V1 series - Vulcan Air

First issue dated 30 April 2018 Rev.2 dated 30 July 2018

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Vulcanair S.p.A. via G. Pascoli, 7 80026 Casoria (NA) – Italia Tel +39 081 5918111 Fax +39 081 5918172 [email protected] www.vulcanair.com

V1 series

Approved by Vulcanair Design Organisation

The technical content of this document is approved under the authority of DOA No. EASA.21J.009.

Operator obligations with regards to inspections, modifications and/or other technical directives and their times of

compliance are laid out in the relative Airworthiness Directives.

SERVICE BULLETIN

No. VA-02 Rev.2 (Supersedes the previous issue approved on 17 July 2018)

Design Organisation Approval No. AS-SB/18/018 dated 03 August 2018

INFORMATION

SUBJECT: PROCEDURE FOR AIRCRAFT RE-ASSEMBLING AND TESTING

1. GENERAL

1.1 AIRCRAFT AFFECTED

Vulcanair V1.0 from s/n 1003 onwards.

1.2 PURPOSE

The purpose of this Service Bulletin is to supply information for aircraft re-assembling and

testing for the aircraft shipped inside a container, once arrived to the final destination.

1.3 DESCRIPTION

The airplane, once arrived disassembled in container at the final destination, must be re-

assembled and tested (on-ground and in-flight) by a certified Maintenance Organisation of the

Importing State in order to release to service the airplane, in accordance with the procedures

laid out in paragraph 2 hereunder.

No change is needed about Operating Limitations, Emergency Procedures, Normal

Procedures, Performance and Weight and Balance Data.

No additional maintenance tasks are required when the aircraft embodies this Service

Bulletin, therefore the current aircraft maintenance program remains unchanged.

Vulcanair S.p.A. Service Bulletin No. VA-02 Rev.2


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The instructions laid out in the paragraph 2 hereunder, are divided into seven Parts as

follows:

− Part A: DISASSEMBLED PARTS DISEMBARKING OPERATIONS

− Part B: HORIZONTAL EMPENNAGES INSTALLATION

− Part C: WING AND MOVABLE CONTROL SURFACES INSTALLATION

--- deleted ---

− Part D: PROPELLER INSTALLATION

− Part E: ON-GROUND TESTS

− Part F: IN-FLIGHT TESTS

1.4 COMPLIANCE

At owner’s discretion.

1.5 MANHOURS

The time necessary for the application of this Service Bulletin is estimated as being 30 man-hours.

1.6 SPECIAL TOOLS

Not applicable.

1.7 VARIATION IN WEIGHT & BALANCE

Not applicable.

1.8 ELECTRICAL SYSTEM LOAD

Not applicable.

1.9 REFERENCE DOCUMENTS

• Lycoming pertinent technical documentation

• Hartzell pertinent technical documentation

• Garmin pertinent technical documentation

• Aircraft Maintenance Manual AMM10.702-5

• Aircraft Flight Manual AFM10.701-7

• Parts Catalogue IPC10.703-7

1.10 PUBBLICATIONS AFFECTED

None.

1.11 MODIFICATION TO BE CARRIED OUT BY

Vulcanair Part 145 or other Approved Maintenance Organisation recognised also as

Garmin Dealer Resource Center for Garmin Authorized Service Centers.



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2. WORK PROCEDURE

WARNING

This work procedure calls for the use of

substances and/or procedures that may be

injurious to health if adequate precautions are not

taken. This document refers only to technical

suitability and in no way absolves the Operator

from statutory and other legal obligation relating

to health and safety at any stage of manufacture

or use.

WARNING

SAFETY PRECAUTIONS

In addition to local requirements or where local

regulations are not specified, the following safety

precautions are recommended during fuelling and

de-fuelling activities:

1) Place the aircraft in a designated fuelling or

de-fuelling area (external area).

2) Ground the aircraft using designated

grounding cables.

3) Ground and bond all fuelling and de-fuelling

equipment to the aircraft. As bonding point

use the muffler tube protruding from the

engine cowlings.

4) Position a suitable firefighting equipment

near the aircraft. It must be readily available.

5) Use suitable plugs or caps to seal all opened

fuel lines.

6) Use only hermetically sealed lights, if an

artificial lighting is necessary.

7) Do not operate any avionics or electrical

equipment on the aircraft (all switches OFF).

8) Do not allow fire, sparks or heat near fuel.

Fuel burns violently and can cause injury to

persons and damage to the aircraft.

9) Do not wear nylon or synthetic fabrics,

and/or shoes with metal heel taps, to avoid

generating static electricity or causing sparks.

10) Do not smoke or use a naked flame in

proximity of the aircraft.

11) Do not get fuel on your skin. Fuel can cause

skin disease.

12) Fuelling and de-fuelling operations with

person on board are prohibited.



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WARNING

Before performing any work in the propeller

areas, be sure that the magnetos and the master

switches are OFF, and that the mixture control

lever is in the IDLE CUT-OFF position, to avoid

bodily injury when the propeller is rotated during

installation.

WARNING

Carry out this work procedure in a FOD control

area.

• Practice “Clean as you go”.

• Monitor all your personal items. Personal

items should be accounted for upon exit of

FOD area.

• Keep and account for all your Tools,

Hardware, Equipment.

• Dispose of trash properly.

• No food or beverage allowed.

Before finishing this work procedure check that

all the area affected by this activity is FOD free.

WARNING

Read the entire procedure and the latest

applicable revision of reference documents to

make sure you have a complete understanding of

the requirements.

WARNING

All the following procedures must be performed

by specific authorized personnel.

CAUTION

Always follow the manufacturer’s instructions and

safety precautions during application and usage of all

the substances called out in this work procedure.

NOTE

Refer, as applicable, to the Lycoming and/or Hartzell

pertinent technical documentation.

NOTE

The discarded materials and fluids used during the

maintenance activities should be disposed of in

accordance with applicable regulations.



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Part A: DISASSEMBLED PARTS DISEMBARKING OPERATIONS

1) Perform an accurate visual inspection of the entrance door and external area of the container in

order to check its general condition and the possible presence of damages occurred on the

container during the shipment.

2) Verify the undamaged presence of all the security seals applied to the entrance door of the

container.

3) Gain access to the internal area of the container.

4) Get access to the aircraft cabin and identify the g-meter installed between the pilot and copilot

seats. Take note of the g-meter reading and transmit the load factor saved by the g-meter to

Vulcanair Customer Support by means of the online form at the address

http://support.vulcanair.com/ section “Support form” (a picture is appreciated): if g-meter

reading is less or equal than 4 (four), continue on performing this work instructions; if the

reading is greater than 4 (four), stop any kind of activities and wait for Vulcanair instructions.

5) Remove the g-meter together with its bracket and discard the bracket-to-aircraft attaching

screws.

6) Re-install the object holder attaching screws grouped in a bag next to the object holder.

7) Perform an accurate visual inspection of all the items inside the container in order to check

their general status and the possible evidence of damages occurred on the disassembled parts,

tools or security devices during the shipping (see Figure 1).

NOTE

Take care to extract opportunely the disassembled

parts out from the container.

8) Disengage the half-wings from the container, then carefully move them slowly forwards out of

the concerned container.

9) Disengage all the packing boxes from the container, then carefully move each of them slowly

forwards out of the container.

10) Disengage all embarked items from the container, then carefully move each of them slowly

forwards out of the container.

11) Carefully remove all the security devices used to assure all the aircraft disassembled parts and

tools to the container during the shipment.

12) Carefully remove all the protections and packaging used to avoid damages to the disassembled

parts.

13) Guarantee a correct disembarking of all aircraft disassembled parts arranged inside the

container.

14) Unmoor completely the aircraft fuselage from the container, maintaining it in the current

inclined position to permit its extraction.

15) Disengage the aft mooring hook from the container floor, then carefully move the aircraft

fuselage slowly forwards out of the container.

16) Handling the aircraft fuselage, install the NLG wheel in accordance with concerning

procedure laid out in the AMM and then lower the aircraft on its NLG wheel assembly.

http://support.vulcanair.com/



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WARNING

Assure that all the disassembled parts, previously

tagged as “EFFICIENT”, are still efficient after

the shipment (no damage found).

17) Place all the aircraft disassembled parts in a suitable working area for the operations to be

carried out.

18) Tow the aircraft fuselage on a compact and level surface.

19) Check that all electrical switches are in OFF position.

20) Maintain disconnected the battery cables and the external power unit.

21) Ground the aircraft using designated grounding cables.

22) Put in place a trestle under the aft mooring hook (tail of the airplane) in correspondence of the

fuselage frame No.6.

23) Proceed with the following Part B.

Figure 1 Parts predisposition inside the container



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Part B: HORIZONTAL EMPENNAGES INSTALLATION

WARNING

Be careful not to damage both halves-stabilator

during their reinstallation.

NOTE

During re-assembling procedure apply MIL-PRF-

8116C (Mastinox D40, or equivalent) anticorrosive

compound to all bolt shanks.

NOTE

During re-assembling procedure install the safety

wires as applicable, using stainless steel wires with

0.8mm (0.03in) diameter.

NOTE

During re-assembling procedure install the ground

leads as applicable.

1) Refer to Figure 2 for horizontal empennages installation.

2) Gently withdraw from the container and from the concerned packing boxes, if not already

done, all the items necessary to perform the horizontal empennages re-installation. Discard

and replace the damaged items, as appropriate.

3) Ascertain that the fuselage is solidly positioned.

4) Carefully raise each half-stabilator and push it onto the torque tube, checking a clearance of

approximately 12mm to 3mm (0.47in to 0.12in) between the root chord (set in the horizontal

attitude) and the fuselage.

5) Install the attaching bolts, washers and nuts through stabilator, tie-clamp and torque tube,

without tightening the nuts (use new provided attaching items).

6) Connect half-stabilators to each other by means of the bolt to be installed coupling link-plates

at the rear spar with the plate for tail surface gust lock. Torque to 0.47÷0.52 Kgm

(40.79÷45.13 lb.in).

7) Check for a full engagement of tie-clamps on the external diameter of the torque tube and then

torque the nuts to 2.565÷2.835 Kgm (222.63÷246.07 lb.in).

8) Check for absence of horizontal and vertical backlash of the stabilator: for this check, shake

lightly each half-stabilator longitudinally, up and down and along its hinge bearings axis.

WARNING

No stabilator backlash is permissible.

9) Connect the trim tab halves to each other by means of bolt, washer and nut, interposing the

spacer. Torque the nuts to 0.47÷0.52 Kgm (40.79÷45.13 lb.in).

10) Connect the 2 (two) trim tab control rods to trim tab brackets by means of bolts, washers and

nuts, interposing, if necessary, washer p/n NAS1149F0332P or NAS1149F0316P as shims

between bracket and control rod head. Torque to 0.5±5% kgm.

11) Check that trim tab control rods are set to proper length ensuring that both ball joint ends have

the same number of engaged threads.



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12) Ascertain that all stabilator surfaces operate freely.

13) Apply reference red marks on all the coupling bolts.

14) Lock temporarily the stabilator surfaces with suitable locking device p/n 8903-401.

15) Proceed with the following Part C.

Figure 2 Stabilator installation



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Part C: WING AND MOVABLE CONTROL SURFACES INSTALLATION

NOTE

The following is applicable to both LH and RH

wing.

NOTE

During re-assembling procedure install the safety

wires as applicable, using stainless steel wires with

0.8mm (0.03in) diameter.

NOTE



1) Refer to Figure 3 for LH/RH wing installation to the fuselage, and to Figure 4 for wing struts

installation.

Figure 3 Wing installation



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Figure 4 Wing struts installation

2) Gently withdraw from the container and from the concerned packing boxes, if not already

done, all the items necessary to perform the wing and movable control surfaces re-installation.

Discard and replace the damaged items, as appropriate.


WARNING

Be careful not to damage the wing and the other

components therein installed during the wing re-

installation.

4) Raise the LH/RH wing to allow its installation on the fuselage.

5) Place the LH/RH wing near the fuselage.

6) Put in place the trestle with height adjustable padded cradles under the LH/ RH wing.

7) Open the most inboard inspection hatches at the bottom of wing leading edge.

8) Unfix the fresh cabin air hoses from the fuselage, by removing the tie wraps.

9) Insert the air flexible hoses in the lightning hole of the leading edge rib (see Figure 5).



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Figure 5 Fresh air hoses from wing air inlet to the cabin

10) Unfix the aileron control cables from the fuselage.

WARNING

Be careful not to damage the control cables

during their re-routing.

11) Connect aileron control cables to guide wires installed in the wing leading edge.

12) Open the most outboard leading edge inspection hatches and pull the guide wires just enough

to make free the wing-to-fuselage installation area.

13) Insert the fuel system lines in the wing leading edge.

14) Proceed to the wing-to-fuselage alignment to permit a correct coupling between them.

15) Verify the presence of any possible item in the concerned wing-to-fuselage area that can

obstruct the wing re-installation.

16) Install the LH/RH wing, and wing struts to the fuselage:

a) Release slowly the LH/RH wing on the 2 (two) padded cradles.

WARNING

Be careful not to damage the wing-fuselage

attachments during the bolts re-installation.

b) Adjust wing cradles as required to slide the wing into position on the fuselage until the

wing-fuselage attachments are aligned to each other, then insert bolts with washer under

head, and spacers.

NOTE

Before re-assembling procedure apply “MIL-PRF-

8116C” (Mastinox D40 or equivalent) anticorrosive

compound to all bolt shanks and to washer/spacer.



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c) Install washers and nuts of the attaching bolts and torque in accordance with

specifications given in Figure 3, and install the cotter pins (use new provided attaching

items).

d) Put in place the strut for installation, until the strut-to-wing attachments are aligned to

each other, then insert bolt and washer under head. Temporarily install washers and nuts

(use new provided attaching items).

e) Insert the strut-to-fuselage fairing on the strut.

f) Adjust the strut until the strut-to-fuselage attachments are aligned to each other, then

insert bolt and washer under head.

g) Install washers and nut of the strut-to-fuselage attaching bolt, and torque in accordance

with specification given in Figure 4, then install the cotter pin (use new provided

attaching items).

h) Torque nut of strut-to-wing attachment in accordance with specification given in Figure

4, then install the cotter pin.

i) Apply reference red marks on all the couplings carried out.

j) Install strut-to-fuselage and strut-to-wing fairings.

17) Install fresh cabin air hoses, as following:

a) Unplug the cabin air hoses inserted in the wing leading edge.

b) Referring to Figure 5, install the air hoses to the leading edge air inlet, by using serflex

p/n NOR7.427-15.

18) Connect all the wing-fuselage electrical wires, as following:

CAUTION

Assure that all the electrical switches are in OFF

position.

a) Get access to the wing-to-fuselage attachment areas.

b) Disengage all the electrical wire connectors previously plugged and remove all the

concerned tie wraps.

c) Carefully connect the electrical wires male connectors to the respective female

connectors located at the LH/RH wing-to-fuselage attachment areas.

d) Restore GND connections to airframe.

e) Secure the concerned wiring harnesses and connectors by installing tie wraps.

19) Connect Pitot line at LH wing, as following:

a) Unfix the Pitot flexible line segment from the fuselage.

b) Unplug the line ends at the fuselage and wing sides.

c) Connect the flexible line to the LH wing line side, by using clamp p/n NOR7.427-24.

20) Install the fuel system hoses, as following:

a) Unfix the fuel system hoses from the fuselage.

b) Unplug all the line ends at the fuselage and wing sides.

c) Connect the fuel system flexible hoses to the wing fuel tanks, by using clamps p/n

NOR7.427-15.

d) Install the fuel tank fairings.

21) Install LH/RH aileron control surfaces, as following:

a) Gently withdraw from the container and from the concerned packing boxes, if not

already done, all the items necessary to perform the aileron control system re-

installation. Discard and replace the damaged items, as appropriate.



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b) Check all the hinge bearings for damage and freedom of rotation. Replace if necessary.

WARNING

Be careful not to damage the ailerons during

their re-installation.

c) Position the aileron on the wing aligning the inboard, centre and outboard aileron hinges

with the hinge brackets on the wing, then install the attaching screws, bonding cable (at

the central hinge), washers and nuts, securing the hinges (use new provided attaching

items). Referring to Figure 6, tighten the nuts to the required torque value.

Figure 6 Aileron installation

d) Connect the aileron control rod to the aileron inboard hinge by using the proper

attaching bolt, washer and nut. Referring to Figure 7, tighten the nut to the required

torque value.

e) Apply reference red marks on all the couplings carried out.

f) If not already done, pull the guide wire from the most outboard inspection hatch in order

to replace the guide wire with the proper aileron control cables in the wing leading edge.

g) Disconnect the guide wire from the aileron bellcrank and control cables.



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h) Assure aileron control cables are in pulleys groove and connect the aileron control

cables to the aileron bellcrank, in accordance with specifications given in Figure 7.

i) Apply reference red marks on all the couplings carried out.

j) Check the aileron for free and full travel.

Figure 7 Aileron control system



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22) Install LH/RH flap control surfaces, as following:

a) Gently withdraw from the container and from the concerned packing boxes, if not

already done, all the items necessary to perform the flap system re-installation. Discard

and replace the damaged items, as appropriate.

b) Check all the hinge bearings for damage and freedom of rotation. Replace if necessary.

WARNING

Be careful not to damage the flaps during their

re-installation.

c) Position the flap on the wing aligning all the flap hinges with the hinge brackets on the

wing, then install the proper attaching screws, washers and nuts, interposing the ground

lead under the head of the inboard hinge bolt. In accordance with Figure 8, tighten the

nuts to the required torque value (use new provided attaching items).

d) With the flap fully extended, connect the flap control rod to the provided hinge on the

flap using the proper bolt, washer and nut. In accordance with Figure 8, tighten the nut

to the required torque value.

e) Apply reference red marks on all the couplings carried out.

Figure 8 Flap installation

23) Using an electric torch and a mirror, perform a final check for security of installation, integrity

and general condition of all the lines, wires, electrical connections, cables and mechanical

installation.

24) Install the LH/RH wing-to-fuselage fairings, in accordance with instructions given in Figure 9.



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Figure 9 Wing-fuselage and fuel tank hose fairings installation

25) Put in place all the concerned inspection hatches on the wing leading edges into its proper

position, then secure it by installing the concerned screws.

26) Seal the wing-to-fuselage fairing, the fuel tank hose fairing and the strut-to-wing fairing,

during installation. Use SIKAFLEX-221 sealing compound, or other equivalent product.

Remove, if necessary, the excess of sealant.



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CAUTION

Follow the Manufacturer’s instructions and safety

precautions during application and usage of the

above sealant component.

--- deleted ---

27) Where necessary, touch up the concerned external surfaces of the wing with finish

polyurethane paint, as per existing livery of the aircraft.

28) Proceed with the following Part D.



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Part D: PROPELLER INSTALLATION

WARNING

Be careful not to damage the propeller and its

components during the re-installation.

NOTE



1) Gently withdraw from the container and from the concerned stand and packing boxes, if not

already done, all the items necessary to perform the propeller re-installation. Discard and

replace the damaged items, as appropriate.


3) Gain access to the engine compartment.

4) Identify the tool installed on the engine starter gear used to secure the forward side of the

aircraft to the container. Remove the tool by unscrewing the mounting bolts until the gap is

covered and then pull forward the tool as far as the gap reappears. Repeat this until the tool

becomes removable.

CAUTION

Do not rotate the engine shaft, the engine is

preserved.

NOTE

Do not use the tool attaching items for the

subsequent propeller installation. Use the provided

propeller attaching items.

Figure 9a Tool removal

5) If necessary, clean the propeller and engine flanges, as appropriate, with a non-corrosive

solvent (Methyl-Ethyl-Ketone, or equivalent).



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NOTE

For information regarding propeller and spinner

installation, refer to Hartzell pertinent technical

documentation.

6) Place the spinner adapter slowly in its proper position on the engine starter gear, and carefully

connect it by installing the attaching bolts, washers and nuts.

CAUTION

Take care to install the spinner adapter bolts with

their heads at the rear of the starter ring gear as per

instructions provided in Hartzell Propeller Owner’s

Manual p/n 115N (latest revision). The bolts

installed incorrectly may damage the engine

components.

7) Tighten the alternator drive belt.

NOTE

Adjust the alternator drive belt tension in accordance

with the pertinent Lycoming technical documentation.

8) Lubricate and insert the new provided shaft O-ring into the groove inside the propeller

mounting flange.

CAUTION

Do not put any further O-ring on the crankshaft

flange.

NOTE

For information on recommended propeller

lubricating oil, refer to Hartzell pertinent technical

documentation.

9) Put in place the propeller and secure it to the engine shaft by installing the concerned

mounting bolts. Torque the bolts to 8.30÷9.68 Kgm (720÷840 lb.in).

NOTE

It is useful to place a drip pan under the propeller to

catch eventual oil spillage.

10) Install the safety wires, using stainless steel wires with 0.8 mm (0.03 in) diameter, in the

concerned propeller mounting bolts.

11) Put in place and install the spinner by using its attaching screws.

12) Install temporarily on the propeller a “PRESERVED ENGINE – DO NOT ROTATE THE

PROPELLER” placard, to be removed before the engine de-preservation.

13) Proceed with the following Part E.



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Part E: ON-GROUND TESTS

NOTE

If any check is not passed successfully, send a

technical request to Vulcanair Customer Support by

means of the online form at the following web

address: http://support.vulcanair.com/

1) Lower the underwing trestles and the trestle under the aft mooring hook slowly.

2) Place the aircraft in a suitable working area for the operations to be carried out.

3) Maintain disconnected the battery cables and the external power unit.

4) Check the tire inflation pressure and condition in accordance with AMM10.702-5, Section 3,

para. 1.4.

5) Check for the correct sealing of all the concerned areas.

WARNING

No seepages of water are permitted. If seepage of

water is detected, restore sealing by using

SIKAFLEX-221 sealing compound, or other

equivalent product, along all the concerned areas.

6) Perform the aircraft triangulation procedure in accordance with AMM10.702-5, Section 2,

para. 5.

7) Unlock the ailerons and flaps surfaces by removing the concerned locking devices.

8) Ascertain that the ailerons and the flaps surfaces operate correctly (full and free travel as per

Figure 10).

9) Check for ailerons controls adjustment (control cables tension).

10) Rig the aileron control system in accordance with AMM10.702-5, Section 7, para. 4.3.

11) Carry out a flap functional test in accordance with AMM10.702-5, Section 7, para. 8.1. If

necessary, calibrate flap position indication system in accordance with AMM10.702-5,

Section 7, para. 8.3.

12) Unlock the stabilator surfaces and stabilator trim tabs by removing the concerned locking

devices.

13) Check the stabilator control surfaces travels. If necessary, rig the stabilator control system in

accordance with AMM10.702-5, Section 7, para. 5.1.

14) Check the stabilator trim tab free play in accordance with AMM10.702-5, Section 6, para.

4.2.9.

15) Check the stabilator trim tab control surfaces travels and cable tensions (refer to Figure 10 for

proper values). If necessary, rig the stabilator trim control system in accordance with

AMM10.702-5, Section 7, para. 6.3.

16) Unlock the rudder surface by removing the concerned locking device.

17) Ascertain that the rudder surface operates correctly (full and free travel), then check for rudder

control cables tension (refer to Figure 10 for proper values). If necessary, rig the rudder

control system in accordance with AMM10.702-5, Section 7, para. 7.3.




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Figure 10 Control surfaces travels and cable tensions

18) Perform the rigging procedure of throttle, propeller and mixture controls in accordance with


19) Re-install the wheel fairings to the MLG, if included in the aircraft configuration. Install

fairings to their support, by installing the concerned screws.

20) Re-install the wheel fairing to the NLG, if included in the aircraft configuration. Install the

front half of the fairing to the NLG wheel assembly and NLG wheel fork, together with the

related components, by installing the concerned screws. Carefully joint the rear half of the

fairing to the front one by installing the concerned screws.

21) Place the aircraft in a designated area, for the engine de-preservation operations.

22) Remove the placard installed on the propeller at the end of the propeller re-installation.



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23) Perform the engine de-preservation, in accordance with the following procedure:

a) Remove the dehydrator spark plugs and the desiccant bags from the engine.

b) Rotate the propeller by hand (propeller shaft clockwise rotation), with magnetos OFF,

for about 3 or 4 turns of the crankshaft to discharge the preservative oil from the engine

cylinders.

c) Drain the remaining preservative oil in the oil sump through the concerned drain plug.

NOTE

Before to proceed with this operation, the engine

must be kept to an environmental temperature of at

least 21°C (70°F) for a period of 24 hours. If this

condition is not possible, warm up the engine by

means of the use of appropriate lamps before

charging the lubricating oil into it.

d) When the oil sump is completely drained, reinstall its drain plug and lock it with a

locking wire.

e) Refill the oil sump with approved lubricating oil, more than one time.

WARNING

Engine operations with no oil (or very low oil

level) will cause engine malfunction or damage.

For information on recommended engine

lubricating oil, refer to Lycoming Service

Instruction No.1014 (latest revision).

NOTE

Follow carefully the Manufacturer’s instructions

before using the lubricating oil.

f) Remove, where installed, the desiccant bags and the impermeable paper.

g) Install the spark plugs.

--- deleted ---

24) Place the aircraft in a designated fuelling area (an external area, far from the hangar, is

recommended for safety reasons).

25) Clean the aircraft fuel tanks to eliminate any possible residual material in accordance with


26) Prepare to fill the fuel tanks in accordance with the safety precautions specified at the work

procedure beginning of this SB, and in the AMM10.702-5, Section 3, para. 1.1.

27) Perform the fuel quantity calibration procedure on EDM-930 unit, in accordance with


28) Check all the fuel system for leaks. Eliminate any leakage if found.

29) Place the aircraft in a suitable engine test area, for the operations to be carried out.

30) Position the aircraft upwind and place chocks under the main landing gear wheels.

31) Once blocked the wheels, set the parking brake by depressing rudder pedals and pulling the

knob located on the pedestal.



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32) Assure that the engine and the propeller are correctly installed, and all engine commands and

cabin systems are properly connected.

33) Connect the external power unit to the aircraft and then switch OFF all the other utilities.

34) Position a suitable firefighting equipment near the aircraft.

35) Assure that there is enough fuel in the tanks to guarantee at least 30 (thirty) minutes of

continuous engine operation.

WARNING

To avoid any possible engine bearings failure

resulting from an inappropriate lubrication

during the initial engine start, the aircraft engine

must be pre-oiled before the first engine start.

36) Prepare the first engine start in accordance with the following procedure:

NOTE

The following procedure must be performed with

appropriate oil level in the concerned oil sump.

a) Remove the lower spark plugs from the engine cylinders.

b) Place the mixture control lever in the “IDLE CUT-OFF” position.

c) Turn the engine with the starter (use the external power source, if available) until an oil

pressure of 20 psi is reached.

NOTE

If the oil pressure is not reached after the engine

cranking for 1 minute, allow the starter to cool itself

before proceeding.

d) Energize the starter two or more times for 10-15 seconds.

WARNING

Do not energize the starter for periods greater

than 1 (one) minute. Leave the starter to cool

itself after each energizing.

NOTE

Peaks or rapid loss of oil pressure are due to air

presence inside the engine oil lines. In this case

verify the correct filling of the oil sump and the oil

lines, then repeat the pre-oil operation until the

correct oil pressure is reached.

e) Turn the engine with the starter for about 45 seconds to verify that the oil pressure value

remains constantly correct.

f) Reinstall the lower spark plugs.



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WARNING

After the pre-oil operation, take care to perform

the normal engine starting procedure within the

subsequent 3 (three) hours.

WARNING

Before to perform the normal engine starting

procedure, take care to run the engine at

approximately 1000 RPM for about 3 (three)

minutes.

NOTE

Refer also to Lycoming Service Instruction No.1241

(latest revision).

g) Unscrew completely the screw on the propeller governor (max RPM screw) to assure the

governor neutrality during next operations.

37) Start the engine in accordance with the procedure reported in AFM10.701-7, Section 4, para.

4.6.2.

38) Perform the engine shut-down in accordance with the following procedure:

a) Place the propeller lever full forward.

b) Maintain the engine to the minimum RPM value until to the engine parameters

stabilization.

c) Place the mixture control lever in the “IDLE CUT-OFF” position.

d) After engine stop, turn OFF all the switches.

e) Inspect for any oil and/or fuel leak in engine compartment and general security.

Eliminate any leakage and trace, if found.

39) Perform the propeller adjustment in accordance with the following procedure:

WARNING

Be sure that no person or object may compromise

the safety of operations.

CAUTION

Do not operate the engine to the max RPM if the

brake linings are not conditioned.

CAUTION

Perform the propeller pitch regulation as per

instructions provided in Hartzell Propeller Owner’s

Manual p/n 115N (latest revision).

NOTE

RPM adjustments must be made with reference to a

calibrated tachometer. Read the RPM value on the

concerned aircraft instrument and compare it with

that reported on the external tachometer.



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a) Turn ON the concerned switches.

b) Push-in all the circuit breakers.

c) Restart the engine, in accordance with the procedure reported in AFM10.701-7, Section

4, para. 4.6.2.

d) Place the throttle lever at ¼ of its travel.

e) Place the propeller lever full forward.

f) Place the mixture lever in the “IDLE CUT-OFF” position.

g) Stabilize the Cylinder Head Temperature (CHT) and the Oil Temperature (OT) values

inside the concerned green arc.

h) Advance the throttle control lever up to the engine maximum power, and check if the

RPM values reported on the external tachometer match the indications displayed by

EDM-930 unit.

i) If successful, shut-down the engine in accordance with the procedure reported in

AFM10.701-7, Section 4, para. 4.15.

j) If the values are different, operate on the propeller minimum pitch regulator, as per

instructions provided in Hartzell Propeller Owner’s Manual p/n 115N (latest revision),

and re-start the engine. Repeat the steps from a) to j) of this point, until the correct

regulation is obtained.

k) Screw partially, at half travel, the screw on propeller governor (MAX RPM screw).

l) Re-start the engine placing the throttle lever full forward and check that the RPM value

obtained is stabilized between 2600 and 2675 RPM. If not, screw/unscrew, as

appropriate, the MAX RPM screw on the propeller governor and repeat this item m).

NOTE

It is usually only necessary to adjust the high RPM

(low pitch) setting of the governor control system, as

the action automatically takes care of the positive low

RPM (high pitch) setting.

40) Place the aircraft in a designated area, for the electrical/avionic operations to be carried out.

WARNING

Assure that STARTER RELAY breaker is

always pulled out during all the electrical/avionic

activities, except when clearly prescribed its

pulling-in by the following instructions.

NOTE

The test equipment listed below are needed for the

following avionic operations. These test sets must be

equipped with instruments controlled with valid

calibration certificate, as applicable.

• Digital multimeter

• 28Vdc power supply

• Chronometer

• Static-Pitot Test Set

• IFR6000 Transponder Test Set, or equivalent



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• Ramp and Bench Test Set IFR2946A with ADS-B

OUT capability, or equivalent

• Sample Magnetic Compass

• VHF portable radio

41) Perform the functional and absorption verification of the electrical system with Garmin G500,

in the following condition:

a) Check that all the breakers are pulled-out and set all the switches in OFF position.

b) Connect an external 28Vdc±0.5Vdc power unit to the aircraft.

c) Set the MASTER BATTERY switch to ON.

d) Wait for few minutes and proceed with the following step.

42) Push-in all the circuit breakers of Main Bus Bar and verify that each equipment connected to

the Main Bus Bar is supplied, by setting sequentially ON the related switch, as applicable.

Perform this step according to the instructions below, for each equipment on Main Bus Bar:

a) Avionics verification:

i) Check PFD and MFD for properly power ON in normal mode.

ii) Check GTN 650 for properly power up.

iii) Verify if PFD is showing airspeed and altimeter tapes.

iv) Verify if PFD is showing attitude window.

v) Verify the audio panel for proper power up by observing if key-lights are ON.

vi) Verify JPI EDM-930 for proper power up.

vii) Verify ADI standby MD302 for proper power up.

b) Instrument lighting verification:

i) Rotate clockwise the instrument lights dimmer knob on breaker panel, until

instrument lights turn ON.

ii) Check if breaker panel and flap indicator backlighting power increases when

rotating the knob clockwise.

iii) Rotate the knob counterclockwise until the instrument lights turn OFF.

c) Flood (storm) light dimmer verification (if installed):

i) Rotate clockwise the flood (storm) light dimmer knob on breaker panel, until light

turns ON.

ii) Check if flood (storm) light power increases when rotating clockwise the knob.

iii) Rotate the knob counterclockwise until the flood (storm) light turns OFF.

d) Taxi and landing lights verification:

i) Set the TAXI LIGHT and LDG LIGHT switches to ON and check if the green led

lights on the switches turn ON.

ii) Check if the taxi and landing lights are powered ON.

iii) Set the TAXI LIGHT and LDG LIGHT switches to OFF and check if the green led

lights on the switches turn OFF.

e) Navigation lights verification:

i) Set the NAV LIGHTS switch to ON and check if the green led light on the switch

turns ON.

ii) Check if the navigation lights on the wing and tail are powered ON.

iii) Set the NAV LIGHTS switch to OFF and check if the green led light on the switch

turns OFF.



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f) Anti-collision strobe lights verification:

i) Set the STROBE LIGHTS switch to ON and check if the green led light on the

switch turns ON.

ii) Check if the anti-collision strobe lights on the wing and tail are powered ON.

iii) Set the STROBE LIGHTS switch to OFF and check if the green led light on the

switch turns OFF.

g) Stall warning verification:

i) Get access to the stall detector on the leading edge of LH wing, lift the stall

detector lever and verify if the warning horn is activated. Verify also if the

warning horn is audible from headphone.

ii) Set free the stall detector lever and verify if the warning horn is disabled from the

cabin and headphone.

h) Pitot heater verification:

i) Remove Pitot tube protective device (if installed).

ii) Set the PITOT HEAT switch to ON and check if the green led light on the switch

turns ON.

iii) Check for absence of indication status “PITOT HEAT FAIL” on the annunciator

panel.

iv) Verify the proper Pitot tube heater operation. A heat perception should be

detected.

CAUTION

It is sufficient a time of about 3 seconds to test on-

ground the Pitot tube heater after its activation. For

longer times, it is necessary to ventilate the Pitot

tube.

v) Set the PITOT HEAT switch to OFF and check if the green led light on the switch

turns OFF and the Pitot tube cool down.

i) Fuel pump verification:

i) Set the FUEL PUMP switch to ON.

ii) Check if fuel pump is working and if the indication status “FUEL PUMP ON” on

the annunciator panel is present.

iii) Set the FUEL PUMP switch to OFF and check if the fuel pump stops working.

j) Map light verification:

i) Switch ON the map light and check for proper operation.

ii) Check the map light dimmer for proper operation.

iii) Switch OFF the map light.

43) Push-in all the circuit breakers of Avionic Bus Bar, set the AVIONICS switch to ON, and

verify that each equipment connected to the Avionic Bus Bar is supplied, by setting

sequentially ON the related switch, as applicable. Perform this step according to the

instructions below, for each equipment on Avionic Bus Bar:

a) ADF KR87 verification (if installed):

i) Switch ON the ADF and check that ADF module is power supplied.

ii) Switch OFF the ADF.



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b) DME KN62A verification (if installed):

i) Switch ON the DME and check that DME module is power supplied.

ii) Switch OFF the DME.

c) GNC 255B NAV/COM unit verification:

i) Check that GNC 255B module is power supplied.

44) Push-in all the circuit breakers of Secondary Bus Bar and verify that each equipment

connected to the Secondary Bus Bar is supplied, by setting sequentially ON the related switch,

as applicable. Perform this step according to the instructions below, for each equipment on

Secondary Bus Bar:

a) Stall heater verification:

i) Set the STALL HEAT switch to ON and check if the green led light on the switch

turns ON.

ii) Check for absence of indication status “STALL HEAT FAIL” on the annunciator

panel.

iii) Verify the proper stall heater operation. A heat perception should be detected.

CAUTION

It is sufficient a time of about 3 seconds to test on-

ground the stall heater after its activation. For longer

times, it is necessary to ventilate the stall detector.

iv) Set the STALL HEAT switch to OFF and check if the green led light on the switch

turns OFF and the stall detector cool down.

b) AUX power and USB sockets verification:

i) Verify if both AUX power sockets are power supplied, by using a digital

multimeter.

ii) Verify USB sockets for proper operation by connecting a mobile through its

charge cable and check if the mobile goes to charging mode.

45) Perform an avionic test of Garmin G500 in the following condition:

a) Place the aircraft in suitable working area at the external of the hangar so to receive GPS

signal.

b) Check that all the breakers are pulled-out and set all the switches in OFF position.

c) Connect an external 28Vdc±0.5Vdc power unit to the aircraft.

d) Push-in all the circuit breakers unless STARTER RELAY breaker.

e) Set the MASTER BATTERY and AVIONICS switches to ON.

f) Wait for few seconds for system powering up.

g) Check if PFD is showing altitude and airspeed tapes, HIS, and attitude indicator.



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Figure 11 PFD status (only for reference)

h) Check if MFD is showing the home page with database information.

Figure 12 MFD status (only for reference)

i) Press ENT on MFD and check if the MAP page is shown:

Figure 13 MFD MAP page (only for reference)



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j) Check that no MANIFEST or CONFIGURATION ERROR appears in the PFD alert

box.

k) Check that no red X appears in the PFD, alerting for an avionic equipment anomaly.

NOTE

Next checks must be performed by 2 (two)

operators: the first one must be onboard the aircraft

to check the equipment, while the second one must

be outboard with a VHF portable radio.

46) Check VHF-COM for proper transmission, first for COM1, then for COM2, as following:

NOTE

For selection of COM, transmission mode, receiving

mode, frequencies and transmission level, refer to:

1) G500 Pilot’s Guide 190-01102-02

2) GTN 625/635/650 Pilot’s Guide 190-01004-03

3) GNC 255A/255B Pilot’s Guide 190-01182-01

4) GMA 350 Pilot’s Guide 190-01134-12

NOTE

Identify a test frequency to be used. This frequency

will be generally named “freq_test_com” in the

following.

a) Change the frequency on GTN650 to freq_test_com.

b) Press softkeys COM1 and MIC1 on GMA350 Audio Panel.

c) Select key PILOT on GMA350 Audio Panel.

d) Check the radio transmission with the outboard operator.

e) Change the frequency on GNC255 to freq_test_com.

f) Press softkeys COM2 and MIC2 on GMA350 Audio Panel.

g) Check the radio transmission with the outboard operator.

47) Check the interphone system for proper communication between pilot, copilot and passengers,

as following:

NOTE

GMA350 Audio Panel runs an auto-test at power-

up. During auto-test all keys are backlighted. Once

auto-test is finished, the last settings will be setup.

a) Connect the headphones to each Intercom System (ICS) position.

b) Ensure SQUELCH is disabled.

c) Operate the keys PILOT, COPLT and PASS to select ICS configuration, and

sequentially check for proper operation of interphone communication. With “ALL

INTERCOM MODE” check that pilot, co-pilot and passengers are able to hear each

other and to hear aircraft system audio.



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d) Select audio source sequentially for NAV1, NAV2, COM1 and COM2, and check audio

functionality.

48) Verify VOR functionality, as following:

a) Place the simulator (IFR2946A) 3m far from the antenna of the under-test equipment.

b) Set an undisturbed VOR frequency on simulator IFR2946A (this frequency will be

generally named “freq_test_VOR” in the following).

c) Set the radial to match the aircraft heading.

d) Set simulator signal less than -50dBm and check for no-signal.

e) Set simulator signal above -50dBm and check for radial matching aircraft heading.

f) Set on GTN650 the same VOR frequency set on the simulator.

g) Select VOR1 on PFD, by pushing CDI softkey to select VOR source and 1-2 softkey to

select VOR1.

h) Check for presence of radio signal from speaker and headphone.

i) Check if CDI (Course Deviation Indicator) and TO heading are shown on HSI.

j) Move CRS 10° rightward of the lubber line and check that CDI deviates to full-scale.

k) Move CRS 10° leftward of the lubber line and check that CDI deviates to full-scale at

the opposite as before.

l) Push FMS knob on PFD and check that CRS moves to the same heading of signal

generator and that CDI moves to midpoint.

m) Select FROM heading on the signal generator and check if the indication on PFD HIS

shows the same FROM heading.

n) Select TO heading on the signal generator.

o) Select “freq_test_VOR” on GNC255B.

p) Repeat the above steps from g) to m).

49) Verify LOCALIZER functionality, as following:


b) Set an undisturbed LOC frequency on simulator IFR2946A.

c) Set NAV1 to an undisturbed ILS frequency on GTN650.

d) Set simulator signal less than -50dBm and check for no-signal.

e) Set simulator signal at -45dBm and check for signal return.

f) With simulator signal at -45dBm, ensure aircraft heading is 90° within the ILS route

under simulation.

g) Make the CRS aligned with lubber line.

h) Select LOC1 on PFD CDI of Garmin G500.

i) Rotating CRS knob, check for proper operation of the indicator.

j) Apply a DDM (Difference in Depth of Modulation) of 0.0775 and check that for the

frequency range [90→150] Hz, the indicator deviates of 1 dot rightward.

k) Apply a DDM (Difference in Depth of Modulation) of 0.155 and check that for the

frequency range [90→150] Hz, the indicator deviates of 2 dots rightward.

l) Apply a DDM (Difference in Depth of Modulation) of 0.0775 and check that for the

frequency range [150→90] Hz, the indicator deviates of 1 dot leftward.

m) Apply a DDM (Difference in Depth of Modulation) of 0.155 and check that for the

frequency range [150→90] Hz, the indicator deviates of 2 dots leftward.

n) Change NAV1 frequency to (f - 50kHz) and check that indicator disappears on HSI.

Then check that it re-appears changing the frequency to (f).



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o) Change NAV1 frequency to (f + 50kHz) and check that indicator disappears on HSI.

Then check that it re-appears changing the frequency to (f).

p) Check for “no-signal” when excluding the 90Hz frequency-modulated on the signal

generator.

q) Enable the 90Hz frequency-modulated on the signal generator and check for signal

return.

r) Check for “no-signal” when excluding the 150Hz frequency-modulated on the signal

generator.

s) Enable the 150Hz frequency-modulated on the signal generator and check for signal

return.

t) Repeat all the above steps for NAV2 by operating on GNC255B.

50) Verify GLIDE PATH functionality, as following:


b) Set for NAV1 an undisturbed ILS frequency on GTN650.

c) Ensure that aircraft heading is 90° within the ILS route under simulation.

d) Set ON the glideslope emission on simulator; shown frequency changes to 334.7 MHz.

e) Set simulator signal less than -45dBm and check for no-signal.

f) Set simulator signal at -40dBm and check for signal return.

g) Set CDI to LOC1 on PFD, and check for the presence of glideslope indication on the left

side of altimeter.

h) Apply a DDM (Difference in Depth of Modulation) of 0.091 and check that for the

frequency range [90→150] Hz, the indicator deviates of 1 dot upward.

i) Apply a DDM (Difference in Depth of Modulation) of 0.175 and check that for the

frequency range [90→150] Hz, the indicator deviates of 2 dots upward.

j) Apply a DDM (Difference in Depth of Modulation) of 0.091 and check that for the

frequency range [150→90] Hz, the indicator deviates of 1 dot downward.

k) Apply a DDM (Difference in Depth of Modulation) of 0.175 and check that for the

frequency range [150→90] Hz, the indicator deviates of 2 dots downward.

l) Change NAV1 frequency to (f - 50kHz) and check that the glideslope indicator

disappears on altimeter. Then check that it re-appears changing the frequency to (f).

m) Change NAV1 frequency to (f + 50kHz) and check that the glideslope indicator

disappears on altimeter. Then check that it re-appears changing the frequency to (f).

n) Check for no-signal when excluding the 90Hz frequency-modulated on the signal

generator (NO GS message will appear in lieu of GS indicator).

o) Enable the 90Hz frequency-modulated on the signal generator and check for signal

return (GS indicator appears again).

p) Check for no-signal when excluding the 150Hz frequency-modulated on the signal

generator (NO GS message will appear in lieu of GS indicator).

q) Enable the 150Hz frequency-modulated on the signal generator and check for signal

return.

r) Repeat all the above steps for NAV2 by operating on GNC255B.

51) Verify MARKER BEACON functionality, as following (use the simulator equipment

IFR2946A, or equivalent):

a) Connect RF output from the generator to antenna input of GMA350 Audio Panel.

b) Set Marker option on the signal generator. Carrier frequency should be 75Mhz.



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c) Set simulator on Outer Beacon option and set a RF output signal of -47dBm

(AM, 95% deep).

d) Check for 400hz signal on headphone, and that “O” blue light on GMA350 Audio Panel

is blinking.

e) Set simulator on Middle Beacon option and set a RF output signal of -47dBm

(AM, 95% deep).

f) Check for 1.3Khz signal on headphone, and that “M” amber light on GMA350 Audio

Panel is blinking.

g) Set simulator on Inner Beacon option and set a RF output signal of -47dBm

(AM, 95% deep).

h) Check for 3Khz signal on headphone, and that “I” white light on GMA350 Audio Panel

is blinking.

i) Repeat the above steps changing RF output signal to High Sensitivity (-61dBm).

52) Verify GPS functionality and signal acquisition, as following:

NOTE

Place the aircraft where the GPS antennas have a

clear view of the sky. Check for possible external

interference to the GPS receivers. Ensure that a cell

phone or a device using cell phone technology is not

turned on (even in a monitoring mode) in the cabin.

NOTE

Normally the GTN650 acquires GPS signal within

20 minutes since power-on.

a) Starting from the GTN650 home page, press in sequence SYSTEM and GPS STATUS.

GTN650 will display as per in Figure 14.

Figure 14 GTN650 display status



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b) Once GTN650 display status is as reported in Figure 14, check that the “GPS Receiver

Status” is “GPS Solutions 3D DIFF NAV” and SBAS is active.

c) Press SBAS softkey to check WAAS enabled (in Europe, EGNOS). When a corrective

WAAS signal is available, a “D” letter should appear at the respective satellite bar of the

Figure 14.

53) Verify ADF KR87 functionality, as following (if installed):

a) Place the aircraft in a suitable engine test area, for the operations to be carried out.

b) Align the aircraft with magnetic NORTH point.

c) Set at least two known frequencies from NDB stations (these frequencies will be

generally named “f_NDB1” and “f_NDB2” in the following).

d) Check that heading deviates within ±3° as per Table 1.

Stations frequencies (KHz) Radial (°)

f_NDB1 rad1 3°

f_NDB2 rad1 3°

Table 1 ADF frequency

e) Press “PFD” softkey on PFD.

f) Select ADF both for BRG1 and for BRG2 by crossing the menu as in Figure 15.

Figure 15 PFD menu

g) Check for ADF bearing pointers presence on HSI.

h) Check for “ADF” message in the bearing information windows on the bottom sides of

HSI on GDU620 Display Unit.

54) Verify DME KN62A functionality, as following (if installed) - use the simulator equipment

IFR2946A, or equivalent:

a) Activate DME.

b) Set DME frequency to 108.00MHz (both simulator and aircraft sides).

c) Set simulator to DME mode; range/velocity to RANGE; x/y switch to X; squitter switch

to ON; insert an IN or OUT distance by using SLOW SWITCH.

d) Set KN62A unit to Freq Mod as shown in the Figure 16.



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e) Check if NM field of DME panel is showing the same distance (tolerance ±1nm is

allowed).

Figure 16 DME panel

55) Verify TRANSPONDER functionality, as following (use the simulator IFR6000 Transponder

Test Set, or equivalent):

a) Press SETUP key on simulator IFR6000 until SETUP-XPDR page is shown:

Figure 17 IFR6000 SETUP-XPDR page (only for reference)

b) Move the cursor by using keys PREV PARAM and NEXT PARAM and change the

IFR6000 settings as follows:

ANTENNA BOTTOM

RF PORT ANTENNA

ANT RANGE Insert the existing distance between the

transponder antenna and IFR6000 antenna.

ANT HEIGHT 1ft

ANT CABLE LENGHT 6ft

ANT CABLE LOSS 1.8 dB

COUPLER LOSS 0.8 dB

CHECK CAP Yes

DIV TEST OFF

PWR LIM FAR 43

UUT ADDRESS Manual

MANUAL ADDRESS Insert the hexadecimal code of the Transponder

ANT GAIN (dBi) 1.09 GHz + 1.7 dBi

Table 2 IFR6000 settings for transponder check

http://www.wordreference.com/enit/hexadecimal



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NOTE

Place the aircraft where the GPS antennas have a

clear view of the sky.

c) Select XPDR window on GTN650.

d) Touch the MODE field and select STBY, then confirm touching ENTER.

e) Stabilize the frequency on the simulator.

f) Touch VFR field and insert the code of the Transponder by using the keyboard

appearing on the screen.

g) Touch the IDENT field on GTN650 and verify that IDENT field is showing the inserted

code.

h) Connect the Static-Pitot Test Set to the aircraft.

i) Set an altitude of 1000ft and an airspeed of 50kts.

j) Touch the MODE field on GTN650 and select ALT, then confirm touching ENTER.

k) Set the IFR6000 in GENERIC MODE S, select the test UF4 and check the IFR6000 is

showing the same altitude of Static-Pitot Test Set.

l) Touch BACK on GTN650 until the home page is shown.

m) From GTN650 home page, touch XPDR to enter in the Transponder page.

n) Touch the MENU key in the left side of the screen.

o) Verify that the screen is as in Figure 18.

Figure 18 Transponder menu (only for reference)

p) Touch the field Flight ID to enter the flight ID.

q) Touch the ENABLE ES field to enable the ADS-B OUT.

r) Press SETUP key on simulator IFR6000 until SETUP-ADSB page is shown:

Figure 19 IFR6000 SETUP-ADSB page (only for reference)



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s) Move the cursor by using keys PREV PARAM and NEXT PARAM and change the

IFR6000 settings as follows:

POS DECODE GLOBAL

LAT Current latitude of under test equipment

LONG Current longitude of under test equipment

ADS-B GEN DF17

ADS-B MON DF17

GICB DF20

Table 3 IFR6000 settings for ADS-B

t) Set IFR6000 to ADSB monitor in the ADS-B/GICB MAIN: XPDR ADS-B

Transmission Enabled.

u) Once enabled the ADS-B on the simulator IFR6000, press the softkey ADSB MON to

enable the test set to receive Down Link DF17 transmitted from aircraft transponder, and

containing BDS registers. The following screen should be shown:

Figure 20 IFR6000 ADS-B MON LIST Screen (only for reference)

v) Move the cursor to BDS register 0.8 IDENT & CAT and press the softkey RUN TEST

and BDS DATA. The following screen should be shown:

Figure 21 IFR6000 ADS-B MON BDS 0.8 Test (only for reference)



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w) Check for test set showing:

FLIGHT ID The same entered at the step p).

EMIT CAT SET A

EMIT CAT LIGHT

Table 4 IFR6000 ADS-B MON BDS 0.8 Test parameters

x) Press the softkey RETURN to go back to ADS-B MON DF17 setup page.

y) Move the cursor to BDS register 0.6 SURFACE POS. The following screen should be

shown:

Figure 22 IFR6000 ADS-B MON BDS 0.6 Test (only for reference)

z) Press the softkey RUN TEST and wait for test results reporting:

AA field ICAO address of transponder under test

LAT Latitude position of the aircraft

LONG Longitudinal position of the aircraft

MOVMENT STOPPED

HDG Aircraft heading as reported in the Garmin G500 PFD

Table 5 IFR6000 ADS-B MON BDS 0.6 Test results

56) Verify Air Data Computer (ADC) functionality, as following (use an approved Pitot-Static

Test Set and relative Operating Manual):

CAUTION

To avoid any damages to the instruments, and to

assure a correct system operativity, obey at the

following precautions:

• Never apply positive pressure to static lines when

instruments are connected. When applying or

releasing vacuum pressure be sure not to exceed

the maximum indicated rate of climb or descent.

• Dry compressed air or nitrogen may be blown

through the lines of the system, from the

instrument end towards the Pitot and static ports.



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• After doing the test, you must always return the

system to its operating conditions.

CAUTION

Should the test reveal the presence of a leak, check

all the line connections, and fix any leakage.

a) Using the Pitot-Static Test Set, release the vacuum pressure to 1000ft and check that the

instrument reading is 1000±20ft. Close the vacuum source and verify, after waiting for 1

minute, that the instrument reading is not decreased more than 100ft.

NOTE

If test is not successful, the system could be affected

by leakages, then carry out the following procedure:

1- Disconnect instrument static lines.

2- Plug the lines, and coat them with a mild soap

solution. Use the Test Set pressure source to

apply low pressure to the port.

3- Observe the coated lines to locate the leak.

4- Tighten any loose and/or replace any faulty

connectors and damaged hoses in order to fix the

leakage.

5- Remove line plug and test set, re-connect lines

and instruments.

b) Carry out an Airspeed Test, verifying the PFD and ADI stdby readings as per Table 6.

Airspeed

TEST BENCH

(knots)

Allowed tolerances

PFD

(±knots)

Allowed tolerances

ADI stdby

(±knots)

50 5.0 5.0

80 3.5 3.5

100 2.0 2.0

Table 6 Airspeed Test

c) Carry out an Altimeter & Climb Test, verifying the PFD and ADI stdby readings as per

Table 7.

Altitude

TEST BENCH

(feet)

Allowed tolerances

PFD

(±feet)

Allowed tolerances

ADI stdby

(±feet)

0 20 20

1000 20 20

5000 40 40

Table 7 Altimeter & Climb Test

d) During the climb, verify the rate of climb as per Table 8 hereunder.



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Altitude range

(ft)

UP RATE (UP)

DOWN RATE (DOWN)

(ft/min)

Allowed

Tolerances PFD

(ft/min)

2000 2500 500 UP

500 DOWN 35

35

2000 3000 1000 UP

1000 DOWN 75

75

2000 3500 1500 UP

1500 DOWN 150

150

Table 8 Rate of Climb Test

e) Verify that OAT is properly reported on the lower left corner of PFD.

57) Perform calibration and alignment of inertial platform AHRS GRS77/GMU44 through the

following 4 (four) operating steps:

WARNING

The following procedure steps can be performed

only by a Garmin Dealer Resource Center for

Garmin Authorized Service Centers, since it is

required the usage of the Unlock Loader Card

Garmin p/n 010-00769-30 inserted in the front

lower SD card slot.

a) GRS77 Pitch & Roll offset calibration:

i) Place the aircraft in a suitable working area for the kind of operation to carry out.

ii) Level the aircraft in accordance with AMM10.702-5, Section 2, para. 3.

iii) Restart Garmin GDU620 Display Unit in configuration mode.

iv) Select on MFD the GRS/GMU Calibration page, shown in Figure 23.

Figure 23 GRS/GMU Calibration page - Pitch/Roll offset

v) Press the little knob to access to the page.



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vi) Move the cursor to “Select Procedure”, select PITCH/ROLL OFFSET and confirm

by pressing ENT.

vii) MFD will display a checklist with all the actions to be considered before the

calibration procedure. When each action has been completed, press ENT to

continue with the following one.

viii) When CALIBRATE is blinking, press ENT to initialize the calibration procedure.

ix) Wait for few seconds for a check list appearing on lower area of MFD.

x) Press ENT when each action is confirmed.

xi) When CONFIRM AIRCRAFT IS LEVEL is blinking, press ENT to continue.

xii) Offset compensation results will appear on MFD. If it is successful, the AHRS will

save offset values and it will confirm the successful conclusion of the calibration

procedure.

xiii) Press ENT on MFD to terminate the procedure.

xiv) Restart Garmin GDU620 Display Unit in normal mode.

b) Magnetic calibration of GRS77/GMU44:

i) Place the aircraft in an engine test area.

NOTE

Place the aircraft as far as possible from metallic

masses, manholes, storm drains, ferrous railings,

auxiliary power unit, and whatever ferrous material

can alter the compass indication.

ii) If not already done, disconnect external power supply.

iii) Push-in the STARTER RELAY breaker.

iv) Set ON the MASTER BATTERY switch and start the engine in accordance with

the procedure reported in AFM10.701-7, Section 4, para. 4.6.1.

v) Align the aircraft with magnetic north pole (deviation ±5° is allowed), then check

the nose orientation by using a reference sample magnetic compass (if necessary,

carry out the alignment and compensation of magnetic compass in accordance

with AMM10.702-5, Section 13, para. 2.1.2).

vi) Restart Garmin GDU620 Display Unit in configuration mode.

vii) Select on MFD the GRS/GMU Calibration page, shown in Figure 24.



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Figure 24 GRS/GMU Calibration page - Magnetometer

viii) Move the cursor to “Select Procedure” field and select MAGNETOMETER. Press

ENT to confirm.

ix) Move the cursor to “Before Calibration” field.

x) MFD will display a checklist with all the actions to be considered before the



xi) When CALIBRATE is blinking, press ENT to initialize the calibration procedure.

xii) Follow the instructions on MFD which will warn when moving/stopping the

aircraft. At each instruction on MFD, move the aircraft clockwise. MFD will warn

when stopping.

NOTE

Since difficult may arise from slowly moving the

aircraft, the system may activate the HOLD

POSITION command before properly terminating

the aircraft moving. To avoid this, use an external

reference (i.e. a sample compass) to rotate of 30°

(±5°) the aircraft within time limits warned by MFD.

xiii) Repeat the aircraft moving/stopping procedure until the MFD will advise that the

calibration is successful.

xiv) When MFD will display the successful conclusion of the calibration operation,

AHRS will enter in normal mode. Press ENT to end this calibration procedure.

xv) Restart Garmin GDU620 Display Unit in normal mode.

c) Engine run-up:

i) Restart Garmin GDU620 Display Unit in configuration mode.

ii) Select the GRS/GMU Calibration page.

iii) Move the cursor to “Select Procedure” and select ENGINE RUN-UP TEST. Press

ENT to confirm.

iv) Move the cursor to “Before Calibration” field.



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v) MFD will display a checklist with all the actions to be considered before the



vi) When CALIBRATE is blinking, press ENT to initialize the calibration procedure.

vii) Wait for few seconds for a check list appearing on lower area of MFD.

viii) Follow MFD instructions; MFD will advise how to change engine throttle. Press

ENT when each action is confirmed.

ix) When all the instructions have been performed, press ENT and then TEST

COMPLETE will stop blinking.

x) MFD will show if vibration test is successful.

NOTE

If test is not successful, the MFD will display the

improper values.

If test is not successful, repeat the procedure 3

(three) times. If it is still not successful, a

troubleshooting is required to identify the root cause

of vibration and the AHRS unit installation must be

considered not reliable.

xi) Press ENT to terminate the procedure.

d) Check the inertial platform Garmin GRS77/GMU44 alignment:

i) If not already done, carry out the alignment and compensation of magnetic

compass in accordance with AMM10.702-5, Section 13, para. 2.1.2.

ii) Restart Garmin GDU620 in normal mode.

iii) Align the aircraft to each 4 (four) compass point (North, South, East and West)

and check that HSI indicates the heading of sample magnetic compass (max

deviation ±2° is allowed, ref. Table 9).

DEVIATION

NORTH ±2

EAST ±2

SOUTH ±2

WEST ±2

Table 9 Compass point alignment

58) Verify EDM-930 functionality, as following:

a) Place the aircraft in an engine test area.

b) If not already done, disconnect external power supply.

c) Push-in the STARTER RELAY breaker.

d) Set ON the MASTER BATTERY switch and start the engine in accordance with the

procedure reported in AFM10.701-7, Section 4, para. 4.6.1.

e) Activate the ALT switch and check that the red warning ALT OUT on the annunciator

panel turns OFF.

f) Activate the AVIONICS switch and wait for few minutes for the systems powering up.



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g) Carry out an engine test, verifying the EDM-930 for reporting the correct engine

parameters, as per AFM10.701-7, Section 7, para. 7.4, Table 7-1.

h) Check if the fuel indicator is properly reporting the fuel quantity in the fuel tanks.

i) Check if the EDM-930 is properly reporting the main bar voltage of 28Vdc0.5Vdc and

that the ammeter is measuring current from alternator.

j) Verify that no red X is shown on EDM-930.

k) Check if the RAD panel located in the upper area of the instrument panel is reporting the

RPM and MAP values as reported by EDM-930.

Figure 25 RAD panel (only for reference)

l) Shutdown the engine in accordance with AFM10.701-7, Section 4, para. 4.15.

59) Verify cut-off module functionality, as following:

a) Set the MASTER BATTERY switch to ON.

b) Set the STALL HEAT switch to ON and verify that the led light on the switch still

remains OFF and the heater is cool.

c) Set the STALL HEAT switch to OFF.

d) Start the engine and activate the ALT switch. Set the STALL HEAT switch to ON and

verify that the led light on the switch turns green.

e) Shutdown the engine in accordance with AFM10.701-7, Section 4, para. 4.15.

60) Verify hourmeter functionality, as following:

a) Place the aircraft in an engine test area.

b) Start the engine in accordance with the procedure reported in AFM10.701-7, Section 4,

para. 4.6.2.

c) Check if hourmeter is properly working.

61) Reinstall all the access panels and detachable parts, if not already done.

62) Touch up, where necessary, the concerned external surfaces with finish polyurethane paint as

per existing aircraft livery.

63) Disconnect the external power supply, if not already done.

64) Reconnect the battery cable (positive cable first).

65) Proceed with the following Part F.



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Part F: IN-FLIGHT TESTS

WARNING

Aircraft limitations are reported in the Flight

Manual AFM10.701-7, Section 2, and possible

related Supplements.

WARNING

Flight tests must be performed only if all the

above on-ground tests are successfully passed.

WARNING

Adverse weather conditions in the operating area

must be avoided.

WARNING

No “high-risk” manoeuvres are requested to

validate the Test Points.

WARNING

In the event the data point yields an unexpected

result, or a series of data points creates an

unexpected trend, in-flight tests must be finished

immediately, until the results are properly

analysed and understood.

WARNING

No specific loading condition is requested, it is

recommended an intermediate position of CG. It

is responsibility of the pilot in command to

ensure that the airplane is properly loaded before

flight.

NOTE

If any check is not passed successfully, send a

technical request to Vulcanair Customer Support by

means of the online form at the following web

address: http://support.vulcanair.com/

1) Perform the whole pre-flight check list in accordance with AFM10.701-7, Section 4, para. 4.4,

deepening the following verifications:

a) Verify the presence onboard of the following items:

i) Aircraft Flight Manual

ii) Fire extinguisher

b) Verify the proper function of the following items:

i) Safety belts

ii) Locking mechanism of doors (crew, passenger, baggage)




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c) Verify the freedom in movement of airplane control surfaces:

i) Stabilator

ii) Ailerons

iii) Rudder

iv) Flaps

v) Pitch Trim

d) Verify the freedom in movement of engine controls (no abnormal friction or stoppages):

i) Throttle

ii) RPM control

iii) Mixture

iv) Fuel Selector

v) Alternate Air control

2) Carry out an engine run-up as following:

a) Verify the magneto bonding at 1000rpm and full rich mixture: verify the engine

tendency to shutdown setting both magneto OFF.

b) Verify the magneto drop-off at 2100rpm and full rich mixture: verify rpm drop within

limits.

CAUTION

Do not operate on a single magneto for a long

period;

few seconds are usually sufficient to check drop-off

and will minimize plug fouling.

NOTE

Maximum drop-off with single magneto circuit

should be 175rpm.

Maximum difference between drop-off should be

50rpm.

c) Verify the proper function of alternator and relevant warning advisory message: switch-

off alternator field and verify “ALT OUT” light ON.

d) Verify the proper function of mixture control:

i) Stabilize 2400rpm and full rich mixture.

ii) Lean mixture.

iii) Verify EGT increase.

3) Verify the proper operation of brake system (including parking brake).

4) Verify the proper nose-wheel steering operation.

5) Verify the proper operation of radios.

6) Proceed with in-flight checks.

NOTE

Flight Tests exit criteria: each test point is to be

considered PASSED if pilot feedback is positive, no

anomaly has been registered and no investigation or

corrective action is required.



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7) Carry out the take-off and climb as per standard procedure laid out in AFM10.701-7, Section

4, para. 4.11, checking the engine parameters (RPM, MAP, O/P, O/T, F/F, EGT), if abnormal.

8) Perform a flight profile, verifying the following:

a) Stabilize 90KIAS and 130KIAS (PFD reading) at 4000ft in cruise and verify the absence

of difference in airspeed readings between PFD/MFD and STBY.

b) Verify the aileron-free lateral stability (turn tendency) in cruise, as following:

i) Stabilize and trim straight level flight at 5000ft, 120KIAS, FLAP UP.

ii) Release the control wheel temporary.

iii) No bank angle should arise after 15sec. If a bank angle is reported during this test

point, once on-ground, adjust properly the aileron flettner, then repeat this test

point to verify if the instability is solved.

c) Verify the rudder-free directional stability (free rudder pedals return) in descent, as

following:

i) Stabilize and trim straight level flight at 5000ft, 85KIAS, FLAP UP.

ii) Set 10deg about of sideslip.

iii) Release rudder pedals and verify subsequent return.

NOTE

Carry out this test both on the right and on the left.

d) Verify the aircraft stabilization, as following:

i) Stabilize straight and level flight at 5000ft with 65% and 55% of Maximum

Continuous Power setting.

ii) Monitor (and check if abnormal) the powerplant parameters (rpm, MAP, O/T, O/P,

F/P, F/F, CHT, EGT).

e) Verify the stall speeds, as following.

i) Verify PWR OFF stall speeds in CLEAN, T/O and LNDG configuration (Flap 28

deg).

ii) Verify the proper functionality of stall warning.

NOTE

The stall speeds are reported in the Flight Manual

AFM10.701-7, Section 5, para. 5.8.

NOTE

Airspeed decay rate shall be 1KIAS/s about. Starting

airspeed must be 1,5 times the expected stall speed.

The stall warning shall be activated at speeds from

4KIAS to 12KIAS higher than expected stall speed.

f) Verify the proper functionality of the following systems, reporting any anomaly or

abnormal interference:

i) Fuel control valve

ii) Heating system

iii) Outlet airflow

iv) Gyro-instruments

v) VOR Navigation and Approach



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vi) GPS Navigation

vii) GS/ILS Approach

viii) ADF (if installed)

ix) DME (if installed)

x) Intercom

9) Carry out the descent and landing as per standard procedure laid out in AFM10.701-7, Section

4, para. 4.14, checking the following:

a) Verify the proper function of Marker Beacon indication.

b) Verify the appropriate approach speed during standard approach.

c) Verify any abnormal steering during braking action in landing.

10) Record compliance with this Service Bulletin in the Aircraft Log-Book.

NOTE

Get in touch with Vulcanair Sales Dept. at

[email protected] for expedition items to be

returned back to Vulcanair. Note that for safety

reason the g-meter is to be locked before packing for

shipping back (to lock g-meter, gently pull and hold

the “Pull & Turn” knob at the rear side of the

instrument, then turn, while pulling, to LOCK

position).

3. MATERIALS REQUIRED

Commercially available materials required:

ITEM DESCRIPTION Q.TY

--- deleted ---

2 SIKAFLEX-221 sealing compound or equivalent AR

3 MASTINOX D40 AR

4 Methyl-Ethyl-Ketone or equivalent cleaning solvent AR

5 Alodine 1200 (MIL-C-5541) AR

6 Epoxy Primer (MIL-PRF-23377) AR

7 Polyurethane paint as per aircraft livery AR

mailto:[email protected]

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