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(26.) Repeat steps (7.) thru (23.) for right fuel system calibrationcheck.
(a.) In step (7.), replace adapter harnesses with adapter harnesses used for testing right fuel system. (b.) In step (18.) and note in step (20.), replace EMPTY LEFT pot with EMPTY RIGHT pot. (c.) In step (22.), replace FULL LEFT pot with FULL RIGHT pot.
(b) Wet Calibration Procedure:
CAUTION  ENSURETHAT THE WEIGHT OF THE FUEL IS ACCURATE BEFORE ADJUSTING FUEL QUANTITYINDICATOR. (EXAMPLE: 300 U.S. GALLONS OF JET-A FUEL AT 75°F WILL WEIGH 2000 LBS., WHILE 305 U.S. GALLONS OF JET-A AT 100°F WILL ALSO WEIGH 2000 LBS.
CAUTION:  VERIFYEMPTYSETTING AND REPLACE GAUGE IF FULL SETTING MUST BE ADJUSTEDMORETHAN± 50 LBS.
(1.) Drain both fuel systems. (2.) Add fuel to each wing and nacelle in 500 lb increments until all tanks are full. Record fuel quantity gauge readings for each increment (500, 1000, 1500, and full). (3.) Ensure readings agree with tolerances as shown in Chart 502. If a difference greater than the tolerances shown occurs, repeat the wet calibration procedure.
(4.) If a difference in readings still persists after the second wet calibration, check the fuel sensors per step (15.) of dry calibration procedure for both fuel systems (if previously not done). If step (15.) of dry calibration procedure has been performed, replace fuel quantity indicator and calibrate fuel quantity system.
CHART 502 WET CALIBRATION TOLERANCEREADINGS
Amount of Fuel (lbs)  Tolerance (lbs) 
500  ± 50 
1000  ± 50 
1500  ± 75 
2000 (Full)  ±100 

EFFECTIVITY: 040-999

Jan10/9028-40-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL

A. Indicating (continued) 
CHART 503 
FUELQUANTITY CALIBRATION WORK SHEET 
FUEL QUANTITY CALIBRATION DATA 
DATE 
AIRPLANE S/N 
TECHNICIAN(S) 
TEST SET BARFIELD 2548 -G / -GA S/N 
PROCEDURE  L.L.SIDE  R. SIDE 
DRY  pF.  pF. 
3 GAL/SIDE  (WAIT 15 MINUTES FOR SETTLING) 
ADJ LOW  FOR  ZERO  LB.  FOR  ZERO  LB. 
SYSTEM CAPACITANCE  pF.  pF. 
SIMULATE 1870 LBS.  110.0  pF.  110.0  pF. 
ADJUST HIGH  FOR  1870  LB.  FOR  1870  LB. 
500 LB OF FUEL  LB.  LB. 
1000 LB OF FUEL  LB.  LB. 
1500 LB OF FUEL  LB.  LB. 
FULL OR 2000 LB OF FUEL EL  LB.  LB. 

EFFECTIVITY:
040-999 PAGE
28-40-00 Jan 10/90

PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL

A. Indicating (continued) 
SensorFlange- GroundLead 
I  -Ground Post 
I I I I  I I II
I  I I III  I I  Sensor Test -Convenient -Insulated Surface  36 
6" 
1.70" Dia.  NOTE:1. DimensionsApproximate 2. BoxhasOnly5 Sidesas Shown 3. UnderTestConditions,Box Mustbe InsulatedfromGtoundwithGround PostConnectedto Shieldof H1ZCoax TestCableandFlangeof Sensor UnderTest. 

Fabricationof Test Fixturefor TankUnit Testing Figure 504 
Jan 10/90  28-40-00  EFFECTIVITY: 040-999 

PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL

A. Indicating(continued)
8. Testof AutomaticFuel PumpSystem
NOTE:  Referto chapter73 for furtherinformationontest andadjustmentof fuel pressure transmitterandgauge.
(a)
CheckgaugeanditspressuretransmitterforaccuracywithaBarfieldtesterbeforecontinuing. Ifgaugeisdefective,replacewithserviceableunit.

(b)
Twoproceduresexisttocheckthissystem.Thecrossfeedproceduresisasfollows:

(1.)Closefirewallshutoffvalveofsystemnotbeingtested.Opencrossfeedvalve.
(2.)Turnonbatterymasterswitch.Placepumpswitchofsystembeingtestedinautoposition.
(3.)Turnonoppositefuelpumpuntilfuelpressurerisesabove20psiandshutpumpoff. As

fuelpressuredecreasesbelow15± 2psi,annunciatorlightandsubmergedfuelpump mustcomeon. Iftheycomeonbeforeorafter15+2 psi,replacegauge. (4.)Turnallswitchesoff.
(c) Anothercheckprocedureisto start appropriateengineand proceedas follows:
(1.) Positionpumpswitchin autoand shutenginedown. Asfuel pressuredecreases, submergedfuelpumpand annunciatorlightmustcomeon at 15+ 2 psi. If theycomeon beforeor after15 + 2 psi, replaceinstrument.
EFFECTIVITY:

28-40-00Jan

Jan 10/90

PIPERAIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCEMANUAL

CHAPTER 29

LISTOF EFFECTIVE PAGES

CHAPTER  CHAPTER 
SECTION  PAGE  DATE  SECTION  PAGE  DATE 
　
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