Eclipse EA500 User manual

CHAPTER - 34 HIGHLIGHTS
(Summary of Changes)
Revision No. TR34-21 Sep 30/20
TO: HOLDERS OF THE AIRCRAFT MAINTENANCE MANUAL (06-117751)
Pages that have been added or revised are summarized below. Remove and insert the affected
pages as listed, and enter the above revision number with issue date into the Record of Revisions
sheet.
This Temporary Revision incorporates and supersedes previously released temporary
revisions for the chapters listed below.
Do not remove this page. Keep it in place as a record of previous changes.
CH/SE/SU
Page Block No. Description of Change
34-10-00
PgBlk 501 Adjustment / Test - Added Standby Pitot/Static Verification with Standby Display Unit (SDU).
34-10-10
PgBlk 401-Rem
(C) Added MB 500-34-028 to effectivity for Pitot/AOA Probe auxiliary heaters - Removal - Config C.
34-10-10
PgBlk 401-Inst
(C) Added MB 500-34-028 to effectivity for Pitot/AOA Probe auxiliary heaters - Installation - Config C.
34-40-50
PgBlk 1 (A) Description and Operation – Config A. Corrected effectivity.
34-40-50
PgBlk 1 (B) Description and Operation – Config B. Added configuration B – POST SB 500-31-024.
34-40-50
PgBlk 501 (A) Adjustment/Test – Config A. Corrected effectivity.
34-40-50
PgBlk 501 (B) Adjustment/Test – Config B. Added configuration for Stormscope lightning strike test post SB 500-31-024.
34-50-10
PgBlk 1 (B) Description and Operation - Revised Effectivity (ALL POST MB 500-31-018). Revised Description.
34-50-10
PgBlk 201 (A) Description and Operation - Revised Effectivity (ALL POST MB 500-31-018). Updated for ADS-B Out – Config A.
34-50-10
PgBlk 201 (B) Added GPS 3 (GDL 88) Maintenance Practices – Config B.
34-50-10
PgBlk 501 (C) Adjustment/Test for GPS Units – Config C.
34-50-11
PgBlk 401-Rem
(C) Added GPS 3 (GDL 88) Unit Removal procedure.
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34-HIGHLIGHTS
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CH/SE/SU
Page Block No. Description of Change
34-50-11
PgBlk 401-Rem
(D) Added Removal procedure for iFMS 2.7 GPS.
34-50-11
PgBlk 401-Inst
(B) GPS Installation - Revised Effectivity (ALL POST MB 500-31-018) and Job Close-Up.
34-50-11
PgBlk 401-Inst
(C) Added GPS 3 Unit Installation procedure.
34-50-11
PgBlk 401-Inst
(D) Added Installation procedure for iFMS 2.7 GPS.
34-50-13
PgBlk 401-Rem Added GPS 3 Mount Removal procedure.
34-50-13
PgBlk 401-Inst Added GPS 3 Mount Installation procedure.
34-50-14
PgBlk 401-Rem Added GPS 2 Antenna Splitter Removal procedure.
34-50-14
PgBlk 401-Inst Added GPS 2 Antenna Splitter Installation procedure.
34-50-20
PgBlk 1 (C) Revised Description and Operation – Config C.
34-50-20
PgBlk 1 (D) Description and Operation - Revised effectivity.
34-50-20
PgBlk 201 Added Transponder – Maintenance Practices.
34-50-20
PgBlk 501 (A)
Adjustment/Test - Revised General, Table 1 – Special Tools and
Equipment, removed Barfield Altitude testing, Transponder Address Module
Programming Procedure (AMC no longer supports this task). Revised Job
Close-Up. – Config A. Added UC-584 antenna couplers to equipment table.
Renamed existing procedures to with IFR-6000 Test Set Antenna. Added
test procedures with UC-584 Antenna Coupler.
34-50-20
PgBlk 501 (B)
Adjustment/Test - Removed Barfield Altitude testing, Transponder and
Avionics Cooling Fan Fault Checks (Standard System), and referenced
Avionics Cooling Fan to AMM-34-50-24. Deleted Enhanced Downlinked
Parameters test. – Config B. Added UC-584 antenna couplers to equipment
table. Renamed existing procedures to with IFR-6000 Test Set Antenna.
Added test procedures with UC-584 Antenna Coupler.
34-50-20
PgBlk 501 (C)
Adjustment/Test - Added Transponder Adjustment/Test for ADS-B Out. -
Config C. Added UC-584 antenna coupler to equipment table. Renamed
existing procedures to with IFR-6000 Test Set Antenna. Added test
procedures with UC-584 Antenna Coupler.
34-50-21
PgBlk 1 Added ADS-B Out with GPS 3 – Description and Operation.
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CH/SE/SU
Page Block No. Description of Change
34-50-21
PgBlk 501 Adjustment/Test - Added ADS-B Out check. Added antenna coupler to test.
34-50-21
PgBlk 401-Inst Installation - Revised Job Set-Up.
34-50-23
PgBlk 401-Inst Installation - Revised Job Close-up test reference.
34-50-26
PgBlk 401-Rem Removal - Added ADS-B Fail Indicator Removal procedure.
34-50-26
PgBlk 401-Inst Installation - Added ADS-B Fail Indicator Installation procedure.
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34-HIGHLIGHTS
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FLIGHT ENVIRONMENT DATA - ADJUSTMENT/TEST
AMM-34-10-00-071-801
1. General
A. This task gives procedures to do an adjustment/test of the flight environment data
components.
NOTE: This test procedure complies with the requirements of 14 CFR Part 43 Appendix
E.
(1) Unless indicated differently, the adjustment/test procedures are the same for both left
and right sides.
(2) Included are procedures for use of both the Barfield Pitot/Static Tester (Barfield,
DPS450) and the Barfield Pitot/Static Tester (Barfield, DPS500).
(3) After a replacement of the left and right Pitot/AOA probes, static ports, Air Data
Computers (ADCs), Standby Pitot/Static probe and Outside Air Temperature (OAT)
probes, do the test for each component shown in the table below.
Table 501. Component Test Matrix
Component to be Tested Test
Left and right ADCs Pitot and Static System Leak Test SUBTASK
AMM-34-10-00-071-701-001, Pitot and Static Verification Test
SUBTASK AMM-34-10-00-071-701-005 and Angle of Attack
Test SUBTASK AMM-34-10-00-071-701-004 and
AMM-24-00-00-071-801 – Electrical Power - Adjustment/Test,
SUBTASK AMM-24-00-00-071-701-005, Left and Right ADC
Test.
If software only is replaced, perform the following: Pitot
and Static Verification Test SUBTASK
AMM-34-10-00-071-701-005.
Left and right Pitot/AOA
probes Pitot and Static System Leak Test SUBTASK AMM-34-10-00-071-701-001, Angle of Attack Test SUBTASK
AMM-34-10-00-071-701-004 and AMM-30-30-00-071-801 –
Pitot and Static Anti-Ice System - Adjustment/Test.
If software only is replaced, perform the following: Pitot
and Static System Leak Test SUBTASK
AMM-34-10-00-071-701-001, and Angle of Attack Test
SUBTASK AMM-34-10-00-071-701-004.
Left and right Static ports Pitot and Static System Leak Test SUBTASK
AMM-34-10-00-071-701-001 and AMM-30-30-00-071-801 –
Pitot and Static Anti-Ice System - Adjustment/Test.
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Component to be Tested Test
Standby Pitot/Static probe Standby Pitot/Static Probe System Leak Test SUBTASK
AMM-34-10-00-071-701-002, Standby Pitot/Static Probe
Verification Test (Effectivity Noted) SUBTASK
AMM-34-10-00-071-701-006 or SUBTASK
AMM-34-10-00-071-701-007 and AMM-30-30-00-071-801 –
Pitot and Static Anti-Ice System - Adjustment/Test.
If software only is replaced, perform the following: Standby
Pitot/Static Probe Verification Test (Effectivity Noted)
SUBTASK AMM-34-10-00-071-701-006 or SUBTASK
AMM-34-10-00-071-701-007.
Right and left OAT probes Outside Air Temperature Test SUBTASK
AMM-34-10-00-071-701-008.
2. Equipment and Materials
Table 502. Special Tools and Equipment
Name and Part Number
Barfield Pitot/Static Tester (Barfield, DPS450) or Barfield Pitot/Static Tester (Barfield, DPS500)
or Equivalent Tester.
Air Data Accessories Kit (NavAids P/N ADA500MD-945) (or) Air Data Accessories Kit ; (Nav
Aids PN ADA500945) (Note: If using ADA500–945, covering pitot probes with tape is required)
Stop Watch (Inotek, EH365528) or Equivalent (Note: Calibrated with 1 second resolution)
Weight-on-Wheels (WOW) Box (EAI, 87-117390-1001) or Avio Maintenance Computer (AMC)
(EAI 20-120576-1001 or 20-121926-1001), SW version “1.5.71 or higher” for Pre-Avio NG
aircraft and “2.2.02 or higher” for Avio NG aircraft (for Weight off Wheels simulation)
Vinyl Tape (To cover drain hole on Pitot probes)
Ground Power Unit (GPU). AllStar 450 or AllStar G.S.E. or Hobart GPU-400 or Hobart GPU-
600 or Bycan PS-28100 (Note: 28.0 ± 0.5 VDC)
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3. Job Set-Up
SUBTASK AMM-34-10-00-071-921-001
* * * ALL
A. Make aircraft safe for maintenance. Refer to AMM-20-00-01-051-801 – Make Safe For
Maintenance.
B. Apply external power to the aircraft. Refer to AMM-24-40-00-051-801 – External Power -
Maintenance Practices.
CAUTION: IF TRANSPONDER(S) NOT SET TO “STBY”, THE AIRCRAFT WILL CAUSE
NUISANCE TRANSPONDER TRANSMISSIONS TO THE LOCAL AIRFIELD
AND OTHER AIRCRAFT.
D. When performing tests with the Weight On Wheels (WOW) box or Aircraft Maintenance
Computer (AMC) for Weight off Wheels simulation, refer to AMM-20-00-04-051-801 –
Weight On Wheels (WOW) Box - Connect/Disconnect.
(1) Set both the left and right PFD Baro to 29.92 by pressing the BARO SET knob on the
Autopilot Control Panel (ACP). Make sure the baro setting matches on the left and
right PFD.
(2) Collar the following ECBs:
WARNING: BECAUSE THIS TEST IS PERFORMED WITH WOFFW, THE
HEATERS WILL BE COMMANDED ON BY THE SYSTEM. IF THE
PITOT/STATIC HEAT ECBS ARE NOT COLLARED OFF, HARM TO
PERSONNEL OR DAMAGE TO AIR DATA TEST EQUIPMENT CAN
OCCUR.
NOTE: ECBs can only be collared in the Weight-on-Wheels condition.
(4) Collar the following ECB’s:
•ECB - WEATHER RADAR (L FWD Bus)
•ECB - DEICE MANIFOLD HTR (R AFT Bus)
•ECB - L PITOT HEAT (L FWD Bus) or ECB - L PITOT HEAT (BATT Bus)
•ECB - R PITOT HEAT (R FWD Bus)
•ECB - L STATIC HEAT (BATT Bus)
•ECB - L STATIC HEAT (R FWD Bus)
•ECB - R STATIC HEAT (R FWD Bus)
•ECB - R STATIC HEAT (L FWD Bus)
•ECB - STBY PITOT HEAT (BATT Bus) or ECB - STBY PITOT HEAT (L FWD)
•ECB - L WINDSHIELD HEAT (L AFT Bus)
•ECB - R WINDSHIELD HEAT (R AFT Bus)
(5) Make sure that the ADC selection source is not displayed on the left PFD. Make sure
that the ADC selection source is not displayed on the right PFD.
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(6) Set both the left and right PFD Baro to 29.92 by pressing the BARO SET knob on the
Autopilot Control Panel (ACP). Make sure the baro setting matches on the left and
right PFD.
(7) Make sure that the ADC 3 is displayed on the MFD ADI.
CAUTION: IF TRANSPONDER(S) NOT SET TO “STBY”, THE AIRCRAFT WILL CAUSE
NUISANCE TRANSPONDER TRANSMISSIONS TO THE LOCAL AIRFIELD
AND OTHER AIRCRAFT.
4. Pitot and Static System Leak Test
SUBTASK AMM-34-10-00-071-701-001
* * * ALL
CAUTION: DO NOT PRESSURIZE THE AIRCRAFT DURING TESTING.
NOTE: If a Barfield Pitot/Static Tester DPS450 is used for this test complete paragraph
A. If a Barfield Pitot/Static Tester DPS500 is used, go to paragraph B.
A. Pitot and Static System Leak Test with Barfield Pitot/Static Tester DPS450:
Procedure is given for the left side and is the same for the right side.
Refer to Fig. 501, Sheet 1.
CAUTION: DO NOT OVER TIGHTEN HOSES. DAMAGE MAY OCCUR TO TEST
EQUIPMENT. HOSES SHOULD BE SNUG.
CAUTION: THE LEAK TEST CAN BE ACCOMPLISHED WITH ELECTRICAL
POWER OFF. MAKE SURE THAT IF THE WOW BOX IS CONNECTED,
THE SWITCHES ARE SET TO WONW DURING THIS TEST IF
ELECTRICAL POWER IS USED. WITH WEIGHT OFF WHEELS, THE
HEATERS ARE COMMANDED ON BY THE AIRCRAFT COMPUTER
SYSTEM. IF THE PITOT/STATIC HEAT ECBS ARE NOT COLLARED
OFF, HARM TO PERSONNEL OR AIR DATA TEST EQUIPMENT CAN
OCCUR.
NOTE: Refer to step (1) if using Air Data Accessories Kit ; (Nav Aids PN
ADA500945) or step (2) if using Air Data Accessories Kit (NavAids P/N
ADA500MD-945.
(1) Connect the Barfield Pitot/Static Tester DPS450 to the aircraft using the Air Data
Accessories Kit ; (Nav Aids PN ADA500945) as follows:
(a) Install the Pitot/Angle of Attack (AOA) Probe Adaptor (Nav Aids,
APA94520-4-4-4) (7) with the label TOP facing up on the Pitot/AOA probe. If
needed, lubricate with Pitot adaptor lubricating fluid (Part Number LF5050).
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Adjust the Pitot/AOA Probe Adaptor nozzles to align with the holes of the
Pitot/AOA probe.
NOTE: No other lubricating fluid is permitted. Malfunction of the equipment in
flight is possible.
NOTE: When installing the pressure test adapters, make sure that the seal is
good by applying a firm force to seat the adapter on the probe.
NOTE: The Pitot/AOA probes with a drain hole near the base of mast, must
have the drain hole covered. The drain hole must be covered with teflon
or vinyl tape. Failure to do so will result in a failure of this test.
(b) Connect the Pitot Test Hose Assembly (long hose) (3) to the Pt connection (2) on
the Barfield Pitot/Static Tester DPS450. Connect the other end of the long hose
to the quick-connect cross (4) .
(c) Connect the Pitot Test Hose Assembly (three short hoses) (5, 6 and 8) to the
quick-connect cross. Connect the other end of the short hoses to the upper,
center and lower connections on the Pitot/AOA Probe Adaptor (7) .
NOTE: Make sure that the Pitot/AOA Probe Adaptor nozzles are still aligned with
the holes on the Pitot/AOA probe.
(d) Connect the Static Port Adaptor (Nav Aids, SS53515-4-4) (10) to the left static
port and finger tighten the screws to seat the seals over the static ports.
(e) Connect the Static Test Hose Assembly ; (Nav Aids PN E500-5160) (long hose)
(12) to the Barfield Pitot/Static Tester DPS450 Ps connection (1) . Connect the
other end of the Static Test Hose Assembly to the quick connect cross (11) .
(f) Connect the (short hose) (9) to the top fitting of the Static Port Adaptor (Nav Aids,
SS53515-4-4) (10) . Connect the other end of the short hose to the quick connect
cross (11) .
(2) Connect the Barfield Pitot/Static Tester DPS450 to the aircraft using the Air Data
Accessories Kit (NavAids P/N ADA500MD-945) as follows:
NOTE: When installing the pressure test adapters, make sure that the seal is good
by applying a firm force to seat the adapter on the probe.
NOTE: The P22201MD-4 adapter contains a built-in seal that covers the Pitot/AOA
probe drain hole. If using the P22201-3 adapter, the drain hole must be
covered with teflon or vinyl tape.
NOTE: The Pitot/AOA probes with a drain hole near the base of the mast, must have
the drain hole covered. Failure to do so will result in a failure of this test.
(a) Connect the Pitot Test Hose Assembly (3) to the Pt connection (2) on the Barfield
Pitot/Static Tester DPS450. DO NOT OVERTIGHTEN.
(b) Connect the opposite end of the hose to the NAV Aids P22201MD-4 adapter.
(c) Install the NAV Aids P22201MD-4 adapter to the Pitot/AOA Probe. Make sure
that the internal seal of the adapter covers the pitot probe drain hole. If using the
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P22201-3 adapter, make sure that the pitot probe drain hole is covered with tape.
If needed, lubricate with Pitot adaptor lubricating fluid (Part Number LF5050).
NOTE: No other lubricating fluid is permitted. Malfunction of the equipment in
flight is possible.
(d) Connect the Static Port Adaptor (Nav Aids, SS53515-4-4) (10) to the left static
port and finger tighten the screws to seat the seals over the static ports.
(e) Connect the Static Test Hose Assembly ; (Nav Aids PN E500-5160) (long hose)
(12) to the Barfield Pitot/Static Tester DPS450 Ps connection (1) .
(f) Connect the other end of the hose (9) to the top fitting of the Static Port Adaptor
(Nav Aids, SS53515-4-4) (10) .
(3) Use tape to seal the opposite-side Static port.
NOTE: Make sure to select a tape that does not leave any adhesive residue on the
static port when the test is complete.
(4) Power on the Barfield Pitot/Static Tester DPS450. Wait for the Barfield Pitot/Static
Tester DPS450 to the Confirm Settings.
•After a successful self-test sequence, the system changes to the Leak Measure
mode.
NOTE: Skip this step if the Barfield Pitot/Static Tester DPS450 is in Quad mode.
Quad mode displays four values: ALT, ROC, CAS, and Rt CAS.
(5) Press Setup and press F1 to select Display. Press F3 to select Quad. Make sure that
Alt is in ft, CAS is in kts and Rt CAS is in kts/min. If not, press F2 to select Units and
then press F1 to select ft kts ft/min and press F4 to save settings. Press Clear/Quit to
return to Main Menu displayed in the upper right corner.
(6) Press LEAK MEASURE/ CONTROL for CONTROL MODE.
(7) Press F1 to select Rate Timer and then press F3 to select Set Wait.
(8) Press 5 and then press Enter.
•The Set Wait will be updated to 5 minutes.
(9) Press F4 to select Set Time, press 1, and then press Enter.
•The Set Time will be updated to 1 minute.
(10) Press CLEAR/QUIT to return to Main Menu.
(11) Press ROC RATE Ps to select the ROC control aim, enter 4000 and press the Enter
button.
(12) Press ALT Ps to select the ALT control aim, enter 30000 and press the Enter button.
•The system starts to control to the new set point.
(13) Press SPEED Qc, enter 200 and press Enter. Wait for at least a 15 second
stabilization period after the altitude and airspeed achieve these new air data
parameter set point values to continue.
(14) Press LEAK MEASURE/CONTROL to change to LEAK MEASURE MODE.
(15) Press F1 twice to Start Timing.
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•After the Waiting and Timing intervals are complete, the Barfield Pitot/Static
Tester DPS450 displays Timed Rates Available.
(16) Check that the maximum ROC is 100 ft/min or less and the maximum Rt CAS is 2
kts/min. or less.
•If the leak rate is not within tolerances, refer to Leak Testing in the Barfield Pitot/
Static Tester DPS450 and Connecting Hoses (SUBTASK
AMM-34-10-00-071-701-003). Subtract the Barfield Pitot/Static Tester DPS450
leak check altitude value recorded in Leak Testing in the Barfield Pitot/Static
Tester DPS450 and Connecting Hoses subtask from the value obtained in this
section in order to get a corrected total system leak value.
(17) Press LEAK MEASURE/CONTROL to return to CONTROL MODE.
(18) If no further maintenance is required, remove all of the Nav Aids test equipment from
the aircraft. Stow the Air Data Accessories Kit ; (Nav Aids PN ADA500945)
equipment and Barfield Pitot/Static Tester DPS450.
(19) Remove the tape from the opposite-side Static port.
B. Pitot and Static System Leak Test with Barfield Pitot/Static Tester DPS500:
Procedure is given for the left side and is the same for the right side unless noted.
NOTE: To use the Barfield Pitot/Static Tester DPS500 Remote during this test, connect
the Remote (P/N ADTS405-1728-37M0) and Remote Cord (P/N
ADTS405-1728-28M0) to the Barfield Pitot/Static Tester DPS500 Hand Terminal
Connection.
NOTE: The Pt Hose (p/n ADTS405-1729-62m0) may be used in place of the hose (p/n
E500-7270). The AN6-AN4 adaptor is not needed if using the ADTS405-
1729-62m0 Pt hose.
NOTE: The Ps Hose (p/n ADTS405-1729-61m0) may be used in place of the hose (p/n
E500-5160), The AN6-AN4 connector is not required if using this configuration.
Install a AN5 to AN4 adaptor on the Barfield DPS500 Ps connection.
CAUTION: DO NOT OVER TIGHTEN HOSES. DAMAGE MAY OCCUR TO TEST
EQUIPMENT. HOSES SHOULD BE SNUG.
CAUTION: THE LEAK TEST CAN BE DONE WITH ELECTRICAL POWER OFF.
MAKE SURE THAT IF THE WOW BOX IS CONNECTED, THE
SWITCHES ARE SET TO WONW DURING THIS TEST IF ELECTRICAL
POWER IS USED. WITH WEIGHT OFF WHEELS, THE HEATERS ARE
COMMANDED ON BY THE AIRCRAFT COMPUTER SYSTEM. IF THE
PITOT/STATIC HEAT ECBS ARE NOT COLLARED OFF, HARM TO
PERSONNEL OR AIR DATA TEST EQUIPMENT CAN OCCUR.
NOTE: Refer to step (1) if using the Air Data Accessories Kit ; (Nav Aids PN
ADA500945) or step (2) if using the Air Data Accessories Kit (NavAids P/N
ADA500MD-945).
(1) Connect the Barfield Pitot/Static Tester DPS500 to the aircraft as follows:
(a) Install the Pitot/Angle of Attack (AOA) Probe Adaptor (Nav Aids,
APA94520-4-4-4) (7) with the label TOP facing up on the Pitot/AOA probe. If
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needed, lubricate with Pitot adaptor lubricating fluid (Part Number LF5050).
Adjust the Pitot/AOA Probe Adaptor nozzles to align with the holes of the
Pitot/AOA probe.
NOTE: No other lubricating fluid is allowed, possible malfunction of the
equipment in flight is possible
NOTE: When installing the pressure test adapters, make sure of a good seal by
applying a firm force to seat the adapter on the probe.
NOTE: If present, cover the probe drain hole with vinyl tape.
(b) Connect the Pitot Test Hose Assembly (long hose) (3) to the Pt connection (2) on
the Barfield Pitot/Static Tester DPS500. Connect the other end of the long hose
(3) to the quick connect cross (4) .
(c) Connect the Pitot Test Hose Assembly (one short hose) (5) to the quick connect
cross (4) . Connect the other end of the short hose (5) to the center connection
on the Pitot/AOA Probe Adaptor (7) .
NOTE: Make sure that the Pitot/AOA Probe Adaptor nozzles are still aligned with
the holes on the Pitot/AOA probe.
(d) Connect the Static Test Hose Assembly ; (Nav Aids PN E500-5160) (12) to the
Barfield Pitot/Static Tester DPS500 Ps connection (1) .
(e) Connect the other end of the Static Test Hose Assembly (12) to the top fitting of
the Static Port Adaptor (Nav Aids, SS53515-4-4) (10) .
(f) Connect the Static Port Adaptor (Nav Aids, SS53515-4-4) (10) to the left Static
port with the connected fitting to the top port and finger tighten the screws to seat
the seals over the Static ports.
NOTE: The right static upper port can be tested from the left Static lower port by
connecting the short hose to the lower port connection on the Static Port
Adaptor. The aircraft's left lower port is connected to the right upper port
and the left upper port is connected to the right lower port by aircraft
design. Refer to Fig. 504, Sheet 1.
(2) Connect the Barfield Pitot/Static Tester DPS500 to the aircraft using the Air Data
Accessories Kit (NavAids P/N ADA500MD-945) as follows:
NOTE: When installing the pressure test adapters, make sure that the seal is good
by applying a firm force to seat the adapter on the probe.
NOTE: The P22201MD-4 adapter contains a built-in seal that covers the Pitot/AOA
probe drain hole. If using the P22201-3 adapter, the drain hole must be
covered with teflon or vinyl tape.
NOTE: The Pitot/AOA probes with a drain hole near the base of the mast, must have
the drain hole covered. Failure to do so will result in a failure of this test.
(a) Connect the Pitot Test Hose Assembly (3) to the Pt connection (2) on the Barfield
Pitot/Static Tester DPS500. DO NOT OVERTIGHTEN.
(b) Connect the opposite end of the hose to the NAV Aids P22201MD-4 adapter.
(c) Install the NAV Aids P22201MD-4 adapter to the Pitot/AOA Probe. Make sure
that the internal seal of the adapter covers the pitot probe drain hole. If using the
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P22201-3 adapter, make sure that the pitot probe drain hole is covered with tape.
If needed, lubricate with Pitot adaptor lubricating fluid (Part Number LF5050).
NOTE: No other lubricating fluid is permitted. Malfunction of the equipment in
flight is possible.
(d) Connect the Static Test Hose Assembly ; (Nav Aids PN E500-5160) (12) to the
Barfield Pitot/Static Tester DPS500 Ps connection (1) .
(e) Connect the other end of the Static Test Hose Assembly (12) to the top fitting of
the Static Port Adaptor (Nav Aids, SS53515-4-4) (10) .
(f) Connect the Static Port Adaptor (Nav Aids, SS53515-4-4) (10) to the left Static
port with the connected fitting to the top port and finger tighten the screws to seat
the seals over the Static ports.
(3) Use tape to seal the opposite-side static port.
NOTE: Make sure to select a tape that does not leave any adhesive residue on the
Static port when the test is complete.
(4) Power on the Barfield Pitot/Static Tester DPS500 by selecting OPERATE and PUMP
switches to ON. Wait for the Barfield Pitot/Static Tester DPS500 to confirm the
settings.
•After a successful self-test sequence, the system changes to the Warm Up
mode.
(5) Press ROC Ps RATE to select the ROC control aim, enter 4000 and press the Enter
button.
(6) Press ALT Ps to select the ALT control aim, enter 30000 and press the Enter button.
•The system starts to control to the new set point.
(7) Press SPEED Qc and enter 200 then press Enter. Wait for at least a 15 second
stabilization period after the altitude and airspeed achieve these new air data
parameter set point values to continue.
(8) Press LEAK MEASURE/CONTROL to change to LEAK MEASURE MODE.
(9) Press RATE TIMER.
(10) Press F3.
•After the Waiting and Timing intervals are complete, the Barfield Pitot/Static
Tester DPS500 displays Timed Rates.
(11) Check that the maximum ROC is 100 ft/min or less and the maximum Rt CAS is 2
kts/min or less.
•If the leak rate is not within tolerances, refer to Leak Testing in the Barfield Pitot/
Static Tester DPS500 and Connecting Hoses SUBTASK
AMM-34-10-00-071-701-003 and subtract the Barfield Pitot/Static Tester
DPS500 leak check altitude value recorded in Leak Testing the Barfield Pitot/
Static Tester DPS500 and Connecting Hoses subtask from the value obtained in
this section in order to get a corrected total system leak value.
(12) Press LEAK MEASURE/CONTROL to return to CONTROL MODE.
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(13) If no further maintenance is required, remove all of the Nav Aids test equipment from
the aircraft. Stow all the Air Data Accessories Kit ; (Nav Aids PN ADA500945)
equipment and the Barfield Pitot/Static Tester DPS500.
(14) Remove the tape from the opposite-side Static port.
5. Standby Pitot/Static Probe System Leak Test
SUBTASK AMM-34-10-00-071-701-002
* * * ALL
CAUTION: DO NOT PRESSURIZE THE AIRCRAFT DURING TESTING.
NOTE: If a Barfield Pitot/Static Tester DPS450 is used for this test complete paragraph
A. If a Barfield Pitot/Static Tester DPS500 is used, go to paragraph B.
A. Complete the Standby Pitot/Static System Leak Test (using the Barfield Pitot/Static
Tester DPS450) as follows:
CAUTION: DO NOT OVER TIGHTEN HOSES. DAMAGE MAY OCCUR TO TEST
EQUIPMENT. HOSES SHOULD BE SNUG.
CAUTION: THE LEAK TEST CAN BE ACCOMPLISHED WITH ELECTRICAL
POWER OFF. MAKE SURE THAT IF THE WOW BOX IS CONNECTED,
THE SWITCHES ARE SET TO WONW DURING THIS TEST IF
ELECTRICAL POWER IS USED. WITH WEIGHT OFF WHEELS, THE
HEATERS ARE COMMANDED ON BY THE AIRCRAFT COMPUTER
SYSTEM. IF THE PITOT/STATIC HEAT ECBS ARE NOT COLLARED
OFF, HARM TO PERSONNEL OR AIR DATA TEST EQUIPMENT CAN
OCCUR.
NOTE: Refer to step (1) if using the Air Data Accessories Kit ; (Nav Aids PN
ADA500945) or step (2) if using the Air Data Accessories Kit (NavAids P/N
ADA500MD-945).
(1) Connect the Barfield Pitot/Static Tester DPS450 to the aircraft Standby Pitot/Static
probe as follows:
(a) Attach the Pitot/Static probe adaptor (PS35210-4-4) (6) to the Standby Pitot/
Static probe.
(b) Connect the hose (3) from the Pt connection (2) on the Barfield Pitot/Static
Tester DPS450 to the end fitting on the Pitot/Static probe adaptor (PS35210-4-4)
(6) .
(c) Connect the hose from the Ps (1) connection on the Barfield Pitot/Static Tester
DPS450 to the fitting on the side on the Pitot/Static probe adaptor (PS35210-4-4)
(6) .
NOTE: Cover the probe drain hole with vinyl tape.
(2) Connect the Barfield Pitot/Static Tester DPS500 to the aircraft using the Air Data
Accessories Kit (NavAids P/N ADA500MD-945) as follows:
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(a) Remove the P22201MD-4 adapter (or the P22201-3 adapter) from the Pt Hose.
Connect the hose from the Pt adapter on the Barfield to PS35210MD-4-4 adapter
(or PS35210- 4-4 adapter) connector marked PITOT (this is the connector at the
end of the adapter).
(b) Disconnect the hose from the static PTA and connect to the other PS35210
connector (connector on side of adapter). Connect the PS35210 adapter to the
Pitot/Static probe, make sure of a complete coverage of the static ports on the
Pitot/Static probe.
NOTE: The PS35210MD-4-4 adapter contains a built-in seal that covers the pitot
static probe drain hole. If using the PS35210-4-4 adapter, the drain hole
must be covered with vinyl tape.
NOTE: The Pitot/Static probe is the upper pitot probe on the left hand side.
(3) Press CLEAR/QUIT to return to main menu on Barfield Pitot/Static Tester DPS450.
(4) Press F1 to select Rate Timer and then press F3 to select Set Wait.
(5) Press 5 and then press ENTER.
•The Set Wait will be updated to 5 minutes.
(6) Press F4 to select Set Time, press 1, and then press ENTER.
•The Set Time will be updated to 1 minute.
(7) Press CLEAR/ QUIT to return to Main Menu.
(8) Press LEAK MEASURE/ CONTROL for CONTROL MODE.
(9) Press ROC RATE Ps to select the ROC control aim, enter 4000 and press Enter.
(10) Press ALT Ps to select the ALT control aim, enter 30000 and press Enter.
•The system starts to control to the new set point.
(11) Press SPEED Qc, enter 200 and press Enter. Wait for at least a 15 second
stabilization period after the altitude and airspeed achieve these new air data
parameter set point values to continue.
(12) Press LEAK MEASURE/CONTROL to change to LEAK MEASURE MODE.
(13) Press F1 twice to Start Timing.
•After the Waiting and Timing intervals are complete, the Barfield Pitot/Static
Tester DPS450 displays Timed Rates Available.
(14) Check the maximum ROC is 100 ft/min or less and the maximum Rt CAS is 2 kt/min
or less.
•If the leak rate is not within tolerances, refer to Leak Testing the Barfield Pitot/
Static Tester DPS450 and Connecting Hoses (SUBTASK
AMM-34-10-00-071-701-003) and subtract the Barfield Pitot/Static Tester
DPS450 leak check altitude value recorded in Leak Testing the Barfield Pitot/
Static Tester DPS450 and Connecting Hoses SUBTASK
AMM-34-10-00-071-701-003 from the value obtained in this section in order to
get a corrected total system leak value.
(15) Press the LEAK MEASURE/CONTROL to return to CONTROL MODE.
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(16) If no further maintenance is required, remove all of the Nav Aids test equipment from
the aircraft. Stow the Air Data Accessories Kit ; (Nav Aids PN ADA500945)
equipment and Barfield Pitot/Static Tester DPS450.
B. Complete the Standby Pitot/Static System Leak Test (using the Barfield Pitot/Static
Tester DPS500) as follows:
CAUTION: DO NOT OVER TIGHTEN HOSES. DAMAGE MAY OCCUR TO TEST
EQUIPMENT. HOSES SHOULD BE SNUG.
CAUTION: THE LEAK TEST CAN BE ACCOMPLISHED WITH ELECTRICAL
POWER OFF. MAKE SURE THAT IF THE WOW BOX IS CONNECTED,
THE SWITCHES ARE SET TO WONW DURING THIS TEST IF
ELECTRICAL POWER IS USED. WITH WEIGHT OFF WHEELS, THE
HEATERS ARE COMMANDED ON BY THE AIRCRAFT COMPUTER
SYSTEM. IF THE PITOT/STATIC HEAT ECBS ARE NOT COLLARED
OFF, HARM TO PERSONNEL OR AIR DATA TEST EQUIPMENT CAN
OCCUR.
NOTE: Refer to step (1) if using the Air Data Accessories Kit ; (Nav Aids PN
ADA500945) or step (2) if using the Air Data Accessories Kit (NavAids P/N
ADA500MD-945).
(1) Connect the Barfield Pitot/Static Tester DPS450 to the aircraft Standby Pitot/Static
probe as follows:
(a) Attach the Pitot/Static probe adaptor (PS35210-4-4) (6) to the Standby Pitot/
Static probe.
(b) Connect the hose (3) from the Pt connection (2) on the Barfield Pitot/Static
Tester DPS450 to the end fitting on the Pitot/Static probe adaptor (PS35210-4-4)
(6) .
(c) Connect the hose from the Ps (1) connection on the fitting on the side on the
Pitot/Static probe adaptor (PS35210-4-4) (6) .
NOTE: Cover the probe drain hole with vinyl tape.
(2) Connect the Barfield Pitot/Static Tester DPS500 to the aircraft using the Air Data
Accessories Kit (NavAids P/N ADA500MD-945) as follows:
(a) Remove the P22201MD-4 adapter (or the P22201-3 adapter) from the Pt Hose.
Connect the hose from the Pt adapter on the Barfield to the PS35210MD-4-4
adapter (or PS35210- 4-4 adapter) connector marked PITOT (this is the
connector at the end of the adapter).
(b) Disconnect the hose from the static PTA and connect to the other PS35210
connector (connector on the side of the adapter). Connect the PS35210 adapter
to the Pitot/Static probe, make sure of complete coverage of the static ports on
the Pitot/Static probe.
NOTE: The PS35210MD-4-4 adapter contains a built-in seal that covers the pitot
static probe drain hole. If using the PS35210-4-4 adapter, the drain hole
must be covered with vinyl tape.
NOTE: The Pitot/Static probe is the upper pitot probe on the left hand side.
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(3) Press LEAK MEASURE/ CONTROL for CONTROL MODE.
(4) Press ROC RATE Ps to select the ROC control aim, enter 4000 and press Enter.
(5) Press ALT Ps to select the ALT control aim, enter 30000 and press Enter.
•The system starts to control to the new set point.
(6) Press SPEED Qc and enter 200 then press ENTER. Wait for at least a 15 second
stabilization period after the altitude and airspeed achieve these new air data
parameter set point values to continue.
(7) Press LEAK MEASURE/CONTROL to change to LEAK MEASURE MODE.
(8) Press RATE TIMER.
(9) .Press F3
•After the Waiting and Timing intervals are complete, the DPS500 will display
Timed Rates.
(10) Check the maximum ROC is 100 ft/min or less and the maximum Rt CAS is 2 kt/min
or less.
(11) Press the LEAK MEASURE/CONTROL to return to CONTROL MODE.
(12) If no further maintenance is required, remove all of the Nav Aids test equipment from
the aircraft. Stow all the Air Data Accessories Kit ; (Nav Aids PN ADA500945)
equipment and Barfield Pitot/Static Tester DPS500.
6. Leak Testing the Barfield Pitot/Static Tester DPS450 and Connecting Hoses.
SUBTASK AMM-34-10-00-071-701-003
* * * ALL
A. If leakage is excessive during the left and right Pitot and Static System Leak Test for
unpressurized aircraft, do the following test with the Barfield Pitot/Static Tester DPS450:
CAUTION: DO NOT OVER TIGHTEN HOSES. DAMAGE MAY OCCUR TO TEST
EQUIPMENT. HOSES SHOULD BE SNUG.
(1) Connect the Nav Aids Hose E500-7270 (approximately 8 feet long) to the Barfield
Pitot/Static Tester DPS450 Pt connector. Connect the other end of the E500-7270 to
the Pitot/AOA pressure test hose fitting. Connect the pressure test hose fitting to the
PT421-4520 Pre-Test Probe.
(2) Connect the Nav Aids Hose E500-5160 (approximately 4 feet long) or (E500-5170 is
acceptable) to the Barfield Pitot/Static Tester DPS450 Ps connector. Connect the
other end of the E500-5160 to the Static Port Adaptor (Nav Aids, SS53515-4-4).
Connect the Static Test Adaptor to the PTS515 Pre-Test Plate.
(3) Power on the Barfield Pitot/Static Tester DPS450. Wait two minutes for the Barfield
Pitot/Static Tester DPS450 to confirm the settings.
•After a successful self-test sequence, the system changes to the Leak Measure
mode.
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(4) Skip this step if the Barfield Pitot/Static Tester DPS450 is in Quad mode. Quad mode
will display four values: Ps, RtPc, Qc, RtQc. Press SETUP, press F1 to select
Display. Press F3 to select Quad. Make sure that Alt is in ft, CAS is in kts and Rt
CAS is in kts/min. If not, press F2 to select Units, press F1 to select ft Kts ft/min and
press F4 to save settings. Press Clear/Quit to return to the Main Menu displayed in
the upper right corner.
(5) Press ALT Ps, ROC RATE Ps, SPEED Qc, and RATE to display the appropriate air
data parameters.
(6) Press CLEAR QUIT for the Main Menu displayed in the upper right corner. Several
attempts of pressing the CLEAR/QUIT button may be needed to return to the Main
Menu.
(7) Press LEAK MEASURE/CONTROL to scroll to the CONTROL MODE displayed in
lower left corner.
(8) Press ROC RATE Ps to select the ROC control aim. Using the keypad, enter 4000
and press ENTER. Press ALT Ps to select the altitude control aim, enter 10000 and
press ENTER.
•The ROC and ALT control aim values will be updated.
(9) Press SPEED Qc, enter 200 then press ENTER. Wait for at least a 15 second
stabilization period after the ROC and CAS achieves the new air data parameter set
points values before moving to the next step.
(10) Press LEAK MEASURE/CONTROL to change to LEAK MEASURE MODE.
(11) Press F1 to select Rate Timer and then press F3 to select Set Wait. Press 0.3 and
then Enter.
(12) Press F4 to select Set Time, press 0.3 and then ENTER.
•The Set Wait and Set Time will both be updated to 00m.30s.
(13) Press F1: Start Timer.
•The display starts the count down Waiting timer followed by the Timing timer.
After the Timing timer has expired, the ROC and Rt CAS will display Timed Leak
Measure with the final values. Record these values.
•Make sure that the ROC is less than ±25 ft/min and Rt CAS is less than ±0.25 kt/
min.
(14) Press CLEAR QUIT to return to the main menu.
(15) Press LEAK MEASURE/CONTROL to return to CONTROL MODE.
(16) Press GROUND to go to atmospheric pressure. Press F1 to select [Yes] to confirm.
(17) After the Barfield Pitot/Static Tester DPS450 displays the SAFE AT GROUND
prompt, power off the test set and remove the hose caps.
(18) Return to the test section previously run to incorporate the values from Leak Testing
the Barfield Pitot/Static Tester DPS450 and Connecting Hoses section.
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7. Angle of Attack Test
SUBTASK AMM-34-10-00-071-701-004
* * * ALL
NOTE: If a Barfield Pitot/Static Tester DPS450 is used for this test complete paragraph
A. If a Barfield Pitot/Static Tester DPS500 is used, go to paragraph B.
A. Angle of Attack Test with the Barfield Pitot/Static Tester DPS450:
Procedure is given for the left side and is the same for the right side.
Refer to Fig. 502, Sheet 1
(1) Connect the WOW Box or AMC to the aircraft and make sure that the ECB's are
collared. Refer to SUBTASK AMM-34-10-00-071-921-001.
(2) Select WOffW on the WOW test box or select WOffW on the AMC.
(3) Set the transponder to STBY on the PFD.
(4) Make sure both the left and right PFD baro are set to 29.92 by using the BARO SET
knob on the (ACP) Autopilot Control Panel. Also make sure that the baro setting
matches on the left and right PFD.
NOTE: Refer to step (5) if using the Air Data Accessories Kit ; (Nav Aids PN
ADA500945) or step (6) if using the Air Data Accessories Kit (NavAids P/N
ADA500MD-945).
(5) Connect the Barfield Pitot/Static Tester DPS450 to the aircraft using the Air Data
Accessories Kit ; (Nav Aids PN ADA500945) as follows:
CAUTION: DO NOT OVER TIGHTEN HOSES. DAMAGE MAY OCCUR TO
TEST EQUIPMENT. HOSES SHOULD BE SNUG.
NOTE: The Pitot/AOA probes with a drain hole near the base of mast, must
have the drain hole covered. Failure to do so will result in a failure of this
test.
(a) Install the Pitot/Angle of Attack (AOA) Probe Adaptor (Nav Aids,
APA94520-4-4-4) (7) with the label TOP facing up on the Pitot/AOA probe. If
needed, lubricate with Pitot adaptor Lubricating fluid Part Number LF5050. Adjust
the Pitot/AOA Probe Adaptor nozzles to align with the holes of the Pitot/AOA
probe.
(b) Connect the Pitot Test Hose Assembly (long hose) (3) to the Pt connection (2) on
the Barfield Pitot/Static Tester DPS450. Connect the other end of the long hose
(3) to the quick-connect cross (4) .
(c) Connect the Pitot Test Hose Assembly (two short hoses) (5 and 6) to the quick-
connect cross (4) . Connect the other ends of the two short hoses (5 and 6) to
the center and lower connections on the Pitot/AOA Probe Adaptor (7) .
NOTE: Make sure that the Pitot/AOA Probe Adaptor nozzles are still aligned with
the holes on the Pitot/AOA probe.
(6) Connect the Barfield Pitot/Static Tester DPS450 to the aircraft using the Air Data
Accessories Kit (NavAids P/N ADA500MD-945) as follows:
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(a) Remove the PS35210 Pressure Test Adaptor from the Pitot/Static probe.
(b) Remove the E500-7270 hose from the PITOT (end) connector of the PS35210
adapter and connect to a NAV Aids quick connect cross (leave other end of hose
connected to the Barfield Pt connector). Connect (2) LH and/or RH MFP Pitot
hoses approximately 2 ft long to the quick disconnect cross and then to the
Middle and Lower Nozzles of the NAV Aids APA94520MD-4-4-4 (or
APA94520-4-4-4) Pressure Test Adaptor.
(c) Connect another LH and/or RH MFP pitot hose approximately 2 ft long to the
upper nozzle of the APA94250 adapter. Connect the other end to a second NAV
Aids quick connect cross.
(d) Remove the other hose from the PS35210 pitot/static test adaptor and connect it
to the same quick connect cross as the upper hose of the APA94520 adapter.
(e) Attach an E500-5160 hose to the upper static test adaptor. Attach the other end
of the hose to the quick connect cross that is connected to the upper hose of the
APA94520 Pitot/AOA test adaptor.
(f) If needed Lubricate with Pitot adaptor Lubricating fluid Part # LF5050 (NOTE: No
other lubricating fluid is allowed) Insert an APA94520 adapter onto the Left Pitot
probe and adjust the PTA nozzles to align with the holes of the Pitot/AOA Probe
and adjust until the seals are snug. ( DO NOT over tighten)
(7) Power on the Barfield Pitot/Static Tester DPS450 (if needed).
•Wait for the Barfield Pitot/Static Tester DPS450 to finish a sequence of
pneumatic and internal system checks and the system changes to the Leak
Measure mode (shown, lower left display corner).
(8) Press LEAK MEASURE/CONTROL to select the CONTROL MODE.
(9) Press ALT Ps, enter 6000, and press Enter.
(10) Select F2 UNITS then select F3 inHg
•Units on the display change from kts/min to inHg.
(11) Press SPEED Qc, enter 0.5 inHg, and press Enter.
•Wait for at least a 15 second stabilization period after the Barfield achieves this
new air data set point value (within ± 2 feet & and ± 0.010 inHg).
(12) Record the airspeed on the left PFD.
•Expected results are 105.5 kts ± 2.5 kts.
(13) Press GROUND to go to the atmospheric pressure. Press F1 to select Yes to
confirm.
•The Barfield Pitot/Static Tester DPS450 displays shows for SAFE AT GROUND.
(14) Power off the Barfield Pitot/Static Tester DPS450.
(15) If no further maintenance is required, remove all of the Nav Aids test equipment from
the aircraft. Stow the Air Data Accessories Kit equipment and Barfield Pitot/Static
Tester DPS450. Also, refer to SUBTASK AMM-34-10-00-071-921-002.
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