Nachrichten für Luftfahrer 2008 Teil II (weicht ggf. von Druckversion ab)
EASA AD No : 2008-0145
Lufttüchtigkeitsanweisung EASA AIRWORTHINESS DIRECTIVE
LTA-Nr.: D-2008-277
AD No.: 2008-0145
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 11.08.2008
Muster: Thielert Aircraft Engines AD der ausländischen Behörde:
TAE125 EASA AD 2008-0145 vom 01.08.2008 Date: 01 August 2008
Geräte-Nr.: Technische Mitteilungen des Herstellers: Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation
4631, EASA.E.055 Thielert Service Bulletin TM TAE125-0018 vom 19.06.2008 (EC) No 216/2008 on behalf of the European Community, its Member States and of the
Thielert Service Bulletin TM TAE125-1007 P1 vom 11.07.2008 European third countries that participate in the activities of EASA under Article 66 of that
Regulation.
Betroffenes Luftfahrtgerät: This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the
continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate
an aircraft to which an AD applies, except in accordance with the requirements of that AD unless otherwise specified by the Agency
Thielert Aircraft Engines [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].
TAE125
- Baureihen: TAE125-01 und TAE125-02-99 Type Approval Holder’s Name : Type/Model designation(s) :
- Werk-Nrn.: Alle Triebwerke dieser Baureihen, die in dem Luftfahrzeugmuster Diamond Aircraft Thielert Aircraft Engines GmbH TAE125 engines
Industries DA 42 installiert sind.
TCDS Number : EASA.E.055
Betrifft:
Mögliche Abschaltung des Triebwerks im Fluge durch Ausfall des ''Propeller Control Valves''. Foreign AD : Not applicable
Maßnahmen: Supersedure : This AD supersedes EASA AD 2008-0130 dated 15 July 2008.
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA
Airworthiness Directive und den genannten technischen Mitteilungen des Herstellers zu entnehmen.
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß,
vollständig und innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente ATA 61 Propellers – Propeller Control Valve – Replacement (Life Limit)
durchgeführt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeits-
anweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
Manufacturer(s): Thielert Aircraft Engines GmbH.
Fristen:
Alle anzuwendenden Fristen sind der oben genannten EASA Airworthiness Directive zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten TAE125-01 and TAE125-02-99 engines, all serial numbers, if installed on
Applicability:
EASA Airworthiness Directive. Diamond Aircraft Industries Model DA 42 aircraft.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der In-flight engine shutdown incidents have been reported on Diamond Aircraft
EASA AD 2008-0145 vom 01.08.2008 Industries DA 42 aircraft equipped with TAE125 engines. Preliminary
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen investigations showed that it was mainly the result of failure of the propeller
nur in Betrieb genommen werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der control valve. This condition, if not corrected, could lead to further cases of
Sicherheit des Luftverkehrs, das in diesem Fall das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es engine in-flight shutdown, possibly resulting in reduced control of the aircraft.
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
EASA AD 2008-0130 has been published to require implementation of a life
Rechtsbehelfsbelehrung:
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder
limit of 300 flight hours (FH) for the Proportional Pressure Reducing Valve 24V
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen. (propeller control valve) Part Number (P/N) NM-0000-0124501 on TAE125-01
engines and replacement of propeller control valves that have exceeded the
LTAs werden auch im Internet unter http://www.lba.de publiziert Reason: established life limit. The same P/N valve is also installed on TAE125-02-99
***
engines.
As this problem has only manifested itself on those engines, as installed on
Diamond Aircraft Industries DA 42 aircraft, any TAE125-01 and TAE125-02-99
engines installed on other aircraft are not affected.
For the reasons stated above, this EASA AD retains the requirements of AD
2008-0130, which is superseded, and expands the applicability to include
TAE125-02-99 engines on Diamond DA 42 aircraft that have the affected valve
installed.
Effective Date: 15 August 2008
EASA Form 110 Page 1/2
Aktenzeichen: (10)T23-502.1/D-2008-277 Seite 1 von 1
EASA AD No : 2008-0145
Required as indicated, unless accomplished previously: Lufttüchtigkeitsanweisung
(1) For TAE125-01 engines, initially replace the propeller control valve LTA-Nr.: D-2008-278
P/N NM-0000-0124501 in accordance with the instructions of Thielert
Aircraft Engines (TAE) Service Bulletin (SB) TM TAE125-0018 at the time
Luftfahrt-Bundesamt
indicated in Table 1 below:
Datum der Bekanntgabe: 11.08.2008
Table 1
Muster: International Aero Engines AD der ausländischen Behörde:
Gearbox accumulated Compliance time: V2500 FAA AD 2008-14-15 Amdt. 39-15610
time since new: V2500-A5/-D5
More than 400 FH 55 FH or during the next Geräte-Nr.: Technische Mitteilungen des Herstellers:
scheduled maintenance, 6324, 6330 International Aero Engines Service Bulletin V2500-ENG-72-0541
whichever occurs first after Revision 4 vom 12.03.2008
29 July 2008, the effective date of
AD 2008-0130.
Betroffenes Luftfahrtgerät:
Less than 400 FH Upon accumulating 300 FH (first
scheduled maintenance), or within International Aero Engines
110 FH, whichever occurs later V2500, V2500-A5/-D5
after 29 July 2008, the effective
Required Action(s) date of AD 2008-0130. - Baureihen: V2500-A1, V2522-A5, V2524-A5, V2527- A5, V2527E-A5, V2527M-A5, V2530-A5,
and Compliance V2533-A5, V2525-D5, V2528-D5
Time(s): (2) For TAE125-02-99 engines, initially replace the propeller control valve
P/N NM-0000-0124501 in accordance with the instructions of TAE SB TM
TAE125-1007 P1 at the time indicated in Table 2 below: - Werk-Nrn.: Nähere Einzelheiten zu betroffenen Seriennummern können der genannten FAA
Airworthiness Directive entnommen werden.
Table 2
Gearbox accumulated Compliance time: Betrifft:
time since new: Möglicher Ausfall des Triebwerks im Fluge durch Ölverlust am Turbinenlager Nr. 4 infolge von Schäden
an Komponenten des Ölversorgungssystems.
More than 400 FH 55 FH or during the next
scheduled maintenance, Maßnahmen:
whichever occurs first after the Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten FAA
effective date of this AD Airworthiness Directive und der genannten technischen Mitteilung des Herstellers zu entnehmen.
Less than 400 FH Upon accumulating 300 FH (first Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß,
scheduled maintenance), or within vollständig und innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente
110 FH, whichever occurs later durchgeführt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeits-
after the effective date of this AD anweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
(3) After compliance with paragraph (1) or (2) of this AD, as applicable to
Fristen:
engine model, at intervals not to exceed 300 FH, replace the propeller
Alle anzuwendenden Fristen sind der oben genannten FAA Airworthiness Directive zu entnehmen.
control valve P/N NM-0000-0124501 in accordance with the instructions of
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
TAE SB TM TAE125-0018 or SB TM TAE125-1007 P1, as applicable.
FAA Airworthiness Directive.
Thielert Aircraft Engines SB TM TAE125-0018 dated 19 June 2008 and
TM TAE125-1007 P1 dated 11 July 2008. Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
Ref. Publication: FAA AD 2008-14-15 Amdt. 39-15610
The use of later approved revisions of these documents is acceptable for
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen
compliance with the requirements of this AD. 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
1. If requested and appropriately substantiated, EASA can approve Alternative erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
Methods of Compliance for this AD.
Rechtsbehelfsbelehrung:
2. This AD was posted on 16 July 2008 as PAD 08-082 for consultation until Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder
30 July 2008. No comments were received during the consultation period. zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen.
3. Enquiries regarding this AD should be referred to the Airworthiness
LTAs werden auch im Internet unter http://www.lba.de publiziert
Directives, Safety Management & Research Section, Certification ***
Remarks : Directorate, EASA. E-mail ADs@easa.europa.eu.
4. For any question concerning the technical content of the requirements in
this AD, please contact:
Thielert Aircraft Engines GmbH, Platanenstraße 14
D-09350 Lichtenstein, Germany
Telephone +49-37204-696-0, Fax +49-37204-696-55
E-mail info@centurion-engines.com
EASA Form 110 Page 2/2
Aktenzeichen: (10)T23-502.1/D-2008-278 Seite 1 von 1
[Federal Register: July 16, 2008 (Volume 73, Number 137)] proposed to require removing certain No. 4 bearing oil system components from service at the next
[Rules and Regulations] shop visit or by an end date determined by the engine model.
[Page 40715-40719]
From the Federal Register Online via GPO Access [wais.access.gpo.gov] Examining the AD Docket
[DOCID:fr16jy08-1]
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at
–––––––––––––––––––––––––––––––––– the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and
DEPARTMENT OF TRANSPORTATION other information. The street address for the Docket Operations office (telephone (800) 647-5527) is
provided in the ADDRESSES section. Comments will be available in the AD docket shortly after
Federal Aviation Administration receipt.
14 CFR Part 39 Comments
[Docket No. FAA-2007-28058; Directorate Identifier 2007-NE-08-AD; Amendment 39-15610; We provided the public the opportunity to participate in the development of this AD. We have
AD 2008-14-15] considered the comments received.
RIN 2120-AA64 Requests To Change Compliance Schedule
Airworthiness Directives; International Aero Engines AG (IAE) V2500 Series Turbofan Three commenters, Air Transport Association, United Airlines, and Jet Blue Airways ask that we
Engines change the compliance:
• To require removing the parts only when they access the No. 4 bearing compartment, or
AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). • For engines that don't require access to the No. 4 bearing compartment at the next shop visit, to
permit them to defer removing the parts to the subsequent shop visit, but not later than June 30, 2011.
ACTION: Final rule. The commenters state that changing the compliance times will avoid an undue burden of forcing
every engine visit to access the No. 4 bearing compartment and will avoid aircraft-on-ground
–––––––––––––––––––––––––––––––––– situations due to lack of spare parts.
We don't agree. We developed the compliance requirements to maintain an acceptable level of
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for IAE V2500-A1, V2522- safety for the entire V2500 fleet. Revising the compliance requirements will result in having to
A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, V2533-A5, V2525-D5, and accelerate the program in order to maintain the same level of safety. That will most likely have an
V2528-D5 turbofan engines. This AD requires removing certain No. 4 bearing oil system adverse impact on the fleet, due to forcing additional engine removals. The engine manufacturer,
components from service at the next shop visit or by an end date determined by the engine model. IAE, has also stated that a sufficient supply of spare parts exists to handle incorporation within the
This AD results from instances of oil loss from the No. 4 bearing compartment. We are issuing this compliance requirements of the AD, including unexpected shop visit situations. However, operators
AD to prevent heat damage to high-pressure turbine (HPT) and low-pressure turbine (LPT) critical who have special conditions may propose alternate compliance schedules, if they can show that the
life limited hardware such as the HPT stage 1-2 airseal. Damage to the HPT stage 1-2 airseal could alternate compliance schedules provide an acceptable level of safety. We didn't change the AD.
cause uncontained engine failure and damage to the airplane.
Request To Address Design Deficiencies in the HPT Stage 1-2 Airseal
DATES: This AD becomes effective August 20, 2008.
One commenter, Jet Blue Airways, asks us to revise the AD to address design deficiencies in the
ADDRESSES: The Docket Operations office is located at Docket Management Facility, U.S. HPT Stage 1-2 airseal as a contributor to HPT distress, rather than attributing the root cause of all
Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room HPT Stage 1-2 airseal distress to oil in the turbine. The commenter states that one of the reported
W12-140, Washington, DC 20590-0001. ''confirmed instances of oil loss'' in the turbine is inaccurate. One investigation, which was
categorized as an ''oil in turbine'' event, revealed no substantive evidence of oil loss in the turbine, or
FOR FURTHER INFORMATION CONTACT: Mark Riley, Aerospace Engineer, Engine thermal oil ignition that could have caused the dimensional defects in the HPT Stage 1-2 airseal. It is
Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, not beyond reasonable speculation that, of the remaining 23 events, some percentage was incorrectly
Burlington, MA 01803; telephone (781) 238-7758; fax (781) 238-7199. stated as related to ''No. 4 bearing compartment oil loss.''
We don't agree. We have been involved in the manufacturer's Engineering Investigations for
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a each of the subject ''oil in turbine'' (OIT) events, and agree with the manufacturer's conclusions. Due
proposed AD. The proposed AD applies to IAE V2500-A1, V2522-A5, V2524-A5, V2527-A5, to the operating conditions surrounding the No. 4 bearing compartment, it can be extremely difficult,
V2527E-A5, V2527M-A5, V2530-A5, V2533-A5, V2525-D5, and V2528-D5 turbofan engines. We following engine operation, to detect either evidence of oil loss, or thermo oil ignition. The
published the proposed AD in the Federal Register on July 9, 2007 (72 FR 37126). That action investigation concluded that the HPT Stage 1-2 airseal distress experienced is a result of thermo oil
1 2
ignition and not due to design deficiencies in the HPT Stage 1-2 airseal. The investigation also • Deleted P/N 2A0830-01, Tube, Scavenge, No. 4 Bearing Assy, from Table 2 of the AD.
concluded that measurement of specific HPT Stage 1-2 airseal dimensions is a reliable method of • Deleted P/N 2A1949-01, Tube, Scavenge, No. 4 Bearing Assy, from Table 2 of the AD.
determining if oil ignition has occurred. We did not change the AD. • Deleted P/N 5R8111, Tube A/O Oil, No. 4 Bearing Scav Dif Case to Bif Panel, from Table 2 of
the AD.
Request To Eliminate the Requirement To Incorporate ''OIT Package 2'' • Added paragraph (j) for V2525-D5 and V2528-D5 engines stating that with HPT stage 1 rotor
assembly, P/Ns 2A9521-002 and 2A9621-002, the stage 1 HPT hub metering plug, P/N 2A3182,
The same commenter, Jet Blue, asks us to revise the AD to eliminate the requirement to does not need to be removed.
incorporate the ''OIT Package 2'' for compliance. The ''OIT Package 2'' includes mainly external • Replaced IAE Service Bulletin V2500-ENG-72-0541, Revision 1, dated February 26, 2007, in the
hardware revisions to eliminate ''oil traps'' in the oil scavenge tubes for the No. 4 bearing Related Information paragraph, with IAE Service Bulletin V2500-ENG-72-0541, Revision 4, dated
compartment that may adversely impact oil scavenge capability. The commenter states ''To our March 12, 2008.
knowledge, no V2527-A5 engine incorporating the modification standards of 'OIT Package' have
been found with the reported defects or suspected of No. 4 bearing compartment loss.'' Conclusion
We don't agree. We have reviewed the results of the Engineering Investigation of the No. 4
bearing compartment oil loss events, and agree with the manufacturer's conclusions that all hardware We have carefully reviewed the available data, including the comments received, and determined
identified in Tables 1, 2, and 3 of this AD contribute to the root cause of insufficient oil scavenging that air safety and the public interest require adopting the AD with the changes described previously.
from the No. 4 bearing compartment. We didn't change the AD. We have determined that these changes will neither increase the economic burden on any operator
nor increase the scope of the AD.
Request To Revise the NPRM To State a Significant Economic Impact
Costs of Compliance
The same commenter, Jet Blue, asks us to revise the AD to state that the proposed rule would
have a significant economic impact. The commenter states that the modification would cost more We estimate that this AD will affect 686 engines installed on airplanes of U.S. registry. Of those
than $8,000,000 for its fleet. 686 engines, the operators of nineteen V2500-A1 engines, thirty -A5 engines and twenty-one -D5
We don't agree. In order for us to categorize an AD as a ''significant economic impact'' to engines have already complied with the requirements in this AD.
operators, the total cost of the AD must exceed $100,000,000 per year. We based our economic
assessment for this AD on actual hardware replacement cost (using the manufacturer's spare parts Costs of Compliance per Year by Engine Model
pricing), the estimated number of work-hours (at $80 per hour) required to comply with the AD, and
Engine model Number of Total Total Total cost
the estimated number of shop visits per year. Based on those figures, we estimate the cost of the
engines labor cost parts cost per year
proposed AD to U.S. operators to be $45,037,165 per year, which is below the $100,000,000
per year per year per year
threshold criterion. We didn't change the AD.
V2500–A1 33 $355,080 $7,230,564 $7,585,644
Request To Incorporate IAE Service Bulletin V2500-ENG-72-0541 Into the AD
V2522–A5, V2524–A5, V2527–A5, V2527E– 142 1,368,880 35,790,816 37,159,696
A5, V2527M–A5, V2530–A5, V2533–A5
The same commenter, Jet Blue Airways, requests that we revise the AD to incorporate IAE
Service Bulletin (SB) V2500-ENG-72-0541 into the AD. The commenter states that tracking all of V2525–D5, V2528–D5 5 15,400 276,425 291,825
the individual parts listed in the AD, especially from parts that are not serialized, is cumbersome and
beyond reasonable and customary standards. Based on these figures, we estimate the total cost of this AD to U.S. operators to be $45,037,165
We don't agree. Due to the complexity of the various IAE SBs, we determined that it would be per year.
clearer to list in the AD, only the parts that operators must remove from service. We list IAE SB
V2500-ENG-72-0541 in the Related Information section of the AD. That SB provides specific Authority for This Rulemaking
instructions and the current replacement part information. Listing only the parts that the operators
must remove from service also provides operators with increased flexibility for installing other Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety.
approved parts not listed in the IAE SB. However, we have added a statement in the Compliance Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation
section of the AD that states ''If you have accomplished IAE Service Bulletin V2500-ENG-72-0541, Programs, describes in more detail the scope of the Agency's authority.
Revision 4, dated March 12, 2008, you have complied with this AD.'' We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III,
section 44701, ''General requirements.'' Under that section, Congress charges the FAA with
Request To Correct Certain Information in the AD promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices,
methods, and procedures the Administrator finds necessary for safety in air commerce. This
One commenter, IAE, asks us to correct certain information in the Compliance section of the regulation is within the scope of that authority because it addresses an unsafe condition that is likely
AD. to exist or develop on products identified in this rulemaking action.
We agree. We have:
• Corrected the part number (P/N) for the Seal Assembly, No. 4 Bearing, Front, in Table 2 of the
AD, from P/N 2A0853 to P/N 2A2055.
3 4
Regulatory Findings AIRWORTHINESS DIRECTIVE
FAA
We have determined that this AD will not have federalism implications under Executive Order Aircraft Certification Service www.faa.gov/aircraft/safety/alerts/
13132. This AD will not have a substantial direct effect on the States, on the relationship between the www.gpoaccess.gov/fr/advanced.html
national government and the States, or on the distribution of power and responsibilities among the
various levels of government. 2008-14-15 International Aero Engines AG (IAE): Amendment 39-15610. Docket No. FAA-2007-
For the reasons discussed above, I certify that this AD: 28058; Directorate Identifier 2007-NE-08-AD.
(1) Is not a ''significant regulatory action'' under Executive Order 12866;
(2) Is not a ''significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, Effective Date
February 26, 1979); and
(3) Will not have a significant economic impact, positive or negative, on a substantial number of (a) This airworthiness directive (AD) becomes effective August 20, 2008.
small entities under the criteria of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. Affected ADs
You may get a copy of this summary at the address listed under ADDRESSES.
(b) None.
List of Subjects in 14 CFR Part 39
Applicability
Air transportation, Aircraft, Aviation safety, Safety.
(c) This AD applies to IAE V2500-A1, V2522-A5, V2524-A5, V2527-A5, V2527E-A5,
Adoption of the Amendment V2527M-A5, V2530-A5, V2533-A5, V2525-D5, and V2528-D5 turbofan engines with a part listed
by part number (P/N) in this AD installed. These engines are installed on, but not limited to, Airbus
Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation A319, A320, A321, and McDonnell Douglas MD-90 airplanes.
Administration amends 14 CFR part 39 as follows:
Unsafe Condition
PART 39–AIRWORTHINESS DIRECTIVES
(d) This AD results from instances of oil loss from the No. 4 bearing compartment. We are
1. The authority citation for part 39 continues to read as follows: issuing this AD to prevent heat damage to high-pressure turbine (HPT) and low-pressure turbine
(LPT) critical life limited hardware such as the HPT stage 1-2 airseal. Damage to the HPT stage 1-2
Authority: 49 U.S.C. 106(g), 40113, 44701. airseal could cause uncontained engine failure and damage to the airplane.
§ 39.13 [Amended] Compliance
2. The FAA amends § 39.13 by adding the following new airworthiness directive: (e) You are responsible for having the actions required by this AD performed within the
compliance times specified unless the actions have already been done.
V2500-A1 Engines
(f) For V2500-A1 engines, remove the parts listed by P/N in the following Table 1 of this AD at
the next shop visit after the effective date of this AD but not later than November 30, 2008. The ATA
chapter reference of the IAE V2500-A1 engine manual (E-V2500-1IA) contains information on
removing the parts.
Table 1.–V2500-A1 Parts To Be Removed
ATA chapter P/N Nomenclature
reference
72–42–20 2A0367–01 Tube Assy of, Weep, No. 4 Bearing Outer.
72–42–20 2A2873–01 Tube Assy of, Weep, No. 4 Bearing Outer.
72–42–20 2A0830–01 Tube, Scavenge, No. 4 Bearing Assy.
72–42–20 2A1949–01 Tube, Scavenge, No. 4 Bearing Assy.
5 6
72–42–20 2A2028–01 Tube, Scavenge, No. 4 Bearing Assy. V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 Engines
72–42–20 2A0830–001 Tube, Scavenge, No. 4 Bearing Assy. (g) For V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-
72–42–20 2A2274–01 Tube, Scavenge, No. 4 Bearing Assy. A5 engines, remove the parts listed by P/N in the following Table 2 of this AD at the next shop visit
after the effective date of this AD but not later than June 30, 2011. The ATA chapter reference of the
72–42–33 2A0853 Seal Assy, No. 4 Bearing, Front. IAE V2500-A5 engine manual (E-V2500-1IA) contains information on removing the parts.
72–42–33 2A2055 Seal Assy, No. 4 Bearing, Front.
Table 2.–V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5
72–42–33 2A2834 Seal Assy, No. 4 Bearing, Front. Parts To Be Removed
72–42–33 2A2930 Seal Assy, No. 4 Bearing, Front.
ATA chapter P/N Nomenclature
72–42–33 2A3525 Seal Assy, No. 4 Bearing, Front. reference
72–42–33 2A3538 Seal Assy, No. 4 Bearing, Front. 72–42–20 2A0367–01 Tube Assy of, Weep, No. 4 Bearing Outer.
72–42–33 2A0851 Support Assy, No. 4 Bearing Seal. 72–42–20 2A2873–01 Tube Assy of, Weep, No. 4 Bearing Outer.
72–42–33 2A2833 Support, No. 4 Bearing, Seal Assy. 72–42–33 2A2055 Seal Assy, No. 4 Bearing, Front.
72–42–33 2A3537 Support, No. 4 Bearing Seal Assy. 72–42–33 2A2834 Seal Assy, No. 4 Bearing, Front.
72–42–35 2A0892–01 Duct Assy, Cooling Air, No. 4 Bearing, Front. 72–42–33 2A2930 Seal Assy, No. 4 Bearing, Front.
72–42–35 2A2257–01 Duct Assy, Cooling Air, No. 4 Bearing, Front. 72–42–33 2A3525 Seal Assy, No. 4 Bearing, Front.
72–43–20 2A2056 Seal Assy, No. 4 Bearing, Rear. 72–42–33 2A3538 Seal Assy, No. 4 Bearing, Front.
72–43–20 2A2931 Seal Assy, No. 4 Bearing, Rear. 72–42–33 2A0851 Support Assy, No. 4 Bearing Seal.
72–43–20 2A3526 Seal Assy, No. 4 Bearing, Rear. 72–42–33 2A2833 Support, No. 4 Bearing, Seal Assy.
72–43–20 2A0847 Seal Ring Holder. 72–42–33 2A3537 Support, No. 4 Bearing Seal Assy.
72–43–20 2A0891–01 Duct Assy, Cooling Air, No. 4 Bearing, Rear. 72–42–35 2A0892–01 Duct Assy, Cooling Air, No. 4 Bearing, Front.
72–43–20 2A1205–01 Duct Assy, Cooling Air, No. 4 Bearing, Rear. 72–42–35 2A2257–01 Duct Assy, Cooling Air, No. 4 Bearing, Front.
72–43–20 2A3078–01 Duct Assy, Cooling Air, No. 4 Bearing, Rear. 72–43–20 2A2056 Seal Assy, No. 4 Bearing, Rear.
72–45–11 2A0594 Metering Plug, HPT Hub, Stage 1. 72–43–20 2A2931 Seal Assy, No. 4 Bearing, Rear.
72–45–11 2A1040 Metering Plug, HPT Hub, Stage 1. 72–43–20 2A3526 Seal Assy, No. 4 Bearing, Rear.
72–45–11 2A2181 Metering Plug, HPT Hub, Stage 1. 72–43–20 2A0847 Seal Ring Holder.
72–45–13 2A0884 Seal Air, HPT Stage 1. 72–43–20 2A0891–01 Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72–45–13 2A1203 Seal Air, HPT Stage 1. 72–43–20 2A1205–01 Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72–45–13 2A0884–001 Seal Air, HPT Stage 1. 72–43–20 2A3078–01 Duct Assy, Cooling Air, No. 4 Bearing, Rear.
79–22–49 5R8111 Tube A/O Oil—No. 4 Brg Scav Dif Case to Bif Panel. 72–45–11 2A0594 Metering Plug, HPT Hub, Stage 1.
79–22–49 5R8138 Tube A/O Oil—No. 4 Brg Scav Dif Case to Bif Panel. 72–45–11 2A1040 Metering Plug, HPT Hub, Stage 1.
79–22–49 6A5367 Tube A/O Oil—No. 4 Brg Scav Dif Case to Bif Panel. 72–45–11 2A2354 Metering Plug, HPT Hub, Stage 1.
79–22–49 5A9083 Tube A/O Oil—No. 4 Brg Discon to Discon. 72–45–11 2A3182 Metering Plug, HPT Hub, Stage 1.
79–22–49 5A9084 Tube A/O Oil—No. 4 Brg Discon to Scav Valve. 72–45–13 2A1352 Seal Air, HPT Stage 1.
79–22–49 5A8573 Tube A/O Oil—Press ‘T’To Pressure Transducer. 72–45–13 2A3032 Seal Air, HPT Stage 1.
79–23–51 1648MK2 Scavenge Valve. 79–22–49 5R8138 Tube A/O Oil—No. 4 Brg Scav Dif Case to Bif Panel.
79–22–49 6A5367 Tube A/O Oil—No. 4 Brg Scav Dif Case to Bif Panel.
7 8
79–22–49 5A9083 Tube A/O Oil—No. 4 Brg Discon to Discon. (j) For V2525-D5 and V2528-D5 engines with HPT stage 1 rotor assembly, P/Ns 2A9521-002
and 2A9621-002, the stage 1 HPT hub metering plug, P/N 2A3182, does not need to be removed.
79–22–49 5A9084 Tube A/O Oil—No. 4 Brg Discon to Scav Valve.
79–22–49 5A8573 Tube A/O Oil—Press ‘T’To Pressure Transducer. Previous Credit
(k) If you have accomplished IAE Service Bulletin V2500-ENG-72-0541, Revision 4, dated
(h) For V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-
March 12, 2008, you have complied with this AD.
A5 engines with HPT stage 1 rotor assembly, P/Ns 2A9521-002 and 2A9621-002, the stage 1 HPT
hub metering plug, P/N 2A3182, does not need to be removed.
(l) After the effective date of this AD, do not install any part that has a P/N listed in this AD.
V2525-D5 and V2528-D5 Engines
Alternative Methods of Compliance
(i) For V2525-D5 and V2528-D5 engines, remove the parts listed by P/N in the following Table
(m) The Manager, Engine Certification Office, has the authority to approve alternative methods
3 of this AD at the next shop visit after the effective date of this AD but not later than June 30, 2011.
of compliance for this AD if requested using the procedures found in 14 CFR 39.19.
The ATA chapter reference of the IAE V2500-D5 engine manual (E-V2500-3IA) contains
information on removing the parts.
Related Information
Table 3.–V2525-D5 and V2528-D5 Parts To Be Removed
(n) International Aero Engines Service Bulletin No. V2500-ENG-72-0541, Revision 4, dated
ATA chapter P/N Nomenclature March 12, 2008, pertains to the subject of this AD.
reference
(o) Contact Mark Riley, Aerospace Engineer, Engine Certification Office, FAA, Engine and
72–42–20 2A0367–01 Tube Assy of, Weep, No. 4 Bearing Outer. Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238-
72–42–20 2A2873–01 Tube Assy of, Weep, No. 4 Bearing Outer. 7758; fax (781) 238-7199, for more information about this AD.
72–42–33 2A0851 Support Assy, No. 4 Bearing Seal.
Material Incorporated by Reference
72–42–33 2A2833 Support, No. 4 Bearing, Seal Assy.
(p) None.
72–42–33 2A3537 Support, No. 4 Bearing Seal Assy.
72–42–33 2A2834 Seal Assy, No. 4 Bearing, Front. Issued in Burlington, Massachusetts, on July 2, 2008.
72–42–33 2A2930 Seal Assy, No. 4 Bearing, Front. Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service.
72–42–33 2A3525 Seal Assy, No. 4 Bearing, Front. [FR Doc. E8-15686 Filed 7-15-08; 8:45 am]
72–42–33 2A3538 Seal Assy, No. 4 Bearing, Front.
72–42–35 2A2257–01 Duct Assy, Cooling Air, No. 4 Bearing, Front.
72–43–20 2A2056 Seal Assy, No. 4 Bearing, Rear.
72–43–20 2A2931 Seal Assy, No. 4 Bearing, Rear.
72–43–20 2A3526 Seal Assy, No. 4 Bearing, Rear.
72–43–20 2A0847 Seal Ring Holder.
72–43–20 2A1205–01 Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72–43–20 2A3078–01 Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72–45–11 2A3182 Metering Plug, HPT Hub, Stage 1.
72–45–11 2A2354 Metering Plug, HPT Hub, Stage 1.
72–45–13 2A1352 Seal Air, HPT Stage 1.
72–45–13 2A3032 Seal Air, HPT Stage 1.
9 10
EASA AD No : 2008-0133
Lufttüchtigkeitsanweisung EASA AIRWORTHINESS DIRECTIVE
LTA-Nr.: D-2008-279
AD No.: 2008-0133
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 12.08.2008
Muster: TURBOMECA AD der ausländischen Behörde:
ARRIUS EASA AD 2008-0133 vom 17.07.2008 Date: 17 July 2008
Geräte-Nr.: Technische Mitteilungen des Herstellers: Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with
7032, DGAC M-16, EASA.E.080 Turbomeca Service Bulletin No. 319 72 0811 Regulation (EC) No 216/2008 on behalf of the European Community, its Member States
and of the European third countries that participate in the activities of EASA under Article
66 of that Regulation.
Betroffenes Luftfahrtgerät:
This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the
continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may
TURBOMECA operate an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of that Airworthiness
ARRIUS Directive unless otherwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the
State of Registry [EC 216/2008, Article 14(4) exemption].
- Baureihen: ARRIUS 1A
Type Approval Holder’s Name : Type/Model designation(s) :
- Werk-Nrn.: alle
TURBOMÉCA ARRIUS 1A turbo-shaft engine
Betrifft:
Reduzierung der zulässigen Betriebszeiten des ''Balancing Pistons'' aufgrund eines Rechenfehlers bei TCDS Number : France No. M16
der ursprünglichen Lebensdauerberechnung des Bauteils.
Foreign AD : Not applicable
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA
Airworthiness Directive und der genannten technischen Mitteilung des Herstellers zu entnehmen. Supersedure : None
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß,
vollständig und innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente
durchgeführt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeits-
anweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt. ATA 73 Engine Fuel & Control - Balancing Piston Life Limit - Reduction
Fristen:
Alle anzuwendenden Fristen sind der oben genannten EASA Airworthiness Directive zu entnehmen.
Manufacturer(s): Turboméca
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
EASA Airworthiness Directive.
Applicability: ARRIUS 1A turbo-shaft engines, all serial numbers.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
EASA AD 2008-0133 vom 17.07.2008 These engines are known to be installed on, but not limited to,
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen Eurocopter AS355N helicopters.
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. Reason: Cycle life limit value for ARRIUS 1A balancing piston Part Number
(P/N) 0 319 20 152 0, initially set at 40 000 cycles, has been reduced to
Rechtsbehelfsbelehrung: 16 000 cycles, following the discovery of a calculation error during a
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.
recent review of the ARRIUS 1 engine family files.
LTAs werden auch im Internet unter http://www.lba.de publiziert As of the publication date of this Airworthiness Directive, no ARRIUS 1A
*** engines in service are fitted with a balancing piston that has logged more
than 16 000 cycles, and the outlook for the consumption of cycles on the
ARRIUS 1A fleet indicates that no balancing pistons will exceed this new
limit for a few years’ time.
Moreover, this new cycle life limit value for the balancing piston has been
incorporated end of 2007 in ARRIUS 1A Maintenance documentation.
Failure to comply with the new life limits provided in the Airworthiness
Limitations Section of ARRIUS 1A Maintenance documentation could
potentially result in an engine in-flight-shutdown and the release of high
energy debris.
EASA Form 110 Page 1/2
Aktenzeichen: (10)T23-502.1/D-2008-279 Seite 1 von 1
EASA AD No : 2008-0133
Effective Date: 31 July 2008 Lufttüchtigkeitsanweisung
LTA-Nr.: D-2008-280
Required action(s) Required as indicated, unless accomplished previously:
and Compliance Luftfahrt-Bundesamt
Before 31 December 2008, modify the cycle life limit value of the Datum der Bekanntgabe: 12.08.2008
Time(s):
balancing piston in the engine log book in accordance with the instructions
of Turboméca Mandatory Service Bulletin N° 319 72 0811 and update Muster: TURBOMECA AD der ausländischen Behörde:
accordingly the approved operator’s maintenance programme. ARRIUS 2 EASA AD 2008-0134 vom 17.07.2008
Geräte-Nr.: Technische Mitteilungen des Herstellers:
Ref. Publications:
Turboméca Service Bulletin N° 319 72 0811 original issue 7004, DGAC TCDS M-22 Turbomeca Service Bulletin No. 319 75 4810
The use of later approved revisions of this document is acceptable for
compliance with the requirements of this AD. Betroffenes Luftfahrtgerät:
TURBOMECA
Remarks : 1. If requested and appropriately substantiated, EASA can approve
ARRIUS 2
Alternative Methods of Compliance for this AD.
2. This AD was posted on 09 July 2008 as PAD 08-067 for consultation - Baureihen: ARRIUS 2F
until 11 June 2008. No comments were received during the
consultation period. - Werk-Nrn.: alle
3. Enquiries regarding this AD should be referred to the Airworthiness
Directives, Safety Management & Research Section, Certification Betrifft:
Directorate, EASA. E-mail ADs@easa.europa.eu. Mögliche Störungen in der Kraftstoffversorgung des Triebwerks durch Bruch der ''P3 Air Pipe'' infolge
von Scheuerstellen aufgrund fehlerhafter Bauteilabstände zu anderen Triebwerkskomponenten.
4. For any question concerning the technical content of the requirements
in this AD, please contact: Maßnahmen:
Turboméca, S.A., ARRIUS Customer Support, 40220 TARNOS,
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA
FRANCE. Fax: +33 5 59 74 45 15, or contact your nearest technical
Airworthiness Directive und der genannten technischen Mitteilung des Herstellers zu entnehmen.
representative at www.turbomeca-support.com
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß,
vollständig und innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente
durchgeführt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeits-
anweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
Fristen:
Alle anzuwendenden Fristen sind der oben genannten EASA Airworthiness Directive zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
EASA Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
EASA AD 2008-0134 vom 17.07.2008
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
***
EASA Form 110 Page 2/2
Aktenzeichen: (10)T23-502.1/D-2008-280 Seite 1 von 1
EASA AD No: 2008-0134 EASA AD No: 2008-0134
EASA AIRWORTHINESS DIRECTIVE Effective Date: 31 July 2008
AD No.: 2008-0134 Required as indicated, unless accomplished previously:
Within 100 operating hours after the effective date of this AD, in
accordance with the instructions of Turbomeca Mandatory Service Bulletin
N° 319 75 4810:
Date: 17 July 2008 Required action(s)
and Compliance Visually inspect P3 air pipe (first section) and RH rear half-wall.
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with
Time(s): Inspect play between P3 air pipe (first section) and RH rear half-wall.
Regulation (EC) No 216/2008 on behalf of the European Community, its Member States Replace P3 air pipe (first section) if any damage is found.
and of the European third countries that participate in the activities of EASA under Article Readjust the first section of the P3 air pipe if the inspected
66 of that Regulation. clearance is found to be not compliant.
This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the Replace RH rear half-wall if any damage is found.
continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may
operate an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of that Airworthiness Turboméca Service Bulletin N° 319 75 4810 original issue
Directive unless otherwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the
State of Registry [EC 216/2008, Article 14(4) exemption]. Ref. Publications: The use of later approved revisions of this document is acceptable for
compliance with the requirements of this AD.
Type Approval Holder’s Name : Type/Model designation(s) :
1. If requested and appropriately substantiated, EASA can approve
TURBOMÉCA ARRIUS 2F turbo-shaft engine Alternative Methods of Compliance for this AD.
2. This AD was posted on 09 July 2008 as PAD 08-068 for consultation
TCDS Number : France No. M22 until 11 June 2008. No comments were received during the
consultation period.
Foreign AD : Not applicable 3. Enquiries regarding this AD should be referred to the Airworthiness
Remarks : Directives, Safety Management & Research Section, Certification
Supersedure : None Directorate, EASA. E-mail ADs@easa.europa.eu.
4. For any question concerning the technical content of the requirements
in this AD, please contact:
Turboméca, S.A., ARRIUS Customer Support, 40220 TARNOS,
ATA 73 Engine Fuel & Control - P3 Air Pipe – Inspection/Modification FRANCE. Fax: +33 5 59 74 45 15, or contact your nearest technical
representative at www.turbomeca-support.com
Manufacturer(s): Turboméca
ARRIUS 2F turbo-shaft engines, all serial numbers.
Applicability: These engines are known to be installed on, but not limited to,
Eurocopter EC120B helicopters.
On several ARRIUS 2F engines, the clearance between the P3 air pipe
P/N 0319719180 and the rear right bulkhead P/N 0319998240 has been
found to be too small.
Investigations have shown that both P3 air pipe and rear right bulkhead
were compliant to the design. The Turbomeca Engineering Department
concluded that the tolerance of assembly established during the design
could result in some rubbing between parts.
Reason:
Rubs between the pipe and the bulkhead may lead to premature wearing
and finally rupture of the P3 air pipe. The loss of P3 air pressure would
then force the fuel control system to idle which could have a detrimental
effect in critical phases of flight.
For the reason stated above, this Airworthiness Directive (AD) requires the
inspection of the P3 air pipe (first section) and RH rear half-wall and, in
case it is found damaged or non-compliant (idem), the replacement or
readjustment of parts.
EASA Form 110 Page 1/2 EASA Form 110 Page 2/2
