housing at the correct level attach a strut pump to the air valve and with the airplane on the ground inflate the oleo strut to the corre...

Page 200: ... recommended MIL L 22851 Average Ambient MIL L 6082B Ashless Dispersant Temperature SAE Grade SAE Grades All Temperatures 15W 50 or 20W 50 Above 80 F 60 60 Above 60 F 50 40 or 50 30 F to 90 F 40 40 0 F to 70 F 30 30 40 or 20W 40 Below 10 F 20 30 or 20W 30 When operating temperatures overlap indicated ranges use the lighter grade oil NOTE Refer to the latest issue of Textron Lycoming Service Instru...

Page 201: ...d it must meet the specification MIL I 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 One and one half liquid ozs per ten gallon of fuel would fall within this range A blender supplied by the additive manufacturer should be used Except for the inf...

Page 202: ...r of the firewall Each of the fuel tank sumps should be drained first Then the fuel strainer should be drained twice once with the fuel selector valve on each tank Each time fuel is drained sufficient fuel should be allowed to flow to ensure removal of contaminants This fuel should be collected in a suitable container examined for contaminants and then discarded CAUTION When draining any amount of...

Page 203: ...ube which is normally closed off with a cap and which should be opened occasionally to drain off any accumulation of liquid The battery should be checked for proper fluid level DO NOT fill the battery above the baffle plates DO NOT fill the battery with acid use only water A hydrometer check will determine the percent of charge in the battery If the battery is not up to charge recharge starting at...

Page 204: ... corrosion of metal Cover areas where cleaning solution could cause damage To wash the airplane use the following procedure 1 Flush away loose dirt with water 2 Apply cleaning solution with a soft cloth a sponge or a soft bristle brush 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 surf...

Page 205: ...hand soap and water f Cleaning Carpets To clean carpets first remove loose dirt with a whisk broom or vacuum For soiled spots and stubborn stains use a noninflammable dry cleaning fluid Floor carpets may be removed and cleaned like any household carpet 8 29 COLD WEATHER OPERATION For cold weather operation a winterization plate is installed on the inlet opening of the oil cooler This plate should ...

Page 206: ... Autopilot Installation 9 3 2 AutoControl IIIB Autopilot Installation 9 5 3 Piper Electric Pitch Trim 9 9 4 Air Conditioning Installation 9 11 5 Century 21 Autopilot 9 15 6 Piper Control Wheel Clock Installation 9 19 REPORT VB 880 9 i 7 8 Avidyne IFD540 GPS NAV COM 9 L3 LYNX NGT 9000 ADS B transponder 9 ...

Page 207: ... of the airplane when equipped with one or more of the various optional systems and equipment not provided with the standard airplane All of the Supplements provided by this section are FAA Approved and consecutively numbered as a permanent part of this Handbook The information contained in each Supplement applies only when the related equipment is installed in the airplane ISSUED DECEMBER 16 1976...

Page 208: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 9 2 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA 28 161 CHEROKEE WARRIOR II ...

Page 209: ...or overpower autopilot at either control wheel b AutoFlite II master switch OFF c In climb cruise or descent configuration a malfunction with a 3 second delay in recovery initiation may result in 60 bank and 320 foot altitude loss d In approach configuration coupled or uncoupled a malfunction with a 1 second delay in recovery initiation may result in 15 bank and 20 foot altitude loss SECTION 4 NOR...

Page 210: ...position and push IN to engage tracker Aircraft will track desired radial established on NAV 1 or as selected if equipped with a NAV selector switch NOTE Tracker must be engaged within 10 of being on course i e VOR course needle centered and aircraft heading within 10 of VOR course 2 Trim knob push IN for high sensitivity Use high sensitivity position for localizer tracking and as desired for OMNI...

Page 211: ...er switch OFF b The autopilot can be overpowered at either control wheel c An autopilot runaway with a 3 second delay in the initiation of recovery while operating in climb cruise or descending flight could result in a 60 bank and 320 foot altitude loss d An autopilot runaway with a 1 second delay in the initiation of recovery during an approach operation coupled or uncoupled could result in an 15...

Page 212: ...OM arrows may remain out of view depending upon the design of the NAV converter used in the installation SECTION 4 NORMAL PROCEDURES PREFLIGHT a AUTOPILOT 1 Place radio coupler in HDG mode if installed and place the A P ON OFF switch to the ON position to engage roll section Rotate roll command knob left and right and observe that control wheel describes a corresponding left and right turn then ce...

Page 213: ...on localizer Select LOC REV to intercept and track outbound to the procedure turn area c Select HDG mode on autopilot console to engage coupler 3 ILS Back Course a Set inbound front localizer course on H S I b Select LOC REV on radio coupler to intercept and track inbound on the back localizer course Select LOC NORM to intercept and track outbound on the back course to the procedure turn area c Se...

Page 214: ...c performance provided by Section 5 of the Pilot s Operating Handbook are necessary for this supplement REPORT VB 880 ISSUED DECEMBER 16 1976 9 8 REVISED JULY 11 1977 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA 28 161 CHEROKEE WARRIOR II ...

Page 215: ...tch on instrument panel to OFF position b In an emergency electric pitch trim may be overpowered using manual pitch trim c In cruise configuration malfunction results in 10 pitch change and 200 ft altitude variation d In approach configuration a malfunction can result in a 5 pitch change and 50 ft altitude loss SECTION 4 NORMAL PROCEDURES The electric trim system may be turned ON or OFF by a switc...

Page 216: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED DECEMBER 16 1976 9 10 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA 28 161 CHEROKEE WARRIOR II ...

Page 217: ...ed OFF manually prior to takeoff to disengage the compressor and retract the condenser door Also the air conditioner must be turned OFF manually before the landing approach in preparation for a possible go around b Placards In full view of the pilot in the area of the air conditioner controls when the air conditioner is installed WARNING AIR CONDITIONER MUST BE OFF TO INSURE NORMAL TAKEOFF CLIMB P...

Page 218: ...CE Operation of the air conditioner will cause slight decreases in cruise speed and range Power from the engine is required to run the compressor and the condenser door when extended causes a slight increase in drag When the air conditioner is turned off there is normally no measurable difference in climb cruise or range performance of the airplane NOTE To insure maximum climb performance the air ...

Page 219: ...or in the event of a malfunction which would cause the compressor to operate and the condenser door to be extended a decrease in rate of climb of as much as 100 fpm can be expected Should a malfunction occur which prevents condenser door retraction when the compressor is turned off a decrease in rate of climb of as much as 50 fpm can be expected ISSUED JULY 11 1977 REPORT VB 880 9 13 PIPER AIRCRAF...

Page 220: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED JULY 11 1977 9 14 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA 28 161 CHEROKEE WARRIOR II ...

Page 221: ...ly disconnecting the autopilot by depressing the AP ON OFF switch on the programmer OFF Do not operate until the system failure has been identified and corrected 1 Altitude Loss During Malfunction a An autopilot malfunction during climb cruise or descent with a 3 second delay in recovery initiation could reslut in as much as 60 of bank and 320 altitude loss Maximum altitude loss was recorded at 15...

Page 222: ...slaving indication is not obtained switch to free gyro mode and periodically set card as an unslaved gyro NOTE In the localizer mode the TO FROM arrows may remain out of view depending upon the design of the NAV converter used in the installation SECTION 4 NORMAL PROCEDURES Refer to Edo Aire Mitchell Century 21 Autopilot Operator s Manual P N 68S805 dated 1 79 for Autopilot Description and Normal ...

Page 223: ... 4 Perform Steps 1 7 in Section 4 item b except in Steps 4 and 5 substitute course arrow for HDG bug when checking control wheel movement in relation to L R needle HDG bug is inoperative with NAV APPR or REV mode selected d IN FLIGHT PROCEDURE 1 Trim aircraft for existing flight condition all axes 2 Rotate heading bug to desired heading Engage autopilot 3 During maneuvering flight control aircraft...

Page 224: ...THIS PAGE INTENTIONALLY LEFT BLANK REPORT VB 880 ISSUED AUGUST 14 1980 9 18 REVISED DECEMBER 18 1980 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA 28 161 CHEROKEE WARRIOR II ...

Page 225: ...Operating Handbook are necessary for this supplement SECTION 3 EMERGENCY PROCEDURES No changes of the basic Emergency Procedures provided by Section 3 of this Pilot s Operating Handbook are necessary for this supplement SECTION 4 NORMAL PROCEDURES a SETTING While in the CLOCK mode the time and the date can be set by the operation of the RST button b DATE SETTING Pressing the RST button once will c...

Page 226: ...e normal timekeeping mode without altering the minutes timing This feature is useful when changing time zones when only the hours are to be changed d AUTOMATIC DATE ADVANCE The calendar function will automatically advance the date correctly according to the four year perpetual calendar One day must be added manually on Feb 29 on leap year The date advances correctly at midnight each day e DISPLAY ...

Page 227: ...Airplane Flight Manual when Avidyne 700 00182 XXX Integrated Flight Display IFD and or 700 00179 XXX Integrated Flight Display installed in accordance with STC SA00343BO The information contained herein supplements or supersedes the basic manual only in those areas listed For limitations and procedures not contained in this supplement consult the basic Airplane Flight Manual FAA Approved _________...

Page 228: ...FD410 IFD510 IFD545 IFD550 and software version 10 2 04 Pages 4 24 Added 91 227 compliance statement 05 Pages 11 13 22 Added limitation regarding use of radar display added EmProc for disabling wireless connectivity ACO comments incorporated Anthony Pigott Mar 06 2017 06 Pages 13 Added note regarding IFD4XX FLTA aural alert conflicts with other sensors Anthony Pigott Mar 20 2017 07 Pages 4 5 8 26 ...

Page 229: ...iness approval for navigation using GPS and SBAS Satellite Based Augmentation System complying with ICAO Annex 10 for IFR en route terminal area and non precision approach operations GPS or GPS and RNAV GPS approaches The IFD4XX and IFD5XX are approved for approach procedures with vertical guidance including LPV and LNAV VNAV and approaches without vertical guidance including LP and LNAV The IFD4X...

Page 230: ...lds a FAA Type 2 Letter of Acceptance LOA in accordance with AC 20 153 for database integrity quality and database management practices for the navigation database Flight crew and operators can view the LOA at www avidyne com ADS B OUT Compliance The IFD4XX and or IFD5XX installed per this STC in conjunction with the following transponders UAT transceivers have been shown to meet the equipment req...

Page 231: ...ot receive ADS R or TIS B broadcasts from ATC unless the aircraft is in the same area as a valid TIS B client broadcasting that it has ADS B In capability Figure 1 Avidyne IFD540 700 00182 XXX Integrated Flight Display IFD Volume Power Squelch Knob Frequency Swap USB Port Line Select Keys Com Nav Manual Tuning Knob Page Function Keys Latch Context Sensitive IFD Knob CDI Nav Source Knob Ambient Lig...

Page 232: ... 26 P N 600 00298 000 Rev 08 Figure 2 Avidyne IFD440 700 00179 XXX Integrated Flight Display IFD Volume Power Squelch Knob Frequency Swap USB Port Line Select Keys LSKs Com Nav Manual Tuning Knob Page Function Keys Cam Latch Context Sensitive IFD Knob CDI Nav Source Knob Ambient Light Sensor Dedicated Function Keys ...

Page 233: ...rporation 4 Middlesex Green Suite 221 561 Virginia Road Concord MA 01742 FAA APPROVED Date 2FW Page 7 of 26 P N 600 00298 000 Rev 08 Figure 3 Avidyne IFD550 700 00182 XXX Integrated Flight Display Ego centric SVS ...

Page 234: ...additional approved GPS and or VHF receiver For all other Airplanes Class II III and IV dual VHF communications transceivers and dual GPS or VHF Navigation receivers are required for flight under instrument flight rules IFR One communication transceiver or one GPS receiver or one VHF navigation receiver may be inoperable for IFR flight In all airplanes an approved navigation display external CDI H...

Page 235: ...conducted under instrument flight rules IFR x VOR LOC ILS procedures procedures using VHF radio guidance IFD440 IFD540 IFD550 only x RNP instrument approach procedures using the following lines of minima o LNAV minima x RNP terminal procedures including RNP arrival procedures and RNP departure procedures x RNAV terminal procedures including RNAV arrival procedures and RNAV departure procedures 4 W...

Page 236: ... Operating Handbook checklists and are advisory only The pilot shall not use the electronic checklists as the primary set of on board aircraft checklists FAA Approved Flight Manual paper checklist must be available to the pilot as the primary reference 10 The IFD integrates with separately approved system installations such navigation indicators remote annunciators Adherence to limitations in inst...

Page 237: ...information horizontal of vertical The IFD545 and or IFD550 may only be used as a secondary non required source for this information 15 The Avidyne IFD4XX and IFD5XX may only be operated in IMC conditions as a radar display when used in conjunction with an independent lightning detection and display system Approved Thunderstorm Detection Equipment CAUTION Terrain information shown on the MAP page ...

Page 238: ...v 08 CAUTION In IFD545 and IFD550 units the inertial reference accelerometers may be irreparably damaged by exposure to temperatures below 40 C The units are capable of operating at 40 C but exposure to temperatures below this even when powered off can stress the parts internally causing a detectable and annunciated failure of the sensors ...

Page 239: ...to remaining navigation receiver required for IFR operations Warning Messages Caution and warning messages provided by the IFD4XX and IFD5XX are related to functions performed by the IFD4XX and IFD5XX and are additional to the caution and warning annunciation system provided by the aircraft NOTE The original caution and warning annunciator panel remains as the primary indication POH AFM Emergency ...

Page 240: ...98 000 Rev 08 To Disable WiFi Bluetooth Connectivity on IFD4XX IFD5XX 1 Press and hold the IFD4xx IFD5XX power button knob for 1 second upper left bezel 2 ALLOW IGNORE WiFi Bluetooth dropdown is presented Press IGNORE Dropdown is removed 3 Verify the WiFi and Bluetooth icons on the upper right of the display are removed Extinguish ...

Page 241: ...mminent obstacle collision Initiate an immediate recovery maneuver Unit Overtemp Unit Unreliable Unit Overtemp internal component name Unit reliability in question Get IFD serviced One or more of the internal components has exceeded its maximum design temperature and reliability cannot be ensured until the unit is tested by the Avidyne Service Center Contact the Avidyne Service Center or a local d...

Page 242: ... Crosscheck Nav This is alerting about imminent exceedence of horizontal fault detection limits or protection levels Crosscheck the nav solution and determine the best course of action If on a GPS based approach Missed Approach is required GPS Fault Dead Reckoning Position updated via dead reckoning The system will use the last known position and groundspeed and heading if available to estimate th...

Page 243: ... Contact the Avidyne Service Center or a local dealer for service LPV Unavailable Use L VNAV DA GPS integrity is insufficient for LPV Approach Transition to a non LPV approach and the appropriate minima if possible Otherwise execute a missed approach LPV Unavailable Use LNAV MDA GPS integrity is insufficient for LPV Approach Transition to a non LPV approach and the appropriate minima if possible O...

Page 244: ...led global Contact a local dealer for service Traffic Low High Bearing in clock direction Distance in NM Traffic Brg e g 1 00 dist e g 2 NM alt e g 200 ft Traffic advisories Alert to be used to facilitate visual acquisition of traffic Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic Traffic Low High Distance in NM Traffic Di...

Page 245: ...f the conflicting traffic Traffic distance in NM Traffic distance in NM Traffic advisories with no relative altitude information and no bearing Alert to be used to facilitate visual acquisition of traffic Pilots should maneuver their aircraft based only on ATC guidance or positive visual acquisition of the conflicting traffic COM TX Fault Transmitter Fault No TX Ability Transition to a backup VHF ...

Page 246: ...proving air flow in around the IFD Low Volts Backlight reduced to 25 Main supply voltage has fallen to approximately 11VDC Check the aircraft alternators are on and functional Consider load shedding the power bus that is powering the IFD Manual Sequence Req d Altitude invalid leg will not auto sequence In basic E M aircraft where the IFD does not have altitude input this message will appear when t...

Page 247: ...ne Service Center if this persists across power cycles Radar Echos Ahead Radar Heavy Echos Ahead Generated when a number of red and or magenta echos are present within the area 22q off the nose of the aircraft at the current displayed radar range Radar Target Alert Radar Target Alert Detected Alerts the pilot to the presence of a significant weather cell that exists beyond the currently selected d...

Page 248: ...mined corrective action should be t aken immediately TAWS Fail Invalid GPS Positon Velocity The GPS solution is lost or the GPS velocity quality parameters drop below required accuracy limits A bing bong chime is played if this condition occurs Contact the Avidyne Service Center if this persists across power cycles TAWS System Failure TAWS Failed Self Test reason why TAWS failed self test for the ...

Page 249: ...D4XX IFD5XX 4 Avionics or Radio Master if equipped OFF or 5 Press and hold the Power Knob OFF IMC Operations with Weather Radar 1 While operating in IMC conditions with weather radar active activate lightning detection system and monitor Correlate lightning strike information with painted radar information to confirm proper system operation 2 In the event that radar data and lightning do not coinc...

Page 250: ...Avidyne Corporation 4 Middlesex Green Suite 221 561 Virginia Road Concord MA 01742 FAA APPROVED Date 2FW Page 24 of 26 P N 600 00298 000 Rev 08 Section 5 Performance No change from basic Handbook ...

Page 251: ... Green Suite 221 561 Virginia Road Concord MA 01742 FAA APPROVED Date 2FW Page 25 of 26 P N 600 00298 000 Rev 08 Section 6 Weight and Balance No change from basic Handbook See AFM POH for current weight and balance for this aircraft ...

Page 252: ... 2FW Page 26 of 26 P N 600 00298 000 Rev 08 Section 7 Systems Description See Avidyne IFD4XX and IFD5XX FMS GPS Nav Com Pilot Guides P N 600 00300 001 for the IFD5XX Series P N 600 00304 000 for the IFD4XX Series P N 89000039 010 Bendix King AeroNav 900 and 910 P N 89000041 008 Bendix King AeroNav 800 ...

Page 253: ...Piper PA 28 161 28 7916159 N3067D ...

Page 254: ...MANUAL For The L3 Aviation Products Lynx Multilink Surveillance System Models NGT 9000 L3 Part Number 9029000 20000 RECORD OF REVISIONS Revision Date of Revision Description Original 3 31 2015 Original Issue 1 6 19 2015 Typographical error corrections Corrections to Table 3 1 in section 3 2 1 2 3 27 2016 Incorporation of s w Revision 2 0 ATAS and TAWS 3 2 24 2017 Updated for s w Version 2 1 4 9 19...

Page 255: ...Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT 9000 Revision 4 Issue 9 19 17 Page 3 of 27 Document Number L3 76AK AFMS1 FAA Approved This page intentionally left blank ...

Page 256: ... Displays 9 1 12 Lightning Detection Optional 9 1 13 Traffic Displays 10 1 14 Interaction of Major Components 12 1 15 Installation Configuration for This Aircraft 13 SECTION 2 LIMITATIONS 14 2 1 Minimum Documentation 14 2 2 Minimum Equipment 14 2 3 ADS B OUT Compliance 14 2 4 IDENT Function 14 2 5 ALT Function 14 2 6 Standby Function 14 2 7 Traffic Awareness 14 2 8 Terrain Awareness 15 2 9 Applica...

Page 257: ...Figure 1 1 Lynx NGT 9000 6 Figure 1 2 Typical NGT 9000 Traffic Screen 10 Figure 1 3 NGT 9000 Connections and Functions 12 Figure 1 4 Installation Configuration Data 13 TABLE OF TABLES Table 1 1 Typical Target Symbology 11 Table 2 1 Required Equipment 14 Table 2 2 Software Version 15 Table 3 1 Troubleshooting for the Panel Mount NGT 9000 17 Table 7 1 Light and Switch Functions 27 ...

Page 258: ...e Mode S Transponders individually using a 24 bit ICAO Mode S address which is unique to the particular aircraft In addition ground stations may interrogate the unit for its transponder data capability and the aircraft s Flight ID The ADS B provides own aircraft data with Enhanced Visual Acquisition EVAcq traffic information that improves situational awareness and flight safety by providing aircra...

Page 259: ...irport environment aircraft that are within a range of 6 nmi of ownship with a vertical distance of 1200 ft if altitude is reporting are classified as a Proximate Advisory PA A PA is displayed only for aircraft that are in air ATAS and TAS TCAS may operate at the same time with traffic information being correlated by the unit When ATAS is installed an Audio Acknowledge button will cancel the curre...

Page 260: ...n screen symbology and aural alerts for each system The system display shows the relative position of traffic using text shapes i e Traffic Advisory solid circle Other Traffic open diamond and colors The effective active mode surveillance range is 35 nm and the system is capable of tracking 35 Intruders simultaneously with the target bearing relative to the nose of own aircraft The tracking of tar...

Page 261: ...ons are set up during installation and cannot be changed except by a licensed installer NOTE The NGT 9000 s configuration parameters can only be changed by a licensed installer 1 10 Personal Electronic Devices The Lynx NGT 9000 supports the use of personal electronic devices e g iPad via a Wi Fi connection The PED must use approved applications that support the ADS B broadcast services i e ADS B I...

Page 262: ...00 01 Revision K or later for details on operation and a description of how the information is depicted Check with an L3 approved avionics dealer or contact L3 Aviation Products for a current list of approved traffic displays Figure 1 2 Typical NGT 9000 Traffic Screen 1 13 1 Traffic Priority Traffic is displayed on the screen using the following priority scheme 1 TAS TCAS Traffic Advisories TA s 2...

Page 263: ...e NGT 9000 Revision 4 Issue 9 19 17 Page 11 of 27 Document Number L3 76AK AFMS1 FAA Approved Table 1 1 Typical Target Symbology To promote cockpit commonality installation configuration options are available to set the airborne PA OT traffic color to either cyan or white ...

Page 264: ...the NGT 9000 Revision 4 Issue 9 19 17 Page 12 of 27 Document Number L3 76AK AFMS1 FAA Approved 1 14 Interaction of Major Components Figure 1 3 shows how the major components of the NGT 9000 connect to other aircraft systems Figure 1 3 NGT 9000 Connections and Functions ...

Page 265: ...xtended Callout Enable Disabled Enabled FIS B Enable Disabled Enabled Auto TIS B ADS R Service Status Indication Enable Disabled Enabled Normal Prox Other Traffic Color Cyan White ATAS Disabled Enabled Terrain Display Enable Disabled TAWS B Default Aural Phrases TAWS B Alternate Aural Phrases Display Only No Alerts WX 500 Enabled Stormscope Disabled Enabled Bottom Antenna Enabled Top Antenna Headi...

Page 266: ...being illuminated and or interfaced display ADS B messages not being present 2 4 IDENT Function The system must be capable of squawking IDENT when requested by Air Traffic Control 2 5 ALT Function While operating within airspace requiring an ADS B OUT compliant transmitter Pressure Altitude Broadcast Inhibit PABI shall only be enabled when requested by Air Traffic Control 2 6 Standby Function The ...

Page 267: ... Display Only no aural alerts then unit is not considered a Class B TAWS 2 9 Applicable System Software This AFMS SFM is applicable to the software versions shown in Table 2 2 or later FAA approved version Table 2 2 Software Version Software Part No Version NGT 9000 Ops s w 9020010 where 9020010 004 is the first in the series Rev 3 x where Rev 3 0 is the first in the series 68DC Navigational Datab...

Page 268: ...ion Alert Display Alert Audio Alert and or Terrain Caution Amber Lamp TAWS Display TERRAIN Audio Alert of Caution Terrain Caution Terrain or Caution Obstacle Caution Obstacle and or Amber Terrain Warning Lamp IMMEDIATELY STOP DESCENT AND BEGIN A SAFE RATE OF CLIMB CONSISTENT WITH PHASE OF FLIGHT CHECK TERRAIN CLEARANCE OR ATTEMPT TO VISUALLY ACQUIRE OBSTACLE CONTINUE CLIMB UNTIL CLEAR OF TERRAIN O...

Page 269: ...avionics switch 2 Verify Battery BAT Master switch is on 3 Check the Lynx MAT fault log Contact L3 Field Service before removal of unit The unit has manual brightness adjustment only All Loss of light sensor data 1 Try clearing the failure by restarting the unit by tapping the Restart button 2 Check System Status Messages 3 Check the Lynx MAT fault log Contact L3 Field Service before removal of un...

Page 270: ...not operate in normal mode and starts in Bootloader or maintenance mode MSG button on screen N A The following internal hardware test failures cause the unit to automatically reset This happens without cycling power to the unit If the hardware failure being detected does not clear a system fail message is sent ARINC 429 Receiver Loop Back Self Test Panel Mount Refresh Display Test Panel Mount Froz...

Page 271: ...S B traffic information is not available 1 The TAS TCAS is operational on the ground but there is no heading input and ground speed is 7kts 2 The GPS is failed GPS has not acquired 3 Possible problem with L Band antenna or internal hardware 4 Cycle power to the unit 5 Check System Status Messages 6 Check the Lynx MAT fault log Contact L3 Field Service before removal of unit Display indicator TAS T...

Page 272: ...k the GPS antenna for problems 4 Check System Status Messages 5 Check the Lynx MAT fault log Contact L3 Field Service before removal of unit Other aircraft are not shown on the traffic screen Ownship data is displayed Alternate display shows normal operation ADS B Out Fail lamp is OFF No Coverage Indicator is showing on the display Traffic The aircraft is not in an ADS B UAT 1090ES coverage area o...

Page 273: ...ing up on the display Traffic Lack of data as described below 1 The ADS B In requires other aircraft to be equipped with ADS B Out 2 The TIS B and ADS R services are supported when in range of ground stations and are providing the service 3 If receiving the TIS B service but the Mode C and Mode S transponder equipped aircraft that do not provide altitude information are not seen on the traffic dis...

Page 274: ...ating in the on ground mode 1 This is a normal condition when the aircraft is on ground 2 If the indication is seen during flight Contact L3 Field Service Display indicator XPDR FAIL Amber text showing on transponder screen MSG button on screen Transponder Transponder data is invalid This indication is shown on the transponder screen and alternate traffic screen 1 Possible problem with internal ha...

Page 275: ...pplication screen ADS B Out Fail lamp is Off for 2 minutes and then flashes 1 second On Off indefinitely until a GPS position is acquired Compatible displays may indicate STANDBY or DATA FAIL and Wi Fi information is not available Weather The indication is shown on the weather map indicating that GPS is Acquiring On Ground no previous position fix 1 This is a normal condition It continues to be sh...

Page 276: ...ailable however the GPS position was available once during this power ON or it is shown when a fault is detected that prevents the FIS B data from showing on the screen 1 The GPS signal may be weak Move the aircraft into an area where the unit can reacquire the GPS signal 2 Cycle power to the unit 3 Possible problem with L Band antenna or internal hardware 4 Check System Status Messages 5 Check th...

Page 277: ...ystem Status Messages 3 Check the Lynx MAT fault log Contact L3 Field Service before removal of unit Display indicator Lightning Failed amber text showing on Lightning screen Lightning Displayed when Lightning detection is not available 1 Cycle power to the unit 2 Cycle power to the WX 500 3 Check System Status Messages 4 Check the MPC MAT fault log Contact L3 Field Service before removal of unit ...

Page 278: ... NGT 9000 NGT 9000D and NGT 9000 Pilot s Guide Document Part Number 0040 17000 01 Revision K and later contains additional information regarding the system s description function and control The Pilot should become familiar with the contents of this Guide and keep it available for reference 7 2 Traffic Sources The NGT 9000 is capable of receiving ADS B IN traffic advisories and displaying them on ...

Page 279: ... Power Power for the NGT 9000 is provided through a circuit breaker labeled NGT 7 6 External Switches Lights and Controls Optional The following external lights listed in Table 7 1 are supported by the NGT 9000 Table 7 1 Light and Switch Functions Switch or Light Function ADS B FAIL lamp optional amber Out Normal operation Steady ADS B Failure Slow Flashing GPS aligning TRAFFIC Caution lamp amber ...

Page 280: ...TABLE OF CONTENTS SECTION 10 SAFETY TIPS Paragraph Page No No 10 1 General 10 1 10 3 Safety Tips 10 1 REPORT VB 880 10 i ...

Page 281: ...the 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 f Anti collision lights should not be operating when flying through cloud fog or haze since the reflected light can produce spatial disorientation Strobe lights should not be used in close proximity to the ground such as d...

Page 282: ...t this procedure The magneto selector should be placed to LEFT during the starting procedures to reduce the probability of kick back Place the ignition switch to BOTH position after the engine has started REPORT VB 880 ISSUED DECEMBER 16 1976 10 2 REVISED MAY 30 1980 SECTION 10 PIPER AIRCRAFT CORPORATION SAFETY TIPS PA 28 161 CHEROKEE WARRIOR II ...

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