Rotax 912 Series Operator's Manual

1.7) Type description
The type description consists of the following:
e.g.
ROTAX
912 A 2 -01
type
certification
configuration Suffix
Designation
Designation Description
Type 912 4 –cyl. horizontally opposed, normal aspirated
engine
Certifica-
tion
A Certified to JAR 22 (TC No. EASA.E.121)
F, S Certified to FAR 33 (TC No. E00051 EN) JAR-E
(TC No. EASA.E.121)
UL,
ULS
Non-certified aircraft engines
Configura-
tion
2 Prop shaft with flange for fixed pitch propeller.
3 Prop shaft with flange for constant speed propeller
and drive for hydraulic governor for constant speed
propeller.
Suffix –XX Explanation of the type designation suffix, see
SB-912-068
Options
Available options (optional equipment) for the engine type men-
tioned above:
external
alterna-
tor
vacuum
pump
drive for rev
counter/
hour meter
gover-
nor
for configura-
tion 2
yes yes yes no
for configura-
tion 3
yes no yes yes
NOTE
Conversion of the configuration 2 to configuration 3 may be ac-
complished by ROTAX® authorized aircraft engines distributors
or their Independent service centers.
Page 1-16
November 01/2016
BRP-Rotax Effectivity: 912 Serie
Edition 4 / Rev. 0

Rotax 912 Series Specifications

General

Redline	5800 rpm
TBO	2000 hours
Displacement	1211 cc
Bore	79.5 mm
Stroke	61 mm
Power Output	80 hp (59.6 kW)
Compression Ratio	9.0:1
Fuel Type	Avgas 100LL
Ignition System	Dual electronic ignition
Fuel System	Fuel Injected
Oil System	Dry sump
Engine Type	4-cylinder, horizontally opposed, 4-stroke