Via Giovanni Agusta, 520

21017 Cascina Costa di Samarate (VA) Italy

Tel.: +39 0331-229111 - Fax: +39 0331-229605/222595

An Company

TRANSLATION OF

BOLLETTINO TECNICO N° 139-46-001

The technical content of this document is approved
under the autority of DOA nr EASA.21J.005 March
DATECosta
21017 Cascina 1, 2005
di Samarate (VA) Italy
Via Giovanni Agusta, 520
A FINMECCANICA COMPANY Tel.: +39 0331 229111 - Fax: +39 0331 229605 - 222595
REV. /

Compliance with
this bulletin is: MANDATORY

SUBJECT: PART I: “PRIMUS EPIC®” FLIGHT SOFTWARE RELEASE 2.4.0

21017 Cascina Costa di Samarate (VA) Italy
INSTL.
S.p.A.
Via Giovanni Agusta, 520
Tel. (0331) 229111 - Tlx. 332569 - Fax: (0331) 229605
PART II: GPS ANTENNA P/N S67-1575-132 INSTL.
PART III: PILOT MASTER CAUTION/WARNING P/N 3G3150V00353
COPILOT MASTER CAUTION/WARNING P/N 3G3150V00453
INSTL. and DIMMING SYSTEM CTRL PANEL P/N
3G3320V00353;
PART IV: MAIN ROTOR BLADES COLLECTIVE MINIMUM PITCH
SETTING.

REASON: PART
Costruzioni I: provide
Aeronautiche the necessary
Giovanni AGUSTA procedures to perform
- Cascina Costa the “PRIMUS
(Gallarate) - Italia
EPIC®” Flight Software release 2.4.0 installation with the
subsequent required ADI panels and modules substitution.
PART II: provide the necessary instructions to perform the GPS antenna
P/N S67-1575-132 installation.
PART III: to expand the flight envelope allowing the night flight.
PART IV: to expand the flight envelope reducing the minimum flyable
weight.

HELICOPTERS AFFECTED: Agusta-Bell AB139 helicopters N/C 31008 and 31010.

An appropriate entry should be made in the aircraft log book upon accomplishment.
I f o w n e r s h i p o f a i r c r a f t h a s c h a n g e d , p l e a s e , f o r w a r d t o n e w o w n e r.

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B.T. 139-46-001

COMPLIANCE: within and not later the next 50 flight hours.

DESCRIPTION: release 2.4.0 of the “PRIMUS EPIC®” Flight Software been made
available by Honeywell and certified by Agusta.

PART I of this Bollettino Tecnico is issued to provide the necessary procedures to be

followed to install the “PRIMUS EPIC®” Flight Software release 2.4.0 on the
helicopter.
The software has to be installed by use of the remote terminal provided with the
proper installation tools and must be installed only by Honeywell or Agusta
authorised personnel.
The software uploading is performed by mean the LAN network connected to a
remote terminal. The “PRIMUS EPIC®” Flight Software release 2.4.0 installation will
greatly improve the operational capabilities of the AB139 helicopter activating :
ü new autopilot;
ü flight management system (FMS);
ü GPS;
ü flight director (FD);
ü Vne Envelope improvement
PART II of this Bollettino Tecnico is issued to provide the necessary procedures to
be followed to install the GPS antenna P/N S67-1575-132 on the helicopter and to
activate the corresponding system.
PART III of this Bollettino Tecnico is issued to provide the necessary modifications
that allows the night flight.
PART IV of this Bollettino Tecnico is issued to provide the necessary procedures to
set main rotor blades minimum collective pitch in order to:
• reduce the minimum flyable weight from the present 4800 kg to 4400 kg;
• permit to operate a slope landing or take-off from inclined ground up to 10
degrees nose-up and 5 degrees in all others directions.

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 B.T. 139-46-001

REQUIRED MANPOWER:
PART I: approximately 5 man-hours are required for the software installation and
additional 5 man-hours are required for the ADI instruments panel and modules
replacement.
PART II: approximately 4 man-hours are required for the GPS antenna installation.
PART III: approximately 2 man-hours are required for the for the instruments
replacement.
PART IV: approximately 4 man-hours are required for the main rotor blades and
collective adjustable setting. A new tracking procedure for the main rotor blade
should follow the minimum collective pitch setting that could require some rotors
launches and stops with pitch link rods fine tuning
Man-hours are based on hands-on time and may vary with personnel and facilities
available.

WARRANTY: N.A.

REQUIRED MATERIALS:
PART I: the following materials, necessary to accomplish the PART I of this
Bollettino Tecnico, can be required to Agusta company:

P/N NOMENCLATURE Q.TY

MM7030191-003 PRIMUS EPIC® Flight Software CD 1
501-1860-0201 Mod.10 ADI STBY Display 2
501-1870-38 Configuration Module 2
7011702-946 Guidance Control Panel 1

PART II: the following materials, necessary to accomplish the PART II of this
Bollettino Tecnico, can be required to Agusta company:

P/N NOMENCLATURE Q.TY

S67-1575-132 GPS Antenna 1
MS24693S274 Screw 4

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B.T. 139-46-001

P/N NOMENCLATURE Q.TY

ED300E17 Decal 1
Adesivo Proseal 890 Classe B2
MIL-S-8802 AR
(cod. 900001586)

PART III: the following materials, necessary to accomplish the PART III of this
Bollettino Tecnico, can be required to Agusta company:

P/N NOMENCLATURE Q.TY

3G3150V00353 Pilot Master Caution/Warning 1
3G3150V00453 Copilot Master Caution/Warning 1
3G3320V00353 Dimming Control Panel 1

PART IV: N.A.

SPECIAL TOOLS: for the equipments required to accomplish this Bollettino Tecnico see
the documents in REFERENCES.

WEIGHT AND BALANCE CHANGES: N.A.

REFERENCES:
1) Honeywell Engineering Specification n° EB7034547
2) AB139 Aircraft Maintenance Publication (AMP)
3) Avionic System S/W Load Acceptance Test Procedure – 139G0630D005
4) AB139 AFCS System Acceptance Test Procedure – 139G2200D002
5) AB139 GPS-FMS Acceptance Test Procedure – 139G3450D001
6) AB139 Avionic System ground and flight test report – 139G4600T002/2
7) AB139 Avionic System Acceptance Test Procedure - 139G4600D001
8) AB139 Internal and External Lighting Electrical System ATP – 139G3300D001
9) AB139 Flight Control Acceptance Test and Rigging Procedure – 139G6700D001

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 B.T. 139-46-001

PUBLICATIONS AFFECTED:
ü AB139 Aircraft Maintenance Publication (AMP)
ü AB139 Illustrated Parts Data (IPD)
ü Rotorcraft flight manual (RFM)

COMPLIANCE INSTRUCTIONS:
PART I:
1. Prepare the helicopter for a safe ground maintenance. Disconnect the battery and
all the electrical power sources and/or the external power supply.
2. In accordance with AB139 Aircraft Maintenance Publication (AMP) and with
reference to figure 1, from the instruments panel remove the Pilot and the Copilot
ADI-STBY Display P/N 501-1860-0201 Mod. 5 and the Pilot and the Copilot
Configuration Module P/N 501-1870-29 and install the new Pilot and Copilot ADI-
STBY Display P/N 501-1860-0201 Mod. 10 and the new Pilot and Copilot
Configuration Module P/N 501-1870-38.
3. With reference to figure 4 - point A and B - from the instruments panel, remove
the placard P/N 3G1130L00153 “VNE placard illuminated” and P/N
3G1130L00251 “Day/Night operation placard” and install the new placard P/N
3G1130L00152 and P/N 3G1130L00252
4. In accordance with AB139 Aircraft Maintenance Publication (AMP) and with
reference to figure 1, from the interseat console remove the Guidance Control
Panel P/N 7011702-942 and install the new Guidance Control Panel P/N
7011702-946.
5. Perform the installation of the PRIMUS EPIC® Flight Software CD P/N
MM7030191-003, in accordance with the following Honeywell document, included
in the set of Component Maintenance Publications (AB139-CMP) available to the
Customer:
Vendor Publication Code: EB7034547
Vendor: Honeywell

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B.T. 139-46-001

WARNING !
THE PRIMUS EPIC® FLIGHT SOFTWARE
MUST BE INSTALLED ONLY BY
HONEYWELL or Agusta authorized
PERSONNEL.

6. Perform the acceptance test procedure of the avionic system S/W load in
accordance with appendix A.
7. Perform the acceptance test procedure of the AFCS system in accordance with
appendix B.
8. Return helicopter to flight configuration and record for compliance of PART I of
this bollettino.

PART II:
1. Prepare the helicopter for a safe ground maintenance. Disconnect the battery and
all the electrical power sources and/or the external power supply.
2. Gain access the GPS antenna support assy P/N 3G5315A09731, installed over
the tail rotor shaft cowling, and remove the existing cover and fixing hardware.
3. Remove any possible sign of sealant from the GPS antenna support assy P/N
3G5315A09731, with cloth dampened with Methylethilketone.
4. In accordance with figure 2, gain access the GPS coax cable assy P/N D383,
stowed inside the tail rotor shaft cowling, and untie the connector E17P1 from the
cable loom.
5. In accordance with figure 3 detail D, remove the protective NOMEX sleeve P/N
A582A32 and the NAS813-10 protective plug from the connector E17P1.
6. In accordance with figure 3 view B, connect the connector E17P1, of the GPS
coax cable assy P/N D383, to the GPS antenna P/N S67-1575-132 connector.
7. Install and secure the GPS antenna P/N S67-1575-132 to the GPS antenna
support assy P/N 3G5315A09731 with four MS24693S274 screws.
NOTE
Apply sealant MIL-S-8802 type II class B-4 on
antenna edges and screws heads.

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 B.T. 139-46-001

8. Perform the acceptance test procedure of the GPS system in accordance with
appendix C.
9. Perform the acceptance test procedure of the avionic system ground and flight in
accordance with appendix D.
10. Return helicopter to flight configuration and record for compliance of PART II of
this bollettino.

PART III:
1. Prepare the helicopter for a safe ground maintenance. Disconnect the battery and
all the electrical power sources and/or the external power supply.
2. In accordance with AB139 Aircraft Maintenance Publication (AMP) and with
reference to figure 1, from the instruments panel remove the Pilot Master
Caution/Warning P/N 3G3150V00351 and the Copilot Master Caution/Warning
P/N 3G3150V00451 and install the new Pilot Master Caution/Warning P/N
3G3150V00353 and the new Copilot Master Caution/Warning P/N
3G3150V00453.
3. In accordance with AB139 Aircraft Maintenance Publication (AMP) and with
reference to figure 1, from the instruments panel remove the dimming system ctrl
panel P/N 3G3320V00352 and install the new dimming system ctrl panel P/N
3G3320V00353.
4. Perform the acceptance test procedure of the MWL and MCL in accordance with
appendix E.
5. Perform the acceptance test procedure of the internal dimming system in
accordance with appendix F
6. Return helicopter to flight configuration and record for compliance of PART III of
this bollettino.

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B.T. 139-46-001

PART IV:
1. Prepare the helicopter for a safe ground maintenance. Disconnect the battery and
all the electrical power sources and/or the external power supply.
2. Perform the main rotor blades and collective adjustable stop setting in accordance
with appendix G.
3. Return helicopter to flight configuration and record for compliance of PART IV of
this bollettino.

Page 8 of 68
 REMOVE:
3G3320V00352 Dimming system ctrl panel
INSTALL:
3G3320V00353 Dimming system ctrl panel

Page 9 of 68
Figure 1
B.T. 139-46-001
B.T. 139-46-001

Figure 2

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B.T. 139-46-001

Figure 3

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Figure 4

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Appendix – A

A.1 SYSTEM PARAMETERS DISPLAY

Power ON the helicopter and check that the following parameters are valid.
RESULT
Parameter scale Normal *MAU 1 OFF **MAU 2 OFF NOTE
(PASS/FAIL)
NG1 (MFD)
NG2 (MFD)
ITT1 (MFD)
ITT2 (MFD)
TQ1 (MFD)
TQ2 (MFD)
NG1 ANALOGUE (MFD) AMBER DASH
NG2 ANALOGUE (MFD) AMBER DASH
ITT1 ANALOGUE (MFD) AMBER DASH
ITT2 ANALOGUE (MFD) AMBER DASH
TQ1 ANALOGUE (MFD) AMBER DASH
TQ2 ANALOGUE (MFD) AMBER DASH
ENG OIL PRESS1 (MFD) AMBER DASH
ENG OIL PRESS2 (MFD) AMBER DASH
ENG OIL TEMP1 (MFD) AMBER DASH
ENG OIL TEMP2 (MFD) AMBER DASH
MGB OIL PRESS (MFD) AMBER DASH
MGB OIL TEMP (MFD) AMBER DASH
IGB OIL TEMP (MFD) AMBER DASH
TGB OIL TEMP (MFD) AMBER DASH
FUEL PRESS1 (MFD) AMBER DASH
FUEL PRESS2 (MFD) AMBER DASH
HYDOIL PRESS 1 (MFD) AMBER DASH
HYDOIL PRESS 2 (MFD) AMBER DASH
HYD OIL TEMP 1 (MFD) AMBER DASH
HYDOIL TEMP 2 (MFD) AMBER DASH
MAIN BUS 1 (MFD) AMBER DASH
MAIN BUS 2 (MFD) AMBER DASH
ESS BUS 1 (MFD) AMBER DASH
ESS BUS 2 (MFD) AMBER DASH
DC GEN LOAD 1 (MFD) AMBER DASH
DC GEN LOAD2 (MFD) AMBER DASH
MAIN BATTERY LOAD (MFD) AMBER DASH
AUX BATTERY LOAD (MFD) AMBER DASH
OAT 1 (PFD) (OAT 2 visual.)
OAT 2 (PFD) (OAT 1 visual.)
FUEL QUANTITY (MFD)

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B.T. 139-46-001

RESULT
Parameter scale Normal *MAU 1 OFF **MAU 2 OFF NOTE
(PASS/FAIL)
FUEL QTY LEFT (MFD)
FUEL QTY RIGHT (MFD)
FUEL FLOW LEFT (MFD)
FUEL FLOW RIGHT (MFD)
NR (PFD/MFD)
NF1 (PFD/MFD)
NF2 (PFD/MFD)
PI 1 (PFD/MFD)
PI 2 (PFD/MFD)
NR (PFD/MFD) ANALOGUE
NF1 (PFD/MFD) ANALOGUE AMBER DASH
NF2 (PFD/MFD) ANALOGUE AMBER DASH
PI 1 (PFD/MFD) ANALOGUE AMBER DASH
PI 2 (PFD/MFD) ANALOGUE AMBER DASH
AHRS HDG1
AHRS HDG2
AHRS ROLL1
AHRS ROLL2
AHRS PITCH 1
AHRS PITCH 2
ADS IAS1 AMBER DASH
ADS IAS 2 AMBER DASH
ADS BARO ALT1 AMBER DASH
ADS BARO ALT2 AMBER DASH
ADS ALTIMETER1 DIGITAL AND
ANALOGUE INDICATION AMBER DASH
ADS ALTIMETER2 DIGITAL AND
ANALOGUE INDICATION AMBER DASH
(RAD ALT 2
RADIO ALTIMETER 1
visual.)
(RAD ALT 1
RADIO ALTIMETER 2
visual.)
HDG (MISCOMPARE)
PITCH (MISCOMPARE)
ROLL (MISCOMPARE)

*1 MAU DISPLAYED on PFD bottom left

**2 MAU DISPLAYED on PFD bottom left

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 B.T. 139-46-001

A.2 RADIO – NAVIGATION FUNCTIONS

Results Note
System TEST
(PASS/FAIL)
Verify the correct interphonic communication with 2 headsets
ICS (AUDIO panel in BKUP mode).
ICS Verify the correct cockpit and cabin Interphonic communication.
Verify the correct Setting control of the radios (MCDU’s and CCD’s)
VHF 1, 2 and communication with an external radio.
Verify the Emergency setting of the radios and communication with
VHF 1, 2 an external radio (both MAU OFF à MCDU’s in BKUP mode).
ADS 1, 2 Perform the test for altitude and airspeed. Ref. to Appendix A.4
XPDR Check the correct XPDR functionality with an external source. (1)

NOTE 1: all the tests are performed as described Avionics ATP (139G4600D001)
NOTE 2: only qualitative tests are executed on Radio & NAV equipment.

A.3 CONTROL PANELS FUNCTIONS

Results
System TEST Note
(PASS/FAIL)
Check the correct functionality of all controller
Display Controller
buttons
Remote instrument Check the correct functionality of all controller
Controller buttons
Verify maintenance PAGE can be open ON MFD
CMC
on ground
Press LNAV pushbutton and verify that the FMS is
FMS displayed on PFD. Verify the relevant Flight Plan is
displayed on MFD (MAP/PLAN page).
Dimming Display Display dimming
REV Panel Reversionary functionality (display, AHRS, ADM)
Press the MGB, TGB and IGB OIL LOW TEST
TEST Panel/MGB,
buttons and check the relevant cautions are
TGB Oil Low Level
displayed
Press the ENG 1 FIRE, ENG 2 FIRE and BAG
TEST Panel/ENG1,2,
FIRE TEST buttons and check the relevant
Bag FIRE
cautions and warnings are displayed
Press the ENG CHIP 1 and ENG CHIP 2 TEST
TEST Panel/ENG1, 2 CHIP buttons and check the relevant cautions are
displayed
Press AWG for more than 6 seconds and check the
TEST Panel/AWG "full" test
full list of aural warnings

A.4 ADM Test Procedure

Note 1:
CAUTION: Pitot heat shall not be applied when the Air Data Probe adapters are installed
on the pitot probes. Significant damage to the Air Data system pitot probes

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 B.T. 139-46-001

and pitot system lines will occur if pitot heat is applied with the Air Data Prove
adapters installed.
Note 2:
CAUTION: The ADMs contain sensitive pressure sensing devices. Ensure that the Air
Data test set and pitot system lines are connected correctly to prevent
incorrect application of pressure to the system (i.e. Connecting total pressure
lines to ADM static pressure input).

Note 3:
CAUTION: The ADM shall survive application of pressure from 10.2 mB (0.301 inHg) to
2200 mB (64.966 inHg) without damage, so air Data test set procedures shall
be followed to prevent pressure inputs outside the operating range of the
ADM. Overpressure and excessive pressure rate changes shall be avoided.

Note 4:
The two Display Controllers, which contain the Barometric Correction input knobs
and Barometric Correction set and standard push button, provide input
parameters to the ADS. The Display Controller inputs are received by the ADS via
ASCB, hence the verification of the integrity of the interface is included as part of
the Ground Test procedure pertaining to the Display Controller.

Note 5:
In order to shorten the Testing time it is suggested execute the ADS System test
and the Standby ADI Instruments air data test at the same time.

A.4.1 Airspeed Test

NOTE: The following tests shall be performed for either ADS1, ADS2, ADI STBY1 and
ADI STBY2 (if applicable).

1. Verify both BARO Setting values are 1013 BAR.

2. Connect the headset to an ICS plug (Pilot or Copilot).
3. Set the Air Data test bench to the indicated airspeed values indicated in A1 for an
altitude of zero feet. Verify that the airspeed values displayed on the Pilot PFD

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 B.T. 139-46-001

(ADS2), Copilot PFD (ADS1), Pilot ADI Standby display and Copilot ADI Standby
display.
4. The IAS miscompare annunciator (IAS) is displayed on both airspeed tapes (IAS
miscompare annunciator is activated when the ADS1-ADS2 airspeed difference
exceeds 20 Knots and the airspeed is higher than 60 Knots).
5. On the reversionary control panel set the ADS switch to ADS1 position (ADS1 is
the only Air data source) and verify that the only air data from ADS1 and the source
indication ADS1 are visualized on both Pilot and Copilot PFDs.
6. On the reversionary control panel set the ADS switch to ADS2 position (ADS2 is
the only Air data source) and verify that the only air data from ADS2 and the source
indication ADS2 are visualized on both Pilot and Copilot PFDs.
7. On the reversionary control panel, set the ADS switch back to NORMAL position.
8. Verify the Aural Warning “AIRSPEED AIRSPEED” is generated when 170 Knots
speed is visualized (*).
9. Verify that the Red Barber Pole is indicated on the Airspeed tape corresponding to
the Vne Value (Vne 167 Knots).

Table A1 - Displayed Airspeed Tolerances ADS

Simulated Expected Displayed Airspeed Read Value Read Value

Tolerance
Airspeed ( = Simulated Airspeed + 5 Kts ADS1 (CPLT PFD) ADS2 (PLT PFD)
(Kts)
(Kts) )

0 0 +5 ↑ ↓ ↑ ↓

10 10 +5 ↑ ↓ ↑ ↓

20 25 +5 ↑ ↓ ↑ ↓

30 35 +5 ↑ ↓ ↑ ↓

40 45 +5 ↑ ↓ ↑ ↓

50 55 +5 ↑ ↓ ↑ ↓

60 65 +5 ↑ ↓ ↑ ↓

70 75 +3 ↑ ↓ ↑ ↓

80 85 +3 ↑ ↓ ↑ ↓

90 95 +3 ↑ ↓ ↑ ↓

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B.T. 139-46-001

Simulated Expected Displayed Airspeed Read Value Read Value

Tolerance
Airspeed ( = Simulated Airspeed + 5 Kts ADS1 (CPLT PFD) ADS2 (PLT PFD)
(Kts)
(Kts) )

100 105 +2 ↑ ↓ ↑ ↓

120 125 +2 ↑ ↓ ↑ ↓

140 145 +2 ↑ ↓ ↑ ↓

160 165 +2 ↑ ↓ ↑ ↓

162 167 (Vne) +2 ↑ ↓ ↑ ↓

170 (*) ↑ ↓ ↑ ↓
165 +2
(ADS1) (ADS2)

180 185 +2 ↑ ↓ ↑ ↓

(*): Verify the Aural Warning “AIRSPEED AIRSPEED” is generated in headphone.

ADS1 ADS2: Air Data Reversionary Panel Test.
↑: Airspeed increasing;
↓: Airspeed decreasing;

A4.2 Altitude Test

NOTE: The following tests shall be performed for both ADS1 and ADS2.
NOTE: It is suggested to perform the Standby ADI Instruments Pressure Altitude tests
described in Section A.5 at the same time of the following ADS Pressure
Altitude tests. In this case the Tests described in Section A.5, have to be
successfully completed.
1. Verify the BARO Setting value is 1013 BAR.
2. Set the Air Data test bench to the pressure altitude values indicated in A2. Verify
the altitude values displayed for each test point on Pilot and Copilot PFD and on
both the ADI Stdby displays are within the tolerance specified. The test must be
performed at first ascending and then back descending.
3. The “ALT” miscompare amber flag (ALT) appears on the Pressure Altitude tape
when the delta between the ADS1 and ADS2 Pressure Altitude values exceeds the
200 feet.

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 B.T. 139-46-001

Table A2 - Displayed Altitude Tolerances

Altitude Tolerance Read Value Read Value

(ft) (ft) ADS1 ADS2

-1000 + 15.0 ↑ ↓ ↑ ↓

0 + 15.0 ↑ ↓ ↑ ↓

1000 + 15.0 ↑ ↓ ↑ ↓

1500 + 15.0 ↑ ↓ ↑ ↓

2000 + 15.0 ↑ ↓ ↑ ↓

3000 + 15.0 ↑ ↓ ↑ ↓

4000 + 15.0 ↑ ↓ ↑ ↓

6000 + 17.5 ↑ ↓ ↑ ↓

8000 + 17.5 ↑ ↓ ↑ ↓

10000 + 17.5 ↑ ↓ ↑ ↓

12000 + 17.5 ↑ ↓ ↑ ↓

15000 + 20.0 ↑ ↓ ↑ ↓

20000 + 20.0 ↑ ↓ ↑ ↓

↑: Ascending;
↓: Descending;

A.5 Electronic Standby Attitude System

A.5.1 Start-up and Self test

1. Push IN the ADI Standby Electrical Circuit Breakers in order to power ON both
systems.
2. Verify the units display the “ATT FAIL” indication with the message “ALIGNING”
and a completion timer/counter below the Aircraft Symbol until the alignment
transient is completed (time required. 3 minutes).
3. After the start-up transient verify a valid page is displayed: check the Display shows
a normal attitude presentation and ready for proper operation, ie: level pitch, level
roll. Check the indicator is functioning properly.

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B.T. 139-46-001

A.5.2 ADI Attitude Test

1. After the alignment, verify that both ADI standby displays show the proper
helicopter attitude (With helicopter on ground should be 0° of pitch and 0° of roll).

A.5.3 ADI Altitude Test

Note 1:
In order to shorten the Testing time it is suggested to perform the ADI Standby
altitude tests at the same time of the ADS Altitude Tests (ref. Section A.4).
Mind that the Pilot ADI Standby is connected to Pilot Side Pitot and the Copilot
ADI Standby to the Copilot Side Pitot.
Note 2:
Both the ADI Standby pressure lines have to be fully installed in order to
perform this test.
Note 3:
CAUTION: Pitot heat shall not be applied when the Air Data Probe adapters are
installed on the pitot probes. Significant damage to the Air Data system
pitot probes and pitot system lines will occur if pitot heat is applied with the
Air Data Prove adapters installed.
Note 4:
CAUTION: The ADI Standby pressure line ports contain sensitive pressure sensing
devices. Ensure that the Air Data test set and pitot system lines are
connected correctly to prevent incorrect application of pressure to the
system.

Note 5:
CAUTION: Test set procedures shall be followed to prevent pressure inputs outside
the operating range of the ADI Standby sensor. Overpressure and
excessive pressure rate changes shall be avoided.
1. Connect the Air Data Test Set to the Aircraft's Pitots and Static system.
2. Set the ADI Standby devices Baro Correction Value to standad
1013mB using the rotary knob.

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 B.T. 139-46-001

3. On the Air Data Test set the vertical speed to 1000 feet/min and verify
the value is displayed on the RH tape indicator correctly on both the
ADI Standby displays.
4. Move slowly the vertical speed input from 1000 feet/min to 3000
feet/min, verify the RH tape indicator smoothly tracks the input and the
value is properly indicated on both the ADI Standby displays..
5. Set the Air Data Test altitude output to the values listed in Table A.3
and verify the proper altitude value indication (in feet and metres) on
both the ADI Standby displays.

Table A.3 - Simulated Altitude Values for ADI Standby Test

Read Value Read Value

Altitude Tolerance ADI STBY PILOT ADI STBY CPLT
(ft) (ft) - Left Pitot - (if installed)
- Right Pitot -

↓
-1000 + 25.0 ↑ ↑ ↓

0 + 25.0 ↑ ↓ ↑ ↓

1000 + 25.0 ↑ ↓ ↑ ↓

1500 + 25.0 ↑ ↓ ↑ ↓

2000 + 25.0 ↑ ↓ ↑ ↓

3000 + 25.0 ↑ ↓ ↑ ↓

4000 + 25.0 ↑ ↓ ↑ ↓

6000 + 25.0 ↑ ↓ ↑ ↓

8000 + 25.0 ↑ ↓ ↑ ↓

10000 + 33.0 ↑ ↓ ↑ ↓

12000 + 35.0 ↑ ↓ ↑ ↓

15000 + 40.0 ↑ ↓ ↑ ↓

20000 + 50.0 ↑ ↓ ↑ ↓

↑: Altitude increasing;
↓: Altitude decreasing;

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B.T. 139-46-001

6. Using the Air Data Test Set, control the pressures to provide a vertical
velocity between 1000 and 3000 feet/min descent to ambient pressure.
7. Check on both the ADI displays that the Altitude tape moves smoothly
and properly displays Altitude in the window.
8. Using the Air Data Test Set, set the pressure value to provide a –2000
feet altitude.
9. Verify on both the ADI displays that the Altitude tape shows a Red cross.
10. Using the Air Data Test Set, control the Air Data Test Set pressure to
provide 0 feet simulated altitude.
11. Check on both the ADI displays the Altitude tape indicates 0 feet.
12. Move both the ADI Standby displays Set knob in order to vary the Baro
Set value (Increasing and Decreasing) and verify the Pressure Altitude
tracks properly the knob movements.
13. Set again the Baro Set Value to the default value (1013 mB) and verify
the displayed value on both the ADI Standby displays return 0 feet.

A.5.4 ADI Airspeed Test

Note1:
Mind the Cautions listed in section A.5.3
Note 2:
In order to shorten the Testing time it is suggested to perform the ADI Standby
Airspeed tests at the same time of the ADS Altitude Tests (ref. A.4). Mind that
the Pilot ADI Standby is connected to Pilot Side Pitot and the Copilot ADI
Standby to the Copilot Side Pitot.
1. Verify the connection or connect the Air Data Test Set to the Aircraft's
Pitots and Static system.
2. Using the Air Data Test Set, control the pressures to provide an indicated
airspeed rate of 3 Kts/sec on both ADI Displays.
3. Check on both the ADI displays the AIRSPEED tape moves smoothly and
properly displays Airspeed value in the window.
4. Set the Air Data Test Set to the value listed in the Table A.4 and verify the
proper airspeed value indication on both ADI Standby displays.

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5. Verify the minimum displayed airspeed is 20 kts (± 5 kts tolerance)

Table A.4 - Simulated Airspeed Values for ADI Standby Test

Expected Displayed Read Value Read Value

Simulated
Airspeed Tolerance ADI STBY PILOT ADI STBY CPLT
Airspeed
( = Simulated Airspeed + (Kts) - Left Pitot - (if installed)
(Kts)
5 Kts ) - Right Pitot -

40 45 +5 ↑ ↓ ↑ ↓

50 55 +5 ↑ ↓ ↑ ↓

60 65 +5 ↑ ↓ ↑ ↓

70 75 +3 ↑ ↓ ↑ ↓

80 85 +3 ↑ ↓ ↑ ↓

90 95 +3 ↑ ↓ ↑ ↓

100 105 +2 ↑ ↓ ↑ ↓

120 125 +2 ↑ ↓ ↑ ↓

142 147 (Vne power OFF)** +2 ↑ ↓ ↑ ↓

160 165 +2 ↑ ↓ ↑ ↓

162 167 (Vne power ON)* +2 ↑ ↓ ↑ ↓

165
170
+2 ↑ ↓ ↑ ↓

180 185 +2 ↑ ↓ ↑ ↓

* Vne Power ON displayed

** Vne Power OFF displayed
↑: Airspeed increasing;
↓: Airspeed decreasing;
6. Using the Air Data Test Set, control the pressures to provide a an
indicated airspeed rate of -3 Kts/sec from 180 to 0 Kts.
7. Check on both the ADI displays the AIRSPEED tape moves smoothly
and properly displays Airspeed in the window.

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A.5.5 ADI Vertical Speed Test

Note 1:
Mind the Cautions listed in section A.5.3
Note 2:
In order to shorten the Testing time it is suggested to perform the ADI Standby
Vertical Speed tests at the same time of the ADS Altitude Tests (ref. “ADM test
procedure). Mind that the Pilot ADI Standby is connected to Pilot Side Pitot and
the Copilot ADI Standby to the Copilot Side Pitot.
1. Verify the connection or connect the Air Data Test Set to the Aircraft's Pitots
and Static system.
2. Verify the Baro correction is set to standard 1013mB value on both ADI
Displays.
3. Using the Air Data Test Set, control the pressures to provide a climbing
vertical speed velocity of 1000 feet/min.
4. Check on both ADI displays that the RH Vertical Speed tape indicates a
value of 1000 feet/min (± 20 ft ) with an arrow “↑” indicating climbing.
5. Set the Air Data Test for climbing vertical speed of values listed in Table A.5
and verify they are properly displayed with the upward arrow “↑”.

Table A.5 - Simulated Climbing Vertical Speed Values for ADI Standby
Test
Read Value Read Value
Roll Value Expected Value (Plt. STBY ATT – Plt. (Cplt. STBY ATT –
Pitot) Cplt. Pitot)

1.000 ft/min 1.000 ft ± 50 ft “↑”

2.000 ft/min 2.000 ft ± 100 ft “↑”

3.000 ft./min 3.000 ft ±.150 ft “↑”

6. Set the Air Data Test for descent vertical speed of values listed in Table A.6
and verify they are properly displayed on both the ADI displays with the
downward arrow “↓”.

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Table A.6 - Simulated Descent Vertical Speed Values for ADI Standby
Test
Read Value Read Value
Roll Value Expected Value (Plt. STBY ATT – Plt. (Cplt. STBY ATT –
Pitot) Cplt. Pitot)

3.000 ft/mn 3.000 ft ± 50 ft ↓

2.000 ft/mn 2.000 ft ± 100 ft ↓

1.000 ft./mn 1.000 ft ±.50 ft. ↓

7. Set up the Air Data Test Set for no vertical speed.

8. Check on both the ADI displays the Vertical speed with an arrow “←” in
accordance with the Vertical speed set up of 0 ft/mn

A.5.6 VOR Indication on ADI

The ADI system consumes on side VOR information via Arinc429 and provides VOR
information on the display. In order to test these functionalities, set a VOR station on
NAV 1 and NAV 2 VOR, select NAV option on the Menu button on each ADI Stby and
verify that the relevant on side VOR bearing are correctly displayed.

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Appendix – B –

B.1 Requirements
Prior to initiating any of the tests described in this document, the AB139 test aircraft shall
be configured according to the fundamental requirements in this section. Any deviations
from this set-up will be stated within the appropriate subsections.
System Wiring
Prior to initial installation of system components, all aircraft wiring shall be checked for
proper continuity in accordance with the applicable drawings referenced in paragraphs
A.2.1 (see references n° 4).
Power Application
The Primus EPIC® AFCS uses 28 V dc Power.
Initial Power Application
Upon completion of the AFCS installation, all pins of all connectors associated with the
AFCS installation shall be checked for proper grounds. This will minimize the
possibility of inadvertently damaging any system components due to mis-wires within
the aircraft harness. The above tests should be accomplished with all power off and all
circuit breakers pulled.
After the above grounding tests have been completed, all circuit breakers can be set
and aircraft DC power applied. All pins of all connectors shall then be checked for
proper power.
Normal Power Application
After all test in paragraph “Initial power application” have been completed connect the
backshells to the AIOP cards contained in the MAUs. Apply aircraft power.
The cockpit circuit breakers listed in Table B1 are pertinent to the AFCS installation and
this test procedure. All circuit breakers are 28 Vdc and should be IN.

Table B1 - Pertinent Circuit Breakers

Position Label System
D7 ADM 1 Co-Pilot’s Air Data Module
M4 ADM2 Pilot’s Air Data Module
S4 AHRS PLT Pilot’s AHRS Primary Power
A4 AHRS CPLT Co-Pilot’s AHRS Primary Power
P7 AHRS PLT Pilot’s AHRS Auxiliary Power
C7 AHRS CPLT Co-Pilot’s AHRS Auxiliary Power

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 B.T. 139-46-001

Position Label System

A1 STBY 1 ATT GH-3100 Stand-by AHRU #1
S9 STBY 2 ATT GH-3100 Stand-by AHRU #2
L6 ACT PLT MAU 2 AIOP Power/Pilot Series Actuator Power
F6 ACT CPLT MAU 1 AIOP Power/Co-Pilot Series Actuator Power
G6 FD 1 Guidance Controller Channel 1
J6 AUTO TRIM Trim Enable Power
K6 FD 2 Guidance Controller Channel 2
C1 FORCE TRIM Trim Servo Clutch Power
A7 MAU1 PRI PWR MAU 1 Power Supply (Primary) and Control I/O module
A2 MAU2 PRI PWR MAU 2 Power Supply (Primary) and Control I/O module
S7 MAU1 AUX PWR MAU 1 Power Supply (Secondary)
S2 MAU2 AUX PWR MAU 2 Power Supply (Secondary)
L5 PFD PLT Pilot Primary Flight Display
F5 PFD CPLT Co-pilot Primary Flight Display
J5 MFD PLT Pilot Mulit-function Display
C5 MFD CPLT Copilot Mulit-function Display
M5 PFD PLT CONTR Pilot Display Controller
E5 PFD CPLT CONTR Co-pilot Display Controller
B7 RAD ALT 1 Radio Altimeter #1
R7 RAD ALT 2 Radio Altimeter #2

AFCS Ground Test

Prior to checkout of the AFCS, verify that the Attitude Heading Reference System, the
Air Data System, the Radio Altimeter System, and the Navigation Radios are fully
operational.
Hydraulics
The AB139 hydraulic system shall be ON. The tests within this procedure require
movement of the linear and trim actuators. Any attempt to move these actuators
against the large loads imposed by the entire control assemblies without the aid of a
hydraulic boost may cause damage to the actuators.

B.2 Radio Altimeter Checkout Procedure

CAUTION
UNDER NO CIRCUMSTANCES SHALL POWER BE APPLIED TO THE RADIO
ALTIMETER SYSTEM WITH THE TRANSMIT ANTENNA DISCONNECTED FROM
THE RECEIVER / TRANSMITTER.

⇒ Apply power in accordance with paragraph “Power Application”.

⇒ Set the decision height (DH) altitude on the pilot and copilot PFDs to 30 feet using
the RI-553 Remote Instrument Controllers.
⇒ The DH indications shall be displayed on the PFDs and the RAD ALT display shall
indicate 0 ± 5 feet.

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⇒ Ensure that all flight director modes are off. Press and hold the Push Test button
on the DH knob of the pilot RI-553 Remote Instrument Controller. The ‘TEST’ flag
shall be annunciated on the Rad Alt tape On the both the pilot and copilot PFD the
RAD ALT display shall indicate 100 ± 10 feet.
⇒ Release the DH knob push button and repeat paragraph for the copilot RI-553
controller.

B.3 Control position Sensor Alignment procedure

The control position sensors are an integral component within the SAGEM rotary trim
servos. The sensor alignment is a result of the installation and rigging of the trim servos.
Refer to the AB139 Maintenance Manual for the installation and rigging of the Trim
Servos.

B.4 AFCS checkout procedure

Ensure that the aircraft power is applied in accordance with paragraph “Power
Application”. Ensure that hydraulic power is applied to the aircraft by the No. 1 hydraulic
systems. Check that the CPL light on the PC-770 Autopilot Controller is off.
Lamp Test
Press and hold the DSPL push button on the TEST panel of the center console. All the
lamps on the PC-770 Autopilot Controller and the GC-810 Guidance Controller and
both the Master Warning and Master Caution should turn on full bright. Release the
button.
Force-Feel System (Force Trim)
This section will verify that the force-feel mechanism in the trim and collective actuators
is providing feedback to the pilot, and that the force-feel system is operational.
Switch (button) Positions:
• AP1 .................................... - OFF
• AP2 .................................... - OFF
• Guidance Control Panel ..... - STBY
• Force Trim.......................... - OFF
• CLTV/YAW Force Trim ...... - OFF
• PFD Sel.............................. - SIDE 2

1 Move the cyclic stick, pedals, and collective. There shall be no spring force and
minimum friction.
2 Set the Force Trim switch to ON. The cyclic stick shall have spring force when
moved from the detent position in both the pitch and roll axis. Check that when

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released the cyclic stick returns to the original detent position to verify that the trim
motors do not back-drive.
3 Set the CLTV/YAW Force Trim switch to ON. The collective and pedals shall have
spring force when moved from their detent position.
Note: that the pedals must be moved without depressing the pedal mounted Yaw
FTR switches.
Check that when released the collective stick and pedals return to their original
detent position to verify that the trim motors do not back-drive.
4 Press the FTR on the pilot cyclic stick. There shall be no spring force and minimum
friction on the cyclic when moved. The pedals and collective shall have spring
force when moved from their detent position.
5 Press the pilot's collective FTR switch. There shall be no spring force and
minimum friction on the collective when moved.
6 Press the pilot's left yaw pedal FTR switch, and then press the right yaw pedal FTR
switch. There shall be no spring force and minimum friction on the pedals.
7 Repeat parts 4, 5, and 6 for the co-pilot’s side.
Autopilot Engage Tests
Switch (button) Positions:
• AP1 .................................... - OFF
• AP2 .................................... - OFF
• Guidance Control Panel ..... - STBY
• Force Trim.......................... - ON
• CLTV/YAW Force Trim ...... - ON
• PFD Sel.............................. - SIDE 2
Aircraft must be Weight OFF Wheels (IN AIR CONDITION).

1 Verify on the CAS display window that the “1-2 AP OFF” caution message is
displayed.
2 Momentarily press the AP1 pushbutton on the Autopilot Controller. The AP1 and
the ATT pushbuttons will illuminate. The CAS window annunciates “2 AP OFF” and
“AFCS DEGRADED”. The master caution will flash. Press the master caution
button.
3 Set the Force Trim switch to the OFF position. The ATT lamp on the Autopilot
Controller will extinguish and the SAS button lamp will illuminate. “ATT OFF” will
be displayed on the CAS Window. Press the AP1 pushbutton. The AP1 on and
SAS lamps will extinguish. CAS window will show “1-2 AP OFF”. The master
caution will flash. Press the master caution button
4 Press the AP2 pushbutton. The AP2 button and the SAS button will illuminate.
CAS messages “1 AP OFF” and “AFCS DEGRADED” and “ATT OFF” will be

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displayed and Master Caution will flash. Set the Force Trim switch to ON and
press the ATT pushbutton. The ATT button lamp will go on and the SAS button
lamp will turn off.
5 Re-engage AP1. CAS window shall have no AFCS related AP CAS messages.
AP1, AP2 and ATT pushbutton will be illuminated
6 Pull the MAU1 circuit breakers. The AP1 push button lamp shall extinguish. AP2
pushbutton and the ATT pushbutton will remain lighted. The CAS messages “1 AP
FAIL”, “AFCS DEGRADED”, “1 ADS FAIL”, and “AVIONIC FAULT” will be
displayed, the air data information on co-pilot PFD will be red X’d, and the Master
Caution will flash. The side one linear actuator position indicators on the AFCS
system page will be X'd. Press the master caution button.
7 Reset the MAU1 circuit breakers. Re-engage AP1 after the pitch and roll attitudes
are valid on the ADI. The AP1 pushbutton shall illuminate and the CAS messages
and red X’s shall clear.
8 Pull the co-pilot linear actuator circuit breaker. The AP1 push button lamp shall
extinguish. AP2 pushbutton and the ATT pushbutton will remain lighted. The CAS
messages “1 AP FAIL” and “AFCS DEGRADED” will be displayed and the Master
Caution will flash. Press the master caution button.
9 Reset the co-pilot linear actuator circuit breaker. Re-engage AP1. The AP1
pushbutton shall illuminate and the CAS messages shall clear.
10 Pull the MAU2 circuit breakers. The AP2 lamp shall extinguish. AP1 pushbutton
and the ATT pushbutton will remain lighted. The CAS messages “2 AP FAIL”,
“AFCS DEGRADED”, “2 ADS FAIL”, and “AVIONIC FAULT” will be displayed, the
air data information on pilot PFD will be red X’d, and the Master Caution will flash.
The side two linear actuator position indicators on the AFCS system page will be
X'd. Press the master caution button.
11 Reset the MAU2 circuit breakers. Re-engage AP2 after the pitch and roll attitudes
are valid on the ADI. The AP2 pushbutton shall illuminate and the CAS messages
shall clear.
12 Pull the pilot linear actuator circuit breaker. The AP2 lamp shall extinguish. AP1
pushbutton and the ATT pushbutton will remain lighted. The CAS messages “2 AP

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FAIL” and “AFCS DEGRADED” will be displayed and the Master Caution will flash.
Press the master caution button.
13 Reset the pilot linear actuator circuit breakers. Re-engage AP2. The AP2
pushbutton shall illuminate and the CAS messages shall clear.
14 Press the Quick Disconnect (SAS REL) button on the co-pilot side cyclic grip. Both
AP1 and AP2 should disengage. The CAS message “1-2 AP OFF” will show and
the Master Caution will flash. Press the master caution button.
15 Engage AP1 and AP2. Press the Quick Disconnect (SAS REL) button on the pilot
side cyclic grip. Both AP1 and AP2 should disengage. The CAS message 1-2 AP
OFF will show and the Master Caution will flash. Press the master caution button.
Attitude Gain Polarity Tests
Initial Switch (button) Positions:
• AP1 .................................... - ON
• AP2 .................................... - ON
• ATT ................................... - ON
• Guidance Control Panel ..... - STBY
• Force Trim.......................... - ON
• CLTV/YAW Force Trim ...... - OFF
• PFD Sel.............................. - SIDE 2
Check that the CPL light on the PC-770 Autopilot Controller is off.
Aircraft must be Weight OFF Wheels (IN AIR CONDITION).
1 Pull the Stand-by AHRS CB (GH-3100 Stand-by AHRU turned OFF). Position the
collective above 50%.
2 Move the cyclic stick pitch out of detent to prevent trim from running and prevent
the cross side linear actuator from moving. Unfasten and tilt the co-pilots AHRS to
simulate a small pitch up attitude. The side 1 pitch linear actuator position
indication on the AFCS system page shall indicate approximately 50% down
deflection. Level the gyro. The linear actuator position shall return to center. The
cross side linear actuators should not move throughout the test.
3 Tilt the co-pilots AHRS to simulate a small pitch down attitude. The side 1 pitch
linear actuator position indication on the AFCS system page shall indicate
approximately 50% up deflection. Level the gyro. The linear actuator position shall
return to center. Return the stick to the detent position. The cross side linear
actuators should not move throughout the test.

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4 Move the cyclic stick roll out of detent to prevent trim from running and prevent the
cross side linear actuator from moving. Tilt the co-pilots AHRS to simulate a small
roll right attitude. The side 1 roll linear actuator position indication on the AFCS
system page shall indicate approximately 50% left deflection. Level the gyro. The
linear actuator position shall return to center. The cross side linear actuators should
not move throughout the test.
5 Tilt the co-pilots AHRS to simulate a small roll left attitude. The side 1 roll linear
actuator position indication on the AFCS system page shall indicate approximately
50% right deflection. Level the gyro. The linear actuator position shall return to
center. Return the stick to the detent position. The cross side linear actuators
should not move throughout the test.
6 Repeat parts 2 through 5 using the pilot’s AHRS and observing the pitch and roll
side two linear actuators position indications, checking that the side one linear
actuators do not move.
Yaw Axis Test
Initial Switch (button) Positions:
• AP1 .................................... - ON
• AP2 .................................... - ON
• ATT ................................... - ON
• Guidance Control Panel ..... - STBY
• Force Trim.......................... - ON
• CLTV/YAW Force Trim ...... - ON
• PFD Sel.............................. - SIDE 2
Check that the CPL light on the PC-770 Autopilot Controller is off.
Aircraft must be Weight OFF Wheels (IN AIR CONDITION).
NOTE: These tests cause trim to run and cause the actuators to move towards
center.

1 Ensure that the collective stick is set above the 50% position and that the aircraft is
Weight OFF Wheels (IN AIR Condition). Pull the Stand-by AHRS CB (GH-3100
Stand-by AHRU turned OFF).
2 Rotate the co-pilot AHRS 10 degrees clockwise as viewed from the top. The side 1
yaw linear actuator position indicator shall show a left deflection then it will center.

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3 Rotate the co-pilot AHRS 10 degrees counter-clockwise. The side 1 yaw linear
actuator position indicator shall show a right deflection then it will center. Return
the AHRS to its normal position. Disengage AP1.
4 Repeat parts 2 and 3 above using the pilot side AHRS and observing the side 2
yaw linear actuator position indication.
5 Push in the Stand-by AHRS CB (GH-3100 Stand-by AHRU turned ON).
6 Set AP2 as trim master (engage AP2 before AP1), perform test using pilot side
controls.
7 Beep right on the yaw beep switch on the pilot collective grip. Verify that the
actuator position movement responds in the correct direction (right beep
commands right actuator). Yaw Trim should run to move the linear actuator position
indicator back towards center. Center the yaw position indicators by pressing the
left pedal FTR switch. Repeat the test beeping left on the yaw beep switch. Center
the linear actuator positions and the yaw pedals by pressing the right yaw pedal
FTR switch.
8 Repeat part 7 with AP1 as trim master, the co-pilot yaw beep switch and centering
with the co-pilot’s yaw pedals/yaw FTR switches.
ATT Mode Tests
Initial Switch (button) Positions:
• AP1 .................................... - ON
• AP2 .................................... - ON
• ATT ................................... - ON
• Guidance Control Panel ..... - STBY
• Force Trim.......................... - ON
• CLTV/YAW Force Trim ...... - OFF
• PFD Sel.............................. - SIDE 2
Check that the CPL light on the PC-770 Autopilot Controller is off.
Aircraft must be Weight OFF Wheels (IN AIR CONDITION).
NOTE: These tests cause trim to run and cause the actuators to move towards
center.

1 Position the collective above 50%.

2 Both of the autopilots are engaged, trim master: AP2 (trim master is the first AP to
be engaged). Press the pilot’s cyclic FTR to center the pitch and roll actuators.
Beep forward on the pilot’s cyclic beep switch. Check that the pitch actuators are

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B.T. 139-46-001

commanded pitch down and that they stop at approximately 50 percent deflection
on the AFCS systems page. As trim runs the cyclic stick moves forward and the
actuator position indications move towards the center.
3 Disengage AP1. Verify actuator position for side 2 and trim movement continues
normally. Momentarily press the cyclic FTR switch to center the actuator and stop
trim. Beep forward on the pilot's beep switch. The side 2 pitch actuator shall move
greater than 50% down deflection. Press FTR and check that the actuator re-
centers. Disengage AP2.
4 Engage AP1. Beep forward on the pilot's beep switch. The side 1pitch actuator
shall move full down deflection. Press FTR and check that the actuator re-centers.
Disengage AP1.
5 Engage both autopilots, trim master: AP2. Press the pilot’s cyclic FTR to center the
pitch and roll actuators. Beep aft on the pilot's cyclic beep switch. Check that the
pitch actuators are commanded pitch up and that they stop at approximately 50
percent deflection on the AFCS systems page. As trim runs cyclic moves aft and
the actuator position indications move towards the center.
6 Disengage AP1. Verify actuator position for side 2 and trim movement continues
normally. Momentarily press the cyclic FTR switch to center the actuator and stop
trim. Beep aft on the pilot's beep switch. The side 2 pitch actuator shall move
greater than 50% up deflection. Disengage AP2.
7 Engage AP1. Beep aft on the pilot's beep switch. The side 1pitch actuator shall
move full up deflection. Disengage AP1.
8 Engage both autopilots, trim master: AP2. Press the pilot’s cyclic FTR to center the
pitch and roll actuators. Beep right on the pilot’s cyclic beep switch. Check that the
roll actuators are commanded roll right and that they stop at approximately 50
percent deflection on the AFCS systems page. As trim runs cyclic moves right and
the actuator position indications move towards the center.
9 Disengage AP1. Verify actuator position for side 2 and trim movement continues
normally. Momentarily press the cyclic FTR switch. Beep right on the pilot's beep
switch. The side 2 pitch actuator shall move greater than 50% right deflection.
Press FTR and check that the actuator re-centers. Disengage AP2

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10 Engage AP1. Beep right on the pilot's beep switch. The side 1 roll actuator shall
move full right deflection. Press FTR and check that the actuator re-centers.
Disengage AP1.
11 Engage both autopilots, trim master: AP2. Press the cyclic FTR to center the pitch
and roll actuators. Beep left on the pilot’s cyclic beep switch. Check that the roll
actuators are commanded roll left and that they stop at approximately ds50 percent
deflection on the AFCS systems page. As trim runs cyclic move left and the
actuator position indications move towards the center.
12 Disengage AP1. Verify actuator position for side 2 and trim movement continues
normally. Momentarily press the cyclic FTR switch. The side 2 pitch actuator shall
move greater than 50% left deflection. Disengage AP2.
13 Engage AP1. Beep left on the pilot's beep switch. The side 1 roll actuator shall
move full left deflection. Disengage AP1.
14 REPEAT: parts 1 through to 13 with trim master: AP1 when both autopilots are
engaged and performing the single AP tests by reading AP1 as AP2 and vice
versa. Use the copilot’s cyclic FTR and beep switches to perform the tests.
SAS Mode Test
Initial Switch (button) Positions:
• AP1 .................................... - OFF
• AP2 .................................... - OFF
• Guidance Control Panel ..... - STBY
• Force Trim.......................... - ON
• CLTV/YAW Force Trim ...... - OFF
• PFD Sel.............................. - SIDE 2
Aircraft must be Weight OFF Wheels (IN AIR CONDITION).

1 Engage AP1. Press SAS pushbutton on the PC-770 Autopilot Controller. Move the
cyclic approximately 1 inch forward. The side one pitch linear actuator position
indicator on the AFCS system page shall deflect down. Allow the cyclic stick to
return to the in detent (neutral) position.
2 Move the cyclic approximately 1 inch aft. The side one pitch linear actuator
position indicator on the AFCS system page shall deflect up. Allow the cyclic stick
to return to the in detent (neutral) position.

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3 Move the cyclic approximately 1 inch right. The side one roll linear actuator
position indicator on the AFCS system page shall deflect right. Allow the cyclic stick
to return to the in detent (neutral) position.
4 Move the cyclic approximately 1 inch left. The side one roll linear actuator position
indicator on the AFCS system page shall deflect left. Allow the cyclic stick to return
to the in detent (neutral) position. Disengage AP1.
5 Engage AP2. Press the SAS pushbutton to engage the SAS mode. Repeat parts
1 through to 4 above monitoring the side 2 pitch and roll linear actuator position
indications on the AFCS system page.

B.5 Autotrim checkout procedure

Apply power in accordance with paragraph “Power Application”. Ensure that hydraulic
power is applied to the aircraft No. 1 hydraulic system.
Autotrim Tests – Logic
Initial Switch (button) Positions:
• AP1 .................................... - OFF
• AP2 .................................... - OFF
• Guidance Control Panel ..... - STBY
• Force Trim.......................... - ON
• CLTV/YAW Force Trim ...... - OFF
• PFD Sel.............................. - SIDE 2
Check that the CPL light on the PC-770 Autopilot Controller is off.
The aircraft must be in a Weight OFF Wheels (IN AIR) condition.

1 Engage AP1. Press the cyclic FTR and position the cyclic stick full aft in the roll
neutral position. Beep forward on the pilot cyclic beep switch. The cyclic shall
begin trimming forward approximately 1 to 2 seconds after the beeping starts.
Once trim is moving release the beep switch. The pitch linear actuator position on
the AFCS system page should move towards approximately 30 % forward. Trim
should run smoothly.
2 Move the cyclic stick about 5 cm aft (out of detent); the auto trim must stop.
3 NOTE: If the stick out of detent does not stop trim movement investigate prior to
continuing the test procedure.

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4 Allow the stick to return to the detent position. The autotrim shall start again. Allow
trim to continue to run until it reaches the maximum forward position and stops
automatically. Press FTR.
5 Beep aft on the cyclic beep switch. Once trim is running release the beep switch
and allow the cyclic to move to the full aft position until it stops automatically.
Observe that it runs smoothly throughout its travel. Press cyclic FTR and position
the cyclic in the centered pitch position, full left roll.
6 Beep right on the cyclic beep switch. The cyclic shall begin trimming right
approximately 1 to 2 seconds after the beeping starts. Once trim is moving release
the beep switch. The roll linear actuator position on the AFCS system page should
move towards approximately 30 % right. Trim should run smoothly.
7 Move the cyclic stick about 5 cm left (out of detent); the auto trim should stop.
8 NOTE: If the stick out of detent does not stop trim movement investigate prior to
continuing the test procedure.
9 Allow the stick to return to the detent position. The autotrim shall start again. Allow
trim to continue to run until it reaches the maximum right position and stops
automatically. Press FTR.
10 Beep left on the cyclic beep switch. Once trim is running release the beep switch
and allow the cyclic to move to the full left position until it stops automatically.
Observe that it runs smoothly throughout its travel. Press cyclic FTR and position
the cyclic in the pitch and roll centered position.
11 Set the CLTV/YAW Force Trim switch to the ON position. Set the pedals using the
YAW FTR switch (pedal switch) to the full left position. Beep the yaw beep switch
on the pilot collective grip right. The pedals shall begin trimming right
approximately 1 to 2 seconds after beeping starts.
12 Move the pedals about 5 cm left out of detent (Note: do not press pedal switches).
The auto trim shall stop.
13 NOTE: If the pedal out of detent does not stop trim movement investigate prior to
continuing the test procedure.
14 Allow the pedals to return to the detent position. Yaw trim shall start again. Allow
the pedals to move to the full right pedal position observing for smooth travel.

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15 Press the YAW FTR switch down for 1 second. Beep the yaw beep switch left.
The pedals shall begin to move after approximately 1 to 2 seconds. Allow the
pedals to move to the full left position observing for smooth travel until the yaw trim
automatically stops. Press YAW FTR for 1 second and leave the pedals centered.
Disengage AP1.
16 Repeat parts 1 through 15 above for AP2.
17 Set the aircraft to the Weight on Wheels (ON GROUND) condition. Engage both
AP1 and AP2. Beep first pitch forward, and then pitch aft. Verify that the pitch
linear actuator position indicators on the AFCS system page move to first forward
then aft and that the cyclic stick does not move (trim does not run). Press cyclic
FTR.
18 Beep roll first left, then right. Verify that the both the roll linear actuator position
indicators move left then right and that the cyclic stick does not move (trim does not
run). Press cyclic FTR.
19 Beep yaw first left, then right. Verify that both the yaw linear actuator position
indicators move left then right and that the pedals do not move (trim does not run).
Press the pedal FTR switch for 1 second.

COLLECTIVE TRIM TESTS TO BE WRITTEN WHEN 4 AXIS CONTROL PROVIDED

B.6 Flight director checkout procedure (flight director configurations only)

Prior to testing the Flight Director interface subsystem, tests must be performed to
ensure that AHRS, Air Data, and Navigation Radios are operational.
Apply power in accordance with paragraph “Power application”. Upon power
application the Flight Guidance Control Panel STBY pushbutton shall illuminate and the
PFD source selection arrow shall be illuminated indicating side 2 (pilot’s side).
Initial Switch (button) Positions:
• AP1 .................................... - OFF
• AP2 .................................... - OFF
• Guidance Control Panel ..... - STBY
• Force Trim.......................... - ON
• CLTV/YAW Force Trim ...... - OFF
• PFD Sel.............................. - SIDE 2
Aircraft must be Weight OFF Wheels (IN AIR CONDITION).

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Air Data Test Set must be connected to both the number 1 and the number 2 air
data systems and airspeed set to greater than 50 knots.

1 Select the HDG and the ALT push buttons on the Flight Guidance Controller. The
HDG and the ALT pushbuttons shall illuminate on the control panel. There shall be
HDG and ALT displayed along the top of both PFDs. The pitch and roll command
bars will be displayed in the center of both the pilot’s and the copilot’s PFD.
2 Turn the Heading knob on the Pilot side Remote Instrument Controller 45 degrees
to the right. The roll command bars shall deflect right. Turn the pilot’s side
barometric setting knob to increase the baro altitude setting. The pitch command
bars shall deflect downward.
3 Press the STBY push button. The HDG and ALT pushbuttons shall extinguish, and
the STBY pushbutton shall illuminate, and the HDG and ALT mode annunciation at
the top of both the pilot and copilot PFD shall be removed
4 Set the PFD Sel to Side 1 (PFD button on Guidance Control Panel).
5 Select the HDG and the ALT push buttons on the Flight Guidance Controller. The
HDG and the ALT pushbuttons shall illuminate on the control panel. There shall be
HDG and ALT displayed along the top of both PFDs. The pitch and roll command
bars will be displayed in the center of both the pilot’s and the copilot’s PFD.
6 Turn the Heading knob on the Co-pilot side Remote Instrument Controller 45
degrees to the right. The roll command bars shall deflect right. Turn the co-pilot’s
side barometric setting knob to increase the baro altitude setting. The pitch
command bars shall deflect downward.
7 Press the STBY push button. The HDG and ALT pushbuttons shall extinguish, and
the STBY pushbutton shall illuminate, and the HDG and ALT mode annunciation at
the top of both the pilot and copilot PFD shall be removed

B.7 Hov mode checkout procedure (applicable to sar aircraft)

The HOV mode checkout procedure is to be supplied once the functionality is
implemented.

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B.8 Coupling tests (flight director configurations only)

Ensure that the aircraft power is applied in accordance with paragraph 0. Ensure that
hydraulic power is applied to the aircraft by the No. 1 hydraulic systems. Check that the
CPL light on the PC-770 Autopilot Controller is off.
Flight Director Coupling Tests – Pitch and Roll
Initial Switch (button) Positions:
• AP1 .................................... - OFF
• AP2 .................................... - OFF
• Guidance Control Panel ..... - STBY
• Force Trim.......................... - ON
• CLTV/YAW Force Trim ...... - OFF
• PFD Sel.............................. - SIDE 2
Aircraft must be Weight OFF Wheels (IN AIR CONDITION).
Air Data Test Set must be connected to both the number 1 and the number 2 air
data systems and airspeed set to greater than 50 knots.
NOTE: These tests cause trim to run and cause the actuators to move towards
center.

1 Engage AP1 and AP2 in ATT mode. The PFD arrow annunciator on the Flight
Guidance Controller should be selected to side 2 (pilot side). Align the pilot’s
heading bug with the actual heading. Engage the VS and HDG modes on the
Guidance Controller. The CPL button on the Autopilot Controller should illuminate
and the pitch and roll command bars should be centered on the ADI spheres on
both Pilot and Copilot PFDs.
2 Rotate the pilot’s heading bug 45 degrees left. The Roll Actuator Position
Indicators on the Flight Controls Synoptic page and the Flight Director roll
command bars should deflect left. Beep forward on the cyclic beep switch to
achieve a vertical speed descent command of –500fpm. The Pitch Actuator
Position Indicators on the Flight Controls Synoptic page and the Flight Director
pitch command bars should deflect down.
3 De-couple the FD by pressing the CPL pushbutton. The CPL pushbutton
annunciator on the Autopilot Controller shall extinguish and UCPL will flash on the
top left side of both PFDs. The command bars shall remain deflected. The linear
actuator position indicators will move towards center.

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4 Re-couple the Flight Director to the Autopilot by pressing the CPL pushbutton
again. The CPL light on the Autopilot Controller shall illuminate and the UCPL
annunciator shall be removed from the PFDs.
5 Select the PFD Arrow annunciator on the Flight Guidance Controller to side 1
(copilot side). Repeat parts 1 through 4 above.
Flight Director Coupling Tests – Collective (4 Axis Configurations Only)
This section to be completed when the 4 Axis (Collective) functionality is implemented.

B.9 PREFLIGHT test

Apply hydraulic power to the aircraft at the number 1 hydraulic system. Apply electrical
power to the aircraft in accordance with paragraph “Power application”
Initial Switch (button) Positions:
• AP1 .................................... - OFF
• AP2 .................................... - OFF
• Guidance Control Panel ..... - STBY
• Force Trim.......................... - ON
• CLTV/YAW Force Trim ...... - ON
• PFD Sel.............................. - SIDE 2
Check that the CPL light on the PC-770 Autopilot Controller is off.
The aircraft must be in a Weight ON Wheels (ON GROUND) condition.

1 Position the collective 2 cm from the bottom stop. Ensure that airspeed is set to zero.
2 Press the TEST button on the Autopilot Controller and complete the self test as
directed by the instructions provided from the MFD display

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 B.T. 139-46-001

Appendix – C –

C.1 TEST RESULTS TOLERANCE

The Position calculated by the GPS system should be within the tolerance of:
(1) 49.21 feet (15 Meters) of Horizontal Precision;

(2) 66 feet (20.17 Meters) for Altitude Precision.

C.2 SYSTEM DESCRIPTION

The GPS function resides on an independent module within MAU 2. The following
components comprise the GPS:
• GPS module in MAU 2
• GPS antenna
The function of the FMS is to provide flight planning capability, navigation information and
flight performance data to Pilot/Copilot. The Pilot builds, reviews and modifies flight plans
via the MCDU. A flight plan is presented on the MFD as a series of legs. The legs are
ordered according to their occurrence during the flight. The legs are bounded by
waypoints that are precisely located by latitude and longitude. Two Installation options are
available:
• Single FMS: One FMS system is installed to be operated by both MCDUs (pilot & copilot);
• Dual FMS: Two FMS systems are installed (one for each MCDU );
SYSTEM INTERFACES
Although resident in the MAU, the GPS does not feature an ASCB interface to the
Primus Epic avionics system. The GPS features two ARINC 429 data buses (IN/OUT)
to both MAU Custom I/O modules. GPS Module is powered by MAU2 power supply
module via back plane connection.

C.3 SYSTEM TESTS

TEST PREREQUISITES
The following requirements shall be fulfilled prior to proceeding with the test procedures
described within this document:
(3) The AB 139 Avionics Acceptance Test Procedure (139G4600D001) shall be successfully
executed.

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(4) The GPS/FMS systems shall be fully installed. The systems Comprises:
• GPS Antenna;
• GPS Module in MAU 2;
• GPS wiring installation;
(5) The FMS database shall be uploaded and FMS activated via Software.
(6) Before all the tests procedures verify that the External Power Bench is operative and set to
the appropriate Voltage.
TOOLING REQUIRED
The following test equipment is required for the test specified under this section:
(1) DC External Power Bench (28VDC – 3 KW);
(2) DC Voltmeter (range 0-32 VDC) for troubleshooting operation;
(3) Conductor Pins and Wire Extensions for troubleshooting operation.
INSTRUMENT PRECISION: +/- 2% MIN

GPS FUNCTIONAL TESTS

1. Park the Helicopter outdoor, in an open space whose coordinates are precisely r
known.
2. Electrically power up the Helicopter and verify the avionic system is fully r
operative.
3. Wait the GPS system calculates the present position (NOTE: The System may r
need some minutes to compute the coordinates) and access to the GPS page
pressing in sequence on the Pilot MCDU: “NAV” pushbutton, “POS SENSORS”
line select key. Verify that the displayed coordinates are the expected ones. The
tolerance shall be the one specified in the paragraph “Test Results Tolerance”
(Es.: Vergiate plant Ramp Area N 45° 43’ 000- E 8°42’220).
4. Repeat the test described in the point 3 for the Copilot MCDU. r
5. Power off MAU2 pulling out the Circuit Breakers CB110 and CB118 and verify the r
caution message “GPS FAIL” is activates in the CAS list.
6. Power on MAU2 pushing in the Circuit Breakers CB110 and CB118 and verify the r
caution “GPS FAIL” disappears from the CAS list.

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B.T. 139-46-001

SINGLE FMS INSTALLATION FUNCTIONAL TESTS

The tests described in this section shall be performed on the FMS system in single
installation configuration. The checks described in point 6 are applicable to a 4 DUs
configuration only.
1. Define a Flight Plan on the Pilot MCDU (See appendix B of the references n°5). r
2. Activate the Pilot Flight Plan and load the present position (See appendix B of the r
references n°5).

3. Select FMS2 as navigation source by the “LNAV” pushbutton on the Pilot display r
controller and verify the FMS2 bearing is displayed on the Pilot PFD.

4. On the Pilot MFD select the “PLAN” page and activate the “waypoint centered” r
and “IDENT” option in the relevant menu. Verify that the Pilot Flight Plan legs and
IDs are properly displayed on the Pilot MFD (Select the proper range for the
PLAN by the OUTER knob of the MFD active CCD). See NOTE1.

5. Select FMS2 as navigation source by the “LNAV” pushbutton on the Copilot r

display controller and verify the FMS2 bearing is displayed on the Copilot PFD.

6. Applicable to a 4 display Configuration Only: On the Copilot MFD select the r

“PLAN” page and activate the “waypoint centered” and “IDENT” option in the
relevant menu. Verify that the Pilot Flight Plan legs and IDs are properly
displayed on the Copilot MFD (Select the proper range for the PLAN by the
OUTER knob of the MFD active CCD).

7. Verify on the Copilot MCDU, that the previously defined Flight Plan has been
added in the “FLIGHT PLAN LIST” page.

8. Power off MAU2 pulling out the Circuit Breakers CB110 and CB118 and verify the r
caution message “FMS FAIL” is activates in the CAS list.

9. Power on MAU2 pushing in the Circuit Breakers CB110 and CB118 and verify the r
caution “FMS FAIL” disappears from the CAS list.

NOTE1: If the helicopter is placed in the neighborhoods of the flight plan

waypoints and the GPS system is operative, it is suggested to select
“helicopter centered” instead of the option “waypoint centered” from the
“PLAN” menu (i.e.: helicopter parked on the Vergiate plant ramp and flight plan
“AB139FPL FPL” operative –See appendix B of the references n°5).

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 B.T. 139-46-001

DUAL FMS INSTALLATION FUNCTIONAL TESTS (Optional)

The tests described in this section shall be performed on the FMS system in dual
installation configuration. The checks described in point 7 and 12 are applicable to a 4
DUs configuration only.
1. Define a Flight Plan with the Pilot FMS on the Pilot MCDU (See appendix B of r
the references n°5).

2. Define a different Flight Plan with the Copilot FMS on the Copilot MCDU (See r
appendix B of the references n°5).

3. Activate the Pilot Flight Plan and load the present position (See appendix B of r
the references n°5).

4. Select FMS2 as navigation source by the “LNAV” pushbutton on the Pilot r

display controller and verify the FMS2 bearing is displayed on the Pilot PFD.

5. On the Pilot MFD select the “PLAN” page and activate the “waypoint centered” r
and “IDENT” option in the relevant menu. Verify that the Pilot Flight Plan legs
and IDs are properly displayed on the Pilot MFD (Select the proper range for
the PLAN by the OUTER knob of the MFD active CCD) See NOTE1.

6. Select FMS2 as navigation source by the “LNAV” pushbutton on the Copilot r

display controller and verify the FMS2 bearing is displayed on the Copilot
PFD.

7. Applicable to a 4 display Configuration Only: On the Copilot MFD select r

the “PLAN” page and activate the “waypoint centered” and “IDENT” option in
the relevant menu. Verify that the Pilot Flight Plan legs and IDs are properly
displayed on the Copilot MFD (Select the proper range for the PLAN by the
OUTER knob of the MFD active CCD).

8. Activate the Copilot Flight Plan and load the present position (See appendix B r
of the references n°5).

9. Select FMS1 as navigation source by the “LNAV” pushbutton on the Pilot r

display controller and verify the FMS1 bearing is displayed on the Pilot PFD.

10. On the Pilot MFD select the “PLAN” page and activate the “waypoint centered” r
and “IDENT” option in the relevant menu. Verify that the Copilot Flight Plan
legs and IDs are properly displayed on the Pilot MFD (Select the proper range

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 B.T. 139-46-001

for the PLAN by the OUTER knob of the MFD active CCD).

11. Select FMS1 as navigation source by the “LNAV” pushbutton on the Copilot r
display controller and verify the FMS1 bearing is displayed on the Copilot
PFD.

12. Applicable to a 4 display Configuration Only: On the Copilot MFD select r

the “PLAN” page and activate the “waypoint centered” and “IDENT” option in
the relevant menu. Verify that the Copilot Flight Plan legs and IDs are properly
displayed on the Copilot MFD (Select the proper range for the PLAN by the
OUTER knob of the MFD active CCD).

7. Power off MAU2 pulling out the Circuit Breakers CB110 and CB118 and verify r
the caution message “2 FMS FAIL” is activates in the CAS list.

8. Power on MAU2 pushing in the Circuit Breakers CB110 and CB118 and verify r
the caution “2 FMS FAIL” disappears from the CAS list.

9. Power off MAU1 pulling out the Circuit Breakers CB109 and CB117 and verify r
the caution message “1 FMS FAIL” is activates in the CAS list.

10. Power on MAU1 pushing in the Circuit Breakers CB109 and CB117 and verify r
the caution “1 FMS FAIL” disappears from the CAS list.

NOTE1: If the helicopter is placed in the neighborhoods of the flight plan

waypoints and the GPS system is operative, it is suggested to select
“helicopter centered” instead of the option “waypoint centered” from the
“PLAN” menu (i.e.: helicopter parked on the Vergiate plant ramp and flight plan
“AB139FPL FPL” operative –See appendix B of the references n°5).

C.4 GPS – FMS TESTS RESULTS

GPS - FMS ACCEPTANCE TEST PROCEDURE

DESCRIPTION OPERATOR DATE REMARKS

TEST PREREQUISITES

TOOLING REQUIRED

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 B.T. 139-46-001

DESCRIPTION OPERATOR DATE REMARKS

GPS FUNCTIONAL TESTS

SINGLE FMS INSTALLATION

FUNCTIONAL TESTS

DUAL FMS INSTALLATION

FUNCTIONAL TESTS (Optional)

Engineering dpt signature(if required):

Quality dpt approval:

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 B.T. 139-46-001

Appendix – D –

Electronic display system (EDS)

D.1 System Description
The Electronic Display System (EDS) provides the display of data to the flight crew for
aircraft control, navigation, and aircraft systems. The Electronic Display System includes
the Engine Indication and Crew Alerting System. The Engine Indication and Crew Alerting
System has two primary functions: it provides the flight crew with displays for the
monitoring of engine parameters, rotor parameters and aircraft systems, and generates
annunciations in the form of visual (Master Caution and Master Warning pushbutton
switch illumination) and aural messages (AWG) to inform the flight crew of aircraft
systems anomalies.
The MCDU is a keyboard control/display that provides general purpose control and
display for several functions in the aircraft such as FMS, COMMs and NAVs. Each MCDU
is connected to on side MAU Custom I/O module and to on side MRC NIM Module via
ARINC-429 line. This connection permits a backup radio tuning.
The EDS is comprised of the following components:
• Primary Flight Display units (PFD);
• Multifunction Display unit(s) (MFD);
• Multifunction Control Display Unit (MCDU);
• Modular Avionics Unit Custom I/O Module;
• Modular Avionics Unit Control I/O Module;
• Display Controller;
• Remote Instrument Controller;
• Cursor Control Device;
• Reversion Control Panel;
• Dimming Display Control Panel;
• Master Warning & Master Caution Announciator
The EDS Configuration can be as follow:
• 3 Displays Configuration (2PFD, 1 MFD Pilot);
• 4 Display Configuration (2 PFD, 1 MFD Pilot & 1 MFD Copilot).
In case of 4 displays configuration the appropriate tests will be specified in the following
sections.

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System Interfaces
The systems that interface with the components of the EDS, and the respective type of
interface, are listed in Table D.1.

Table D.1 - EDS Interfaces

ARINC Discrete Discrete

System ASCB-D RS-422 Analog
429 Input Output

PFD X X

MFD X X

MCDU X

MAU Custom I/O Module X X X X X

MAU Control I/O Module X X X X X

Display Controller X X X

Remote Instrument Controller X

Cursor Control Device X

Reversion Control Panel X

Dimming Display Control

X
Panel

Master Warning & Master

X X
Caution Indicator

Test Prerequisites

(1) Turn ON the EXT PWR. only after the Helicopter is fully configured (Switches, CB
breakers, connectors and devices) as specified for the following test. Verify the
BATTERY SWITCH is in OFF position.

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Test Equipment
The following test equipment is required for EDS system test procedure:
Table D.3 - EDS Test Equipment

DEVICE P/N S/N NOTE

(1) DC External Power Bench (28VDC).

(2) Two headset for ICS system

(David Clark model H10-13H or equivalent).

Electrical Circuit Breakers Configuration

All the Electrical Circuit Breakers pulled out except the ones listed in Table D.4 (Power
Distribution CBs)
Table D.4 - Electrical Circuit Breaker Starting Configuration for EDS Test
Procedure.

Position
Nomenclature System Done/Verified
Required

(DISPLAY) PFD PLT Pilot PFD IN

(DISPLAY) PFD PLT CONTR Pilot’s Display Controller IN

(DISPLAY) MFD PLT Pilot MFD IN

(DISPLAY) MFD CPLT IN

Copilot MFD
(4 Display Config.)

(DISPLAY) PFD CPLT Copilot PFD IN

(DISPLAY) PFD CPLT CONTR Copilot’s Display Controller IN

Pilot’s Multifunction Control

(DISPLAY) MCDU PLT IN
Display Unit

Copilot’s Multifunction Control

(DISPLAY) MCDU CPLT IN
Display Unit

MAU1 PRI PWR MAU 1 Power Supply IN

(Primary)

MAU2 PRI PWR MAU 2 Power Supply IN

(Primary)

MAU1 AUX PWR MAU 1 Power Supply IN

(Secondary)

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 B.T. 139-46-001

Position
Nomenclature System Done/Verified
Required

MAU2 AUX PWR MAU 2 Power Supply IN

(Secondary)

(NAV/COMM) NIM1 MRC1 NIM IN

(NAV/COMM) NIM2 MRC2 NIM IN

D.2 EDS Test Procedure
The following tests are to verify that the proper display mode is shown on PLT PFD, MFD,
CPLT PFD in the different system conditions and to check the functionality of the Control
Panels listed above linked to EDS system.
All the results of the tests shall be check on the following displays:
• DU1 = PFD Copilot;
• DU2 = MFD Copilot (Optional)
• DU3 = MFD Pilot;
• DU4 = PFD Pilot;

DUs Identification Strapping

The following steps verify the correct configuration and integrity of the Display Units
NIC strapping: System status:
1. Verify that on the Display Reversion Control panel that both the reversion switches
are set to the “NORMAL” position.
2. Verify that the displays DU1, DU3, DU4 (DU2 for a 4 displays configuration) are
powered and the correct display format is visualized (PFD format for DU1 and DU4,
MFD Power Plant format for DU2-4 displays config only- and DU3).

DUs Dimming
1. On the DU Dimming control panel, turn the Pilots PFD Dimming knob clockwise,
and verify that the brightness of the Pilot’s PFD increases.
2. On the DU Dimming control panel, turn the Pilot’s PFD Dimming knob counter-
clockwise, and verify that the brightness of the Pilot’s PFD decreases.
3. On the DU Dimming control panel, turn the Pilot’s PFD Dimming Knob to the lowest
brightness position and verify the Pilot PFD display is still legible.
4. On the DU Dimming control panel, set the Pilot’s PFD Dimming knob to a
brightness level which allows for the data displayed on the DU to be legible.

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B.T. 139-46-001

5. Repeat the tests listed in points 1, 2, 3 and 4 for pilot MFD, copilot MFD (for 4
displays configuration) and copilot PFD.

Display Reversion Test

The EDS system provides both the autoreversion and the manual reversion features.
Normally, if a malfunction is detected by the system, the affected display will be
automatically powered off and the other on-side DU set to composite mode. Otherwise
the pilot and copilot have the authority to force the DU’s to composite, just operating by
mean the reversion control panel.
Pilot Side Reversion Switch
NOTE: The tests described in this section are applicable to both the “3 DU” and “4 DU”
configuration.
1. Verify that the pilot DU’s reversion switch is set to “NORMAL” position.
2. Set the pilot reversion switch to the “PFD ONLY” position.
3. Verify that the Composite format is displayed on DU4 (Pilot’s PFD) and the
DU3 (Pilot’s MFD) is blank.
4. Set the pilot reversion switch to “MFD ONLY” position.
5. Verify that the composite MFD format is displayed on DU3 (Pilot MFD) and
DU4 (Pilot’s PFD) is blank.
6. Set the Pilot Reversion switch to “NORMAL” position.
7. Verify that the normal (non-reversion) PFD format is displayed on DU4 and a
MFD format is displayed on DU 3.
Pilot Side DU Autoreversion
NOTE: The tests described in this section are applicable to “4 DU” configuration only.
1. Verify that the pilot DU’s reversion switch is set to “NORMAL” position.
2. Power off the pilot PFD pulling out the relevant circuit breaker.
3. Verify that the pilot MFD automatically reverts to composite mode.
4. Power on the pilot PFD pushing in the relevant circuit breaker and verify that
the pilot PFD powers up in normal PFD while the pilot MFD remain in
composite mode.

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5. Toggle the pilot manual reversion switch from “NORM” to “MFD ONLY” and
then back to “NORM”. Verify that the normal visualization is restored on both
DU’s (Normal PFD display on pilot PFD and normal MFD display on pilot MFD).
6. Power off the pilot MFD pulling out the relevant circuit breaker.
7. Verify that the pilot PFD automatically reverts to composite mode.
8. Power on the pilot MFD pushing in the circuit breaker and verify that the pilot
MFD powers up in normal MFD mode while the pilot PFD remains in composite
mode.
9. Toggle the pilot manual reversion switch from “NORM” to “PFD ONLY” and
then back to “NORM”. Verify that the normal visualization is restored on both
DU’s (Normal PFD display on pilot PFD and normal MFD display on pilot MFD).
Copilot side Reversion Switch
NOTE: The tests described in this section are applicable to both the “3 DU” and “4 DU”
configuration.
1. Verify that the pilot DU’s reversion switch is set to “NORMAL” position.
2. Set the copilot reversion switch to the “PFD ONLY” position.
3. Verify that:
• 3 DU Config.: the Composite PFD format is displayed on DU1 and the DU3 (Pilot’s
MFD) is blank.
• 4 DU Config.: the Composite PFD format is displayed on DU1 and the DU2
(Copilot’s MFD) is blank.
4. Set the pilot reversion switch to the “MFD ONLY” position.
5. Verify that
• 3 DU Config.: The composite MFD format is displayed on DU3 (Pilot’s MFD) and
DU1 (Copilot’s PFD) is blank.
• 4 DU Config.: The composite MFD format is displayed on DU2 (Copilot’s MFD) and
DU1 (Copilot’s PFD) is blank.
6. Set the Copilot Reversion switch to “NORMAL” position.
7. Verify that the normal (non reversion) PFD format is displayed on DU1 and a
MFD format is displayed on DU2 (Copilot’s MFD).
Copilot Side DU Autoreversion
NOTE: The tests described in this section are applicable to “4 DU” configuration only.
1. Verify that the copiltot DU’s reversion switch is set to “NORMAL” position.
2. Power off the copilot PFD pulling out the relevant circuit breaker.
3. Verify that the copilot MFD automatically reverts to composite mode.

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B.T. 139-46-001

4. Power on the copilot PFD pushing in the circuit breaker and verify that the
copilot PFD powers up in normal PFD while the copilot MFD remain in
composite mode.
5. Toggle the copilot manual reversion switch from “NORM” to “MFD ONLY” and
then back to “NORM”. Verify that the normal visualization is restored on both
DU’s (Normal PFD display on copilot PFD and normal MFD display on copilot
MFD).
6. Power off the copilot MFD pulling out the relevant circuit breaker .
7. Verify that the copilot PFD automatically reverts to composite mode.
8. Power on the copilot MFD pushing in the relevant circuit breaker and verify that
the copilot MFD powers up in normal MFD mode while the copilot PFD remains
in composite mode.
9. Toggle the copilot manual reversion switch from “NORM” to “PFD ONLY” and
then back to “NORM”. Verify that normal visualization is restored on both DU’s
(Normal PFD display on copilot PFD and normal MFD display on copilot MFD).
Display Controller
The Display Controller serializes (RS 422 Protocol) discrete inputs from the on-side RI
controller and from the on-side and cross-side CCD for transmission to the on-side and
cross-side MAU Control I/O module. There is, therefore, redundancy in the operability
of the CCD in the event of failure of the on-side (with respect to the CCD) Display
Controller.
Refer to Table D2 for procedures verifying the integrity of the interface between the
Remote Instrument Controller and the Display Controller
The following steps verify the integrity of the electrical interface between the
Pilot/Copilot CCD, Pilot/Copilot RI and the Pilot/Copilot DC, and the integrity of the RS-
422 data bus constituting the interface between the Pilot/Copilot DC and the MAU 1,
MAU 2 Control I/O module:
Pilot CCD (Copilot Display Controller OFF)
1. Verify all the CB are set in the configuration specified in Table D4.
2. Pull the DISPLAY PFD CONTR CPLT electrical circuit breaker to the “OUT”
position. (“AVIONIC FAULT” Caution displayed on ground)

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 B.T. 139-46-001

3. Press the Pilot’s CCD display select left (LH) pushbutton in order to select DU3
(Pilot MFD).
4. Verify that the pilot cursor appears on the softkeys bar on the top of the MFD
Page.
5. Move the Pilot’s CCD joystick in the LEFT direction.
6. Verify that the cursor moves to the left on the menu bar.
7. Move the Pilot’s CCD joystick in the RIGHT direction.
8. Verify that the cursor moves to the right on the menu bar.
9. Press the Pilot’s CCD “ENTER” pushbutton.
10. Verify that the SYSTEM pull-down menu is displayed.
11. Move the Pilot’s CCD joystick in the DOWN direction.
12. Verify that the cursor moves downward on the selected menu.
13. Move the Pilot’s CCD joystick in the UP direction.
14. Verify that the cursor moves upward on the selected menu.
15. Press the Pilot’s CCD display select right (RH) pushbutton in order to select
DU4 (Pilot PFD).
16. Rotate the CCD inner rotary knob and verify that the scroll function has no
effect on MFD CAS messages list.
17. Verify that the cursor appears on the Pilot PFD as a square around one of the
four frequencies displayed.
18. Using the CCD joystick select “COM1” (Highlighting square set around the
relevant frequency)
19. Tune the preset frequency rotating the inner (verify KHz change) and outer
(verify MHz change) CCD knobs.
Copilot CCD (Copilot Display Controller OFF)
1. Press the Copilot’s CCD display select right (RH) pushbutton in order to select:
DU3 (Pilot MFD) for a 3 displays config. or DU2 (Copilot MFD) for a 4 displays
config.
2. Verify that the Pilot’s cursor automatically moves onto the Pilot PFD and the
Copilot’s cursor appears on the MFD.
3. Move the Copilot’s CCD joystick in the DOWN direction.
4. Verify that the cursor moves downward on the selected menu.

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5. Move the Copilot’s CCD joystick in the UP direction.

6. Verify that the cursor moves upward on the selected menu.
7. Move the Copilot’s CCD joystick in the LEFT direction
8. Verify that the cursor moves to the left on the MFD menu bar.
9. Move the Copilot’s CCD joystick in the RIGHT direction.
10. Verify that the cursor moves to the right of the MFD menu bar.
11. Select DC Elect monitoring Page.
12. Press the Copilot’s CCD “ENTER” pushbutton.
13. Verify that the DC ELECT monitoring page is displayed.
14. Press the copilot’s CCD display select left (LH) pushbutton in order to select
the DU1 (Copilot PFD).
15. Verify the cursor appears on the Copilot’s PFD.
16. Using the CCD Joystick select “COM1” (Highlighting square set around the
relevant frequency).
17. Tune the standby frequency rotating the inner (verify KHz change) and outer
(verify MHz change) CCD knobs.
Pilot DC (Copilot Display Controller OFF)
1. Press the “BRG O” pushbutton on the Pilot’s Display Controller.
2. Verify that the display for the short-range navigation mode toggles through the
following annunciations on the Pilot’s PFD right bottom:
• First button press: VOR 1
• Second button press: ADF
• Third pushbutton press: FMS 1
• Fourth pushbutton press: No annunciation.
3. Press the “BRG ◊” pushbutton on the Pilot’s Display Controller.
4. Verify that the display for the short-range navigation mode toggles through the
following annunciations on the Pilot’s PFD right bottom corner:
• First button press: VOR 2
• Second button press: ADF
• Third pushbutton press: FMS 2
• Fourth pushbutton press: No annunciation.
5. Press the “NAV” pushbutton on the Pilot’s Display Controller.
6. Verify that the following annunciations are displayed on the Pilot’s PFD:

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• First press: VOR 2

• Second press: VOR 1
7. Press the “LNAV” pushbutton on the Pilot’s Display Controller.
8. Verify that the following annunciations are displayed on the Pilot’s PFD:
• First press: FMS 2
• Second press: FMS 1
9. Ensure that the NAV source is set to FMS1 or FMS2 and press the “PREV”
(Preview) pushbutton on the Pilot’s Display Controller.
10. Verify that the following annunciations are displayed on the Pilot’s PFD:
• First press: VOR2 annunciation displayed (Preview Mode)
• Second press: VOR1 annunciation displayed (Preview Mode)
• Third pushbutton press: No annunciation
11. Press the “HSI” pushbutton on the Pilot’s Display Controller.
12. Verify that the HSI display on the Pilot’s PFD toggles between the arc format
and the full HSI display format.
13. Press the “MAP” pushbutton on the Pilot’s Display Controller.
14. Verify that the HSI indicator is displayed in the following mode on the Pilot’s
PFD:
• First press: FMS MAP displayed (Arc Mode)
• Second press: No annunciation
15. Press the “WX” pushbutton on the Pilot’s Display Controller.
16. If a Weather Radar is installed, verify that the following pages are displayed on
the MFD:
• First press: WX data ON displayed on an Arc Compass mode page;
• Second press: WX data OFF.
• If a WX is not installed, an advisory “WX NOT INSTALLED” will be
displayed.
17. Rotate clockwise the “ALT SEL” Knob and verify the altitude reference on the
Pilot’s PFD altitude tape increases.
18. Rotate counter-clockwise the “ALT SEL” Knob and verify the altitude reference
on the Pilot’s PFD altitude tape decreases.
19. Rotate the “BARO” knob setting and verify on the Pilot PFD that the barometric
set value below the altitude tape and the altitude tape moves.

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Pilot and Copilot CCD with MAUs failure (Copilot Display Contr. OFF)
1. Set the MAU 1 electrical circuit breakers to the “OUT” position. Verify that the
“MAU 1” failure caution is displayed on both the PFD’s.
2. On the Pilot CCD press the left-hand arrow pushbutton and verify that the Pilot
cursor appears on the MFD.
3. On the Pilot CCD move LEFT/RIGHT UP/DOWN the Joystick and verify the
cursor moves properly on the MFD menus.
4. On the Copilot CCD press the right-hand arrow pushbutton and verify that the
Copilot cursor appears on the MFD.
5. On the Copilot move LEFT/RIGHT UP/DOWN the Joystick and verify the cursor
moves properly on the MFD menus.
6. Set the MAU 1 electrical circuit breakers to the “IN” position and verify, after the
MAU1 start-up transient, that the “MAU 1” failure caution is removed from the
PFD’s.
7. Set the MAU 2 electrical circuit breakers to the “OUT” position. Verify that the
“MAU 2” failure caution is displayed on both the PFD’s.
8. On the Pilot CCD press the left-hand arrow pushbutton and verify the cursor
appears on the MFD.
9. Move LEFT/RIGHT UP/DOWN the Joystick and verify the cursor moves
properly on the MFD menus.
10. On the Copilot CCD press the right-hand arrow pushbutton and verify that the
Copilot cursor appears on the MFD.
11. On the Copilot move LEFT/RIGHT UP/DOWN the Joystick and verify the cursor
moves properly on the MFD menus.
12. Set the MAU 2 electrical circuit breakers to the “IN” position and verify, after the
MAU2 start-up transient, that the “MAU 2” failure caution is removed from the
PFD’s.
Pilot CCD (Pilot Display Controller OFF)
1. Push the DISPLAY PFD CONTR CPLT electrical circuit breaker to the “IN”
position.
2. Set the DISPLAY PFD CONTR PLT electrical circuit breaker to the “OUT”
position. (“AVIONIC FAULT” Caution displayed on ground)

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3. On the Pilot CCD press LH – RH - LH arrow pushbuttons and verify the cursor
moves into PLT MFD - PLT PFD – PLT MFD.
4. Move LEFT/RIGHT UP/DOWN the Joystick and verify the cursor moves
properly on the MFD menus.
5. Move the Cursor into the PLT PFD. Verify that the Inner and Outer knobs work
properly (tuning one of the visualized frequency) and the ENTER push button is
operative (Swapping active and preset frequency).
Copilot CCD (Pilot Display Controller OFF)
1. On the Copilot CCD press RH – LH - RH arrow pushbuttons and verify the
cursor moves into PLT MFD - CPLT PFD – PLT MFD (For 4 displays
configuration verify lo swapping: CPLT MFD - CPLT PFD – CPLT MFD)
2. Move LEFT/RIGHT UP/DOWN the Joystick and verify the cursor moves
properly on the MFD menus.
3. Move the Cursor into the CPLT PFD. Verify that the Inner and Outer knobs
work properly (tuning one of the visualized frequency) and the ENTER push
button is operative (Swapping active and preset frequency).
Copilot DC (Pilot Display Controller OFF)
1. Press the “BRG O” pushbutton on the Copilot’s Display Controller.
2. Verify that the display for the short-range navigation mode toggles through the
following annunciations on the Copilot’s PFD right bottom corner:
• First pushbutton press: VOR 2
• Second pushbutton press: ADF
• Third pushbutton press: FMS 2
• Fourth pushbutton press: No annunciation.
3. Press he “BRG ◊” pushbutton on the Copilot’s Display Controller.
4. Verify that the display for the short-range navigation mode toggles through the
following annunciations on the Pilot’s PFD right bottom corner:
• First pushbutton press: VOR 1
• Second pushbutton press: ADF
• Third pushbutton press: FMS 1
• Fourth pushbutton press: No annunciation.
5. Press the “NAV” pushbutton on the Copilot’s Display Controller.
6. Verify that the following annunciations are displayed on the Copilot’s PFD:

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• First press: VOR 1

• Second press: VOR 2
7. Press the “LNAV” pushbutton on the Copilot’s Display Controller.
8. Verify that the following annunciations are displayed on the Copilot’s PFD:
• First press: FMS 1
• Second press: FMS 2
9. Ensure that the NAV source is set to FMS1 or FMS2 and press the “PREV”
pushbutton on the Copilot’s Display Controller.
10. Verify that the following annunciation are displayed on the Copilot’s PFD:
• First press: VOR1 annunciation displayed in grey color (Preview Mode)
• Second press: VOR 2 annunciation displayed in gray color (Preview Mode)
• Third pushbutton press: No annunciation
11. Press the “HSI” pushbutton on the Copilot’s Display Controller.
12. Verify that the HSI display on the Copilot’s PFD toggles between the arc format
and the full HSI display format.
13. Press the “MAP” pushbutton on the Copilot’s Display Controller.
14. Verify that the HSI indicator is displayed in the following mode on the Copilot’s
PFD:
• First press: FMS MAP displayed (Arc Mode);
• Second press: Normal Mode HSI
15. Press the “WX” pushbutton on the Copilot’s Display Controller.
16. If a Weather Radar is installed, verify that the following pages are displayed on
the MFD:
• First press: WX data ON displayed on an Arc Compass mode page;
• Second press: WX data OFF.
• If a WX is not installed, an advisory “WX NOT INSTALLED” will be
displayed.
17. Rotate clockwise the “ALT SEL” Knob and verify the altitude reference on the
Copilot’s PFD altitude tape increases.
18. Rotate counter-clockwise the “ALT SEL” Knob and verify the altitude reference
on the Copilot’s PFD altitude tape decreases.
19. Rotate the “BARO” knob setting and verify on the Copilot PFD that the
barometric set value below the altitude tape and the altitude tape moves.
Pilot and Copilot CCD with MAUs failure (Pilot Display Contr. OFF)
1. Set the MAU 1 electrical circuit breakers to the “OUT” position.

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2. On the Pilot CCD press the left-hand arrow pushbutton and verify that the Pilot
cursor appears on the MFD.
3. On the Pilot CCD move LEFT/RIGHT UP/DOWN the Joystick and verify the
cursor moves properly on the MFD menus.
4. On the Copilot CCD press the right-hand arrow pushbutton and verify that the
Copilot cursor appears on the MFD.
5. On the Copilot move LEFT/RIGHT UP/DOWN the Joystick and verify the cursor
moves properly on the MFD menus.
6. Set the MAU 1 electrical circuit breakers to the “IN” position.
7. Set the MAU 2 electrical circuit breakers to the “OUT” position.
8. On the Pilot CCD press the left-hand arrow pushbutton and verify that the Pilot
cursor appears on the MFD.
9. On the Pilot CCD move LEFT/RIGHT UP/DOWN the Joystick and verify the
cursor moves properly on the MFD menus.
10. On the Copilot CCD press the right-hand arrow pushbutton and verify that the
Copilot cursor appears on the MFD.
11. On the Copilot move LEFT/RIGHT UP/DOWN the Joystick and verify the cursor
moves properly on the MFD menus.
12. Set the MAU 2 electrical circuit breakers to the “IN” position.

Master Warning & Master Caution lights

In case of anomalies detected in any of the Helicopter Systems, the MAUs generate
messages that are displayed on the MFD CAS window and determine the flashing of the
Master Pilot and Copilot Warning/Caution lights in order to inform the flying crew of the
failures. The failure Messages are classified in Warnings (Red Light) and Caution (Amber
Light). In case of noticed Warning/Caution message, the Pilot or Copilot can reset the
flashing master light just pressing it. In this case the Warning/Caution message still
remain displayed on the MFD CAS window but it will be no longer highlighted.

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Appendix – E –

E.1 Master Warning and Caution Light Test

1. Connect the Headset to an ICS Plug (Pilot or Copilot).

2. Power off both MAUs pulling out the relevant circuit breakers.
3. Power on MAU2 pushing in the circuit breakers.
4. Verify that a long list of WARNING (red highlighted) and CAUTION (amber
highlighted) messages is displayed in the CAS window and the relevant aural
warnings are properly generated in the headsets.
5. Verify both pilot and copilot master warning light (red light) and master caution light
(amber light) start flashing.
6. Press the pilot master warning light pushbutton.
7. Verify both master warning lights reset and all warnings in the CAS message on
the MFD is represented without highlighting.
8. Press the pilot master caution light pushbutton.
9. Verify both master caution lights reset and all cautions in the CAS message on the
MFD is represented without highlighting.
10. Reset MAU2 again (pull out circuit breakers and push them in after a few seconds).
11. Verify that a long list of WARNING (red highlighted) and CAUTION (amber
highlighted) messages is displayed in the CAS window and the relevant aural
warnings are properly generated in the headsets. Verify both pilot and copilot
master warning light (red light) and master caution light (amber light) start flashing.
12. Press the copilot master warning light pushbutton.
13. Verify both master warning lights reset and all warnings in the CAS message on
the MFD is represented without highlighting.
14. Press the copilot master caution light pushbutton.
15. Verify both master caution lights reset and all cautions in the CAS message on the
MFD is represented without highlighting.
16. Reset MAU2 again (pull out circuit breakers and push them in after a few seconds).
17. When the warning/caution messages are generated in CAS list and the master
warning/caution lights start flashing, press the RESET pushbutton on the pilot

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collective stick. Verify the master warning and caution lights turn off and the
warnings and cautions in the CAS message list on the MFD are represented
without highlighting.
18. Reset MAU2 again (pull out circuit breakers and push them in after a few seconds).
19. When the warning/caution messages are generated in CAS list and the master
warning/caution lights start flashing, press the RESET pushbutton on the copilot
collective stick. Verify the master warning and caution lights turn off and the
warnings and cautions in the CAS message list on the MFD are represented
without highlighting.
20. Power off MAU2 pulling out circuit breakers.
21. Power on MAU1 pushing in circuit breakers.
22. Repeat the tests above from point 4 to point 19 resetting MAU1 in place of MAU2
when required.

E.2 Lamp Test Switch

1. Press Lamp Test Switch on Test Control Panel.
2. Verify all the required lamps are lighted ON as long as the button is pressed.

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Appendix – F –
F.1 Instruments panel lights

Disconnect connector PS1

INSTRUMENT PANEL FUNCTIONAL TEST:

Connect back connectr PS1-P1.

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F.2 Console panel lights

Connect connector PL2-P1 & P2 and disconnect connectors PS2 and PS3

CONSOLE PANEL FUNCTIONEL TEST:

Connect back connector PS2-P1, PS3-P1.

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F.3 OVERHEAD PANEL LIGHTS

Disconnect connector PS4.

OVERHEAD PANEL FUNCTIONEL TEST

Connect back connector PS2-P1, PS3-P1.

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F.4 DOME LIGHTS

Disconnect connectors PL2-P1 & P2.

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Appendix – G –

SETTING OF MAIN ROTOR BLADES AND COLLECTIVE ADJUSTABLE STOP

Starting from the nominal condition (helicopter ready to flight, controls ATP and dynamic
balancing performed) after removal of the locking wire, operate each of the 5 pitch links
in such a way to obtain a decrease of the minimum collective blade angle of 0.5 ÷ 0.6
deg.
The reduction of the collective angle is obtained by rotating the mean body of the pitch
link in order to shorten the pitch link to the correct value.
One complete turn corresponds to 0° 57’ 10”.

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