Nachrichten für Luftfahrer 2013 Teil II (weicht ggf. von Druckversion ab)
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
38144 Braunschweig
D-2004-477R1 Fax: +49-531-2355-5298
email: ad@LBA.de
CESSNA Datum der Bekanntgabe: 07.05.2013
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: Cessna Aircraft Company
Hersteller: Cessna Aircraft Company
Muster: CESSNA 195
Baureihen: Cessna 190, 195 (L-126A,B,C), 195A und 195B
Werknummern: Alle Luftfahrzeuge dieser Baureihen, an denen Inboard Aileron Hinge Brackets
mit der Hersteller-Teilenummer (P/N) 0322709 oder 0322709-1 installiert sind.
Gerätenummer: 545
Revisionsstand:
Diese LTA ersetzt D-2004-477 vom 25.11.2004
Airworthiness Directive der ausländischen Behörde:
FAA AD 2004-21-08 R1 (Correction: 29.04.2013) - Amdt. 39-17400
Betrifft:
(ATA 27) Rissbildung an Inboard Aileron Hinge Brackets durch Korrosionsschäden
Maßnahmen und Fristen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der 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 Lufttüchtigkeitsanweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
Alle anzuwendenden Fristen sind der 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 2004-21-08 R1 (Correction: 29.04.2013) - Amdt. 39-17400.
Zugehörige technische Dokumente:
Hinweis: Die Anwendung von nachfolgenden Ausgaben bzw. Revisionsständen der genannten zugehörigen technischen Dokumente ist zulässig, wenn dies nach
der Airworthiness Directive der ausländischen Behörde ausdrücklich gestattet ist oder wenn diese von der ausländischen Behörde in Bezug auf die referenzierte
Airworthiness Directive genehmigt worden sind.
Cessna Aircraft Company Single Engine Service Bulletin SEB04-1 Revision 1 vom 03.10.2012
Die sofortige Vollziehung dieses Bescheides wird gemäß § 80 Absatz 2 Satz 1 Nr. 4 der Verwaltungsgerichtsordnung (VwGO) angeordnet.
Begründung
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, dass es nach Ablauf der genannten Fristen nur in Betrieb genom-
men 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 Lufttüchtigkeitsanweisung
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. Ein eventueller Widerspruch hat keine aufschiebende Wirkung. Das Verwaltungsge-
richt Braunschweig, Am Wendentor 7, 38100 Braunschweig, kann auf Antrag nach § 80 Abs. 5 VwGO die aufschiebende Wirkung jedoch ganz oder teilweise wie-
derherstellen bzw. anordnen.
D-2004-477R1 Seite 1 von 1 267/2013
[Federal Register Volume 78, Number 65 (Thursday, April 4, 2013)]
[Rules and Regulations]
[Pages 20227-20229]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-06589]
––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-18033; Directorate Identifier 2004-CE-16-AD; Amendment 39-17400;
AD 2004-21-08 R1]
RIN 2120-AA64
Airworthiness Directives; Cessna Aircraft Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
––––––––––––––––––––––––––––––––––
SUMMARY: We are revising an existing airworthiness directive (AD) for all Cessna Aircraft
Company (Cessna) Models 190, 195 (L-126A,B,C), 195A, and 195B airplanes that are equipped with
certain inboard aileron hinge brackets. That AD currently requires you to repetitively inspect the
affected inboard aileron hinge brackets for cracks or corrosion and replace them if cracks or corrosion
is found. Replacement with aluminum brackets would terminate the need for the repetitive
inspections. This new AD retains the actions of AD 2004-21-08 while requiring future compliance
following a revised service bulletin that clarifies the casting numbers and part numbers to be
inspected. This AD was prompted by reports of confusion between the casting number on the aileron
hinge bracket and the part number (P/N) called out in the AD. We are issuing this AD to correct the
unsafe condition on these products.
DATES: This AD is effective May 9, 2013.
The Director of the Federal Register approved the incorporation by reference of a certain
publication listed in the AD as of May 9, 2013.
ADDRESSES: For service information identified in this AD, contact Cessna Aircraft Company,
Customer service, P.O. Box 7706, Wichita, KS 67277; telephone: (316) 517-5800; fax: (316) 517-
7271; email: customercare@cessna.textron.com; Internet: http://www.cessnasupport.com. You may
review copies of the referenced service information at the FAA, Small Airplane Directorate, 901
Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call
(816) 329-4148.
1
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at
the Docket Management Facility 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 address for the Docket Office (phone: 800-647-5527) is Document
Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Gary Park, Aerospace Engineer, Wichita ACO,
FAA, 1801 Airport Road, Wichita, KS 67209; phone: (316) 946-4123; fax: (316) 946-4107; email:
gary.park@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to revise AD
2004-21-08, amendment 39-13828 (69 FR 62396, October 26, 2004). That AD applies to the
specified products. The NPRM published in the Federal Register on January 8, 2013 (78 FR 1155).
That NPRM proposed to retain the actions of AD 2004-21-08 while requiring future compliance
following a revised service bulletin that clarifies the casting numbers and part numbers to be
inspected.
Comments
We gave the public the opportunity to participate in developing this AD. We received no
comments on the NPRM (78 FR 1155, January 8, 2013) or on the determination of the cost to the
public.
Conclusion
We reviewed the relevant data and determined that air safety and the public interest require
adopting the AD as proposed. We have determined that these minor changes:
• Are consistent with the intent that was proposed in the NPRM (78 FR 1155, January 8, 2013)
for correcting the unsafe condition; and
• Do not add any additional burden upon the public than was already proposed in the NPRM
(78 FR 1155, January 8, 2013).
Costs of Compliance
We estimate that this AD affects 643 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
Action Labor cost Parts cost Cost per Cost on U.S.
product operators
Inspection of the affected 1 work-hour × $85 Not $85 643 airplanes ×
inboard aileron hinge brackets per hour = $85 Applicable $85 = $54,655.
for cracks or corrosion.
2
The new requirements of this AD add no additional economic burden.
We estimate the following costs to do any necessary replacements that would be required based
on the results of the inspection. We have no way of determining the number of aircraft that might
need these replacements:
On-condition Costs
Action Labor Cost Parts cost Cost per product
Replacement of left- 3 work-hours × $85 per $1,999 $2,254
hand (LH) brackets hour = $255
Replacement of right- 3 work-hours × $85 per 1,592 1,847
hand (RH) brackets hour = $255
Replacement of LH and 6 work-hours × $85 per 4,101 4,611
RH brackets hour = $510
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 DOT Regulatory Policies and Procedures (44 FR 11034,
February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR
part 39 as follows:
3
PART 39–AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13 [Amended]
2. The FAA amends § 39.13 by removing Amendment 39-13828 (69 FR 62396, October 26, 2004),
and adding the following new AD:
4
AIRWORTHINESS DIRECTIVE
FAA
www.faa.gov/aircraft/safety/alerts/
Aviation Safety
www.gpoaccess.gov/fr/advanced.html
2004-21-08 R1 Cessna Aircraft Company: Amendment 39-17400; Docket No. FAA-2012-18033;
Directorate Identifier 2004-CE-16-AD.
(a) Effective Date
This AD is effective May 9, 2013.
(b) Affected ADs
This AD revises AD 2004-21-08, Amendment 39-13828, (69 FR 62396, October 26, 2004).
(c) Applicability
This AD affects Models 190, 195 (L-126A,B,C), 195A, and 195B airplanes, all serial numbers,
that are:
(1) certificated in any category; and
(2) equipped with at least one part number (P/N) 0322709 or P/N 0322709-1 inboard aileron
hinge bracket.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code
2710, Aileron Control System.
(e) Unsafe Condition
This AD was first prompted by several reports of cracks and corrosion found on the magnesium
aileron hinge brackets. Magnesium is known to be susceptible to corrosion. Since issuance of AD
2004-21-08 (69 FR 62396, October 26, 2004), reports of confusion between the casting number on
the aileron hinge bracket and the part number called out in the AD have caused us to issue this
revision to AD 2004-21-08. We are issuing this AD to correct the unsafe condition on these products.
(f) Compliance
Comply with this AD at the times specified following the procedures in Cessna Aircraft
Company Single Engine Service Bulletin SEB04-1, Revision 1, dated October 3, 2012, unless already
done.
(g) Credit for Actions Accomplished in Accordance With Previous Service Information
This paragraph provides credit for the actions required by paragraphs (h), (i), and (j) of this AD,
if the actions were performed before the effective date of this AD using Cessna Aircraft Company
Single Engine Service Bulletin SEB04-1, dated April 26, 2004. All actions performed after May 9,
2013 (the effective date of this AD) will be required following Cessna Aircraft Company Single
Engine Service Bulletin SEB04-1, Revision 1, dated October 3, 2012.
5
(h) Inspect Each P/N 0322709 and P/N 0322709-1 Inboard Aileron Hinge Bracket or Any Other
Bracket Made From Magnesium for Cracks or Corrosion
Within the next 100 hours time-in-service (TIS) after November 30, 2004 (the effective date
retained from AD 2004-21-08, Amendment 39-13828 (69 FR 62396, October 26, 2004)), and
repetitively thereafter at intervals not to exceed 100 hours TIS until each bracket is replaced with
aluminum, inspect each P/N 0322709 and P/N 0322709-1 inboard aileron hinge bracket or any other
bracket made from magnesium for cracks or corrosion.
(i) Replace Any Cracked or Corroded Inboard Aileron Hinge Bracket
Before further flight after any inspection where any cracked or corroded bracket is found, replace
any cracked or corroded inboard aileron hinge.
(1) If replacement is with an FAA-approved bracket made from magnesium, do the 100-hour TIS
interval repetitive inspections as required in paragraph (h) of this AD.
(2) If replacement is with an FAA-approved bracket that is made from aluminum, then no further
inspections are necessary. These can be Cessna parts or non-Cessna parts.
(j) Terminating Action for the Repetitive Inspections
(1) As terminating action for the repetitive inspections, you may replace all inboard aileron hinge
brackets with FAA-approved brackets that are made from aluminum (as specified in paragraph (i)(2)
of this AD) regardless if any corrosion or crack is found.
(2) You may do this replacement at any time, but you must replace any corroded or cracked
bracket before further flight after the applicable inspection where any corrosion or crack is found.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Wichita Aircraft Certification Office (ACO), FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information directly to the manager of the ACO,
send it to the attention of the person identified in the Related Information section of this AD.
(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a
principal inspector, the manager of the local flight standards district office/certificate holding district
office.
(3) All AMOCs approved for AD 2004-21-08 (69 FR 62396, October 26, 2004) are approved for
this AD.
(l) Related Information
For more information about this AD, contact Gary Park, Aerospace Engineer, Wichita ACO,
FAA, 1801 Airport Road, Wichita, KS 67209; phone: (316) 946-4123; fax: (316) 946-4107; email:
gary.park@faa.gov.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the
service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do the actions required by this AD,
unless the AD specifies otherwise.
6
(i) Cessna Aircraft Company Single Engine Service Bulletin SEB04-1, Revision 1, dated
October 3, 2012.
(ii) Reserved.
(3) For Cessna Aircraft Company service information identified in this AD, contact Cessna
Aircraft Company, Customer service, P.O. Box 7706, Wichita, KS 67277; telephone: (316) 517-
5800; fax: (316) 517-7271; email: customercare@cessna.textron.com; Internet:
http://www.cessnasupport.com.
(4) You may view this service information at FAA,, Small Airplane Directorate, 901 Locust,
Kansas City, MO 64106. For information on the availability of this material at the FAA, call (816)
329-4148.
(5) You may view this service information that is incorporated by reference at the National
Archives and Records Administration (NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on March 14, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate,
Aircraft Certification Service.
7
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
38144 Braunschweig
D-2005-314R1 Fax: +49-531-2355-5298
email: ad@LBA.de
SOCATA Datum der Bekanntgabe: 08.05.2013
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: SOCATA
Hersteller: SOCATA, EADS SOCATA
Muster: TBM 700
Baureihen: Alle TBM 700 Baureihen
Werknummern: 1 bis 345
Gerätenummer: 2070, EASA.A.010
Revisionsstand:
Diese LTA ersetzt D-2005-314 vom 18.08.2005
Airworthiness Directive der ausländischen Behörde:
EASA AD 2013-0100 vom 30.04.2013
Betrifft:
(ATA 53) Fuselage - Rivets at Frames C18 BIS and C19 - Inspection / Replacement
Maßnahmen und Fristen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der genannten EASA 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 Lufttüchtigkeitsanweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt.
Alle anzuwendenden Fristen sind der 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 2013-0100 vom 30.04.2013.
Zugehörige technische Dokumente:
Hinweis: Die Anwendung von nachfolgenden Ausgaben bzw. Revisionsständen der genannten zugehörigen technischen Dokumente ist zulässig, wenn dies nach
der Airworthiness Directive der ausländischen Behörde ausdrücklich gestattet ist oder wenn diese von der ausländischen Behörde in Bezug auf die referenzierte
Airworthiness Directive genehmigt worden sind.
SOCATA Service Bulletin 70-129-53 Revision 01 vom Februar 2009
SOCATA Service Bulletin 70-129-53 Revision 02 vom Oktober 2012
SOCATA Service Bulletin 70-129-53 vom Juni 2005
Die sofortige Vollziehung dieses Bescheides wird gemäß § 80 Absatz 2 Satz 1 Nr. 4 der Verwaltungsgerichtsordnung (VwGO) angeordnet.
Begründung
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, dass es nach Ablauf der genannten Fristen nur in Betrieb genom-
men 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 Lufttüchtigkeitsanweisung
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. Ein eventueller Widerspruch hat keine aufschiebende Wirkung. Das Verwaltungsge-
richt Braunschweig, Am Wendentor 7, 38100 Braunschweig, kann auf Antrag nach § 80 Abs. 5 VwGO die aufschiebende Wirkung jedoch ganz oder teilweise wie-
derherstellen bzw. anordnen.
D-2005-314R1 Seite 1 von 1 271/2013
EASA AD No.: 2013-0100
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2013-0100
Date: 30 April 2013
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 of the
European third countries that participate in the activities of EASA under Article 66 of that
Regulation.
This AD is issued in accordance with EU 748/2012, 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 [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].
Design Approval Holder’s Name: Type/Model designation(s):
SOCATA TBM 700 aeroplanes
TCDS Number: EASA A.010
Foreign AD: Not applicable
Supersedure: This AD supersedes DGAC France AD 2005-132 (EASA Approval 2005-6117)
dated 27 July 2005.
Fuselage – Rivets at Frames C18 BIS and C19 – Inspection /
ATA 53
Replacement
Manufacturer(s): SOCATA (formerly EADS SOCATA)
Applicability: SOCATA TBM 700 aeroplanes, manufacturer serial numbers (MSN) 1 through
345 inclusive.
Reason: In 2005, some loose rivets were detected on frames C18 BIS and C19.
This condition, if not detected and corrected, could adversely affect the
structural integrity of the tail area of the aeroplane.
To address this unsafe condition, DGAC France issued AD 2005-132 to require
repetitive inspections and, depending on findings, the accomplishment of
corrective actions.
After that AD was issued, further analyses have been performed in the frame of
an improvement of the TBM 700 Aircraft Maintenance Program. The results of
these analyses revealed that the inspection threshold and interval allowing a
timely detection of loose rivets and the accomplishment of an applicable
corrective action can be extended. Prompted by these results, SOCATA issued
Revision 02 of Service Bulletin (SB) 70-129-53.
For the reasons described above, this AD retains the requirements of DGAC
France AD 2005-132, which is superseded, but extends the inspection
thresholds and intervals.
Effective Date: 14 May 2013
TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/2
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
