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P68 VARIANTS
SERVICE INSTRUCTION
No. 99
Design Organisation Approval No. AS-SI/14/001 dated 15 May 2014
SUBJECT:
PROPELLER ELECTROTHERMAL DE-ICING SYSTEM –
BRUSH BLOCK ASSY RELOCATING
1. GENERAL
1.1
AIRCRAFT AFFECTED
All P.68C-TC and P.68TC Observer aircraft up to s/n 399.
1.2
PURPOSE
To supply instructions for the relocating of the brush block assy of the propeller
electrothermal de-icing system when a new engine, installed in replacement of the previous
one, includes a new crankcase design which interferes with the brush block assy in the actual
configuration (refer to Fig. 1).
1.3
DESCRIPTION
The modification consists in the replacement of the existing support arm p/n 7.8085-2 with
the new one p/n 7.8085-3, and in a simple drilling operation to be carried out on the
concerned existing baffle to allow the installation of the existing brush block assy mounting
bracket p/n 7.8085-1 by means of existing attaching parts.
1.4
MAN-HOURS REQUIRED
Time necessary for the application of this Service Instruction is estimated as 2 man-hours.
1.5
SPECIAL TOOLS
No special tool is required.
First Issue dated 15 May 2014
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Vulcanair S.p.A.
Service Instruction No. 99
1. GENERAL
1.6
1.7
VARIATION IN WEIGHT AND BALANCE
This change does not involve variations in Weight and Balance data.
ELECTRICAL SYSTEM LOAD
Not applicable.
1.8
REFERENCE DOCUMENTS
- Applicable Maintenance Manual for aircraft type.
- Applicable Parts Catalogue for aircraft type.
1.9
PUBLICATIONS AFFECTED
- Applicable Parts Catalogue for aircraft type.
- Applicable Maintenance Manual for aircraft type.
1.10 MODIFICATION TO BE CARRIED OUT BY
Vulcanair Part 145 or other Certified Maintenance Facility.
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Service Instruction No. 99
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.
NOTE
The following instructions refer to only for the
relocating of the brush block assy of the propeller
electrothermal de-icing system. For its complete
installation procedure and the required tests to be
performed refer to the latest applicable revision of the
manufacturer’s pertinent technical publication.
Refer to Figure 2 and 3 for the Brush Block Assy PREMODIFICATION and
POSTMODIFICATION installation layout, respectively.
1. First of all, it is necessary to install the existing engine baffles on the new engine, then trim and
adjust the concerned baffle to avoid any interference with the new engine crankcase.
2. Referring to manufacturer’s pertinent technical publication, reposition the brush block assy p/n
NOR7.479-14 together with the mounting bracket p/n 7.8085-1 and the new support arm p/n
7.8085-3 on the engine baffle and the engine crankcase as shown in Figure 3, aligning the
brushes with the slip ring surfaces as required. Lock the brush block assy/mounting
bracket/support arm group temporarily in place.
3. Drill 3.5 mm diameter No.2 holes on the engine baffle, copying from the existing ones on the
mounting bracket. Remove the brush block assy/mounting bracket/support arm group.
4. Deburr the holes. Clean all the reworked surfaces with Methyl-Ethyl-Ketone or equivalenmt
cleaning solvent, then treat them with alodine 1200 (MIL-C-5541).
5. Reposition and install the brush block assy/mounting bracket/support arm group on the engine
baffle using the proper two removed screws, and on the engine crankcase using the concerned
existing bolt.
6. Referring to manufacturer’s pertinent technical publication, perform the correct radial and fore
and aft brush block assy alignments as required, then tighten the relevant attaching screws.
7. Restore all the electrical connections to the brush block assy and, when you have completed all
the engine installation, check the propeller electrothermal de-icing system for correct operation.
8. Record application of this Service Instruction in the Aircraft Log-Book.
First Issue dated 15 May 2014
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Service Instruction No. 99
3. MATERIALS REQUIRED FOR THE MODIFICATION
Item
1
Description
P/N
7.8085-3
Support Arm
Q.ty
1
Commercially available materials required but not included in the Kit:
- Methyl-Ethyl-Ketone or equivalent cleaning solvent.
- Alodine 1200 (MIL-C-5541).
First Issue dated 15 May 2014
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Vulcanair S.p.A.
Service Instruction No. 99
Fig. 1
Differences between the previous and the new engine
crankcase design in the concerned area
First Issue dated 15 May 2014
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Vulcanair S.p.A.
Service Instruction No. 99
Fig. 2
Brush Block Assy Installation layout
(PREMODIFICATION)
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Vulcanair S.p.A.
Service Instruction No. 99
Fig. 3
Brush Block Assy Installation Layout
(POSTMODIFICATION)
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