INSTRUCTIONS FOR CONTINUED
AIRWORTHINESS
FOR
- --- -.
.-.
•
•
•
••
CORPORAliON
EFIS - AHRS Kit
Part Number: HAS-909-00 158-01
Consisting of:
BENDIX / KING EFS 40 EFIS
ELECTRONIC FLIGHT INSTRUMENT SYSTEM
AND
LITEF LCR-92 AHRS
ATTITUDE AND HEADING REFERENCE SYSTEM
Installed on:
BELL MODEL 407 HELICOPTERS
Document Number: MM97-09-01
Revision: A
Date: 2 March 98
Helicopter Aviation Services Corporation
P.O. Box 1117, Mount Pleasant Airport
Mount Pleasant, Pennsylvania 15666 USA
Telephone: 724/887-4413
Facsimile: 724/887-3977
ECCN
9E991
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
INTRODUCTION
NOTICE
The Instructions set forth in this manual, as supplemented or modified by Alert
Service Bulletins (ASB) or other directions issued by HAS and Airworthiness
Directives (AD) issued by the appropriate airworthiness authority, shall be strictly
followed.
All maintenance on the HAS EFIS/AHRS should be done by an Allied Signal
approved sales and service center.
NOTE:
Revised text is indicated by a I on the left side of the page. Insert the
latest revision page(s) and dispose of the superseded page(s).
I 02 March 98
Page 2 of 34
HAS Corporation
Bell 407
MM97-09-01
Revision: A
Instructions For Continued Airworthiness
EFIS -AHRS
RECORD OF REVISIONS
I
I
REVISION
NUMBER
ISSUE DATE
IR
08 Sept. 97
A
02 March 98
I 02 March 98
DATE INSERTED
BY
Page 3 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
LIST OF EFFECTIVE PAGES
I LIST OF REVISIONS
Revision IR ( Initial Release)
Revision A
September 8, 1997
March 2, 1998
LIST OF EFFECTIVE PAGES
I
PAGE
REVISION
DATE
All
A
2 March 98
DESCRIPTION
Revision A
Revision Control Procedure
HAS maintains a database of all HAS EFIS/AHRS's in service. In the case that a
revision to this document becomes necessary, HAS will notify the owner/operator of
the aircraft by mail, fax, or E-mail as appropriate, and supply the owner/operator with
the revision.
These Instructions for Continued Airworthiness (lCA)
except for the Airworthiness Limitations Section have
been reviewed and found to comply with the applicable
requirements of .1\~"7diX A to Federal Aviation
Regulation Part
.
FAA
AccePtan~e~
Date O~/~31 J918
Fort
E;valllation Group
Worth Aircraft
I 02 March 98
Page 4 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
IMPORTANT
HELICOPTER SALE NOTICE
Please complete this Form and return by Mail or FAX (724-887-3977) to HAS Corporation.
This will insure that the New Owners receive updates to their HAS technical manuals and
bulletins.
Model of Helicopter Sold or Purchased
Bell Serial Number
_
_
Registration Number
_
Company or Individual who purchased Helicopter
_
Address
_
City
_
State
_
Zip Code
_
County
_
Fax No.
_
Telephone No.
I 02 March 98
_
Page 5 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFtS -AHRS
MM97-09-01
Revision: A
TABLE OF CONTENTS
PAGE
Introduction
2
Introduction
Record of Revisions
List of Effective Pages
Helicopter Sale Notice
Table of Contents
3
4
5
6
Section One
AHRS
1.1 LCR-92 Attitude and Heading Reference System (AHRS)
1.1.1 Attitude and Heading Reference Unit (AHRU)
1.1.2 Flux Valve (MSU)
1.1.3 Compass Control Panel (CCP)
1.1.4 AHRS Test Switch
1.1.5 Equipment Shelf
1.1.6 Circuit Breaker Switches
1.2 System Test
1.3 Adjustment
1.3.1 Flux Valve Calibration
1.4 Standby Attitude Indicator
1.5 System Test
1.5.1 Adjustments
7
7
8
8
9
10
10
11
12
12
13
14
14
Section Two
EFIS
2.1 EFS 40 Electronic Flight Information System (EFIS)
2.1.1 EFIS Displays EHSJlEADI
2.1.2 Symbol Generator
2.1.3 Composite Switch (CMPST)
2.1.4 Supplemental Cooling
2.1.5 Electronic Display Overtemperature Annunciation
2.1.6 Circuit Breaker Switches
2.2 System Tests
2.2.1 Initial Turn On
2.2.2 Switch Function Test
2.2.3 Operational Checks
2.3 Configuration
2.3.1 Configuration Setup
15
15
15
16
17
17
18
18
18
19
20
22
24
Section Three
AIRWORTHINESS LIMITATIONS
3.1 Airworthiness Limitations Information
26
Section Four
INSPECTION REQUIREMENTS
4.1 100 Hour and Annual Inspection Requirements
Section Five
ELECTRICAL DIAGRAMS
I 02 March 98
27
29
Page 6 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
This document contains data to understand the operation of the EFIS/AHRS systems
and to do the necessary maintenance steps. This document also describes the
removal, installation and adjustment of the various HAS- EFIS/AHRS Equipment.
Inspection requirements are described in Section One and Section Two that are
pertinent when a component has been removed or replaced.
SECTION ONE
1.1 LCR-92 Attitude and Heading Reference System
The LCR-92 Attitude and Heading Reference System (AHRS) is an inertial sensor
system which provides both digital and analog heading, attitude and rate of turn data
to aircraft systems and instruments.
This section provides for on-aircraft maintenance procedures for the LCR-92 AHRS.
The LCR-92 AHRS consists of an Attitude and Heading Reference Unit (AHRU), a
Magnetic Sensor Unit "Flux Valve" (MSU), and a Compass Control Panel (CCP).
1.1.1 AHRU - Attitude and Heading Reference Unit
The AHRU is a strap down inertial measurement unit, using three Fiber
Optic Gyro (FOG) Sensors. Utilizing no moving parts, the FOG's
employ a split light beam that is sent in opposite directions through a
coil of glass fiber. Rotation around the coil axis causes increased beam
travel in one direction and reduced travel distance in the opposite
direction. . The difference in distance traveled produces phase
difference patterns sensed by a photo-detector. These differences are
a direct measure of gyro rate of rotation and are nulled by a feedback
loop. This closed loop operation results in a linear rate output signal
and is able to sense rotational rates in excess of 600 degrees per
second. A digital computer mathematically integrates the rate data to
provide attitude and magnetic heading data to aircraft systems. Long
term references for the system are comprised of an internal dual axis
level sensor (a spirit level that senses level up to 45 deg. in pitch and
roll) and the remotely mounted MSU.
The AHRU is located above the baggage compartment. Access to the
AHRU is through the baggage compartment overhead access panel.
The AHRU is mounted on the equipment shelf.
I 02 March 98
Page 7 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS - AHRS
MM97-09-01
Revision: A
Removal
1.
Disconnect the battery and external power from the helicopter
Disconnect electrical connectors.
Loosen the quick release knurled knob.
2.
3.
4. Slide the AHRU aft to remove.
Inspection
1. Inspect unit for general condition.
2. Inspect connector pins for damage and cleanliness.
Installation
1.
2.
3.
4.
5.
Disconnect the battery and external power from the helicopter
Slide the AHRU forward into position.
Tighten the quick release knurled knob.
Connect the electrical connectors.
Perform system test per section 1.2.
1.1.2 Flux Valve (MSU)
The MSU detects the horizontal component of the earth's magnetic field and
transmits it to the AHRU for use as long term correction information. The flux
valve is located aft of the baggage compartment. Access to the flux valve is
gained by removing the aft baggage compartment access panel.
Removal
1. Disconnect the battery and external power from the helicopter
2. Remove the six screws from the flux valve cover and remove the cover.
3. Identify and remove wires from flux valve.
4. Remove flux valve hold-down screws.
5. Remove flux valve from mounting bracket..
Inspection
1.
2.
Inspect unit for general condition.
Inspect wiring connections for evidence of corrosion.
Installation
1. Disconnect the battery and external power from the helicopter
Position flux valve in mounting bracket.
Install flux valve hold-down screws
Connect wires to flux valve.
Install the flux valve cover using the six screws.
6. Perform flux valve calibration per section 1.3.
2.
3.
4.
5.
1.1.3 Compass Control Panel
The CCP contains controls and annunciators to facilitate manual slaving of the
AHRU to the MSU. It also provides for additional AHRS capabilities such as;
Setting of the compass heading during free gyro (DG) mode, fast slaving
I 02 March 98
Page 8 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS - AHRS
MM97-09-01
Revision: A
during operation at extreme latitudes, slaved or free gyro (DG) operation
mode selection and nulling of compass error after alignment in areas of high
magnetic disturbances. The CCP is located in the aircraft pedestal.
Removal
1.
2.
3.
4.
Disconnect the battery and external power from the helicopter
Loosen two Dzues fasteners.
Pull CCP out of pedestal.
Disconnect electrical connector.
Inspection
1.
2.
3.
Inspect unit for general condition.
Inspect all fasteners for security.
Inspect the connector pins for damage and cleanliness.
Installation
1.
2.
3.
4.
5.
Disconnect the battery and external power from the helicopter
Connect the electrical connector.
Place the CCP in position in the pedestal.
Tighten the two Dzues fasteners.
Perform system test per section 1.2.
1.1.4 AHRS Test Switch
Manual self test of the AHRS can be initiated by depressing the AHRS Test
Switch located in the instrument panel. Activation of this switch causes the
AHRU to output test values to the EFS 40 System and other installed
equipment. The existing Weight on Gear Switch is used to inhibit the manual
self test of the AHRS when the aircraft is in the air.
Removal
1. Disconnect the battery and external power from the helicopter.
2. Remove the screws that attach the shroud inspection cover to the shroud.
3. Remove the shroud inspection cover from the shroud.
4. Pull the lens cover aft out of position in the panel.
5. Loosen the two screws inside the socket.
6. Pull the switch out of the panel.
Inspection
1.
2.
Inspect the switch for cleanliness and general condition.
Check lens legibility.
Installation
1. Disconnect the battery and external power from the helicopter.
Position the switch in place in the panel.
Tighten the two screws inside the socket.
Push the lens cover into position in the panel.
Place the shroud inspection cover in place on the shroud.
Install the screws that attach the shroud inspection cover to the shroud.
2.
3.
4.
5.
6.
I 02 March 98
Page 9 of 34
HAS Corporation
8ell407
Instructions For Continued Airworthiness
EFIS - AHRS
MM97-09-01
Revision: A
7. Perform system test per section 1.2.
1.1.5 Equipment Shelf
The equipment shelf is located behind the hat rack and above the baggage
compartment. The equipment shelf provides for a mounting place for the
AHRU.
Removal
1.
2.
Refer to section 1.1.1 for removal of the AHRU from the equipment shelf.
Remove the six screws from the equipment shelf and remove the shelf.
Inspection
1. Inspect the unit for general condition.
Installation
1. Disconnect the battery and external power from the helicopter.
2. Position the equipment shelf in position and install with the six screws.
3. Refer to Section 1.1.1 for installation of the AHRU onto the equipment shelf.
1.1.6 Circuit Breaker Switches
The circuit breaker switches for the AHRS system both provide a means for
turning power on and off of components and circuit protection in the case of
an overload on the circuit. There is a circuit breaker switch for the AHRS
system and the Standby Attitude Indicator.
Removal
1. Disconnect the battery and external power from the helicopter.
2. Loosen the Dzues fasteners from the breaker panel.
.3. Swing the breaker panel down and forward.
4. Identify the connected wires, remove the screws from the terminals.
5. Remove the attaching nut from the circuit breaker switch and remove the circuit
breaker switch.
Inspection
1. Inspect the unit for general condition.
Installation
1. Disconnect the battery and external power from the helicopter.
2. Position the circuit breaker and attach with mounting nut.
3. Connect the wires to the circuit breaker terminals with attaching screws.
4. Swing breaker panel back and up into position.
5. Tighten the Dzues fasteners.
I 02 March 98
Page 10 of 34
HAS Corporation
8ell407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
1.2 System Test
The following procedure may be used to verify proper operation and to isolate
defective components of the LCR-92 Attitude Heading Reference System
(AHRS). The EFS 40 System must be properly setup (configured) and
operational prior to performing these tests on the LCR-92 AHRS. Refer to
Section Two for details on test and adjustment of the EFS 40.
1. With power applied to the EFS 40, turn on the LCR-92 System
(switch type circuit breaker labeled AHRS in the overhead
circuit breaker panel) and verify that the ATT, HOG, and Rate of
Turn flags are extinguished within approximately 30 seconds. If
valid information is not displayed with in 90 seconds, remove
power from the system and verify power, ground and other
associated wiring is correct. If no fault is found, replace the
Attitude Heading Reference Unit (AHRU).
2. Press and Hold the AHRS Test switch and verify:
a. Magnetic Heading
b. Pitch Angle
c. Roll Angle
=
=
=
15 Oeg.
5 Oeg. Up
45 Oeg. Right 8ank
If the AHRS test is not initiated check the AHRS Test switch
and associated wiring. Verify that the Weight and Gear Switch
in the On Ground position. If no fault is found replace the
AHRU.
3.
Remove the AHRU from it's equipment rack, perform steps 4
and 5 and return the AHRU to it's rack to restore cooling air
within 10 minutes.
4. Move the AHRU in pitch and roll.
reacts correctly.
Verify the attitude display
5. Turn the AHRU and verify the heading displayed on the EHSI
(Electronic Horizontal Situation Indicator) and the Rate of Turn
Indication on the EADI (Electronic Attitude Director Indicator)
reacts correctly.
6. If satisfactory results are not observed in step 4 or 5, check the
associated wiring to the displays. If no fault is found replace the
AHRU.
7. With the MAG I DG switch in the MAG position the EHSI should
indicate the approximate heading of the helicopter. Select DG
and manually slave the heading using the + I 0 switch.
I 02 March 98
Page 11 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS - AHRS
MM97-09-01
Revision: A
8. Verify the heading displayed increases in the + position and
decreases in the 0 position.
9. Select the MAG position and verify the compass display returns
to the original heading.
10. If satisfactory results are not observed in steps 6 through 8,
check the operation of the Compass Control Panel switches
and the associated wiring. If no fault is found replace the AHRU.
11. Remove power from the AHRS.
12. Verify that the pitch scale, roll scale, roll index pointer, horizon
line, heading tape, blue sky and brown ground are removed
from the EADI. A red box with a red attitude fail inside it is
displayed on a black background in the upper center of the
EADI. Verify that the lubber line is replaced by a rectangular
red box with a red HOG inside it. Verify that the course arrow
declutters and a course deviation bar appears with the selected
course shown digitally in the upper left corner on the EHSI (with
valid signal from nav receiver).
13. Restore power to the AHRS and verify the EADI and EHSI
displays return to normal within approximately 30 seconds.
1.3 Adjustment
Adjustment of the AHRS system is not normally required once the initial
calibration has been perform after system installation. Calibration data is
stored in the Cal Prom, and is automatically read on system power up.
Therefore, no calibration is requires after replacement of the Compass Control
Panel or AHRU. If it becomes necessary to replace the Cal Prom or the Flux
Detector (Magnetic Sensor Unit), then the Flux Valve Calibration Procedure
must be performed.
1.3.1 Flux Valve Calibration
The AHRS utilizes the weight on gear switch that disables the
calibration mode by applying a ground to J4 pin 37 on the AHRU
while the helicopter is airborne.
The flux valve calibration
procedure (positioning the helicopter on the compass rose) may be
accomplished by hovering the helicopter provided J4 pin 37
remains open. This may be accomplished by temporarily removing
and stowing wire # AHS29A22 from J4 pin 37.
1.
I 02 March 98
Position the helicopter in an area that is known to be free of magnetic
disturbances.
Page 12 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
2.
Complete LCR 92 AHRS Flux Valve Calibration in accordance with
L1TEF Installation I Maintenance Instruction PIN 1141450-0000-840,
As Revised, Dated Nov. 1996, Section 1, Paragraph 11.
3.
Install wire # AHS29A22 in J4 pin 37 if previously removed.
1.4 Standby Attitude Indicator
The Standby Attitude Indicator provides the flight crew with a back-up attitude
reference. The Standby Attitude Indicator is installed in the instrument panel.
Removal
1.
Disconnect the battery and external power from the helicopter.
CAUTION - Wait 10 minutes for the gyroscope to come to a
complete stop prior to removing the attitude indicator. Failure
to obey this precaution may result in damage to the gyroscope
of the attitude indicator.
2.
3.
4.
5.
Remove the screws that attach the shroud inspection cover to the shroud.
Remove the shroud inspection cover from the shroud.
Disconnect the electrical connector from the attitude indicator.
Hold the attitude indicator and remove the screws that attach the attitude
indicator to the instrument panel.
CAUTION - Handle the attitude indicator carefully to avoid
damage to the gyroscope.
6. Remove the attitude indicator.
Inspection
1. Inspect the indicator for damage, the electrical connector pins for
cleanliness and alignment.
Installation
1.
2.
3.
4.
5.
6.
I 02 March 98
Disconnect the battery and external power from the helicopter.
Install the attitude indicator into its location on the instrument panel.
Attach the attitude indicator to the instrument panel with screws (3).
Connect the electrical connector to the receptacle of the attitude indicator.
Place the shroud inspection cover in place on the shroud.
Install the screws that attach the shroud inspection cover to the shroud.
Page 13 of 34
HAS Corporation
8ell407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
1.5 System Test
1. Verify the Gyro Warning Flag is in view prior to applying power.
2. Apply power to the Standby Attitude Indicator (switch type circuit breaker labeled
An in the overhead circuit breaker panel).
3. Verify the Warning Flag retracts. The pitch and roll scales should initially oscillate
and then become stable.
4. Verify no loud noises are present (indication of impending bearing failure)
5. Pull the PULL TO CAGE knob and verify the indicator cages.
6. Release the cage knob and verify the pitch and roll indication does not drift over a
10 minute period.
1.5.1 Adjustments
No field adjustments are authorized.
I 02 March 98
Page 14 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
SECTION TWO
2.1 EFS 40 Electronic Flight Instrument System (EFIS)
The Bendix/King EFS 40 is an Electronic Flight Instrumentation System (EFIS) that
uses cathode ray tubes (CRT's) to display required flight information. The system
consists of a remote mounted Symbol Generator (SG), Electronic Attitude Director
Indicator (EADI), Electronic Horizontal Situation Indicator (EHSI) and a panel
mounted control for adjusting the brightness of the EADI. Information processed by
the SG is displayed in a multicolor graphic form on the EADI and EHSI.
2.1.1 EFIS Displays· EHSIIEADI
The EHSI and EADI are both four inch by four inch multicolor electronic displays.
The EHSI includes the mode, course, heading selectors, and brightness control,
which are mounted into the front bezel. The EADI incorporates a bezel mounted
inclinometer. The panel mounted potentiometer, located to the right of the display
allows brightness control of the EADI. Both electronic displays receive power from
the symbol generator.
Removal
1. Disconnect the battery and external power from the helicopter
2. Remove four screws from the indicator face.
3. Slide the unit aft out of the mounting tray.
Inspection
1.
2.
Inspect unit for general condition.
Inspect connector pins for damage and cleanliness.
Installation
1. Disconnect the battery and external power from the helicopter
2. Slide the unit into its mounting tray.
3. Install the four screws in the indicator face.
4. Perform functional test per section 2.2.1. If the EHSI has been replaced perform
switch function test per section 2.2.2.
2.1.2 Symbol Generator
The symbol Generator receives information from other navigational systems
such as attitude and heading reference, air data, navigation and flight director.
Additionally, the Symbol Generator serves as a concentrator of navigation
I 02 March 98
Page 15 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
information and sends the displayed information to the Automatic Flight Control
System. Either part number 066-04021-1111 (software version 11) or 06604021-1113 (software version 13) may be used. The Symbol Generator is
located above the baggage compartment. Access to the symbol generator is
provided by removing the baggage compartment overhead access panel.
Removal
I.
2.
3.
Disconnect the battery and external power from the helicopter.
Loosen the two quick release knurled knobs.
Slide the symbol generator forward by pulling on the handle built
into the symbol generator.
Inspection
1.
2.
Inspect unit for general condition.
Inspect connector pins for damage and cleanliness.
Installation
1.
2.
3.
4.
Disconnect the battery and external power from the helicopter.
Slide the symbol generator aft into position.
Tighten the two quick release knurled knobs.
Perform operational check of EFS 40 system per section 2.2.3.
2.1.3 Composite Switch (CMPST)
An EFS Composite switch, mounted on the instrument panel below the EHSI,
allows the pilot to combine the EADI and EHSI on the remaining display in the
event of a failure of one of the displays.
Removal
1. Disconnect the battery and external power from the helicopter.
2. Remove the screws that attach the shroud inspection cover to the shroud.
3. Remove the shroud inspection cover from the shroud.
4. Pull the lens cover aft out of position in the panel.
5. Loosen the two screws inside the socket.
6. Pull the switch out of the panel.
Inspection
1.
Inspect the unit for general condition.
2. Inspect the lens for legibility.
Installation
1. Disconnect the battery and external power from the helicopter.
2. Position the switch in place in the panel.
3. Tighten the two screws inside the socket.
4. Push the lens cover into position in the panel.
5. Place the shroud inspection cover in place on the shroud.
6. Install the screws that attach the shroud inspection cover to the shroud.
7. Perform switch function check per section 2.2.3, step 48.
I 02 March 98
Page 16 of 34
HAS Corporation
8ell407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
2.1.4 Supplemental Cooling
A supplemental cooling fan is installed to ensure the electronic displays do not
exceed their operational temperature limits during maximum hot day
operation. The fan is located on the bottom of the instrument panel shroud on
the pilots side.
Removal
1. Gain access to the fan mounting hardware.
2. Disconnect the electrical connector.
3. Remove the fan attachment hardware.
4. Remove fan and screens.
Inspection
1.
2.
Inspect the fan for cleanliness and general condition.
Inspect fan blades for damage.
Note:
Screens must be installed properly. The high side of the screen is
placed away from the fan to prevent fan/screen interference.
Installation
1. Position fan and screens in place with fan flow arrow into the panel.
2. Install fan attachment hardware.
3. Connect the fan electrical connector.
4. Apply power to the rotorcraft and verify fan operation.
2.1.5 Electronic Display Overtemperature Annunciation
The EDTEMP annunciator in the Caution Panel, in conjunction with the
electronic display thermostat, alerts the pilot that either or both of the
EFIS displays are operating in an overtemperature condition. Access to
the thermostat is through removal of the shroud inspection cover.
Removal
1.
2.
3.
4.
5.
6.
Disconnect the battery and external power from the helicopter.
Remove the screws that attach the shroud inspection cover to the
shroud.
Remove the shroud inspection cover from the shroud.
Disconnect the electrical connections from the thermostat.
Remove the attaching hardware from the thermostat.
Remove the thermostat.
Inspection
1.
Inspect the thermostat for cleanliness and damage.
Installation
1.
I 02 March 98
Place the thermostat into position.
Page 17 of 34
HAS Corporation
Bell 407
2.
3.
4.
5.
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
Install the attaching hardware.
Connect the electrical connections.
Place the shroud inspection cover in place on the shroud.
Install the screws that attach the shroud inspection cover to the
shroud.
2.1.6 Circuit Breaker Switches
The circuit breaker switches for the EFIS system both provide a means for
turning power on and off of components and circuit protection in the case of
an overload on the circuit. There is a circuit breaker switch for the EADI and
EHSI Displays.
Removal
1. Disconnect the battery and external power from the helicopter.
2. Loosen the Dzues fasteners from the breaker panel.
3. Swing the breaker panel down and forward.
4. Identify the connected wires, remove the screws from the terminals.
5. Remove the attaching nut from the circuit breaker switch and remove the circuit
breaker switch.
Inspection
1. Inspect the unit for general condition.
Installation
1. Disconnect the battery and external power from the helicopter.
2. Position the circuit breaker and attach with mounting nut.
3. Connect the wires to the circuit breaker terminals with attaching screws.
4. Swing breaker panel back and up into position.
5. Tighten the Dzues fasteners.
2.2 System Tests
2.2.1 Initial Turn On
1.
Apply power to the EFIS, AHRS, and other avionics systems as
required.
2.
Adjust the EHSI and EADI dim control to a comfortable level.
3. Press the TST/REF button and hold for 3 seconds.
4.
I 02 March 98
Verify that the EFS 40 system enters self- test and displays a yellow
"SELF TEST PASS" message. Confirm that the compass and roll
scale is white. (This confirms that all three colors are operating in the
display unit.) The EFS 40 will automatically exit the self-test mode
and revert to normal after 5 seconds.
Page 18
of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFtS -AHRS
MM97-09-01
Revision: A
2.2.2 Switch Function Test
1.
Navigation Sensor Select (NAV)
Push the Navigation Sensor Select (NAV) button. and verify the display
sequentially selects VOR (or LOC), ADF, and GPS as the primary display on the
course pointer / deviation indicator.
2.
System Select (1/2)
With NAV displayed push the System Select (1/2) button and verify the NAV
Source annunciation alternates between NAV 1 and NAV 2.
3.
HSI Mode Select
Push the HSI Mode Select Button and verify the display sequences through the
available 360 degree HSI formats.
4.
Course Select (DIR)
Verify that by rotating the Course knob that the pointer moves in a corresponding
direction. Verify that the digital readout corresponds to the course pointer.
5.
Number 1 Bearing Pointer Select
Verify that by repeatedly pressing this button, the Number 1 Bearing Pointer cycles
sequentially through Nav 1, ADF. and GPS sensors.
6.
Number 2 Bearing Pointer Select
Verify that by repeatedly pressing this button, the Number 2 Bearing Pointer cycles
sequentially through Nav 2, ADF and GPS sensors).
7.
Heading SET / SYNC
Verify that by rotating the HDG knob that the heading bug moves in a
corresponding direction. Push on the center of this knob (sync button) and verify
the Heading Bug synchronizes to the present heading. Verify that the digital
readout corresponds to the heading bearing.
8.
Arc Mode Select (ARC)
Push the Arc Mode Select (ARC) button and verify the system converts the
standard 360 deg. compass rose presentation to a large scale 85 deg. sector
presentation.
9.
Range Down
Pressing the Range Down button selects the next shorter distance range to be
displayed when in the NAV MAP mode.
10. Range Up
Pressing the Range Up button selects the next longer distance range to be
displayed when in the NAV MAP mode.
11. Self Test (TST / REF)
Pressing and holding the Self Test (TST / REF) button for 3 seconds will start the
system self test. While the EHSI is in the Map Mode, momentarily pressing the
TST / REF button will sequentially cycle through the following MAP formats. Verify
each of the following formats:
a) FPL ID
b) AIRPORTS
c) NAVAIDS
I 02 March 98
Flight plan waypoints with ICAO
identifiers
TO waypoint and nearest airports with
ICAO identifiers
TO waypoint and nearest navaids with
ICAO identifiers
Page 19 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
2.2.3 Operational Checks
Operation of the EFS 40 System is dependent upon proper configuration.
The system needs configured if the Symbol Generator has been replaced
or if CHECK CONFIGURATION is displayed on start up. Refer to the end
of this section for details on configuration of the EFS 40.
The order of the following tests may be adjusted for convenience. If
required, the helicopter may be relocated outside to provide required
signals. Those tests requiring real world signals may be complete at the
end of this procedure. It is recommended that this procedure is read in its
entirety before starting.
1.
Ensure power is applied to all other associated systems (NAV's,
GPS. etc.).
2.
Generate a calibrated NAVand DME signal. Tune only Nav 1 to the
test frequency. (Nav 2 will remain invalid for this test). Select NAV 1
on the display.
3. Verify the HSI displays left I right and to I from information.
4. Verify that proper DME distance is displayed in the upper right
corner of the display.
5.
Set in a ground speed and verify the proper display is shown.
6.
Put the DME in hold and verify the DME distance display turns white
and an "W appears.
7. Adjust the generated Nav signal to center the needle with a TO flag.
Increase bearing by 10 degrees for a full scale right deflection, push
the DIR knob and verify the course pointer rotates to center the 0bar.
8.
Decrease the bearing by 10 degrees and verify that the D-bar
deflects full scale to the left.
9.
Select NAV on the #1 Bearing Pointer Selector. Verify the single
needle bearing pointer appears and points to the appropriate bearing.
10. Select NAV on the #2 Bearing Pointer Selector. Red dashes should
appear under the #2 Pointer annunciator.
11. Turn off the DME signal and confirm the distance display field is
green dashes.
12. Turn off the Nav signal and confirm D-bar and TO I FROM declutters.
13. Repeat steps 13 through 23 for the Nav 2 system.
14. Tune the ADF to a good NOB or broadcast station and select ADF
with the EFIS NAV button. It may be necessary to move the
helicopter outside in order to receive a sufficient signal.
15. Verify deviation and TO I FROM are displayed on the HSI.
16. Tum the CRS pointer to deflect the needle away from center. Push
the course DIR button and confirm that the course pointer moves to
center the D-bar.
I 02 March 98
Page 20 of 34
HAS
Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
17. Verify that when the ADF is tuned to an unused frequency that the Dbar freezes for 3 seconds, then centers, and that a red X appears
over the D-bar scale and that the TO / FROM declutters.
18. Select ADF on the #1 Bearing Pointer Selector. Verify the single
needle bearing pointer appears and points to the appropriate bearing.
19. Select ADF on the #2 Bearing Pointer Selector. Verify the double
needle bearing pointer appears and points to the appropriate bearing.
20. Generate a valid GPS signal and select GPS with the EFIS NAV
button. It may be necessary to move the helicopter outside in order
to receive a sufficient signal. The GPS test output (if available) may
be used instead of moving the helicopter outside.
21. Verify the Course arrow automatically slew's to the desired track.
22. Verify GPS distance is displayed.
23. Provided valid wind data is being supplied by the GPS, verify wind
vector appears in the upper left comer of the EHSI.
24. Select GPS on the #1 Bearing Pointer Selector. Verify the single
needle bearing pointer appears and points to the appropriate bearing.
25. Select GPS on the #2 Bearing Pointer Selector. Verify the double
needle bearing pointer appears and points to the appropriate bearing.
26. Select NAV 1 using the EFIS NAV button, tune the nav receivers to
the test set localizer / GS frequency, and set the CRS pointer under
the lubber line.
2? Verify LOC 1 is displayed on the EHSI.
28. Set Nav Test Set to provide simultaneous localizer and glideslope
signal. Check for proper localizer and glideslope indication on the
EHSI and the EADI.
29. Set the Nav Test Set to provide, in turn, 1 /2 scale and full scale, left
and right deviations. Check for proper Localizer display deflections.
30. Set the Nav Test Set, in turn, for 1 /2 scale and full scale, up and
down deviations. Check for proper Glide Slope display deflections.
31. Rotate the CRS pointer 360 degrees and note the glideslope display
declutters whenever the course pointer is more than 105 degrees
from the lubber line.
32. Press the 1 /2 button and repeat steps 37 through 42 for the Nav 2
system. Verify that LOC 2 is displayed on the EHSI.
33. With Radio Altimeter operating, and the Course Arrow set under the
lubber line verify the rising runway is active.
34. Set the Nav Test Set to provide, in turn, 1 /2 scale and full scale, left
and right deviations. Verify the runway moves laterally with localizer
deviation.
35. Activate Radio Altimeter Test and confirm that 50 feet is displayed in
the upper right corner of the EADI and that the rising runway reflects
the 50 foot altitude.
I 02 March 98
Page
21 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
36. Set the DH Selector on the Radar Altimeter Indicator to 100 feet and
verify that DH is displayed on the EADI.
37. Generate a Marker Beacon signal and verify the ED 461 displays the
outer, middle, and inner marker.
38. Press HSI button until the EHSI display cycles to the NAV MAP
mode. A standard 360 degree compass rose will be displayed.
39. Tune the NAVand DME test sets to provide a simulated VORTAC.
Tune the NAVand DME to the test set frequencies and select Nav 1
on the EFIS. Verify a VORTAC symbol is displayed with a course
line going through it.
40. Press the NAV button to cycle the display to GPS.
41. Verify the series of map locations are plotted on the EHSf.
42. With GPS selected, verify the TST/REF button changes the format
selection.
43. Press the NAV button to cycle to ADF and confirm the display
annunciates either LNAV MAP when the GPS is valid or NO MAP
with invalid GPS.
44. Press the ARC mode selector button. The 360 degree compass rose
on the EHSI should change to a large scale 85 degree sector
presentation.
45. Rotate the heading bug off the display. Verify a digital readout
appears before the bug is fully out of view and a digital indication the
location of the bug appears.
46. Confirm the course pointer and its digital readout are displayed.
47. Confirm LOC and GS displays are present when an ILS frequency is
selected and the system switches from VOR to LOC.
48. Press the Composite Display Switch located below the ED 461 and
verify both attitude and heading I navigation information is displayed
on both displays.
2.3 Configuration
The configuration is set on installation and stored in a Configuration
Module located in the Symbol Generator Equipment Rack. If it becomes
necessary to replace the Symbol Generator, the stored configuration may
be copied into the new Symbol Generator by use of the following
procedure.
1.
Apply power to the EFS 40 System.
2. Allow the system to complete the power on self test. CHECK
CONFIGURATION should be displayed.
I 02 March 98
3.
Press and hold the TST/REF button on the EHSI for 3 seconds.
4.
While the self test is displayed on the EHSI, press the HSI and ARC
simultaneously. The EHSI Maintenance Page should now be
displayed.
Page 22 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
5.
Gain access to the front of the Symbol Generator and with a suitable
tool press switch S1. This allows the configuration of the Symbol
Generator or the Configuration Module to be changed.
6.
The Range Up and Down buttons and the Single and Double Arrow
RMI buttons are used to control the cursor (pointing hand) and
menus on the maintenance pages.
Range Down
Range Up
Double Arrow
Single Arrow
=
7.
=
=
=
Next Menu
Previous Menu
Next Item
Previous Item
Use the Next Item button to move the pointing hand on the display to
the System Configuration Line.
8. Press the Next Menu button to view the Configuration Menu.
9.
Using the Next Item button, select Copy Rack 1 to GS & Rack 2.
10. Press the Next Menu button. The display should read:
"PRESS NEXT MENU BUTTON"
"TO COpy THE CONFIG DATA IN"
"RACK 1 TO THE SG AND RACK 2"
11. Press the Next Menu button. The display should read COPYING and
then COPY PASS.
12. Press the Prevo Menu button to return the configuration menu. Verify
the symbol generator and the configuration module have the same
configuration by using VIEW/EDIT EQUIPMENT CONFIG and VIEW
EDIT OPERATION CONFIG.
13. Once the configuration has been verified, return to the configuration
menu and press the TST / REF button. This will return the system to
normal operation.
14. Cycle power to the EFS 40 system and verify no CHECK CONFIG
message is present on the EADI of EHSI.
I 02 March 98
Page 23 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
2.3.1 Configuration Setup
The configuration setup shown below is representative of a typical avionics suite and
does not necessarily apply to each customer's configuration. Those values that may
change are indicated by an asterisk (*) following the value. The installing agency is
required to determine and configure the system using values appropriate to the
customer requirements in accordance with Bendix I King EFS 40 I 50 Installation
Manual and record the configuration in the appropriate section of the Pilots Guide.
Equipment Configuration
View Edit Equipment
Item
Value
SG Number
0
Description
#1 EFIS
Single I Dual
2
Single EADII EHSI
DU Type
0
ED 461
AttitudeIHDG#1
2
429ATT
AttitudeJHDG#2
0
None
429 ROT
429 HOG
Rate otTum
4
ADF#1
1·
DC SIN/COS
ADF#2
O·
None
VORlILS#1
2·
429 BRG
VORlILS#2
2·
429 BRG
DME#1
2·
King Serial DME
DME#2
2·
King Serial DME
MlS#1
O·
O·
None
MLS#2
FMS#1
5"
KlN 90 GPS
FMS#2
O·
O·
None
RNAV#2
0"
None
TACAN#1
TACAN#2
O·
O·
None
RNAV#1
None
None
None
FMSVNAV
0
None
Radar A1t
1·
KRA405
AFCS Type
0
None
AFCS Command Bar
0
Scaling None
AFCS Mode Ann
0
None
F/S Air Data
0
None
Radar Type
0
None
Radar CII Pnl
0
None
Radar Indicator
0
None
Checklist
0
None
Joystick
0
None
TCAS
None
Lightning Det
O·
O·
O·
O·
None
Hover Mode
0
None
Cable Mode
0
None
Variable LNAV
1"
LNAV 1: Var.
Homing #1
Homing #2
I 02 March 98
None
None
LNAV2: Fix
Page 24 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
Operational Configuration
View Edit Equipment
Item
Value
Description
Vert Scale Side
0
Right
DCLTR GS On BC
1
Yes
Full Time FMS Map
1
Yes
Display Wind Vec
1
Yes
Display Drift
1
Yes - when FMS Selected
DC Only Mode
0
No
DME Dist Only
0
No
Radar Only Mode
0
No
MFD Nav Control
0
Normal CP Operation
Spare
Display HDG Tape
0
No
ADI Plane/CMD Bar
1
Bulls eye I Split Cue
Roll Indicator
1
Sky Pointer
Yes
DCLTER Unus AIT
1
CAT" Available
0
No
Perspective Lines
1"
Yes
DH Select
0
No
CTL PNLSync
0
No
SEL HDG Sync
0
No
SELCRS Sync
0
No
North Up Map
0
No
Vert PTR Type
0
Small Diamond
Display FMS MSG
1"
Yes
Sel HDG Color
0
Orange
CMD Bar Color
0
Green
Rev Mode Ann
0
None
Rising Runway
0"
ADI Loc Display Rising Runway
ADI DEVSRC
0
ON Side ILS
CMD Bar Filter
3"
0.25 sec.
MLS VRT Annunc
0
GS
Datum Scaling
0"
393mV I Deg
HDG Fail Annunc
0
Normal
VNAV APR Scale
0
1000 Ft
LNAV CRS CTRL
0
No
SG #1 Side
0
Left
Aircraft Symbol
1
Rotary Wing
TACAN Annunc
0
None
TCAS Displays
0
None
CAT II Sensors
0
LOC Only
Radar Scan
0
90 Deg.
Radar SDI
0
None
Pitch Sync Disc
0
No
Hold Dst on ADF BRG Plr
0"
No
I 02 March 98
(SW Ver. 13 Only)
Page 25 of 34
HAS Corporation
Bell 407
MM97-09-01
Revision: A
Instructions For Continued Airworthiness
EFIS -AHRS
3.1 No Airworthiness Limitations associated with this STC.
Approving ACO
.fr/yA-eo
I 02 March 98
Page 26 of 34
HAS Corporation
8ell407
Instructions For Continued Airworthiness
EFtS -AHRS
MM97-09-01
Revision: A
SECTION FOUR
4.1 100 Hour and Annual Inspection Requirements
REFERENCE
INSPECTION, TASK DESCRiPTION
GENERAL
The EFS 40 and LCR-92 are modular self testing
systems. There are no manual tests required and
the components of these systems do not require
scheduled overhaul or any special inspection.
1. Review logbooks for reported discrepancies
and / or deferred maintenance items.
EFS 40 EFIS
Bendix I King Installation
Manual, Service
Bulletins, Service
Letters, HAS Service
and Advisory Letters.
FAA AD's or your
cognizant CAA's
Airworthiness
Directives, Bendix I King
Service Bulletins,
Service Letters, HAS
Service and Advisory
Letters.
1. Troubleshoot and correct discrepancies, if
applicable.
2. Ensure that all Airworthiness Directives,
Service Bulletins and Service Letters have
been reviewed for applicability and/or complied
with.
3. Inspect all electrical wiring at the components,
for worn or frayed cables, loose or broken
connectors, clamps and fasteners.
4. Inspect all equipment mounting for cracks,
corrosion, distortion, loose or missing rivets
and hardware, chaffing and security of
attachment.
5. Inspect placards, decals and markings for
appearance, legibility and conformity to
configuration. See HAS document IPB9? -0601 for details.
I 02 March 98
Page 27 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFtS -AHRS
MM97-09-01
Revision: A
100 Hour and Annual Inspection Requirements
REFERENCE
INSPECTION, TASK DESCRIPTION
INITIAL
INITIAL
MECH.
INSP.
LCR-92 AHRS
L1TEF Installation
Manuals, L1TEF Service
Bulletins, Service
Letters, HAS Service
and Advisory Letters.
FAA AD's or your
cognizant CAA's
Airworthiness
Directives, L1TEF
Service Bulletins,
Service Letters, HAS
Service and Advisory
Letters.
1. Troubleshoot and correct discrepancies, if
applicable.
2. Ensure that all Airworthiness Directives,
Service Bulletins and Service Letters have
been reviewed for applicability and/or complied
with.
Note: FAA AD 96-21-13 Amendment 39-9789 - L1TEF GmbH
AHRS System Misleading Pitch and Roll Information is
not applicable by part number.
3. Inspect all electrical wiring at the components,
for worn or frayed cables, loose or broken
connectors, clamps and fasteners.
4. Inspect all equipment mounting for cracks,
corrosion, distortion, loose or missing rivets
and hardware, chaffing and security of
attachment.
5. Inspect placards, decals and markings for
appearance, legibility and conformity to
configuration.
I 02 March 98
Page 28 of 34
HAS Corporation
Bell 407
Instructions For Continued Airworthiness
EFIS -AHRS
MM97-09-01
Revision: A
SECTION FIVE
Diagrams
Page
AHRU Wiring Diagram
30
EFIS - Power and Ground Wiring Diagram
31
EFIS - EADI, EHSI and Symbol Generator Wiring Diagram
32
EFIS - Symbol Generator/Avionics Interface Wiring Diagram
33
Cooling Fan, EFIS Display Overtemperature System, Standby Attitude Gyro,
Compass Control Panel Wiring Diagram
34
I 02 March 98
Page 29 of 34