Lufttüchtigkeitsanweisung LTA-Nr.: D-2006

Lufttüchtigkeitsanweisung
LTA-Nr.: D-2006-438R1
ersetzt: D-2006-438
Datum der Bekanntgabe: 20.02.2008
Luftfahrt-Bundesamt
Muster: Eurocopter
SA 330 F
AD der ausländischen Behörde:
EASA AD 2006-0163R1 vom 13.12.2007
Geräte-Nr.:
EASA.R.002
Technische Mitteilungen des Herstellers:
Eurocopter AS 332 Alert Service Bulletin No. 05.00.65
Eurocopter EC 225 Alert Service Bulletin No. 05A002 Revision 1
Betroffenes Luftfahrtgerät:
Eurocopter
SA 330 F
- Baureihen:
AS 332 L2 und EC 225 LP
- Werk-Nrn.:
alle
Betrifft:
Rumpf / Hauptgetriebe (''Fuselage – Main Gearbox (MGB) Suspension Bar Attachment Fittings – Checks'')
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA-AD und der
oben genannten Technischen Mitteilung des Herstellers zu entnehmen.
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig
und innerhalb der vorgesehen Fristen auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle
Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen
Zustimmung durch das Luftfahrt-Bundesamt.
Fristen:
Alle anzuwendenden Fristen sind der o. g. EASA-AD zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der o. g. EASA-AD.
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen
nur in Betrieb genommen werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der
Sicherheit des Luftverkehrs, das in diesem Fall das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
Rechtsbehelfsbelehrung:
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen.
LTAs werden auch im Internet unter http://www.lba.de publiziert
***
(LTA-Nr.: D-2006-438 vom 28.12.2006)
Aktenzeichen: (02)T231-502.1/D-2006-438R1
Seite 1 von 1
D-2006-438R1
EASA
AIRWORTHINESS DIRECTIVE
AD No: 2006-0163 R1
Date: 13 December 2007
No person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the
requirements of that Airworthiness Directive unless otherwise agreed with the Authority of the State of Registry.
Type Approval Holder’s Name:
Type/Model designation(s):
EUROCOPTER
AS 332 L2 and EC 225 LP helicopters
TCDS Number: EASA R.002
Foreign AD: Not applicable
Revision: This Airworthiness Directive (AD) revises and replaces EASA AD 2006-0163 dated 09
June 2006.
ATA 53
Fuselage – Main Gearbox (MGB) Suspension Bar Attachment
Fittings – Checks
Manufacturer(s):
EUROCOPTER (formerly EUROCOPTER FRANCE)
Applicability:
AS 332 L2 and EC 225 LP helicopters, all serial numbers.
Reason:
EASA Airworthiness Directive (AD) 2006-0163 was issued following analysis of
the tightening torques, measured once on the helicopter fleet as required by
DGAC France AD F-2005-118, now no longer valid. The measurements that
were taken only on the bolts that secure the rear MGB bar attaching fittings
revealed some cases of tightening torque loss and further analysis showed that
it is necessary to carry out the same check on the front fitting and introduce a
routine check for all these fittings, the front fitting and the rear fittings. In fact,
significant loss of the tightening torque of the bolts that secure the MGB bar
attaching fittings can lead to a change in the loading mode of frames 3855 and
5295, and can give rise to crack initiation at the MGB bar attaching fittings.
Following tests and calculations, the interval for checking/tightening the torque
of front and rear MGB bar attaching fitting attachment bolts has been extended
for EC 225 LP helicopters. Consequently, AD 2006-0163 has been revised to
allow these checks to be made at intervals not exceeding 825 Flight Hours (FH)
instead of 375 FH.
Note: This AD supplements instructions required by EASA ADs 2006-0103 R1
(AS 332 L2) and 2006-0102 R1 (EC 225 LP).
Effective Date:
23 June 2006
1/3
D-2006-438R1
Compliance:
Required as indicated, unless accomplished previously:
1–
Check the tightening torque of the bolts that secure the front MGB bar
attaching fitting in accordance with the instructions specified in
paragraph 2.B of the referenced EUROCOPTER Alert Service Bulletin
(ASB), corresponding to the helicopter version:
1.1. For EC 225 LP helicopters: At the next scheduled 750-hour
inspection after the effective date of this AD, not exceeding 825
FH.
1.2. For AS 332 L2 helicopters: Within 150 FH after the effective date
of this AD.
2–
Thereafter, at intervals not to exceed 825 FH, check the tightening
torque of the bolts that secure the front MGB bar attaching fitting and
the rear RH and LH MGB bar attaching fittings, in accordance with the
instructions specified in paragraph 2.B of the referenced ASB,
corresponding to the helicopter version.
3–
Interpretation of the results concerning the bolts that secure the front
MGB bar attaching fitting.
3.1. If the loss of the tightening torque of the nuts is less than or equal
to 20% of the recommended minimum tightening torque, re-adjust
the tightening torques, in accordance with the instructions
specified in paragraph 2.B.3.a.1. of the referenced ASB,
corresponding to the helicopter version.
3.2. If the loss of the tightening torque of at least one of the nuts of the
fitting is more than 20% of the recommended minimum tightening
torque, before next flight, accomplish the instructions specified in
paragraph 2.B.4 of the referenced ASB, corresponding to the
helicopter version, in order to:
4–
-
re-adjust the tightening torques of all the nuts that secure the
mounting plate under the MGB bar attaching fitting,
-
check the four bolts that secure the MGB bar attaching fitting,
for absence of cracks, and if there is a crack in at least one of
the bolts: Replace the four bolts,
-
check that there is no crack in frame 3855, in the attachment
area of the MGB bar attaching fitting, and if there is a crack:
Suspend flights.
Note: Contact EUROCOPTER for determining how to manage
flights resumption depending on observed crack conditions.
Any subsequent approved corrective action (e.g. repair or
replacement of the frame) does not terminate the repetitive
inspection requirements of § 2 of this AD.
Interpretation of the results concerning the bolts that secure the rear
RH and LH MGB bar attaching fittings.
4.1. If the loss of the tightening torque of the nuts is less than or equal
to 20% of the recommended minimum tightening torque, re-adjust
the tightening torques, in accordance with the instructions
specified in paragraph 2.B.3.b.1 of the referenced ASB,
corresponding to the helicopter version.
4.2. If the loss of the tightening torque of at least one of the nuts of the
fittings is more than 20% of the recommended minimum tightening
torque, before next flight, accomplish the instructions specified in
paragraph 2.B.5 of the referenced ASB, corresponding to the
2/3
D-2006-438R1
helicopter version, in order to:
Ref.
Publications:
-
re-adjust the tightening torques of all the nuts of the mounting
plates under the MGB bar attaching fittings,
-
check the four bolts that secure the MGB bar attaching fittings,
for absence of cracks, and if there is a crack in at least one of
the bolts: Replace the four bolts,
-
check that there is no crack in frame 5295, in the attachment
areas of the MGB bar attaching fittings, and if there is a crack:
Suspend flights.
Note: Contact EUROCOPTER for determining how to manage
flights resumption depending on observed crack conditions.
Any subsequent approved corrective action (e.g. repair or
replacement of the frame) does not terminate the repetitive
inspection requirements of § 2 of this AD.
EUROCOPTER EC 225 Alert Service Bulletin No. 05A002 Revision 1; and
EUROCOPTER AS 332 Alert Service Bulletin No. 05.00.65, as applicable.
The use of later approved revisions of these documents is acceptable for
compliance with the requirements of this AD.
Remarks:
1. If requested and appropriately substantiated, EASA can accept Alternative
Method of Compliance for this AD.
2. The original issue of this AD was posted as PAD 06-083 on 5 April 2006 for
consultation until 19 April 2006. No comments were received during the
consultation period.
3. Enquiries regarding this AD should be referred to the AD Focal Point Certification Directorate, EASA. E-mail: [email protected] .
4. For any questions concerning the technical content of the requirements in
this AD, please contact: EUROCOPTER (STXI) - Aéroport de Marseille
Provence 13725 Marignane Cedex – France;
Telephone: + 33 (0) 4 42 85 97 97 - Fax: + 33 (0) 4 42 85 99 66;
E-mail: [email protected]
3/3