Honeywell MK VIII, MK XXII manual System Maintenance Maintenance Philosophy, BIT Description

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EGPWS LINE MAINTENANCE MANUAL

2.3 SYSTEM MAINTENANCE

2.3.1 MAINTENANCE PHILOSOPHY

The EGPWS is an “on-condition” only maintenance system. No scheduled maintenance is required. This is accomplished by both continuous Built-In-Test (BIT) and event initiated test functions. Event initiated test refers to both power-up tests and manually activated Self-Tests. Results of these functions are indicated by system status indicators and messages so that the systems functionality can be assessed.

Detected faults are indicated to the flight crew during normal flight operations by system status annunciators or flight display (EFIS) messages in the cockpit (i.e., GPWS INOP or FAIL, W/S INOP or FAIL, TERR INOP or NOT AVAILABLE). On the ground, system status indications are expanded to direct fault isolation to the fault source whether internal or external to the EGPWC. Several levels of reporting are provided by the EGPWS Self-Test, and multiple means are provided to access the information. The intent is to provide information that will encourage the line mechanic to correct the real problem through clear fault messages and minimal effort.

2.3.2 SYSTEM OPERATION DURING AN INOP CONDITION

EGPWS continued airworthiness is predicated on system status indications. An indication of TERR INOP (only) or NOT AVAILABLE (only) is likely to indicate a loss of necessary GPS data for performing Terrain Alerting and Display functions, but has no effect on basic GPWS (Modes 1-7) functions. Additionally, a GPWS INOP (only) indicates a loss of basic GPWS functions, but this could be limited to say Mode 4 only because of a loss of necessary data required for that mode alone. In any case, the EGPWS will provide alerting based on the current capability of the EGPWC and its inputs.

For the MK VI and MK XXII, consideration should be given to any operation that will cross the boundaries of the regional database. Although this has no affect on the basic GPWS functions, the enhanced (TAD/TCF) functions will become inoperative once the aircraft leaves the database region. This is indicated by the TERR INOP or NOT AVAILABLE status indicator and the loss of terrain display when enabled and active.

2.3.3 BIT DESCRIPTION

The EGPWC contains an extensive BIT capability. The BIT functions provide high confidence that the Warning Computer and interface signal sources are operating properly, and that the EGPWS will perform its intended function. Detected failures are indicated via GPWS INOP, Windshear INOP, and Terrain INOP/NA annunciations and on the ARINC 429 bus output. Failures detected during flight are saved in the flight history and are enunciated during Level 4 of the cockpit Self-Test. BIT status is also available through the RS-232 port by use of a PC or terminal.

If the EGPWC detects an internal Warning Computer fault, it will turn on all the INOP lights. If the EGPWC detects an external input fault, it may or may not turn on the INOP light(s) depending on the input fault, the type of installation, and whether the aircraft is airborne or on the ground.

The EGPWC BIT performs three types of functions: Operation Monitoring, Operation Tests, and Restricted Tests.

Operation Monitoring consists of software checks that are performed as part of the normal Warning Computer processing. Operation Monitoring includes checks of data values and program flow control variables used for the warning computations to ensure they are within expected ranges. The statuses of various EGPWC hardware sub- systems are continuously verified including core processor checks, voice generator circuitry checks, and ARINC 429 wrap-around tests. Operation Monitoring also includes extensive testing of the input signals to ensure the EGPWC is using proper data for its calculations.

Operation Tests run during normal operation without disrupting the EGPWC warning calculations or annunciations. Operations Tests include CPU instruction set tests, A/D tolerance tests, ROM check-sum verification tests, and non- destructive RAM tests. Operation Tests are scheduled by the operating system to be performed between the routines required for normal operation.

Restricted Tests destroy data or take an excessive amount of time to complete and cannot be run during normal system operation. These tests are usually run during system power up or during a cockpit initiated Self-Test.

CAGE CODE: 97896

SCALE: NONE SIZE: A DWG NO.: 060-4199-180

REV: G

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Contents Egpws Line Maintenance Manual Drawn Revisions DescriptionDate ApprovedEFF PT 14A Disp USE Table of Contents Maintenance Practices 10.1 MK V Egpwc Part Numbers MK VII Egpwc Part Numbers Introduction ScopeApplicability Reference Documents MK VI, MK VIII, MKDescription and Operation General System Description Enhanced Ground Proximity Warning SystemOperation Mode 1 Excessive Descent Rate Mode 2A/2B Terrain Closure RateMode 3 Descent After Takeoff Mode 4A/4B/4C Unsafe Terrain ClearanceCallout Description Mode 5 Descent below GlideslopeMode 6 Advisory Callouts Optional Smart Five Hundred Mode 7 Windshear Detection Optional for MK V/VII only Excessive Bank Angle CalloutTail Strike Callout Envelope Modulation not Available in MK VI/VIIITerrain and Obstacle Database Runway DatabaseTerrain Alerting and Display Optional Weather Radar Autotilt MK V and MK VII only Peaks Display Mode OptionalGeometric Altitude GPS Required Altimeter Monitor Option for MK V and MK VII only System Display and AnnunciationStabilized Approach Monitor Option for MK V and MK VII only Long Landing Monitor Option for MK V and MK VII only LOW Airspeed Monitor MK V Boeing 737NG onlyBelow Lamp FormatBIT Description System Maintenance Maintenance PhilosophySystem Operation During AN Inop Condition Front Panel Test Connector Egpwc Front PanelEgpws Status LED’S Front Panel SELF-TEST Interface MK V and MK VII onlySELF-TEST Functions External Computer Fault Fail Corrective Action Fault Isolation Troubleshooting GeneralTroubleshooting Guide Level 1 SELF-TEST GO/NO GO Test SELF-TEST PreambleShort Level 1 SELF-TEST Gpws INHIBITED, Terrain InhibitedGpws Inhibited SELF-TEST InhibitedLevel 2 SELF-TEST Current Faults Long Level 1 SELF-TESTCurrent Faults Internal Current Faults ExternalFault Example Reason Bussignal Fault BUS Wiring FaultFlap Switch Fault Gear Switch FaultProgram PIN Read Error System or Mode Tasked FailedCallouts Option Invalid Audio Menu InvalidSheet 31 Terrain AWARENESS-POSITION Error Terrain Clearance Floor Position ErrorTerrain Awareness no Valid Latitude Terrain Awareness no Valid LongitudeLevel 3 SELF-TEST System Configuration Following Information is Given in the Level 3 SELF-TESTIRS 1 Attitude Mode Selected Egpws Line Maintenance Manual Level 4 SELF-TEST Fault History Following Information is Given in the Level 4 SELF-TESTFollowing Information is Given in the Level 5 SELF-TEST Level 5 SELF-TEST Alert HistoryLevel 6 SELF-TEST Discrete Input Test 3 +28V Landing Gear Discrete Arinc 552 / ALT 55 Radio Altitude Validity Flag DiscretesGND Landing Gear Discrete GND Landing Flap Discrete or Flap Override 5 +28V Landing Flap or Flap Override DiscreteFlap Position Discretes SELF-TEST DiscreteSteep Approach Discretes Steep Approach Discrete #1 MK V and MK VII onlySteep Approach Discrete #2 GND ILS Tuned Discrete10 +28V ILS Tuned Discrete Glideslope Validity DiscretesGND Glideslope Cancel Discrete GND Glideslope Inhibit Discrete13 +28 V Glideslope Inhibit Discrete Decision Height DiscreteMode 6 Volume Control Discrete Callouts Enable Discrete MK V and MK VII onlyGND Audio SUPPRESSINHIBIT/ALL Modes Inhibit Discrete 19 +28 V Audio SUPPRESSINHIBIT/ALL Modes Inhibit DiscreteAOA Validity Discretes MK V and MK VII only Display Select DiscretesTerrain Awareness & TCF Inhibit Simulator Reposition MK V and MK VII onlyWeather Radar ON/OFF Localizer Validity Discretes MK V and MK VII onlyAttitude Validity Discretes Airspeed Validity DiscreteBarometric Altitude Rate Validity Discretes Acceleration SELF-TEST in Progress DiscreteLongitudinal Acceleration Validity Discrete Normal Acceleration Validity DiscretePLI Deselect Switch Discretes MK V and MK VII only Magnetic Heading Validity DiscreteAOA Vane Heater Discrete Autopilot Disconnect DiscretesTactical Select Discrete Altitude Alert DiscreteCorrected Barometric Altitude Validity Discrete Momentary Flap Override DiscreteWeight on Wheels Discrete Raas Enable Discrete MK V and MK VII onlyGpws Inhibit Discrete Raas Inhibit Discrete MK V and MK VII onlyLOW Airspeed Monitor Inhibit Discrete MK V 737NG only Maintenance Practices General Database UpdateDatabase Update Frequency Loading a DatabaseObtaining AN Egpws Flight History Download Card Download ProcedureFlight History Downloading Transcription of the Pcmcia Card Via email aerotechsupport@honeywell.comSheet 54 CFG CAT 7 92 T CUW command/data string REMOVAL/INSTALLATION 6.1 Egpwc Removal InstallationConfiguration Module MK VI, MK VIII, and MK Xxii only Servicing GeneralEgpws Ground Tests Display Switching Relays if InstalledADJUSTMENT/TEST Adjustment Repairs General CLEANING/PAINTING GeneralINSPECTION/CHECK General Appendix a Winviews Appendix B Troubleshooting DO’S and do NOT’S Appendix C Raas Maintenance Messages Aural & Displayed Maint Function MessageMaint Function Displayed Message RAAS-NA-xxxx amber RAAS-RTO green RAAS-INOP amberAppendix D Stabilized Approach Monitor Maintenance Messages Self-Test Level 3 RCD Part NumberAppendix E Altimeter Monitor Maintenance Messages Self-Test Level 1 Flaps Monitor Inop Appendix G Long Landing Monitor Maintenance Messages Appendix H LOW Airspeed Monitor Maintenance Messages Self-Test Level 3 Airspeed Low Inhibited Annunciated at

MK VIII, MK V, MK XXII, MK VII, MK VI specifications

Honeywell's range of control systems, particularly the MK VI, MK VIII, MK VII, V, and XXII, are pivotal innovations that have revolutionized process automation and control in various industries, especially in power generation and oil and gas sectors. Each of these systems comes with unique features and technologies to enhance operational efficiency, safety, and reliability.

The Honeywell MK VI control system is renowned for its ability to provide effective plant control and management tools, featuring advanced operator interfaces and robust hardware components. It employs a modular design, which allows for easy scalability and integration into existing infrastructure. The MK VI is equipped with Ethernet-based communication protocols, ensuring high-speed data transfer and enabling seamless connectivity with other systems.

The MK VIII system takes automation a step further, emphasizing enhanced performance and reliability. With its built-in redundancy and advanced diagnostics, the MK VIII minimizes downtime and optimizes maintenance efforts. Its powerful software tools are designed to improve operator decision-making, providing critical insights into plant operations and trends.

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The MK V system is one of Honeywell's legacy products, known for its simple and user-friendly interface. Despite its age, it continues to be a dependable choice for many plants. It offers solid performance with basic control functions and has been a reliable backbone for older facilities transitioning into newer technologies.

Lastly, the MK XXII brings a modern twist to control systems with its focus on cybersecurity and data analytics. This system takes advantage of big data and IoT technologies, providing enhanced visibility of operations through real-time monitoring and predictive maintenance capabilities. The MK XXII ensures that plants not only operate efficiently but also mitigate risks associated with cyber threats.

Overall, Honeywell's series of control systems showcases their commitment to innovation and reliability in process automation, catering to the diverse needs of contemporary industrial environments. Each system is designed with specific features and capabilities that address the evolving challenges of process control, ensuring that users can achieve optimal performance and safety in their operations.
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