AIRCRAFT ENGINES
SERVICE INSTRUCTION
INSTALLATION OF ROTARY WATER PUMP SEAL / PUMP IMPELLER
SI-912-001
SI-914-001
Repeating symbols:
Please, pay attention to the following symbols throughout the Service Bulletin
emphasizing particular information.
▲ WARNING: Identifies an instruction, which if not followed, may cause serious injury
or even death.
■ATTENTION:Denotes an instruction which if not followed, may severely damage the
engine or could lead to suspension of warranty.
◆ NOTE:
Information useful for better handling.
1) Planning information
1.1)
Engines affected
All versions of the engine type:
914 (serial production/pre production)
912 (serial production/pre production)
1.2)
Concurrent ASB/SB/SI und SL
none
1.3)
Reason
Feedback from the field indicates that in the course of maintenance the
installation of the rotary seal has not been done proper. Improper installation can
cause damage on the rotary seal, possibly resulting in leakage of coolant.
1.4)
Subject
Important instructions for installation of the rotary seal on the water pump of all
versions of the ROTAX® engine type 912 / 914.
1.5)
Compliance
This information is intended to assist the aircraft builder and operator in
achieving the proper operating conditions, correct engine installation and
consequently optimum performance and reliability.
April1999
initial issue
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INFORMATION
SI-912-001
SI-914-001
Seite 1 of 9
Copyright - ROTAX® GmbH
AIRCRAFT ENGINES
SERVICE INSTRUCTION
At renewal of the rotary seal proceed as per the following instructions.
At leakage of the rotary seal proceed with the following instructions.
◆ NOTE:
Due to the design of the rotary seal, the manufacturer tolerates
a certain amount of leakage. If the leakage is in excess of the
limit rotary seal must be renewed.
Tolerated leakage:
For this check the engine must be operated until all temperatures
have stabilized for a period of 5 minutes. At that point shut down
engine and ensure the ignition is switched off and engine
secured against unintentional operation.
Coolant must not drip through leakage bore, located at the base
of the igniton housing, for a period of 1 minute after the engine
has been stopped.
In case this leakage test can not be passed, the rotary seal must
be renewed.
1.6)
Approval
not required
1.7)
Manpower
estimated man-hours:
(1)
1.8)
engine is installed in the aircraft, manpower depends on
installation and therefore no statement can be made by the
engine manufacturer.
Mass data
change of weight - - - none
moment of inertia - - - unaffected
1.9)
Electrical load data
no change
1.10) Software accomplishment summary
no change
April 1999
initial issue
SI-912-001
SI-914-001
page 2 of 9
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AIRCRAFT ENGINES
SERVICE INSTRUCTION
1.11) References
In addition to this technical information refer to
-
current issue of the Operator’s Manual (OM)
-
engine data sheet
-
power, torque and fuel consumption curves
-
current issue of the Illustrated Parts Catalog (IPC)
-
Installation Manual (IM) and Check List
-
all relevant Service Information
-
all relevant Technical Bulletins
-
Collective Manual (CM)
-
Repair Manual (RM)
-
Maintenance Manual (MM)
1.12) Other publications affected
none
1.13) Interchangeability of parts
all redundant parts which cannot be used must be scrapped
April1999
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SI-912-001
SI-914-001
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AIRCRAFT ENGINES
SERVICE INSTRUCTION
2) Material Information
2.1)
Material - cost and availability
cost and availability will be supplied on request by our ROTAX® Authorized
Distributors or their Service Center.
2.2)
Company support information
none
2.3)
Material volume per engine
parts volume:
For the replacement of the impeller and the rotary seal the following new parts
are necessary:
item no.
New
part no.
Qty.
(1)
922.224
1
impeller
water pump
(2)
850.945
1
rotary seal
water pump
(4)
926.273
1
washer
water pump
(5)
850.977
1
oil seal 12x30x7
water pump
◆ NOTE:
Description
Old
part no.
remarks
The gasket set (part no. 996.943) includes the new rotary seal
(part no. 850.945) and replaces the old gasket set (part no.
996.942).
For all engines of the Type:
912 UL up to and including S/N 4,403.283
912 A up to and including S/N 4,410.366
912 F up to and including S/N 4,412.791
914 UL up to and including S/N 4,417.783
914 F up to and including S/N 4,420.157
the impeller (part no. 922.224) and the washer (part no. 926.273)
have to be ordered additionally to the gasket set.
All versions of the engine Type:
912 ULS (Serie) beginning with and inclusive S/N 4,425.001
912 S (Serie) beginning with and inclusive S/N 4,922.501
are already equipped with the impeller (part no. 922.224) and
the washer (part no. 926.273).
April 1999
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SI-914-001
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AIRCRAFT ENGINES
SERVICE INSTRUCTION
2.4)
Material volume per spare part
none
2.5)
Rework of parts
none
2.6)
Special tooling/lubricant-/adhesives-/sealing compound Price and availability
Price and availability will be supplied on request by our ROTAX® Authorized
Distributors or their Service Center.
parts volume:
For the replacement of the impeller and the rotary seal the following new parts
are necessary:
item no.
New
part no.
Qty.
(3)
877.259
1
897.651
NB
April1999
initial issue
Description
Old
part no.
remarks
insertion punch
rotary seal
LOCTITE 243
pump shaft
SI-912-001
SI-914-001
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AIRCRAFT ENGINES
SERVICE INSTRUCTION
3) Accomplishment / Instructions
Accomplishment
All the measures must be taken and confirmed by the following persons or facilities:
ROTAX® -Distributors or their Service Center
Persons with the respective Aviation Authority permission.
Persons with type-specific training (applicable only for non-certified engines)
▲ WARNING: Proceed with this work only in a non-smoking area and not near open
flames. Switch off ignition and secure engine against unintentional
operation.
Secure aircraft against unintentional operation.
Disconnect negative pole of aircraft battery.
▲ WARNING: Proceed with work on a cold engine and grounded ignition only.
3.1)
Removal of rotary seal and impeller:
— Remove the waterpump, water pump housing, the magneto hub, the ignition
housing, the oil seal, the rotary seal, the washer and the pump impeller as
per instructions found in the current relevant Maintenance Manual and/or
Repair Manual (ICR-Manual).
3.2)
Installation of the new rotary seal (part no. 850.945):
See fig. 1, fig. 3 and fig. 4 .
— The oil seal T must be replaced as per the instructions found in the current
relevant Maintenance Manual and/or Repair Manual (ICR-Manual).
— The new rotary seal (part no. 850.945) W and the new washer (part no.
926.273) R must be installed as per the instructions found in the current
relevant Maintenance Manual and/or Repair Manual (ICR-Manual). The
new rotary seal insertion punch (part no. 877.259) E must be used. Very
careful handling and installation of the rotary seal is vital in preventing coolant
loss.
— Ensure that water pump shaft is parallel to seal bore during installation.
— If the shaft is not parallel to the bore when installed, the edge of the shaft can
dimple the soft material of the seal bore, reducing the sealing effectiveness
of the press fit. To increase the effectiveness of the press fit between the
pump shaft Y and the seal, a small amount of LOCTITE 243 adhesive
must be applied around the shaft.
— If distance (shown in fig. 1) is not within 8,9 ±0,15 mm (0,35 ±0,006 in.)
, the seal spring has been over-compressed and the seal must be replaced.
April 1999
initial issue
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SI-914-001
page 6 of 9
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AIRCRAFT ENGINES
SERVICE INSTRUCTION
3.3)
Installation of the new impeller (part no. 922.224):
See fig. 1, fig. 2 and fig. 4.
— Impeller of new design (part no. 922.224) Q must be installed with new rotary
seal. Installation as per instructions in the current relevant Maintenance
Manual and/or Repair Manual (ICR-Manual).
— The distance (shown in fig. 1) between 0,4 mm÷ 0,5 mm (0,016 in. ÷ 0,02
in.) must be verified in accordance with the current, relevant Maintenance
Manual and/or Repair Manual (ICR-Manual). If measurement is not within
manufacturers recommendations the installation procedure wasn´t followed
properly and the rotary seal and oil seal is no longer serviceable. The seals
must be removed and a new rotary seal and a new oil seal must be installed
as per manufacturers recommendations.
— Reconnect the aircraft battery.
3.4)
Test run:
Start the engine. Conduct testrun inclusive ignition check and leakage test in
accordance with the current Maintenance Manual of the engine type.
3.5)
Summary
▲ WARNING: Non-compliance with these recommendations could result in
engine damage, personal injury or death!
Approval of translation to best knowledge and judgement - in any case the original text in German language and
the metric units (SI-system) are authoritative.
April1999
initial issue
SI-912-001
SI-914-001
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Copyright - ROTAX® GmbH
AIRCRAFT ENGINES
SERVICE INSTRUCTION
4) Appendix
The following drawings should convey additional information:
The drawings below show the rotary seal of new design (part no. 850.945), the new
washer (926.273) and the new impeller (part no. 922.224):
A
Lage/Location:
Abstand 8,9 ±0,15 mm
distance 8,9 ±0,15 mm (0,35 ±0,006 in.)
IG
L B
Detail A
Cyl. 2
Cyl. 1
Cyl. 4
Cyl. 3
A➮
02902
Q Laufrad ....................... impeller
2
W Gleitringdichtung ........ rotary seal
4
E Montagestempel ........ insertion
punch
R Scheibe ...................... washer
T WD-Ring ..................... oil seal
Y Pumpenwelle .............. pump shaft
03085
Abstand 0,4 mm÷ 0,5 mm
distance 0,4 mm÷ 0,5 mm
6
Detail A
5
02873
1
Bild / Fig. 1
cross-section of waterpump
Fig.: 1
April 1999
initial issue
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SI-914-001
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AIRCRAFT ENGINES
SERVICE INSTRUCTION
The illustration below shows the new impeller with 2 holes:
■ ATTENTION:The impeller can only be utilized for
the new rotary seal (part no.
850.945).
1
Bild 2/ fig. 2
02722
The illustration below shows the new insertion punch:
■ ATTENTION:The new insertion punch can only
be utilized for the new rotary seal
(part no. 850.945).
Bild 3/ fig. 3
3
03222
The illustration below show the rotary seal of the old and new design:
Bild 4/ fig. 4
alt/
old
neu/
new
2
03502
new impeller, new tool and
new rotary seal
Fig.: 2,
April1999
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