Nachrichten für Luftfahrer 2009 Teil II (weicht ggf. von Druckversion ab)
Special Flight Permits
(i) Under 14 CFR part 39.23, we are prohibiting special flight permits for this AD. Lufttüchtigkeitsanweisung
LTA-Nr.: D-2009-207
Related Information
Luftfahrt-Bundesamt
(j) Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Datum der Bekanntgabe: 14.08.2009
Directorate, 12 New England Executive Part, Burlington, MA 01803; e-mail: robert.green@faa.gov; Muster: Pratt & Whitney AD der ausländischen Behörde:
telephone (781) 238-7754; fax (781) 238-7199. PW2000 FAA AD 2009-14-05 Amdt. 39-15955
Geräte-Nr.: Technische Mitteilungen des Herstellers:
Material Incorporated by Reference 6310 Pratt & Whitney Alert Service Bulletin No. PW2000 A72-736 vom
05.01.2009
(k) None.
Betroffenes Luftfahrtgerät:
Issued in Burlington, Massachusetts, on June 25, 2009.
Pratt & Whitney
Peter A. White, PW2000
Assistant Manager, Engine and Propeller Directorate,
Aircraft Certification Service. - Baureihen: PW2037, PW2037(M) und PW2040
- Werk-Nrn.: Nähere Angaben zu betroffenen Verdichterscheiben sind der genannten FAA Airworthiness
Directive zu entnehmen.
Betrifft:
Möglicher Bruch von Verdichterscheiben, Stufe 12 Hochdruckverdichter, durch Rissbildung.
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten FAA
Airworthiness Directive und der genannten technischen Mitteilung 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
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 FAA Airworthiness Directive zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
FAA Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
FAA AD 2009-14-05 Amdt. 39-15955
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
***
5
Aktenzeichen: (10)T23-502.1/D-2009-207 Seite 1 von 1
[Federal Register: July 8, 2009 (Volume 74, Number 129)] Contact Pratt & Whitney, 400 Main Street, East Hartford, CT 06108, for the service information
[Rules and Regulations] identified in This AD.
[Page 32421-32423]
From the Federal Register Online via GPO Access [wais.access.gpo.gov] SUPPLEMENTARY INFORMATION: In November 2006, a Pratt & Whitney model PW2037
[DOCID:fr08jy09-10] turbofan engine was found to have a cracked HPC 12th stage disk during routine overhaul. The crack
extended from the disk bore to the disk rim. Investigation by Pratt & Whitney revealed that the disk
–––––––––––––––––––––––––––––––––– had a material defect that occurred during original manufacture. In July 2007, a second HPC 12th
stage disk was found cracked with the same defect. In response to the cracking, Pratt & Whitney
DEPARTMENT OF TRANSPORTATION issued Alert Service Bulletin (ASB) No. PW2000 A72-736 on January 5, 2009, recommending
removal of 26 additional HPC 12th stage disks, manufactured from this same material heat. Pratt
Federal Aviation Administration concluded that this population might have the same material defects and therefore, be susceptible to
cracking. Thereafter, in February 2009, after Pratt & Whitney issued the ASB, we became aware of
14 CFR Part 39 four additional HPC 12th stage disks, manufactured from the same material heat, that had small
cracks in the disk bores that originated from similar material defects. Because of Pratt & Whitney's
[Docket No. FAA-2009-0417; Directorate Identifier 2009-NE-13-AD; Amendment 39-15955; recommended short compliance times in the ASB, we are issuing this final rule; request for
AD 2009-14-05] comments AD. This condition, if not corrected, could result in uncontained failure of the HPC 12th
stage disk and airplane damage.
RIN 2120-AA64
Relevant Service Information
Airworthiness Directives; Pratt & Whitney Models PW2037, PW2037(M), and PW2040
Turbofan Engines We have reviewed and approved the technical contents of Pratt & Whitney ASB No. PW2000
A72-736, dated January 5, 2009. That ASB describes procedures for having Pratt & Whitney perform
AGENCY: Federal Aviation Administration (FAA), DOT. the special eddy-current inspection performed on the 12th stage disks.
ACTION: Final rule; request for comments. Differences Between This AD and the Service Information
–––––––––––––––––––––––––––––––––– The recommended compliance times in the Pratt & Whitney ASB are stated as calendar dates for
each engine model. We specify cycles-in-service rather than calendar dates, because the risk of crack
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney models development is cycle, not time dependant.
PW2037, PW2037(M), and PW2040 turbofan engines. This AD requires 12th stage disks of certain
high-pressure compressor (HPC) drum rotor disk assemblies, to be inspected for cracks by Pratt & FAA's Determination and Requirements of This AD
Whitney using a special eddy current inspection procedure. This AD results from six HPC 12th stage
disks found cracked during HPC module disassembly at overhaul. We are issuing this AD to prevent The unsafe condition described previously is likely to exist or develop on other Pratt & Whitney
uncontained failure of the HPC 12th stage disk and airplane damage. models PW2037, PW2037(M), and PW2040 turbofan engines of the same type design. For that
reason, we are issuing this AD to prevent uncontained failure of the HPC 12th stage disk and airplane
DATES: This AD becomes effective July 23, 2009. The Director of the Federal Register approved damage. This AD requires 12th stage disks of certain HPC drum rotor disk assemblies, to be
the incorporation by reference of certain publications listed in the regulations as of July 23, 2009. inspected for cracks by Pratt & Whitney using a special eddy current inspection procedure.
We must receive any comments on this AD by September 8, 2009.
FAA's Determination of the Effective Date
ADDRESSES: Use one of the following addresses to comment on this AD:
• Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for Since an unsafe condition exists that requires the immediate adoption of this AD, we have found
sending your comments electronically. that notice and opportunity for public comment before issuing this AD are impracticable, and that
• Mail: U.S. Docket Management Facility, Department of Transportation, 1200 New Jersey good cause exists for making this amendment effective in less than 30 days.
Avenue, SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-0001.
• Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Comments Invited
Friday, except Federal holidays.
• Fax: (202) 493-2251. This AD is a final rule that involves requirements affecting flight safety and was not preceded by
notice and an opportunity for public comment; however, we invite you to send us any written relevant
FOR FURTHER INFORMATION CONTACT: Mark Riley, Aerospace Engineer, Engine data, views, or arguments regarding this AD. Send your comments to an address listed under
Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, ADDRESSES. Include ''AD Docket No. FAA-2009-0417; Directorate Identifier 2009-NE-13-AD'' in
Burlington, MA 01803; e-mail: mark.riley@faa.gov; telephone (781) 238-7758, fax (781) 238-7199. the subject line of your comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might suggest a need to modify it.
1 2
We will post all comments we receive, without change, to http://www.regulations.gov, including PART 39–AIRWORTHINESS DIRECTIVES
any personal information you provide. We will also post a report summarizing each substantive
verbal contact with FAA personnel concerning this AD. Using the search function of the Web site, 1. The authority citation for part 39 continues to read as follows:
anyone can find and read the comments in any of our dockets, including, if provided, the name of the
individual who sent the comment (or signed the comment on behalf of an association, business, labor Authority: 49 U.S.C. 106(g), 40113, 44701.
union, etc.). You may review the DOT's complete Privacy Act Statement in the Federal Register
published on April 11, 2000 (65 FR 19477-78). § 39.13 [Amended]
Examining the AD Docket 2. The FAA amends § 39.13 by adding the following new airworthiness directive:
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
other information. The street address for the Docket Operations office (telephone (800) 647-5527) is
the same as the Mail address provided in the ADDRESSES section. Comments will be available in
the AD docket shortly after receipt.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety.
Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation
Programs, describes in more detail the scope of the Agency's authority.
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
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
regulation is within the scope of that authority because it addresses an unsafe condition that is likely
to exist or develop on products identified in this rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States, on the relationship between the
national Government and the States, or on the distribution of power and responsibilities among the
various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ''significant regulatory action'' under Executive Order 12866;
2. Is not a ''significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034,
February 26, 1979); and
3. Will not have a significant economic impact, positive or negative, on a substantial number of
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.
You may get a copy of this summary at the address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Under the authority delegated to me by the Administrator, the Federal Aviation Administration
amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
3 4
AIRWORTHINESS DIRECTIVE R80315 M1/LALY-4025
FAA R80309 M1/LALY-4024
www.faa.gov/aircraft/safety/alerts/
Aircraft Certification Service
www.gpoaccess.gov/fr/advanced.html R80341 M1/LALY-4023
R80329 M1/LALY-4022
2009-14-05 Pratt & Whitney: Amendment 39-15955. Docket No. FAA-2009-0417; Directorate R80312 M1/LALY-4020
Identifier 2009-NE-13-AD.
R80321 M1/LALY-4019
Effective Date R80319 M2/LALY-4040
R80358 M2/LALY-4039
(a) This airworthiness directive (AD) becomes effective July 23, 2009.
R80302 M2/LALY-4038
Affected ADs
R80336 M2/LALY-4037
(b) None.
These engines are installed on, but not limited to, Boeing 757-200 and 757-300 airplanes.
Applicability
Unsafe Condition
(c) This AD applies to Pratt & Whitney models PW2037, PW2037(M), and PW2040 turbofan
engines, with the following high-pressure compressor (HPC) drum rotor disk assemblies installed: (d) This AD results from six HPC 12th stage disks found cracked during HPC module
disassembly at overhaul. We are issuing this AD to prevent uncontained failure of the HPC 12th stage
Table 1–Affected HPC Drum Rotor Disk Assemblies disk and airplane damage.
Drum Rotor Disk Assembly 12th Stage Disk Billet Compliance
Part Number 1B3702; 1B3702- and Heat Number
001; 1B3610; 1B3610-001; or (e) You are responsible for having the actions required by this AD performed at the following
1B7377 – Serial Number compliance times:
T62805 T/LALY-4013 (1) For PW2040 turbofan engines, within 200 cycles-in-service (CIS) after the effective date of
this AD, unless the actions have already been done.
R80293 T/LALY-4012 (2) For PW2037 and PW2037(M) turbofan engines, within 400 CIS after the effective date of
R80289 T/LALY-4010 this AD, unless the actions have already been done.
R80322 T/LALY-4009 Non-Destructive Inspection
R80330 T/LALY-4008
(f) Have a special eddy-current inspection performed on the 12th stage disks installed in the HPC
R78394 T/LALY-4007 drum rotor disk assemblies listed in Table 1 of this AD, for cracks. Use paragraph 1 of the
R80281 T/LALY-4006 Accomplishment Instructions of Pratt & Whitney Alert Service Bulletin No. PW2000 A72-736, dated
January 5, 2009, to do the special eddy current inspection.
R80304 T/LALY-4005
R80343 T/LALY-4004 Alternative Methods of Compliance
R80299 T/LALY-4003
(g) The Manager, Engine Certification Office, has the authority to approve alternative methods
R80313 T/LALY-4002 of compliance for this AD if requested using the procedures found in 14 CFR 39.19.
R80333 M1/LALY-4035
Related Information
R80324 M1/LALY-4034
R80310 M1/LALY-4033 (h) Contact Mark Riley, Aerospace Engineer, Engine Certification Office, FAA, Engine and
Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail:
R80326 M1/LALY-4030 mark.riley@faa.gov; telephone (781) 238-7758, fax (781) 238-7199.
R80305 M1/LALY-4026
5 6
Material Incorporated by Reference
(i) You must use Pratt & Whitney Alert Service Bulletin No. PW2000 A72-736, dated January 5, Lufttüchtigkeitsanweisung
2009, to have the special eddy current inspections performed by this AD. The Director of the Federal LTA-Nr.: D-2009-208
Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact Pratt & Whitney, 400 Main Street, East Hartford, CT 06108, for a Luftfahrt-Bundesamt
copy of this service information. You may review copies at the FAA, New England Region, 12 New Datum der Bekanntgabe: 14.08.2009
England Executive Park, Burlington, MA; or at the National Archives and Records Administration Muster: Pilatus AD der ausländischen Behörde:
(NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: Pilatus PC-9 BAZL LTA HB-2009-008 vom 27.07.2009
http://www.archives.gov/federal-register/cfr/ibr-locations.html. Geräte-Nr.: Technische Mitteilungen des Herstellers:
2068, FOCA TCDS F56-22 Pilatus PC-9 Service Bulletin 57-015
Issued in Burlington, Massachusetts, on June 23, 2009.
Peter A. White, Betroffenes Luftfahrtgerät:
Assistant Manager, Engine and Propeller Directorate,
Aircraft Certification Service. Pilatus
Pilatus PC-9
- Baureihen: PC-9, PC-9/A, PC-9/B und PC-9/F
- Werk-Nrn.: Manufacturer Serial Numbers (MSN)
101 bis 188
501 bis 567
Betrifft:
Inner Wing – Wing Bottom Skin between Ribs 5 and 11 – Inspection
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten BAZL
Lufttüchtigkeitsanweisung und der genannten technischen Mitteilung 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
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 BAZL Lufttüchtigkeitsanweisung zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten
BAZL Lufttüchtigkeitsanweisung.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
BAZL LTA HB-2009-008 vom 27.07.2009
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
***
7
Aktenzeichen: (01)T23-502.1/D-2009-208 Seite 1 von 1
Federal Department of the Environment, Transport, Energy and
Communications DETEC Lufttüchtigkeitsanweisung (LTA) FOCA AD
Consigne de Navigabilité (CN)
Federal Office of Civil Aviation FOCA
Direttive sulla Navigabilità (DN) HB-2009-008
Safety Division - Aircraft
Airworthiness Directive (AD)
(3) If during the inspection required by § (1) of this AD, damage, such
Lufttüchtigkeitsanweisung (LTA) FOCA AD
as rivet heads pulled through the skin panel, loose rivets or “working”
Consigne de Navigabilité (CN)
HB-2009-008 rivets are found, perform the corrective actions within the required
Direttive sulla Navigabilità (DN)
time frame as specified by § 3.A.(3) (d,e) of PILATUS PC-9 Service
Airworthiness Directive (AD)
Bulletin No. 57-015.
Inkraftsetzung
Mise en viguer
27 July 2009
Pilatus – PC-9 (4) If cracks, starting from pulled, loose or “working” rivets holes are
Entrata in vigore found, the aircraft is not allowed to fly before an approved repair,
Effective Date FOCA TC/TCDS No: F56-22
which restores the structural strength and stiffness, is embodied.
Issue Date: 13 July 2009
Ref. Publication(s): PILATUS PC-9 Service Bulletin No. 57-015, initial issue.
ATA Chapter ATA 57 – Wings
The use of later approved revisions of this document is acceptable for
Subject: Inner Wing – Wing Bottom Skin between Ribs 5 and 11 – Inspection compliance with the requirements of this AD.
Supersedure / Revised Not applicable
AD(s): For further information The applicable manufacturer’s documentation may be obtained directly
contact: from:
Type Certificate Pilatus Aircraft Ltd.
Holder’s Name: PILATUS AIRCRAFT LTD.
Customer Liaison Manager
Manufacturer(s): Pilatus Aircraft Ltd. CH-6371 Stans, Switzerland
Applicability: Models PC-9, PC-9/A, PC-9/B and PC-9/F aircraft, Manufacturer Serial Tel.: +41 (0)41 619 62 26 Fax: +41 (0)41 619 61 70
Numbers (MSN) 101 through MSN 188 inclusive and MSN 501 through E-mail: snolan@pilatus-aircraft.com
MSN 567 inclusive.
For further information contact:
Reason: This Airworthiness Directive (AD) is prompted due to reported loose
countersunk rivets which attach the bottom skin of the inner wing to the FEDERAL OFFICE OF CIVIL AVIATION (FOCA)
rear-spar between ribs 5 and 11. Flexing of the wing skin can cause the Design and Production (STEH)
countersunk rivets to work loose and pull through the skin panel. CH-3003 Bern, Switzerland
Such a condition, if left uncorrected, could lead to a loss of torsion stiff- Fax: +41 (0) 31 322 59 18
ness of the wing with potential consequences on the structural strength E-mail: airdir@bazl.admin.ch
and flutter margins.
In order to correct and control the situation, this AD requires a visual
inspection of the relevant area. Additionally to a possible repair, the
installation of supplemental fasteners is always required.
Required actions(s) Required as indicated below, unless already accomplished:
and Compliance
Time(s): (1) Within 28 days after the effective date of this AD, perform a visual
inspection of the countersunk rivets which attach the wing bottom
skin to the rear-spar and end ribs as required by paragraph (§)
3.A.(3) of PILATUS PC-9 Service Bulletin No. 57-015.
Note 1: If only dome head rivets are installed, no further action is
required.
(2) If no damage is found, do the Repair No.1 as required by § 3.A.(3) (c)
of PILATUS PC-9 Service Bulletin No. 57-015 at, or before the next
scheduled 300 hrs or annual inspection, whichever occurs first.
1/2 2/2
Rechtsmittelbelehrung siehe TM Nr. Rechtsmittelbelehrung siehe TM Nr.
Voies de droit voir CT no. 02.020-80 Voies de droit voir CT no. 02.020-80
Rimedi giuridice vedi CT no. Rimedi giuridice vedi CT no.
Right to appeal see TC no. Right to appeal see TC no.
EASA AD No.: 2009-0142
Lufttüchtigkeitsanweisung EASA AIRWORTHINESS DIRECTIVE
LTA-Nr.: D-2009-209
AD No.: 2009 - 0142
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 14.08.2009
Muster: Rolls-Royce AD der ausländischen Behörde:
RB211 Trent 800 EASA AD 2009-0142 vom 13.07.2009
Date: 13 July 2009
Geräte-Nr.: Technische Mitteilungen des Herstellers:
6334, CAAUK TCDS 1051 Rolls-Royce Alert Service Bulletin RB211-79-AG257 vom Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with
Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and
24.06.2009 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 operate
an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of that Airworthiness Directive
Rolls-Royce 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
RB211 Trent 800 [EC 216/2008, Article 14(4) exemption].
- Baureihen: RB211 Trent 895-17, 892-17, 892B-17, 884-17, 884B-17, 877-17 und 875-17 Type Approval Holder’s Name : Type/Model designation(s) :
- Werk-Nrn.: Alle ROLLS-ROYCE plc RB211 Trent 800 Engines
Betrifft: TCDS Number : CAA UK 1051
Engine – Fuel System, Fuel-to-oil Heat Exchanger (FOHE) – Replacement
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. Engine – Fuel System, Fuel-to-oil Heat Exchanger (FOHE) –
ATA 79
Replacement
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 Manufacturer(s): Rolls-Royce plc
EASA Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der Applicability: RB211 Trent 895-17, 892-17, 892B-17, 884-17, 884B-17, 877-17and
EASA AD 2009-0142 vom 13.07.2009 875-17 engines.
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
These engines are known to be installed on, but not limited to
Sicherheit des Luftverkehrs, das in diesem Fall das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es Boeing 777 series aircraft.
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
Rechtsbehelfsbelehrung:
Reason: This Airworthiness Directive has been raised following an incident involving dual
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder loss of engine response in the final stages of approach leading to touchdown
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen. short of the runway. The phenomenon involved in the loss of engine response
has also been seen in flight affecting just one engine.
LTAs werden auch im Internet unter http://www.lba.de publiziert
*** Post incident analysis and investigation has established that, under certain
ambient conditions, ice can accumulate on the walls of the fuel pipes within the
aircraft fuel system, which can then be released downstream when fuel flow
demand is increased. This released ice can then collect on the FOHE front face
and limit fuel flow through the FOHE. This type of icing event was previously
unknown and creates ice concentrations in the fuel system beyond those
specified in the certification requirements.
To mitigate the risk of dual engine FOHE blockage within the Trent 800 engine
powered Boeing 777 fleet, which constitutes a potential unsafe condition, this
Airworthiness Directive instructs replacement of the FOHE with a modified
standard incorporating enhanced anti-icing and de-icing performance.
EASA Form 110 Page 1/2
Aktenzeichen: (10)T23-502.1/D-2009-209 Seite 1 von 1
EASA AD No.: 2009-0142
Effective Date: 27 July 2009 Lufttüchtigkeitsanweisung
LTA-Nr.: D-2009-210
Required Action(s) Within 6 000 flight hours from 10 July 2009 or before 01 January 2011,
and Compliance whichever occurs first: Luftfahrt-Bundesamt
Time(s):
Replace the FOHE with an FOHE modified in accordance with Rolls-
Datum der Bekanntgabe: 14.08.2009
Royce Alert Service Bulletin RB211-79-AG257, dated 24 June 2009 Muster: Thielert Aircraft Engines AD der ausländischen Behörde:
(published 10 July 2009). TAE125 EASA AD 2009-0151 vom 10.07.2009
Geräte-Nr.: Technische Mitteilungen des Herstellers:
Ref. Publications: Rolls-Royce Alert Service Bulletin RB211-79-AG257, dated 24 June 2009
4631, EASA.E.055 1. Thielert Service Bulletin TM TAE125-1007 P1 Revision 2 vom
(published 10 July 2009).
29.04.2009
The use of later approved revisions is acceptable for compliance with the 2. Thielert Service Bulletin TM TAE125-1009 P1 vom 07.07.2009
requirements of this AD. 3. Engine Operation & Maintenance Manual OM-02-02 Issue 1
Revision 7 vom 17.06.2009
Remarks : 1. If requested and appropriately substantiated, EASA can approve 4. Engine Repair Manual RM-02-02 Issue 1 Revision 15 vom
Alternative Methods of Compliance for this AD. 29.04.2009
2. The required actions and the risk allowance have granted the issuance
of a Final AD with Request for Comments, postponing the public Betroffenes Luftfahrtgerät:
consultation process after publication.
Thielert Aircraft Engines
3. Enquiries regarding this AD should be referred to the Airworthiness TAE125
Directives, Safety Management & Research Section, Certification
Directorate, EASA. E-mail ADs@easa.europa.eu - Baureihen: TAE125-02-99
4. For any question concerning the technical content of the requirements in
this AD, please contact: - Werk-Nrn.: Alle Triebwerke dieser Baureihe installiert in Diamond Aircraft Industries Model DA 42
Rolls-Royce plc. PO Box 31, Derby, DE24 8BJ, United Kingdom. und DA 42 M Luftfahrzeugen.
Phone: +44 (0) 1332 242424, Fax: +44 (0) 1332 249936.
Email: tech.help@rolls-royce.com or download the publication from Betrifft:
https://www.aeromanager.com Engine/Propeller – Constant Speed Unit – Propeller Control Valve – Vibration Isolator
Maßnahmen:
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
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 2009-0151 vom 10.07.2009
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-2009-210 Seite 1 von 1
EASA AD No : 2009-0151 EASA AD No : 2009-0151
level on the Proportional Pressure Reducing Valve. For preventing failures
EASA AIRWORTHINESS DIRECTIVE of the valve’s electrical connection, a new Proportional Pressure Reducing
Valve 24V (Propeller Control Valve) Part Number (P/N) 05-7212-E002801
has been introduced by TM TAE 125-1007 P1 Revision 2.
AD No.: 2009- 0151
For the reasons described above, this EASA AD requires the installation
of the Vibration Isolator and the new Proportional Pressure Reducing
Valve 24V (Propeller Control Valve).
Date: 10 July 2009
The content of this AD was partially addressed by PAD 09-071. One
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with comment was received and is answered in the CRD 09-071, which can be
Regulation (EC) No 216/2008 on behalf of the European Community, its Member States found at http://ad.easa.europa.eu/.
and of the European third countries that participate in the activities of EASA under Article
66 of that Regulation.
Effective Date: 24 July 2009
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 Airworthiness Directive applies, except in accordance with the requirements of that Airworthiness Required Action(s) Required as indicated unless already accomplished:
Directive unless otherwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the and Compliance
Within 110 flight hours from the effective date of this AD, install the
State of Registry [EC 216/2008, Article 14(4) exemption]. Time(s):
Proportional Pressure Reducing Valve 24V (propeller control valve)
Type/Model designation(s) : Part Number (P/N) 05-7212-E002801 and the Vibration Isolator
Type Approval Holder’s Name :
P/N 05-7212-K022302 in accordance with TM TAE 125-1007 P1 Rev. 2
Thielert Aircraft Engines GmbH and TM TAE 125-1009 P1.
TAE125-02-99 engines
Note: Vibration Isolator and Proportional Pressure Reducing Valve
TCDS Number : EASA.E.055 (Propeller Control Valve) are part of the Gearbox assembly. The Gearbox,
and thus Vibration Isolator and Proportional Pressure Reducing Valve, has
to be inspected regularly in accordance with OM-02-02 and RM-02-02.
Foreign AD : Not applicable
Ref. Publications: Thielert Service Bulletin TM TAE125-1007 P1 Rev. 2 dated 29 April 2009.
Supersedure: None Thielert Service Bulletin TM TAE125-1009 P1 dated 07 July 2009.
Engine Operation & Maintenance Manual OM-02-02 Issue 1 Rev. 7 dated
17 June 2009.
Engine/Propeller – Constant Speed Unit – Propeller Control Engine Repair Manual RM-02-02 Issue 1 Rev. 15 dated 29 April 2009.
ATA 61
Valve – Vibration Isolator The use of later approved revisions of these documents is acceptable for
compliance with the requirements of this AD.
Manufacturer(s): Thielert Aircraft Engines GmbH. Remarks : 1. If requested and appropriately substantiated, EASA can approve
Alternative Methods of Compliance for this AD.
2. The required actions and the risk allowance have granted the
Applicability: TAE125-02-99 engines, all serial numbers, if installed on Diamond Aircraft issuance of a Final AD with Request for Comments, postponing the
Industries Model DA 42 and DA 42 M aircraft. public consultation process after publication.
3. Enquiries regarding this AD should be referred to the Airworthiness
Reason: In-flight engine shutdown incidents have been reported on Diamond Directives, Safety Management & Research Section, Certification
Aircraft Industries DA 42 aircraft equipped with TAE125 engines. The Directorate, EASA. E-mail ADs@easa.europa.eu.
investigations showed that it was mainly the result of failure of the
Proportional Pressure Reducing Valve (Propeller Control Valve) due to 4. For any question concerning the technical content of the requirements
high vibration. This condition, if not corrected, could lead to further cases in this AD, please contact:
of engine in-flight shutdown, possibly resulting in reduced control of the Thielert Aircraft Engines
aircraft. Platanenstraße 14
As this problem has only manifested itself on these engines installed on D-09350 Lichtenstein, Germany
Diamond Aircraft Industries DA 42 aircraft, TAE125-02-99 engines Telephone +49-37204-696-0; Fax +49-37204-696-55;
installed on other aircraft are not affected. E-mail info@centurion-engines.com
In addition to the information stated above, it has been found out that
failure of the electrical connection to the Proportional Pressure Reducing
Valve 24V (Propeller Control Valve) Part Numbers (P/N) NM-0000-
0124501 and 05-7212-K021401 contributed to power loss events or IFSD.
To address and correct this situation, Thielert Aircraft Engines GmbH
has published TM TAE 125-1009 P1, providing instructions for installation
of the Vibration Isolator P/N 05-7212-K022302 that reduces the vibration
EASA Form 110 Page 1/2 EASA Form 110 Page 2/2
Transport Transports TP 7245E
Canada Canada No.
1/1
Lufttüchtigkeitsanweisung CF-2009-30
Issue Date
LTA-Nr.: D-2009-211 06 July 2009
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 14.08.2009 AIRWORTHINESS DIRECTIVE
The following airworthiness directive (AD) may be applicable to an aircraft which our records indicate is registered in your name. ADs are issued pursuant to Canadian
Aviation Regulation (CAR) 593. Pursuant to CAR 605.84 and the further details of CAR Standard 625, Appendix H, the continuing airworthiness of a Canadian registered
Muster: BOMBARDIER Inc. AD der ausländischen Behörde: aircraft is contingent upon compliance with all applicable ADs. Failure to comply with the requirements of an AD may invalidate the flight authorization of the aircraft. Alternative
means of compliance shall be applied for in accordance with CAR 605.84 and the above-referenced Standard.
CL-600 TC AD CF-2009-30 vom 06.07.2009 This AD has been issued by the Continuing Airworthiness Division (AARDG), National Aircraft Certification Branch, Transport Canada, Ottawa, telephone 613 952-4357.
Geräte-Nr.: Technische Mitteilungen des Herstellers: Number: CF-2009-30
2854, EASA.IM.A.023 Bombardier Service Bulletin 670BA-25-071 vom 15.05.2009
Subject: Aft Baggage Cargo Compartment – Blowout Panel Protective Cages: Damage
Betroffenes Luftfahrtgerät:
Effective: 27 July 2009
BOMBARDIER Inc.
CL-600 Applicability: Bombardier Inc. Models:
- Baureihen: CL-600-2C10, CL-600-2D15 und CL-600-2D24 CL-600-2C10: Serial Numbers 10003 through 10268
CL-600-2D15 and CL-600-2D24: Serial Numbers 15001 through 15205
- Werk-Nrn.: 10003 bis 10268 und 15001 bis 15205
Betrifft: Compliance: Within 5 000 hours air-time after the effective date of this directive, unless already
accomplished.
(ATA 25) Cargo Compartments - Blowout Panel Protective Cages - Replacement
Maßnahmen: Background: There have been several in-service cases reported of impact damage to the blowout
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten Transport Canada (decompression) panel protective cage assemblies installed in the aft baggage cargo
(TC) Airworthiness Directive und der genannten technischen Mitteilung des Herstellers zu entnehmen. Alle compartment. When damaged, these cages could prevent proper operation of the
erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, vollständig und blowout panels, with potential degradation of smoke detection and fire extinguishing
innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente durchgeführt werden. Alle capabilities in the event of a fire.
Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeitsanweisung bedürfen der vorherigen
Zustimmung durch das Luftfahrt-Bundesamt. This directive mandates replacement of the existing cages with new cages that have
greater damage resistance.
Fristen:
Alle anzuwendenden Fristen sind der oben genannten TC Airworthiness Directive zu entnehmen.
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten Corrective Replace the existing cage assemblies in the aft baggage cargo compartment, in
TC Airworthiness Directive. Actions: accordance with Bombardier Service Bulletin (SB) 670BA-25-071, dated 15 May 2009,
or later revisions approved by the Chief, Continuing Airworthiness, Transport Canada.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der
TC AD CF-2009-30 vom 06.07.2009
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, daß es nach Ablauf der genannten Fristen Authorization: For Minister of Transport, Infrastructure and Communities
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: Derek Ferguson
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. Chief, Continuing Airworthiness
LTAs werden auch im Internet unter http://www.lba.de publiziert Contact: Mr. Richard Topham, Continuing Airworthiness, Ottawa, telephone 613-952-4428,
*** facsimile 613-996-9178 or e-mail richard.topham@tc.gc.ca or any Transport Canada
Centre.
Pursuant to CAR 202.51 the registered owner of a Canadian aircraft shall, within seven days, notify the Minister
in writing of any change of his or her name or address.
To request a change of address, contact the Civil Aviation Communications Centre (AARC)
at Place de Ville, Ottawa, Ontario K1A 0N8, or 1-800-305-2059,
or www.tc.gc.ca/civilaviation/communications/centre/ address.asp
24-0022 (01-2005)
Aktenzeichen: (01)T231-502.1/D-2009-211 Seite 1 von 1
