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The ST3400 uses Sandel’s patented rear-projection display technology. The
projector uses a miniature active-matrix LCD display that produces a high-
resolution image that is rear-projected directly to the face of the instrument. This
technology allows the displayed image to extend to the edges of the instrument’s
bezel. The advantage of this edge-to-edge technology is that it eliminates the
unusable area surrounding conventional LCD and CRT displays. Even though the
Sandel display is in a 3-inch form factor, its image is near the size of a 4” primary
display, and it remains directly in the pilot’s field-of-view.

The ST3400 includes built-in warning and caution annunciation. The unit also
supports optional external warning or caution annunciation.

The ST3400 may be installed in a pilot-only or dual pilot/copilot configuration.

The ST3400 has an internal recorder that automatically records ten hours of flight
data. This data can be reviewed for content in the event of a system malfunction.

1.2.2 TAWS Description

TAWS is the enhanced terrain warning technology that replaces the older GPWS
(Ground Proximity Warning System) technology. It is also known as EGPWS
(Enhanced GPWS).

TAWS adds two new and critical capabilities, FLTA (Forward Looking Terrain
Avoidance) and PDA (Premature Decent Alert) to the standard GPWS functions.

The six standard GPWS functional modes are:

•

ERD (excessive rate of descent)

•

ECRT (excessive closure rate to terrain)

•

ALAT (altitude loss after takeoff)

•

FITNL (flight into terrain when not in landing configuration)

•

EDGSD (excessive downward glide slope deviation).

•

500’ Voice Callout

The ST3400 can be configured either as a Class A TAWS compliant system or as
a Class B TAWS compliant system depending on the availability of radar
altimeter and airdata.

When configured as a Class B TAWS system, the ST3400 exceeds Class B
TAWS requirements. Even in Class B mode without radar altimeter, the ST3400
has additional Class A features such as a display and an excessive glide slope
deviation alert. See the POH for additional information

CLASS A TAWS FUNCTIONAL REQUIREMENTS

Mode

Function

FLTA

Forward Looking Terrain Alert

PDA

Premature Descent Alert

GPWS Mode 1

Excessive Rate of Descent

82002-IM-L

ST3400 INSTALLATION MANUAL

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Содержание ST3400

Страница 1: ... With Traffic Capability Installation Manual Document No 82002 IM Revision L 08 18 16 SANDEL AVIONICS 2401 DOGWOOD WAY VISTA CA 92081 PHONE 760 727 4900 FAX 760 727 4899 WEBSITE WWW SANDEL COM EMAIL SUPPORT SANDEL COM ...

Страница 2: ... 6XX 7XX equipment selections 82002 10 3 Audio relay orientation corrected 82002 10 5 Pin corrections Notes updated 82002 10 6 Updated to show additional grounds 82002 10 7 Pin corrections 82002 10 23 New drawing for Garmin GTN 6XX 7XX added J1 09 01 04 Incorporated A R 740 Added error message list J 08 05 04 Incorporated A R 717 Added information about Mod A Speaker Audio Added Airdata AZ 648 Int...

Страница 3: ...Part Number of ST3400 Class B Gray Added GPS interface Trimble 2101 I O Added Airdata IS S ADDU Added separate TCAS Inhibit Output Added Configuration Module Description F 4 15 03 Incorporated A R 626 Note about C92 GPWS systems HDG added to Req d equip list Note added in GEAR section about fixed gear aircraft Note on flaps in takeoff configuration Added GPS interface King KLN94 Added Airdata Coll...

Страница 4: ...2 02 Incorporated A R 572 4 9 Added Signal Characteristics Table 4 5 4 7 Reformatted pin tables Added signal characteristics to pin tables D 09 25 02 Incorporated A R 564 Flaps changed to required input RA1 FAIL and RA2 FAIL added Windshield Wiper shared with RA2 FAIL Note on configuration module Added Gamin 165 GPS Interface Added Penny Giles Airdata C 06 18 02 A R 547 Software 1 04 1 05 Notes OA...

Страница 5: ...al Characteristics 1 15 1 4 Interface Characteristics 1 16 1 5 Part Numbers 1 17 1 5 1 ST3400 Part Number 1 17 1 5 2 Installation Kit Part Number 1 17 1 6 License Requirements 1 17 1 7 Technical Standard Order Stipulation 1 18 1 8 Installation and Operational Approval Procedures 1 18 2 INSTALLATION PLANNING 2 1 2 1 General Information 2 1 2 2 Allowed Sensor Configuration Matrix Class A 2 1 2 2 1 R...

Страница 6: ...4 Flaps 3 2 3 5 Landing Gear 3 2 3 6 Autopilot 3 2 3 7 Audio Panel 3 3 3 8 GPS FMS 3 3 3 9 Radar Altimeter 3 3 3 10 Heading System 3 4 3 11 ADF Receiver 3 4 3 12 NAV Receiver and Glideslope 3 5 3 13 Air Data Computer 3 5 3 14 OAT Probe 3 5 3 15 Traffic 3 6 3 16 ST3400 Interlink 3 6 3 17 Uploading Equipment 3 6 3 18 Display Dimming 3 6 3 19 Windshield Wipers 3 6 4 INSTALLATION 4 1 4 1 Unpacking and...

Страница 7: ...ormal Mode Operation 5 1 5 2 Maintenance Mode 5 1 6 SETUP PROCEDURES 6 1 6 1 General 6 1 6 1 1 Accessing Maintenance Pages 6 1 6 1 2 Uploading Data or System Software 6 1 6 1 3 Configuration Module 6 1 6 1 4 Configuration Module Status Page 6 2 6 1 5 Tail Number 6 2 6 2 Maintenance Index Page 6 3 6 2 1 Maintenance Page Number Title 6 3 6 2 2 Cursor 6 3 6 2 3 Soft Keys 6 4 6 2 4 Edit Read Mode Indi...

Страница 8: ...7 20 7 2 11 ST3400 CONFIGURATION 7 20 7 2 12 AIR DATA INPUT TESTS 7 23 7 2 13 ADF INPUT TESTS 7 24 7 2 14 HEADING INPUT TESTS 7 24 7 2 15 DISCRETE INPUTS TESTS 7 25 7 2 16 NAV ILS INPUT TESTS 7 25 7 2 17 RADAR ALTIMETER 7 26 7 2 18 GPS FMS 1 7 27 7 2 19 GPS FMS 2 7 28 7 2 20 TRAFFIC 7 28 7 2 21 Activate the TAWS Inhibit 7 28 7 2 22 Power up the GPS FMS 7 28 7 2 23 Initialize GPS FMS 7 29 7 2 24 Fa...

Страница 9: ...NC 429 LABELS for Heading 10 3 10 4 ADF 10 3 10 4 1 ARINC 429 LABELS for ADF 10 3 10 5 NAV 10 3 10 5 1 ARINC 429 LABELS for NAV 10 3 10 6 AIRDATA 10 4 10 6 1 ARINC 429 LABELS for Airdata 10 4 10 7 TRAFFIC 10 4 11 APPENDIX B ENVIRONMENTAL QUALIFICATION FORM 11 1 12 APPENDIX C STC 12 1 12 1 STC Permission 12 1 12 2 STC Cessna 421C Series 12 2 12 3 STC King Air C90 200 300 and B300 Series 12 3 82002 ...

Страница 10: ... below approximately 0 C 5 Self test will operate all annunciator outputs 6 Capability of interfacing to CIC brand analog airdata Computers Mod A status can be determined from the data plate or from the Pilot s Menu where the Mod A status is shown in the upper right of the screen NOTE See section on software loading for other information about MOD A 1 1 2 MOD B Status MOD B units contain the same ...

Страница 11: ...AWS is the enhanced terrain warning technology that replaces the older GPWS Ground Proximity Warning System technology It is also known as EGPWS Enhanced GPWS TAWS adds two new and critical capabilities FLTA Forward Looking Terrain Avoidance and PDA Premature Decent Alert to the standard GPWS functions The six standard GPWS functional modes are ERD excessive rate of descent ECRT excessive closure ...

Страница 12: ...levation When configured as a Class B TAWS system the ST3400 exceeds the FAA Class B TAWS requirements Even in Class B mode without radar altimeter the ST3400 includes Class A features such as a terrain display and an excessive glide slope deviation alert when so configured 1 2 3 TAWS Class A Class B Required Equipment The ST3400 uses the following equipment to meet Class A or Class B requirements...

Страница 13: ... against a fixed lubber line Bearing is provided to both a primary pointer and a secondary pointer each of which is read against the compass card Each pointer may be switched independently to any installed navigation source which may be a VOR ADF or the GPS FMS waypoint The ability to assign the GPS FMS to a bearing pointer is unique to the ST3400 RMI If the navigation source has an invalid state ...

Страница 14: ... to the coverage area databases can be obtained on CD ROM from Sandel or downloaded from the Sandel web site into a Windows loader program on a laptop computer The terrain data and or airport data is then downloaded from the PC into the ST3400 through a high speed USB port located on the front right corner Loading instructions are supplied along with the applicable database The databases can be up...

Страница 15: ...s Height 3 175 inches Length 9 5 inches Weight 3 2 pounds with connectors and configuration module Cable weight not included Mounting Clamp Display 1 mega pixel 256 color 144 000 color triad 1 3 3 Operational Characteristics Temperature Altitude 20 C to 70 C up to 55 000 F Power Input 28VDC nominal 40 watt maximum Operating range 22VDC 33VDC Cooling Requirements Internal fan Requires ambient air a...

Страница 16: ...9 Label 270 or Discrete active high or low Active State Gear Down Flap ARINC 429 Label 270 or Discrete active high or low Active State Flaps in Landing Configuration Autopilot Engage ARINC 429 or Discrete active high or low Active State Autopilot Engaged RMI ADF ARINC 429 or DC Sin Cos or Arinc 407 XYZ VOR ARINC 429 or Composite Video Glideslope ARINC 429 or low level deviation and flag Localizer ...

Страница 17: ...ST3400 000 CLASS A BLACK ST3400 001 CLASS A GRAY ST3400 100 CLASS B BLACK ST3400 102 CLASS B GRAY 1 5 2 Installation Kit Part Number An installation kit is available for the ST3400 ST3400 INSTALLATION KIT P N 90130 IK Qty Sandel P N Positronics P N Description J1 1 32063 DD44F10JVLO Connector 44 pin Plastic Hood Slide Lock and Contacts J2 1 32063 DD44F10JVLO Connector 44 pin Plastic Hood Slide Loc...

Страница 18: ...ication Form for the ST3400 is included as an Appendix within this Installation Manual It should be referenced to the categories appropriate to the aircraft type and environment into which the ST3400 is to be installed The environmental category for the ST3400 should be stipulated on the STC form A Functional Ground Test Procedures Report and an Operational Flight Check Procedures Report are inclu...

Страница 19: ...ake and model Refer to the installation schematics in an Appendix of this manual for details on connecting required components 2 2 Allowed Sensor Configuration Matrix Class A 2 2 1 Required Sensors Class A 1 Heading 2 GPS position 3 Localizer and Glideslope 4 Radar Altitude 5 Baro Rate Vertical Speed 6 Flaps 7 Gear only if the aircraft has retractable gear 2 2 2 Additional Required Sensors allowed...

Страница 20: ...rcraft upgraded for RVSM where the altitude source may be a new digital altimeter but the VS source may be the original airdata computer which has been left in the aircraft to interface with other existing systems In order to make a flexible system that requires as little additional equipment as possible the ST3400 supports separate selection of sources for Altitude Vertical Speed and OAT Please p...

Страница 21: ...agram Vert Spd Baro Alt OAT Analog Alt Coarse Fine Analog Vert Spd Analog TAS Analog OAT 429 Data 419 Data Ternary Data Analog Digital Inputs TAS Outputs to System Maintenance Page Selects 82002 IM L ST3400 INSTALLATION MANUAL 2 3 ...

Страница 22: ... desired functional characteristics for the installation 2 Compile an equipment list for the aircraft For Class A installations ensure the radar altimeter model provides an acceptable 2000 or 2500 maximum altitude GPS altitude data from approved receivers may be used to supply altitude See above discussion of altitude sources Airdata may be required See above discussion of altitude sources See abo...

Страница 23: ... review correct wiring by using industry accepted ohmmeter and voltage checks Pay particular attention to presence of 28V on only the correct pins 0 ohm resistance check on ground pins to airframe ground and presence of inverter 400Hz if used only on the appropriate pins 2 Review any special items particular to the subject aircraft installation 3 Power up the ST3400 in maintenance mode and sequent...

Страница 24: ...THIS PAGE INTENTIONALLY LEFT BLANK ST3400 INSTALLATION MANUAL 82002 IM L 2 6 ...

Страница 25: ...ignals on J 2 if used that require excitation must use the same excitation as the inverter 2 input If the installation of the ST3400 does not use any XYZ ARINC407 signal sources the inverter inputs are not required and should be grounded 3 3 External Annunciators Optional external annunciator lamp discrete outputs are available to drive TAWS INH FLAP OVRD G S OVRD CAUT WARN annunciators on J 3 A 6...

Страница 26: ...lay Configuration is performed in the Maintenance Menu pages given in the Setup Procedures section of this manual If the installation aircraft uses flaps for normal takeoff ensure that this input triggers in landing configuration not in takeoff configuration 3 5 Landing Gear Landing Gear Position input is required for Class A compliance and is recommended for Class B if aircraft is retractable gea...

Страница 27: ...stem GPS or Flight Management System FMS input is required for both Class A and Class B compliance Note This system must be GPS based system and meet TSO C129a or C 145 requirements GPS is used for lateral positional and to display flight plan information In certain installations it may also be used for vertical position The ST3400 has provisions for one or two simultaneous GPS ARINC 429 receiver ...

Страница 28: ...r up to two simultaneous Heading System input ports The primary input port is located on J 1 and the optional port is located on J 2 Either one may be from an ARINC 429 or XYZ ARINC 407 source configurable in the Maintenance Menu pages A list of supported Labels is given in an Appendix of this manual The XYZ ARINC 407 is dependent on availability of 26VAC excitation for proper operation In additio...

Страница 29: ...ee above discussion of Altitude Sources Air Data Computer input is required for Class A installations and Class B installations without GPS altitude For Class B installations with GPS altitude airdata may be used as a backup altitude and VS source and is optional For Class A installations using GPS altitude the airdata system must at least supply Vertical Speed and barometric altitude either corre...

Страница 30: ...der program and loading instructions are supplied with the applicable software or data 3 18 Display Dimming The ST3400 screen dimmer is controlled from the Pilot s Menu using the M button The display and push button LED luminance levels are coordinated Units with Mod A have selectable auto manual dimming Units without Mod A have manual dimming only External annunciator dimming may be accomplished ...

Страница 31: ...lear of any objects which would restrict the inflow of air at cabin ambient temperature Cooling should be verified in the post installation checkout by monitoring the temperature on the Diagnostics 1 page For additional cooling or special requirements air from an external avionics blower may be directed near the corner air inlets In helicopter installations it may be desirable to introduce a small...

Страница 32: ...each ground return must be electrically separated 3 In order to ensure optimum performance the ST3400 and associated wiring must be kept a minimum of three feet from high noise sources and not routed with cables from high power sources 4 Prior to installation verify proper wiring by completing a point to point continuity check of the wiring harness 5 Use the Functional Pinout Descriptions to deter...

Страница 33: ...9 RadAlt Analog DC ALT 50 55 ARINC 552 RT220 300 RT200 18 Radalt1 Valid In Discrete Valid Discrete Note Not used when 429 is data source 3 Hdg1A In A429 A side 429 A407 Synchro X Z grounded 33 Hdg1B In A429 B side 429 A407 Synchro Y Z grounded 19 Hdg1 Valid In Discrete Valid Hdg Analog Note Not used when 429 is data source 4 ADF1A In A429 A side 429 DC Sin DC Sine A407 Synchro X Z grounded 34 ADF1...

Страница 34: ...422 side 422 R232 Rx A407 AC resolver Fine Cosine Altitude Synchro Y Fine Altitude Manchester Low 8 Alt1 VS1 Gnd In Note Differential signals paired with pin 39 A429 419 A side 429 419 R422 side 422 R232 Ground side A407 Synchro X Alt DC Coarse Ground at source 38 VS1 Signal In VS Sig DC voltage 5V to 5V 10 000 to 10000 FPM 24 VS1 Ref In VS Ref Note 12Vdc excitation reference 9 VS1 Ref In VS Ref N...

Страница 35: ...13 RS232TxD Out R232 43 n c In Factory use only DO NOT CONNECT Discrete 29 OAT Probe In Connect other lead to pin 1 GROUND A575 Excitation 14 n c n c 44 n c n c 30 Audio LL Out Out Audio LL Low Level Audio output requires external amplifier 15 Speaker Audio Out Out Clone of audio from Audio1 which has the capability of driving 8 ohm speaker directly Volume separately trimmed with respect to LL aud...

Страница 36: ...de 429 RS232 Rx 18 Decision Height Discrete In Discrete Valid Discrete Open Gnd or Open 28VDC 3 Hdg2A In A429 A side 429 A407 Synchro X Z grounded 33 Hdg2B In A429 B side 429 A407 Synchro Y Z grounded 19 Hdg2 Valid In Discrete Valid Hdg Analog Note Not used when 429 is data source 4 ADF2A In A429 A side 429 DC Sin DC Sine A407 Synchro X Z grounded 34 ADF2B In A429 B side 429 DC Cos DC Cosine A407 ...

Страница 37: ...fly up indication 37 Digital Airdata 2A In A429 419 A side 429 419 R422 side 422 R232 Ground side Manchester High 23 Digital Airdata 2B In A429 419 B side 429 419 R422 side 422 R232 Rx Manchester Low 8 Spare Analog 1 In 38 Spare Analog 2 In 24 Flaps Ovrd In Discrete Open Gnd 9 GS Ovrd In Discrete Open Gnd 39 Pressure Altitude 1 Analog In Pressure Altitude 0 25 VDC 1Kft or 0 3175 VDC 1K ft 25 Spare...

Страница 38: ...is not used 13 RA1 FAIL In Discrete Valid If RA1 configured 14VDC indicates RA 1 Fail 43 Audio Increase In Discrete Valid Activates audio level increase 29 AP Engage In Discrete Valid 14 Gear Down In Discrete Valid 44 Flaps Ldg In Discrete Valid Indicate flaps are in landing not takeoff configuration 30 429A Interlink Out For dual installations to feed cross side system A429 A side 429 15 429B Int...

Страница 39: ...onal external enunciator test Discrete Valid 14 Warning Lamp Out Optional Open Drain 7 Caution Lamp Out Optional Open Drain 15 TAWS INH Lamp Out Optional Open Drain 8 Selectable Discrete Out TCAS INH TAWS Warn or Caution or GPWS FAIL or TCAS INDICATOR discrete to TCAS II or AUDIO ENABLE relay drive Open Drain Selectable on SYSTEM maintenance page Note All discrete outputs sink 50ua of current when...

Страница 40: ...ove Configuration module may be left connected to ST3400 using prior software versions but will not store data The ST3400 may be operated with or without a configuration module connected If no configuration module is present the pilot will receive an advisory message 4 10 ST3400 INSTALLATION MANUAL 82002 IM L ...

Страница 41: ... 100K Analog Baro Altitude 0 to10Vdc 100Vdc 100K Analog Radar Altitude 0 to 30Vdc 100Vdc 100K Discrete Valid High 14 0Vdc Note 4 60Vdc 500K Discrete Valid Low 3 5Vdc Note 4 40Vdc 500K Discrete High 1 2Vdc 32Vdc 50K Discrete Low 8Vdc 32Vdc 50K GS 225mv FS 60Vdc 300K Note 2 GS Flag Unflagged 225mv 60Vdc 300K Note 2 Inverter 26Vac rms 400Hz Nom 300Hz 5000Hz Limits 200Vac 50K Power 22 to 30 3Vdc Note ...

Страница 42: ...receiver load requirements Check installation instructions for the interfaced receiver 3 Outputs are protected against shorts to ground Shorts to power supply may cause damage to components 4 Discrete inputs actively pulled to 27 5v through 30k ohms when selected active low or actively pulled to 0v through 30k ohms when selected active high in the maintenance pages This ensures the input is in the...

Страница 43: ...ese buttons From the maintenance mode the system normal operations can be accessed by holding the M button for approximately 3 seconds This feature can be used to test or see the results of a change in maintenance page configuration The maintenance pages can be brought back by holding the M button again for 3 seconds NOTE WHEN DOING A FINAL TEST OF A SYSTEM MAKE SURE THE POWER HAS BEEN RECYCLED TO...

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Страница 45: ...AWS equipment memory The Loader communicates with the ST3400 unit via the USB Port located in the lower right corner of the front bezel The Loader runs on a personal computer with a USB port and Microsoft Windows 98 Windows Me Windows 2000 or Windows XT software The applicable Windows Driver Loader executable and instructions are supplied with the software or data The Loader only operates when in ...

Страница 46: ...Index page 1 Note CM will appear in the upper right corner to indicate that the configuration module is not operational ST3400 TO CM Selecting this option will allow stored ST3400 configuration data to be written to the configuration module and stored NOTE When selecting this option ST3400 configuration data will be written TO the configuration module and overwrite any existing configuration data ...

Страница 47: ...aintenance Index page The PREV or NEXT Soft keys may also be used to reach a particular maintenance page sequentially Figure 6 1 Maintenance Index Page Display 6 2 1 Maintenance Page Number Title The Maintenance Page Number Title is displayed on every maintenance page showing the maintenance page number and title 6 2 2 Cursor The Cursor points to the item which may be modified or selected If there...

Страница 48: ... was displayed prior to transitioning to the Flight Operations Test displays Scroll Up UP Moves the Cursor to the previous selectable item Hold key down to automatically repeat If there are no selectable items key is disabled Scroll Down DOWN Scrolls the Current Line Indicator to the next selectable item Hold key down to automatically repeat If there are no selectable items key is disabled Value M...

Страница 49: ...Maintenance Pages The Maintenance Index shows all maintenance pages and allows the operator to jump directly to any other maintenance page by the use of Soft keys 6 2 5 1 Access the Maintenance Index page Prior to applying power to the system Press and hold the BRG 1 BRG 2 selection buttons until the Maintenance Index page is displayed 6 2 5 2 Jump to a specific page Press the UP Soft key or the D...

Страница 50: ...each item choice on a separate line A multiple choice entry is an item with a set of selectable choices where the set is shown one choice at a time on a single line A request is used to test a system function or to reset internal values 6 3 1 System Maintenance Page The System page see Figure 6 2 provides information that identifies this unit and this unit s hardware software The modifiable values...

Страница 51: ... the items 6 3 1 3 Internal Value Internal Values are items shown for reference which cannot be edited They are shown in GRN or YEL 6 3 2 Air Data Page The Air Data page see Figure 6 3 contains the setup information for the 1 and 2 airdata systems Use the UP or DOWN Softkeys to select a setup item This will move the Cursor to the appropriate line and display the current input data value input volt...

Страница 52: ...ble and pin pairs of the selected signal ADF ADF receiver HDG HDG system When selecting analog inputs a VALID select will be present If no valid signal is available for the interconnected equipment set this to NONE which will treat the signal inputs as always valid If a VALID signal is available set appropriately to VALID HIGH or VALID LOW The effect of these settings will be immediately shown at ...

Страница 53: ...he discrete inputs A Discrete may be VALID LOW or VALID HIGH In either case a 30K resistor is connected to pull the signal to the invalid state ground or aircraft power as applicable unless the valid signal is applied Figure 6 5 DISCRETES 82002 IM L ST3400 INSTALLATION MANUAL 6 9 ...

Страница 54: ...he data VALUE area The data VALUE shows only a single data item This page has an additional softkey labeled VALUE which can be used to scroll through all of the NAV and ILS data coming from the receiver Use the UP DOWN Soft keys to scroll through the various data items Press the TYPE Soft key to exit the Value scroll function When the NAV input is analog composite both the VOR bearing and the LOC ...

Страница 55: ... normal operation and INVALID during TEST of the RA or when the RA is powered off Note For Analog radar altimeters mis setting the Radar altimeter selection may show a correct value below 500 and an incorrect value above 500 Therefore if any troubleshooting is required regarding Radar Altimeter operation it is suggested that a test flight be performed in VFR conditions and the Radar Altitude be mo...

Страница 56: ...ear in the data VALUE area The data VALUE shows only a single data item This page has an additional softkey labeled VALUE which can be used to scroll through all of the GPS FMS DATA coming from the receiver Use the UP DOWN Soft keys to scroll through the various data items Press the MODEL Soft key to exit the Value scroll function Figure 6 8 GPS FMS 1 Select Maintenance Page typical 6 3 7 1 More I...

Страница 57: ...ATA coming from the processor Use the UP DOWN Soft keys to scroll through the various data items Press the MODEL Soft key to exit the Value scroll function If a ST3400 in the field is being upgraded to display Traffic please contact the factory for a software key necessary to enable the traffic display The Traffic key can be entered on this screen manually Software 3 00 and above is required to di...

Страница 58: ...6 3 9 Status Page The Status page see Figure 6 9 shows a composite status of all the ST3400 inputs Figure 6 9 STATUS 6 14 ST3400 INSTALLATION MANUAL 82002 IM L ...

Страница 59: ... autio callouts Use the UP or DOWN Softkeys to select a setup item this will move the Cursor to the appropriate line and select ON or OFF for each callout Radar Altimeter input is required for the Callouts to function Figure 6 10 CALLOUTS 82002 IM L ST3400 INSTALLATION MANUAL 6 15 ...

Страница 60: ...pages In the read mode all configuration values are read only To make changes the edit read mode must be changed to edit 7 1 1 1 Access the Maintenance Index page Prior to applying power to the system Press and hold the BRG 1 BRG 2 selection buttons until the Maintenance Index page is displayed 7 1 1 2 Quickly access a specific page Press the UP Soft key or the DOWN Soft key to move the Cursor Pre...

Страница 61: ...TAWS RMI into aircraft Enter the maintenance mode by depressing BRG1 BRG2 and apply power to the unit 7 2 4 Record the following Aircraft Configuration Aircraft S N __________________Aircraft Registration __________ Aircraft Make ________________ Aircraft Model __________ 7 2 5 Record the following system information Date ______________________________ ST3400 SN ________________________ ST3400 PN ...

Страница 62: ...d lamp cycles to zero or the CANCEL soft key to cancel the action with no changes made If while waiting for confirmation the operator moves the Cursor or exits the Brightness Audio page the action will be cancelled 7 2 8 Alerts Test Initiate an audio level test by selecting the desired volume level and pressing the TEST soft key see Figure 7 1 This may be used to show the result of changing the au...

Страница 63: ...l post an on screen error by way of the systems built in test processes Figure 7 2 Internal Diagnostics 1 Note On ST3400 with Mod A the following differences should be noted The power supply monitor list is slightly different than shown above Any power supply out of tolerance will change from green to red If inverter inputs are floating they will read 1 3V not 0 0V When grounded they will read 0 0...

Страница 64: ...e and record configuration information from the ST3400 TAWS RMI Maintenance and Summary pages Note Meet all approved maintenance and safety conditions Use of appropriate ground power for the aircraft is required Note Aircraft must be in the view of the GPS satellites for a valid GPS Position FMS may show invalid depending on model until valid Groundspeed is achieved 7 20 ST3400 INSTALLATION MANUAL...

Страница 65: ...E AIR DATA ADC 1 3 CBA1 3 BR1 3 TA1 3 OAT AIR DATA ADC 2 4 CBA1 4 BR1 4 TA1 OAT ADF HEADING 5 ADF 1 5 VALID 5 ADF 2 5 VALID 5 HDG 1 5 VALID 5 HDG 2 5 VALID DISCERTES 6 AP 6 ALERT 6 TEST 6 FLAPS 6 GEAR 6 WHEELS 6 WINDSHILD WIPERS 82002 IM L ST3400 INSTALLATION MANUAL 7 21 ...

Страница 66: ...V ILS 7 NAV 1 7 CALIBRATE 7 NAV 2 7 CALIBRATE 7 GS NO 1 7 GS NO 2 7 Back Course RADIO ALTIMETER 8 RA 1 8 VALID 8 Decision Height GPS FMS 1 9 SELECTION GPS FMS 2 10 SELECTION TRAFFIC 11 SELECTION 7 22 ST3400 INSTALLATION MANUAL 82002 IM L ...

Страница 67: ...SI SIGNAL FUNCTION TOLERANCE RECORD VALUE PASS FAIL Adjust Pitot Static Test box to 1 000 2 000 and 4 000 fpm climb BR1 Verify vertical speed readings between Pilot s VSI and TAWS is within 200 FPM Adjust Pitot Static Test box to 1 000 2 000 and 4 000 fpm descent BR1 Verify vertical speed readings between Pilot s VSI and TAWS is within 200 FPM NOTE If using Analog Baro Rate input this tolerance is...

Страница 68: ... HEADING INPUT TESTS Select ST3400 to Maintenance Page 5 ADF HDG SIGNAL FUNCTION RESULT PASS FAIL 1 Heading System use the free mode and slew the heading 360 degrees HDG1 Verify the 1 Mag Heading value matches the aircraft heading displayed on HSI within 4 Degrees 1 Heading Valid pull circuit breaker to go invalid HDG1 VALID Verify value of 1 Mag Heading Valid indicates INVALID DATA 1 Heading Vali...

Страница 69: ...gh all settings FLAPS Verify value with flaps in landing configuration is FLAPS DOWN and in all other positions including takeoff is FLAPS UP Landing Gear GEAR Verify value indicates GEAR DOWN on ground Test Gear up during flight test Windshield Wiper Input WINDSHIELD WIPERS Activate Windshield Wiper and verify input in Audio Output 7 2 16 NAV ILS INPUT TESTS Select ST3400 to Maintenance Page 7 NA...

Страница 70: ...for GS DEV DDM deviation should match generated signal Rotate HSI till Course Pointer is greater than 90 degrees from Lubber Line Back Course Back Course will be enabled when Course Pointer is greater than 90 degrees from Lubber Line 7 2 17 RADAR ALTIMETER Note The Radar Altimeter test maybe performed by pressing the Radar Altimeter self test button or by utilizing a Radar Altimeter test set This ...

Страница 71: ...ATA 1 Radar Altimeter Valid reset circuit breaker RA1 VALID Verify value of 1 Radar Altimeter Valid indicates VALID Rotate the DH Knob through Decision Height Decision Height Aural callout MINIMUMS 7 2 18 GPS FMS 1 Select ST3400 to Maintenance Page 9 GPS FMS 1 SIGNAL FUNCTION RESULT PASS FAIL 1 GPS receiver locked on with valid signal 1 GPS POSITION 1 GPS Lat and Long value displayed should match ...

Страница 72: ...C Check traffic if interfaced to ST3400 Perform checkout per Traffic manufacturers installation manual Put Traffic device in self test mode TRAFFIC Traffic test pattern should display on the ST3400 traffic page 7 2 21 Activate the TAWS Inhibit Verify this inhibit annunciates on screen TAWS inhibited when selected and does not annunciate on screen TAWS inhibited when deselected Pass Fail Remarks __...

Страница 73: ..._______________________________________ 7 2 25 Run TAWS self test And verify aural annunciations are acceptable in clarity and volume both loudspeaker and headphone aural annunciations Pass Fail Remarks ______________________________________________________ 7 2 26 Verify the ST3400 display Verify display is viewable under all expected cockpit ambient light conditions this test should be performed ...

Страница 74: ...ntrols from the pilot s seat View the display from normal expected viewing angles This should include viewing the display from all viewing angles that might be encountered during normal cockpit operations Pass Fail Remarks ______________________________________________________ 7 30 ST3400 INSTALLATION MANUAL 82002 IM L ...

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Страница 76: ......

Страница 77: ...new releases and the content details of the databases may be obtained by visiting the Sandel website Database updates may be ordered on line It is up to the ST3400 customer to determine if a specific database is applicable to their operations Terrain and Airport databases do not have to be updated at the same intervals 8 3 Lamp Replacement The lamp in the ST3400 requires no scheduled maintenance 8...

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Страница 79: ...002 10 pp 6 H GARMIN GNS4XX 5XX 82002 10 pp 7 K RAD ALT ANALOG 82002 10 pp 8 H RAD ALT ARINC 429 82002 10 pp 9 F HDG ARINC 429 82002 10 pp 10 G HDG XYZ 82002 10 pp 11 B ADF ARINC 429 82002 10 pp 12 G1 ADF XYZ 82002 10 pp 13 G1 ADF DC SIN COS 82002 10 pp 14 H NAV LOC ANALOG 82002 10 pp 15 E NAV LOC ARINC 429 82002 10 pp 16 J AIRDATA ANALOG 82002 10 pp 17 J1 AIRDATA ARINC 429 419 82002 10 pp 18 F OA...

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Страница 81: ...nual 10 1 GPS FMS MFG MODEL INTERFACE TYPE FREEFLIGHT 1201 RS232 GARMIN GPS 165 429 GARMIN GNS4XX 429 RS232 GARMIN GNS5XX 429 RS232 GARMIN GTN 6XX 429 RS232 GARMIN GTN 7XX 429 RS232 HONEYWELL KLN90B 0200 429 HONEYWELL KLN900 429 HONEYWELL KLN94 RS232 HONEYWELL GNS Xls 429 LOW SPEED HONEYWELL GNS Xls 429 HIGH SPEED II MORROW 2100 429 II MORROW 2101 429 TRIMBLE 2000 3000 RS422 TRIMBLE 2101 RS422 TRI...

Страница 82: ... DATA 074 Flight Plan 075 Waypoint Hdr 076 GPS Altitude 101 HDOP 102 VDOP 113 Waypoint Checksum 115 WYPT BEARING 136 VFOM 147 MagVar 150 Time HH MM SS 165 GPS Vertical Speed 167 ANP 247 HFOM 260 DATE 261 GPS Discrete 275 LRN Integrity 303 Waypoint Type 304 Waypoint ID LSB 305 Waypoint ID MSB 306 Waypoint Latitude 307 Waypoint Longitude 310 Present Position Latitude 311 Present Position Longitude 3...

Страница 83: ...9 10 4 1 ARINC 429 LABELS for ADF LABEL DATA 162 ADF Heading 10 5 NAV MANUFACTURER MODEL INTERFACE TYPE BENDIX KING KN 40 ARINC 429 BENDIX KING KX165 ANALOG BENDIX KING KNR634 ANALOG COLLINS VIR30 31 32 ANALOG COLLINS VIR432 ARINC 429 GARMIN GNS430 530 ARINC 429 10 5 1 ARINC 429 LABELS for NAV LABEL DATA 173 LOCALIZER DEVIATION 174 GLIDESLOPE DEVIATION LABEL 222 VOR MFG MODEL INTERFACE TYPE BENDIX...

Страница 84: ...HONEYWELL AZ 648 ANALOG HONEYWELL AZ 810 ARINC 429 IS S ADDU ARINC 429 PENNY GILES D60286 ANALOG PENNY GILES 90004 ARINC 429 SHADIN ADC 2000 ARINC 429 10 6 1 ARINC 429 LABELS for Airdata LABEL DATA 203 Uncorrected Altitude 204 Corrected Baro Altitude 210 True Air Speed 211 Total Air Temperature 212 Baro Rate 213 Static Air Temperature 10 7 TRAFFIC MFG MODEL INTERFACE TYPE GoodricL 3 GOODRICHh TCAS...

Страница 85: ...essure 4 0 5 0 4 5 1 4 5 2 4 5 3 4 6 4 6 2 4 6 3 A2 F1 B PASS In Flight Loss of Cooling 4 5 4 A2 Z PASS Humidity 6 0 A PASS Operational Shock and Crash Safety 7 0 B PASS Vibration 8 0 H R PASS RESONANT FREQUENCIES Section 8 7 2 Step a and d Pre Scan X 195Hz Y 500Hz Z 160Hz Post Scan X 195Hz Y 450Hz Z 150Hz Section 8 8 1 3 Steps a and e Pre Scan X 190Hz Y 425Hz Z 145Hz Post Scan X 190Hz Y 625Hz Z 1...

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Страница 87: ...12 APPENDIX C STC 12 1 STC Permission Please contact Sandel Avionics Inc for permission to use these STC s 82002 IM L ST3400 INSTALLATION MANUAL 12 1 ...

Страница 88: ...12 2 STC Cessna 421C Series 12 2 ST3400 INSTALLATION MANUAL 82002 IM L ...

Страница 89: ...12 3 STC King Air C90 200 300 and B300 Series 82002 IM L ST3400 INSTALLATION MANUAL 12 3 ...

Страница 90: ...eco mme Humi dity 6 0 A PASS Oper ation a l Shoc k and Cras h 7 0 B PASS Vibra tion 8 0 H R PASS RESO NANT FREQ UENCI ES Secti on 8 7 2 Step a and d Pre Scan X 195Hz Y 500Hz Z 160Hz Post Scan X 195Hz Y 450Hz Z 150Hz Secti on 8 8 1 3 Steps a and Pre Scan X 190H z Y 425Hz Z 145Hz Post Scan X 190Hz Y 625Hz Z 145Hz Secti on 8 8 1 3 Steps b and Pre Scan X 190Hz Y 390Hz Z 150Hz Post Scan X 190Hz Y 625Hz...

Страница 91: ......

Страница 92: ......

Страница 93: ... CHECKED RESP ENG MFG ENG APPROVAL UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES TOLERANCES ARE FRACTIONS DECIMALS ANGLES X X XX 01 5 MATERIAL FINISH DO NOT SCALE DRAWING APPLICATION USED ON NEXT ASSY ITEM NO PART OR IDENTIFYING NO NOMENCLATURE OR DESCRIPTION MATERIAL SPECIFICATION QTY REQD PARTS LIST 1 2 3 4 5 6 7 8 8 7 6 5 4 3 2 1 REVISIONS REV DESCRIPTION DATE APPROVED VISTA CA A XXX 005 ...

Страница 94: ...SYSTEM RADALT GPS FMS SANDEL ST3400 INVERTER AUTOPILOT SWITCH ANNUNCIATORS optional ARINC 429 WARNING DISCRETE CAUTION DISCRETE 26VAC 400 HZ opt TAWS INHIBIT SWITCH 429 OR ANALOG AIRFRAME GEAR DOWN DISCRETE FLAP DOWN DISCRETE 2 ST3400 optional INTERLINK ENGAGED DISCRETE POWER GROUND 28VDC POWER GROUND TAWS INHIBIT DISCRETE REQUIRED FOR HDG ADF AND AIR DATA XYZ REFERENCE INPUT COMMENTS A REV 04 11 ...

Страница 95: ... XYZ USED RADALT NAV LOC AIR DATA INVERTER AUDIO ADF 26VAC 400 HZ opt 429 OR ANALOG ARINC 429 600 ohm 429 OR SIN COS OR XYZ OPTIONAL CORR BARO ALT TAS VS OAT 429 OR ANALOG OR REQUIRED FOR HDG ADF AND AIR DATA XYZ REFERENCE INPUT VOR LOC COMPOSITE GLIDESLOPE HEADING 429 OR XYZ ENGAGED DISCRETE ALTITUDE VS CORR BARO ALT TAS VS OAT OR GPS ALTITUDE 429 OR ANALOG HEADING CONFIGURATION MODULE POWER GROU...

Страница 96: ...ER INPUT OR A SEPERATE 2 INVERTER INPUT IF REQUIRED ARINC 407 XYZ INPUTS ON J2 MUST HAVE THE SAME AC REFERENCE AS 2 INVERTER INPUT P2 16 04 11 02 A A R 484 INITIAL RELEASE DATE REV COMMENTS COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY SHIELD GROUND 1 SHIELD GROUND 1 AC REFERENCE FOR INPUTS ON J2 SEE NOTE 1 2 IF AIRCRAFT HAS ONLY ONE UNSWITCHED INPUT AND MULTIPLE SOURCES ADD A 470 680 OHM RES...

Страница 97: ...ODEL 1 FMS 429 AIN 31 46 I7 20 15 GARMIN GPS 165 J101 16 ST3400 J2 SECONDARY 17 2 FMS 429 BIN SHIELD GROUND 1 31 2 FMS 429 AIN SECONDARY INPUTS OPTIONAL C 02 21 03 A R 610 Depict J1 J2 Seperately COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY PORT SELECT 40 II MORROW 2001 P1 41 II MORROW 2101 P1 43 44 47 GARMIN GNS 5XX P5001 46 Added II Morrow 2001 2101 UNS 1X Trimble 2101 I O J2 LOW OR HIGH S...

Страница 98: ...y used 1 NOTES 3 1201 GPS provides horizontal and vertical position No flight plan data available SHIELD GROUND 1 1 FMS RS232 IN HI ST3400 17 2 FMS RS232 IN LO 31 Trimble 2000 3000 J1 ST3400 J2 2 FMS RS232 422 IN HI 17 SHIELD GROUND 1 2 FMS RS232 422 IN LO 31 3 RS422 OUT TXD1 2 15 SOFTWARE SELECT TRIMBLE 2000 3000 Trimble 2101 J1 5 37 TRIMBLE 2101 OR OR 23 9 RS422 OUT TXD1 2 GPS FMS 2 GX50 60 SHIE...

Страница 99: ...raphics w Int SDI LNAV 1 SDI1 VOR LOC GS ARINC 429 CONFIGURATION SPD RX LOW SPD TX LOW SDI VOR ILS 1 SDI1 MAIN RS232 CONFIG INPUT OUTPUT CHAN 1 4 OFF HW EPGWS MAIN ARINC 429 CONFIGURATION RECEIVER 2 OUT LOW GAMA 429 Graphics w Int SDI LNAV 2 SDI2 VOR LOC GS ARINC 429 CONFIGURATION SPD RX LOW SPD TX LOW SDI VOR ILS 2 SDI2 MAIN RS232 CONFIG INPUT OUTPUT CHAN 1 4 OFF HW EPGWS RS232 TX GARMIN GNS 430 ...

Страница 100: ...iscrete Input Removed 2 Rad Altimeter Input Added new info on Sperry RT s and interconnects COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY SEE RADAR ALTIMETERS MFG INSTALL MANUAL FOR DECISION HEIGHT OUTPUT AND INTERCONNECT ST3400 HIGH or LOW DECISION HEIGHT IN 18 J2 ACTIVE L ACTIVE H OR NONE SOFTWARE SELECT DH OUT NOTE Available in Software 3 00 and above DH Minimums Callout Radar Altimeter An...

Страница 101: ...TS REV DATE E 02 21 03 A R610RadarAltimeterARINC429interfacemovedfromorignalsheet5 addedBendix KingKRA405B COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY 1 RAD ALT 429 A RX 1 RAD ALT 429 B RX SHIELD GROUND ST3400 3 2 COLLINS RAC 870 P 1 J1 PRIMARY 1 32 2 ARINC 429 TX A ARINC 429 TX B ARINC 429 RADAR ALTIMETER SOFTWARE SELECT ARINC 429 C B BENDIX KING KRA 405B P4051 NOTES 1 SIGNALS MAY BE OBTAI...

Страница 102: ... Ca B 9 ST3400 INSTALLATION DRAWING Thursday July 28 2016 COMMENTS A REV 04 11 02 DATE A R 484 INITIAL RELEASE ST3400 ARINC 429 TX B ARINC 429 TX A J1 PRIMARY 1 HEADING 429 A IN SHIELD GROUND 1 HEADING 429 B IN 3 33 1 ARINC COMPASS SYSTEM OUTPUT ARINC 429 SOFTWARE SELECT ST3400 J2 SECONDARY 3 33 ARINC 429 TX B ARINC 429 TX A 1 2 HEADING 429 A IN SHIELD GROUND 2 HEADING 429 B IN ARINC COMPASS SYSTE...

Страница 103: ... HEADING Y 19 2 INVERTER EXCITATION IN 2 HEADING VALID 16 2 Optional E 02 21 03 COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY W Z T KSG 105 P P1 XYZ OR XYZ 180 H L D s v t r BENDIX KING KCS 55A BENDIX KING KCS 305 OR c 40 25 24 6 COLLINS MCS 65 P1 DGS 65 EXCITATION LO u d f 5 SPERRY HEADING Y HEADING X HEADING Z HEADING VALID EXCITATION HI SOFTWARE SELECT EXCITATION LO C 14A P1 HEADING VALID ...

Страница 104: ...sta Ca B 11 ST3400 INSTALLATION DRAWING Thursday July 28 2016 NOTES 1 OPTIONAL USED FOR RMI OPERATION ONLY COMMENTS A REV 04 11 02 DATE A R484INITIALRELEASE ST3400 J1 PRIMARY 1 ADF 429 AIN 4 1 ADF 429 BIN 34 SHIELD GROUND 1 ADF 429 TX A ADF 429 TX B ADF ARINC 429 OUTPUT SOFTWARE SELECT ST3400 J2 SECONDARY 4 2 ADF 429 AIN 34 2 ADF 429 BIN SHIELD GROUND 1 ADF 429 TX A ADF 429 TX B ADF ARINC 429 OUTP...

Страница 105: ... ADF VALID 5 REQUIRES AC REFERENCE INPUT SECONDARY INPUTS OPTIONAL ST3400 J1 PRIMARY 1 ADF X 4 1 ADF Y 34 SHIELD GROUND 1 ADF X ADF Y ADF Z ADF VALID ADF ARINC 407 OUTPUT 1 ADF VALID 5 XYZ OR XYZ 180 SOFTWARE SELECT REQUIRES AC REFERENCE INPUT E 02 21 03 A R 610 Depict J1 J2 Seperately Added Collins ADF 60A COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY 12 13 11 BENDIX KING KDF 806 P8061 _ COL...

Страница 106: ...ADF DC COS ADF DC REF ADF VALID ADF DC SIN COS OUTPUT 1 ADF VALID 5 _ NOTES SOFTWARE SELECT DC SIN COS COMMENTS REV DATE ST3400 J2 SECONDARY 4 2 ADF DC SIN 34 2 ADF DC COS 20 2 ADF DC REF SHIELD GROUND 1 2 ADF VALID 5 SECONDARY INPUTS OPTIONAL E 02 21 03 COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY B A D BENDIX KING KR 87 P872 _ 25 COLLINS ADF 60A B SEE NOTE 2 33 28 1 OPTIONAL USED FOR RMI O...

Страница 107: ...2 GS FLAG IN ST3400 J2 2 GS FLAG IN 22 6 36 7 2 GS FLY UP 2 GS FLY DOWN 28 NAV 2 COMPOSITE GS FLAG ANALOG VHF NAV OUTPUT GS FLAG NAV 2 COMPOSITE 1 SHIELD GROUND SOFTWARE SELECT GS FLY UP GS FLY DOWN SECONDARY INPUTS OPTIONAL ANALOG S T U R BENDIX KING KX155 165 P401 P901 _ _ _ _ 36 35 34 18 BENDIX KING KNR 634 P1 P2 _ _ _ _ _ 9 13 P1 _ P2 COLLINS VIR 30 31 32 1 _ _ 5 J2 NAV 1 COMPOSITE 42 NAV 1 CO...

Страница 108: ... Ca B 15 ST3400 INSTALLATION DRAWING Thursday July 28 2016 COMMENTS REV DATE E 02 21 03 COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY AR 610 Nav ARINC 429 interface moved from original sheet 8 Added VIR 432 Garmin 430 530 36 42 GARMIN GNS 430 P4006 NAV 429 A TX 21 SOFTWARE SELECT 21 SECONDARY INPUTS OPTIONAL 2 NAV 429 AIN GARMIN GNS 530 P5006 ST3400 2 NAV 429 BIN 35 23 NAV 429 A TX ARINC 429 ...

Страница 109: ...UT 1 C F TA1 TYPE 3 1 TA1 TYPE 3 VS SIG IN 10 5 ST3400 INDICATED AIRSPEED H 25 PENNY GILES D60286 PRESSURE ALTITUDE ANALOG Note 3 40 SHIELD GROUND BAROMETRIC ALTITUDE VALID HIGH J1 AIRDATA VALID IN J1 SOFTWARE SELECT 6 39 AIRDATA VALID IN SHIELD GROUND E 1 CIC AIRDATA VALID OUT TAS SIG IN CBA CIC 8800M 7 CBA P G 20V PA 39 BAROMETRIC ALTITUDE J2 ST3400 Mod A Only 04077 MOD 3 ALTITUDE RATE COMMON 25...

Страница 110: ...J1 PRIMARY SINGLE SOURCE ARINC 429 23 37 23 SHIELD GROUND 1 AIRDATA_429_AIN 1 AIRDATA_429_BIN 2 AIRDATA_429_AIN 2 AIRDATA_429_BIN 37 23 37 J2 SECONDARY 2 DIGITAL SOURCE ARINC 429 1 32 31 ST3400 SECONDARY SECONDARY INPUTS OPTIONAL SHIELD GROUND 1 39 8 1 SHIELD GROUND 1 CBA AIRDATA_429_AIN 1 CBA AIRDATA_429_BIN 1 VS TAS AIRDATA_429_AIN 1 VS TAS AIRDATA_429_BIN AZ252 J1A 36 35 ARINC 419 See Note 2 AR...

Страница 111: ...ITIAL RELEASE ST3400 J1 PRIMARY SHIELD GROUND OAT HI 29 1 CIC PN 05257 PROBE or Equivalent 500 Ohm B A OAT PROBE NOTE 1 See Section 3 for OAT probe requirements See Note 1 COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY CIC PN 05591 Connector CIC PN 05592 Mounting Plate ST3400 J2 SECONDARY AIRDATA RS232 OUTPUT 2 AIRDATA RS232 IN HI 23 6 SHIELD GROUND 1 2 AIRDATA RS232 IN LO 37 SOFTWARE SELECT S...

Страница 112: ...4 11 02 DATE A R484INITIALRELEASE COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY J1 A R 626 Added XYZ Flap Input F 04 14 03 A R 661 Added Windshield Wiper Input G1 10 17 03 WINDSHIELD WIPER WINDWSHIELD WIPER OUTPUT 28VDC 43 NOT REQUIRED USE ONLY IF PRESENT IN AIRCRAFT J2 J2 ST3400 ST3400 43 NOT REQUIRED USE ONLY IF PRESENT IN AIRCRAFT SOFTWARE SELECT SOFTWARE SELECT VALID LO VALID HI WINDSHIEL...

Страница 113: ... TEST MOM GS OVRD LAMP OUT 4 FLAP OVRD LAMP OUT GS OVRD IN FLAP OVRD IN These Lamps Switches operational in software 3 00 and later Switch inputs also require MOD Level 2 TAWS INHIBIT IN COMPUTER CONTROLLED DRAWING DO NOT REVISE MANUALLY H2 A R 675 Changed TAWS INHIBIT to ALERTS INHIBIT Added GPWS Fail Flap Ovrd and Glideslope Ovrd J1 42 28 ALERT OUT 429 B ALERT OUT 429 A AIRCRAFT FLIGHT DATA RECO...

Страница 114: ...mber Rev Create Sheet of Category Mod Monday July 02 2001 82002 10 A1 INTERLINK SANDEL Vista Ca B 21 ST3400 INSTALLATION DRAWING Thursday July 28 2016 PILOT ST3400 COPILOT ST3400 J2 SECONDARY J2 SECONDARY INTERLINK_429_A TX INTERLINK_429_B TX INTERLINK_429_A RX INTERLINK_429_B RX 41 27 30 15 1 27 41 15 30 SHIELD GROUND INTERLINK_429_A RX INTERLINK_429_B TX INTERLINK_429_B RX INTERLINK_429_A TX COM...

Страница 115: ...intenance Page 2 System TCAS 791 2 P3 8 TCAS INH TCAS TRAFFIC 429 A INPUT SHIELD GROUND 16 30 HONEYWELL CAS66 J2 1 32 2 ARINC 429 TX A ARINC 429 TX B TCAS TRAFFIC 429 B INPUT SOFTWARE SELECT 1 HONEYWELL CAS 66 P1B J3 8 TCAS INH secondary TCAS IND primary 34 TA VALID 1 CAS66 2 SEE ABOVE Use P3 8 as TCAS INH to drive relay unless ST3400 is primary indicator 7 CAUTION WARN 14 TCAS PWR Use this relay ...

Страница 116: ... needs to be dedicated to the ST3400 GTN7XX series has additional channels 5 6 on P1005 1 FMS 429 A IN 1 FMS 429 B IN 1 NAV 429 B IN 1 NAV 429 A IN 1 NAV RS232 IN SIGNAL GND J1 31 17 35 21 11 1 GPS FMS 1 ST3400 Garmin GTN 6XX 7XX Series 1 Refer to current Installation Manual for Garmin GTN 6XX 7XX for ARINC 429 and RS232 pins 2 Garmin GTN setup Select GMA FORMAT 3 for the ARINC GPS 429 out Select ...

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