0.1 Erfassung der Berichtigungen / Record of Revisions

SCHEMPP -HIRTH FLUGZEUGBAU GmbH, KIRCHHEIM/TECK
Ventus-2cT FLUGHANDBUCH Ausgabe Juni 1996
FLIGHT MANUAL issue June 1996
0.1 Erfassung der Berichtigungen / Record of Revisions
Lfd. Nr.
der
Berichtigung Abschnitt
Seiten
Datum
der
Berichtigung
Bezug
Datum der
Anerkennung
durch
EASA
Datum der
Einarbeitung
Zeichen
/Unterschrift
Revision
No.
Affected
section
Affected
page
Date of
issue
Reference
Date of
Approval
by EASA
Date of
Insertion
Signature
13 0
4
0.2.5.1
4.3.3
4.3.4
Jan. 2011 TN 825-51
Änderung des Flughandbuchs
und Reparaturverfahren
für
Motorträger
-alle Werknummern-
Amendment of the
Flight Manual and
repair method for
engine pylon
- all serial numbers -
MB: Modification Bulletin – Änderungsblatt
TN : Technical Note – Technische Mitteilung
Hinweis:
Note:
Nicht eingefügte Berichtigungen sind zu streichen.
Das Verzeichnis der Seiten ist gegebenenfalls handschriftlich zu aktualisieren
Cross out revisions which are not included.
The list of effective pages must be amended by hand if necessary.
0.1.5

SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK
Ventus-2cT
FLIGHT MANUAL
(4) a) Check fuselage for damage, especially on its lower side
b) Check that the STATIC pressure ports for the ASI on the
tail boom (0.8 m /2.62 ft forward of the base of the fin) and
below the spar stub cut-out are clear
Visual inspection of the power plant
CAUTION: IGNITION TO BE SWITCHED OFF !
c) Check – while power plant extends – that the tip of the prop blade
pointing to the front has sufficient clearance to the rim of
the engine compartment (blade must not get jammed below the
rim)
d) Check propeller for damage and ease of movements.
Being in the lowermost position, each blade must unfold automatically,
otherwise the bolt at the blade root should be lubricated
e) Check power plant for loose bolts and nuts, check all locks and
stops
f) Check exhaust system and engine pylon for damage and cracks,
especially at the welding joints. The area around the lower engine
suspension must be checked thoroughly, see picture below. If
necessary, the engine pylon should be cleaned with a cloth in this
area. If necessary a torch should be used for the check.
Check this area also
from the rear side
Check the vertical
tube from every side
Note: For better illustration the front plug connector is removed.
January 2011 TN 825-51 approved
Revision 13 4.3.3

SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK
Ventus-2cT
FLIGHT MANUAL
(4) a) Check fuselage for damage, especially on its lower side
b) Check that the STATIC pressure ports for the ASI on the
tail boom (0.8 m /2.62 ft forward of the base of the fin) and
below the spar stub cut-out are clear
Visual inspection of the power plant
Completely extend the power plant with the manual operation switch
CAUTION: IGNITION TO BE SWITCHED OFF !
c) Check – while power plant extends – that the tip of the prop blade
pointing to the front has sufficient clearance to the rim of
the engine compartment (blade must not get jammed below the
rim)
d) Check propeller for damage and ease of movements.
Being in the lowermost position, each blade must unfold automatically,
otherwise the bolt at the blade root should be lubricated
e) Check power plant for loose bolts and nuts, check all locks and
stops
f) Check exhaust system and engine pylon for damage and cracks,
especially at the welding joints. The area around the lower engine
suspension must be checked thoroughly, see picture below. If
necessary, the engine pylon should be cleaned with a cloth in this
area. If necessary a torch should be used for the check.
Check this area also
from the rear side
Check the vertical
tube from every side
Note: For better illustration the front plug connector is removed.
January 2011 TN 825-51 approved
Revision 13 TN 825-42 4.3.3

SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK
Ventus-2cT
FLIGHT MANUAL
(4) (continued)
g) Check components, lines, hoses, pipes and wires etc. for
chafing marks
h) Check condition, function and tension of engine arresting cables,
engine door operating cables and door actuating mechanism
i) Check that the retaining springs are hooked up to the engine
arresting wires
j) Pull back decompression handle and hold – prop must rotate freely.
Release handle and check that the actuating lever on the pylon
returns to its stop.
The gap between the decompression valve interconnecting link and
the actuating lever on the pylon must be at least 2.0 mm (0.08 in.)
(5) a) Check condition of tail skid or wheel. If the latter is installed,
check tire pressure:
2.0 bar / 29 psi (see placard)
b) Should a total energy compensation probe be used, mount it
and check the line (when blowing gently from the front to the probe
with pneumatic valve for the TEK probe set at “Power off”, the
variometer(s) connected should read “climb”)
c) Check that the fin-mounted PITOT tube is clear.
When blowing gently into this probe, the ASI must register
(with pneumatic valve for the pitot pressure set at “Power off”)
d) Check that the opening for the fuel tank vent line
(at the upper end of the fin) is clear
Should a water ballast fin tank be installed (option):
e) Check that the fin tank spill holes are clear
f) Check water ballast level in fin tank (in case of doubt,
discharge ballast)
g) Check that the dump hole for the fin tank in the tail wheel
fairing (if installed) is clear
January 2011 TN 825-51 approved
Revision 13 4.3.4