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barfield DC400 User Instruction Supplement

Adapter module
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DC400 &
DC400A
Copyright © 2020 Barfield Inc. All Rights Reserved.
Adapter Module
USER INSTRUCTION SUPPLEMENT
M/N: DC400 & DC400A
P/N: 101-00802
Doc. P/N: 61-101-00802.EF1
Revision J
September 4, 2020
_________________________________________
MOD C, used with
DC400 or DC400A
P/N 101-00800 or P/N 101-00850
Digital DC Fuel Quantity Test Sets
KING AIR MODELS
100, A100, B100, 200, B200 / GT / GTi,
250, 300, 350 / 350i, 360, C90,
C90A / B / GT / GTi / GTx, E90, F90
BEECHCRAFT C99
For
and

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  • Page 1 KING AIR MODELS 100, A100, B100, 200, B200 / GT / GTi, 250, 300, 350 / 350i, 360, C90, C90A / B / GT / GTi / GTx, E90, F90 BEECHCRAFT C99 Copyright © 2020 Barfield Inc. All Rights Reserved.
  • Page 2 Barfield Inc. Confidential and Proprietary Information. This document and all the information contained herein is the sole property of Barfield Inc. No intellectual property rights are granted by the delivery of this document or the disclosure of its content.
  • Page 3 Inquiries should include specific questions and reference the publication title, number, chapter, page, figure, paragraph, and effective date. Please send comments to: TECHNICAL CUSTOMER SUPPORT - GSTE BARFIELD, INC. P.O. BOX 025367 MIAMI, FL 33102-5367 Telephone: (305) 894-5400...
  • Page 4 In case of malfunction, contact the manufacturer to obtain the list of approved repair facilities worldwide, ensuring that this equipment will be serviced using proper procedures and certified instruments. BARFIELD PRODUCT SUPPORT DIVISION Telephone (305) 894-5400 Shipping Address: (800) 321-1039 Barfield, Inc.
  • Page 5 System Wiring Integrity Test. Moved Probes Bench Test to Chapter 3. Corrected Step #s, Table and Figure references 260-00973 June 4, 2013 In Section 5. 260-01076 January 7, 2015 Updated Barfield logos. 260-01274 September 4, 2020 Complete revision. 61-101-00802.EF1 Revision J Page | v...

  • Page 6: Table Of Contents

    TABLE OF CONTENTS Contact Information / Recertification Maintenance & Repair Information Revision Record Table of Contents PAGE GENERAL INFORMATION .................... 1 APPLICABILITY ......................1 CAPABILITIES ........................ 1 PANEL CONTROLS ......................1 AIRCRAFT SYSTEM DESCRIPTION ................1 PRECAUTIONS ......................2 PRELIMINARY ........................ 2 DISCLAIMER ........................

  • Page 7: General Information

    This manual is one of a family of manuals, each developed to address an individual Adapter Module especially designed for the DC400 / DC400A Digital Fuel Quantity Test Sets. It contains complete instructions for the maintenance, inspection, testing, troubleshooting, and calibration of the Gull Airborne and Ragen Data Fuel Quantity Systems.

  • Page 8: Precautions

    Failure to calibrate the system could result in an inaccurate fuel quantity indication. 8. DISCLAIMER BARFIELD, INC., neither a vendor nor supplier of fuel quantity indicating systems or an airframe manufacturer, has no control over testing and calibration values and procedures.

  • Page 9: Recertification

    9. RECERTIFICATION Barfield Adapter Module, P/N 101-00802, has a one-year recertification requirement. Qualified technicians in a shop equipped with the necessary tooling, facilities, and Barfield- approved procedures must perform the maintenance required by this unit. Please, refer to the Maintenance and Repair Information for approved repair facilities.

  • Page 10: Chapter 1: Operation

    CHAPTER 1: OPERATION 1. INSULATION MEASUREMENT TEST Note: Refer to Precautions and Preliminary in General Information section. Note: This test may be performed with either wet or dry tanks. A. Aircraft Preparation (1) Disconnect aircraft battery. CAUTION: WHEN LOWERING OR RAISING PILOT FUEL PANEL, ENSURE AIRCRAFT BATTERY IS DISCONNECTED.
  • Page 11 Aircraft Wiring Do not connect Figure 2 Insulation Test D. Insulation Test (1) Set T/S ON / OFF switch to ON. (2) Allow time for the T/S display to stabilize. Note: On those occasions when display stabilization cannot be achieved, take the reading after being performing this Test for 30 seconds.
  • Page 12 (8) Connect aircraft battery. (9) Close circuit breakers. (10) Set aircraft fuel panel select switch to AUX / NAC and hold (if applicable). a. The battery switch must be in the ON position for all airplanes except the model C90 / C90A / B / GT / GTi / GTx. b.

  • Page 13: Capacitance Measurement Test

    2. CAPACITANCE MEASUREMENT TEST Note: Refer to Precautions and Preliminary in General Information section. Note: This test must be performed with tanks drained or full. A. Aircraft Preparation (1) Disconnect aircraft battery. CAUTION: WHEN LOWERING OR RAISING PILOT FUEL PANEL, ENSURE AIRCRAFT BATTERY IS DISCONNECTED.
  • Page 14 Figure 4 Capacitance Test D. Test Note: If the CONTINUITY light is illuminated it means that the DC400/A Oscillator Circuit is overloaded. The most probable cause is a short circuit on the LO-Z wire. (1) Set the T/S ON / OFF switch to ON.
  • Page 15 C90, C90A / B / GT / GTi / GTx & C99 Total Nacelle Only Aircraft Type Min. Nom. Max. Min. Nom. Max. C90, C90 / B / GT /GTi / GTx 151.5 164.8 177.0 57.3 63.3 69.3 147.5 160.4 173.0 53.3 58.7...

  • Page 16: Indicator Test

    (9) Push and hold the PRESS TO READ CAP (pF) pushbutton. (10) Verify the tanks’ value is within tolerances as specified in Table 2 (Empty) and Table 3 (Full). Note: Verify that capacitance is within specifications. If a test in not within specification, isolate the fault by referencing the aircraft wiring schematics and disconnecting the probes and / or the aircraft wiring at connecting junctions.
  • Page 17 C. Connecting Test Set (1) Connect T/S as per Figure 5 or Figure 6 and the following steps. Note: Figure 5 depicts the use of Adapter cable P/N 101-00831 for conversion to systems with circular style connectors. (2) Connect T/S IND connector to Indicator. (3) Connect T/S ACFT connector to aircraft wiring plug.
  • Page 18 (3) Press and hold PRESS TO READ CAP (pF) pushbutton while adjusting CAP SIM (pF) control knob to obtain a T/S reading of 189.0 pF. (4) Rotate the TEST FUNCTION switch to IND AMP. (5) Connect the aircraft battery. (6) Close the circuit breakers. (7) Turn the aircraft battery ON / OFF switch ON.
  • Page 19 (30) Repeat steps D.2 through D.29 until an accurate gage adjustment is obtained. (31) Set the MAIN / TOT – AUX / NAC switch to MAIN / TOT. (32) Rotate the TEST FUNCTION switch to CAP SIM CAL (NORM SYS). (33) Set the 200 (pF) / 1000 (pF) switch to 1000 (pF).

  • Page 20: Preferred Calibration Test

    4. PREFERRED CALIBRATION TEST Note: Refer to Precautions and Preliminary in General Information section. Note: When draining facilities are not readily available, the Alternate Calibration Procedure (see Chapter 2, section 3. ALTERNATE CALIBRATION (WET TANKS)) may be used as a temporary measure. Note: The preferred calibration is done with dry tanks.
  • Page 21 Aircraft Add for Full Simulator (pF) C90, C90A / B / 91.6 GT / GTi / GTx, C99 100-380006-93, -121, -179 100-380006-15/-17 & -95, -123, or -181 Tank Units (Transmitters) Tank Units (Transmitters) A100, B100, E90 95.3 95.0 200, 250 93.4 93.1 300, 350 / 350i, 360...

  • Page 22: System Wiring Integrity Test

    (3) Disconnect T/S IND connector from the Indicator. (4) Reconnect aircraft wiring plug to Indicator. (5) Return the aircraft to its original configuration. 5. SYSTEM WIRING INTEGRITY TEST Note: Refer to Precautions and Preliminary in General Information section. Note: Ensure that the Insulation, Capacitance, Indicator test and Preferred Calibration have all been accomplished with satisfactory results and that the tanks are still dry prior to attempting this test.
  • Page 23 Record the capacitance value measured. Release the pushbutton. Rotate the TEST FUNCTION switch to CAP SIM CAL (NORM SYS). Set the CAP SIM (pF) 100’s and the 10’s thumbwheels to the closest approximation of the recorded value of step 4. Press and hold the PRESS TO READ CAP (pF) pushbutton while adjusting the CAP SIM (pF) control knob to obtain the recorded value of step 4.
  • Page 24 (21) Press and hold PRESS TO READ CAP (pF) pushbutton while adjusting CAP SIM (pF) control knob to obtain a T/S reading according to Table.4. (22) Release the pushbutton. (23) Rotate the TEST FUNCTION switch to ADD CAP. (24) Verify the indicator reads 1300 lbs. CAUTION: DO NOT TAP BEZEL OF INSTRUMENT TO VIBRATE.
  • Page 25 (38) Rotate the TEST FUNCTION switch to PROBE(S). (39) Set the T/S ON / OFF switch to ON. (40) Set the aircraft fuel panel select switch to AUX / NAC and hold if applicable. (41) Push and hold the T/S PRESS TO READ CAP (pF) pushbutton. (42) Record the capacitance value measured.
  • Page 26 Note: Do NOT spray contact cleaner on the individual Matrix type connectors. c. If cleaning the connectors does not yield satisfactory results, it may become necessary to de-pin and inspect each Matrix type connector. Replace any matrix type blocks that are suspect. Note: When cleaning the connectors be sure to include the T/S’s connectors.

  • Page 27: Chapter 2: Alternate Tests

    CHAPTER 2: ALTERNATE TESTS 1. PROBES BENCH TEST Note: Refer to Precautions and Preliminary in General Information section. A. Test Set Preparation (1) Set the T/S ON / OFF switch to OFF. (2) Rotate the TEST FUNCTION switch to PROBE(S). (3) Set the INSULATION / SYSTEM switch to SYSTEM.
  • Page 28 (4) If value is not within tolerance, reject probe. Note: The following values are valid as of this publication’s release date and are provided as a reference. Refer to the Aircraft Maintenance manual for actual test values. Aircraft C90, C90A / B / GT / GTi / GTx & C99 Tank Unit Beech Probe P/N Min.
  • Page 29 Aircraft Tank Unit Beech Probe P/N Min. Nom. Max. Aircraft with 100-380006-59 Harness A100, B100, Bulkhead Cable Assy. 100-380006-59 16.8 21.8 26.8 200, 250, Cable Assy & Integral 100-380006-15, -17, 41.5 46.5 51.5 300 / 350i, Tank Units 360, E90 Aircraft with 100-380006-99, -127 Harness Cable Assy &...
  • Page 30 Aircraft 200, 250, 300, 350 / 350i & 360 Tank Unit Beech Probe P/N Min. Nom. Max. Leading Edge Inboard 100-380006-11, -69, -105, -139, -143, -175 40.3 44.8 49.3 Leading Edge Outboard 100-380006-55, -81, -115, -177 32.1 35.7 39.3 Inboard Aft 100-380006-37, -71, -107, -141, -145, -173 24.5 27.2 29.9...
  • Page 31 (14) With the INS TEST POINT switch at SIG / RTN position, verify the T/S display shows a value between 1500 and an “over range” of 1. Note: Ensure conductance is within specifications. If test results are outside limits, repeat test. (15) Set ON / OFF switch to OFF.

  • Page 32: Indicator Bench Test

    E. Disconnecting/Reconfiguring (1) Disconnect the test leads from the DISCRETE LEVEL SENSOR. (2) Disconnect the test leads from the T/S. 2. INDICATOR BENCH TEST Note: Refer to Precautions and Preliminary in General Information section. Note: Failure to calibrate the system after performing the indicator bench test will result in an inaccurate fuel quantity reading.
  • Page 33 Figure 10 Indicator Bench Test C. Test (1) Set the T/S ON / OFF switch to ON. (2) Set the CAP SIM (pF) 100’s to 1. Set the 10’s thumbwheels to 8. (3) Press and hold the PRESS TO READ CAP (pF) pushbutton while adjusting CAP SIM (pF) control knob to obtain a T/S reading of 189.0 pF.
  • Page 34 (19) Rotate the TEST FUNCTION switch to CAP SIM CAL (NORM SYS). (20) Set the 200 (pF) / 1000 (pF) switch to 200 (pF). (21) Set the CAP SIM (pF) 100’s thumbwheel to “-”. Set the 10’s thumbwheel as follows: a.

  • Page 35: Alternate Calibration (Wet Tanks)

    (48) Rotate the TEST FUNCTION switch to IND AMP. (49) Verify the indicator reads 900 ± 35 lbs. (50) Set the 28 VDC power supply to OFF. (51) Set the T/S ON / OFF to OFF. D. Disconnecting/Reconfiguring (1) Disconnect 28 VDC power supply. (2) Disconnect the T/S from the Indicator.
  • Page 36 Note: Figure 11 depicts using Adapter Cable 101-00831 for conversion to systems with circular style connectors. Aircraft Wiring Figure 11 Alternate Calibration (with 101-00831 Adapter) Aircraft Wiring Figure 12 Alternate Calibration D. Test (1) Set the T/S ON / OFF switch to ON. (2) Set the CAP SIM (pF) 100’s and the 10’s thumbwheels to the digits necessary to adjust the T/S display to a MAIN / TOTAL EMPTY nominal value listed in Table 2 for the aircraft under test.
  • Page 37 (8) If pointer position is not acceptable, adjust EMP 1 / E 1 adjustment for the pointer position. (9) Rotate the TEST FUNCTION switch to CAP SIM CAL (NORM SYS). (10) Set the 200 (pF) / 1000 (pF) switch to 1000 (pF). (11) Set the CAP SIM (pF) 100’s and the 10’s thumbwheels to the digits required to adjust the T/S display to a MAIN / TOTAL FULL nominal value for the aircraft listed in Table 3.

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