31 Indicating/Recording Systems

 

TTP	B1-L3	ATA31
Beech 90 Series	B2-L3	Indicating/Recording Systems

31 INDICATING/RECORDING SYSTEMS

 -00 General 

-10 Instrument & Control Panels 

-20 Independent Instruments 

-30 Recorders 

-40 Central Computers 

-50 Central Warning Systems 

-60 Central Display Systems 

-70 Automatic Data Reporting Systems

The indicating and recording systems monitor and report the status of selected airplane systems. Advisory, caution, and warning lights in the cockpit inform the flight crew of each monitored system status.

Annunciator system 

Annuciator system consists of a warning/ caution/advisory panel. The warning (red), caution (amber), and advisory (green) annunciators are centrally located in the glare shield. A red MASTER WARNING flasher, an amber MASTER CAUTION flasher, and a PRESS TO TEST button are also part of the system. These are immediately to the left of the warning/caution/advisory annunciator panel.

The annunciators are the word-readout-type dis- play. Whenever a fault condition covered by the annunciator system occurs, a signal is generated and the appropriate annunciator is illuminated.

 

If the fault requires immediate attention and reaction, the appropriate red warning annunciator in the panel illuminates and the MASTER WARNING  flasher  begins  flashing.  Any  illuminated lens in the warning/caution/advisory annunciator panel remain on until the fault is corrected. However, the MASTER WARNING flasher can be extinguished by depressing the  face  of the MASTER WARNING flasher, even if the fault is not corrected.

When a warning fault is corrected, the  affected warning  annunciator  extinguishes, but the MASTER WARNING flasher continues flashing until depressed.

Whenever an annunciator-covered fault occurs that requires attention, but not immediate reaction, the appropriate amber caution annunciator illuminates, and the MASTER CAUTION flasher begins flashing.

The warning/caution/advisory annunciator panel also contains the  green advisory annunciators. There is no master flasher associated with these annunciators, since they are only advisory in nature, indicating functional situations which do not demand immediate attention or reaction. An advisory annunciator can be extinguished only by disengaging the condition/system indicated on the illuminated lens.

The warning annunciators, caution annunciators, advisory annunciators, MASTER WARNING flasher, and MASTER CAUTION flasher feature both a “bright” and a “dim” mode of illumination intensity. The “dim” mode is used automatically whenever all of the following conditions are met:

•  Generator is on the line

•  Master light switch is ON

•  OVERHEAD FLOOD LIGHTS are OFF

•  PILOT FLIGHT LIGHTS are ON

 

•  Ambient  light  level  in  the  cockpit  (as sensed by a photoelectric cell in the over- head light control panel) is below a preset value

 

Unless all of these conditions are met, the “bright” mode is selected automatically.

Lamps

Test the lamps in the annunciator system periodically and any time the integrity of a lamp is in

question. Depressing the PRESS TO TEST button, to the left of the warning/caution/advisory

annunciator panel in the glare shield, illuminates all  the  annunciator  lights,  MASTER WARNING flasher, and MASTER CAUTION flasher. Replace any lamp that fails to illuminate when

tested.

Integrated avionics processor system 

IAPS performs a part of the integration function required to interconnect and manage the various avionics systems in the aircraft.
The ICC-3000 IAPS card cage (ICC) provides an isolated  interface  between  the  resident line replaceable modules (LRMs) and external avionics units.

The ICC is a fully wired card cage containing:

 

•  Two configuration strapping units (CSUs)

•  Two flight guidance computers (FGCs)

•  One IAPS environmental controller (IEC)

 

•   Two independent input/output  data  concentrators (IOCs)

•   Two independent power supplies (PWRs)

The CSUs provide a matrix of configuration shunts  that  program  the  IAPS  specifically for operation on the King Air C90GTi aircraft. Each CSU provides configuration strapping for its half of the IAPS assembly. There is one OCM-3100 options configuration module (OCM) plugged on each of the two CSU-3100 CSUs. The OCM-3100 interacts with the IOCs to enable specific avionics options.

The two FGCs provide the autopilot and flight director functions, provide independent flight guidance computation, and operate  together to provide three axis autopilot, pitch trim, and rudder boost functions. The FGC-3000 receives attitude heading system data directly from the AHC and receives air data system, navigation radio, and flight management system (FMS) data through the IAPS IOC.

The IAPS environmental controller monitors the temperature  sensors  and  controls  cooling  fans and heaters to automatically regulate the IAPS environment.  The  temperature  sensors  are  on each half of the ICC motherboard.

The I/O concentrators provide a data management function by acting as a central data collection and distribution  point. These  concentrators  receive data  bus inputs from each  major LRU on the aircraft, process (sort) the data words, and then transmit to the receiving LRU as needed.

Maintenance   diagnostic   computer (MDC) module is on the right side of the IAPS card cage. Its function is to monitor the aircraft avionics and store diagnostic data  in memory. The MDC receives data from IOC and outputs data to IOC, MFD, and data base unit (DBU). The  MDC  memory  consists  of  programmable read only memory and nonvolatile random access memory. The programmable read-only memory contains executable routines required to perform MDC functions. The nonvolatile random access memory stores software variable maintenance tables, fault equations, and maintenance history logs.

Flight management computer (FMC) FMC-3000(No.1) in the IAPS card cage. There are also provisions for an optional FMC-3000 (No. 2). The FMC is a lateral and vertical navigator used by the autopilot to fly a programmed flight plan. The FMC also provides a navigation data base storage and several control/planning functions. The  FMC-3000  receives  input  from  the cross-side FMC counterpart (if installed), onside control display unit, and from the IOC. The FMC provides output bus to the cross-side FMC (if installed) onside MFD. The data base unit is used to update the data base memories of both FMCs.

The power supplies provide two separate power sources. One powers the left side LRMs and the associated portions of the ICC. The other powers the right side LRMs and associated portions of the ICC. The power supply protects itself and the LRMs from operation at excessive current levels or excessively high or low voltages and temperatures through internal monitoring and shutdown circuitry.

Built-in  system  diagnostics  monitor  reporting line replaceable units (LRUs) in the avionics system and show both dynamic status reports and recorded fault history logs. Use these diagnostics to test and troubleshoot the avionics system. The system includes a maintenance  diagnostic computer and a data base unit.

MFD Maintenance Access

The technician enables the MFD MAINTENANCE MAIN MENU by setting the maintenance switch to ON, The FCS and MDC annunciations show next to the line-select-keys on the left side. Push the FCS line-select-key to access the FCS DIAGNOSTICS page or push the MDC line- select-key to access the MDC MAINTENANCE MAIN MENU page.

 

The system has the capability to provide the following information:

•  CURRENT FAULTS

•  AIRCRAFT HISTORY

•  ATA INDEX

•  LRU INDEX OPERATIONS

•  MDC SETUP

•  CONFIGURATION DATA

•  REPORT DOWNLOAD

PTP  Beech 90 Series	B1	LOC	FOT	SGH	R/I	MEL	TS
	B2	LOC	FOT	SGH	R/I	MEL	TS

Instruments - Check general condition and markings for legibility.
 Instrument Lines, Fittings, Ducting, and Instrument Panel Wiring - Check for proper routing, support, and security of attachment.