Nachrichten für Luftfahrer 2013 Teil II (weicht ggf. von Druckversion ab)
§ 39.13 [Amended]
2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):
4
AIRWORTHINESS DIRECTIVE
FAA
www.faa.gov/aircraft/safety/alerts/
Aviation Safety
www.gpoaccess.gov/fr/advanced.html
2013-05-16 Hughes Helicopters, Inc., and McDonnell Douglas Helicopter Systems (Type
Certificate currently held by MD Helicopters, Inc., (MDHI): Amendment 39-17388; Docket No.
FAA-2012-0890; Directorate Identifier 2011-SW-019-AD.
(a) Applicability
This AD applies to Model 369D, E, F, and FF helicopters with tailboom assembly, part number
369D23500-505, -507, -511, or -513 with a serial number prefix of ''7604'' and -0001 through -0003,
-0006 through -0047, -0049 through -0082, or -0084 through -0113, installed, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as too short an edge distance from an aft longeron rivet to
the edge of a tailboom frame ring, which could result in failure of the tailboom and subsequent loss of
control of the helicopter.
(c) Effective Date
This AD becomes effective April 30, 2013.
(d) Compliance
You are responsible for performing each action required by this AD within the specified
compliance time unless it has already been accomplished prior to that time.
(e) Required Actions
(1) Within 6 months or 100 hours time-in-service, whichever occurs first, measure the distance
from the aft face of the station 209.78 frame ring to the center of rivet No. 1 and rivet No. 2 at the
four locations where the frame ring attaches to the tailboom longeron as depicted in Figure 2 of MD
Helicopters Service Bulletin (SB) No. SB369D-207, SB369E-102, and SB369F-087, dated July 20,
2010. SB369D-207 applies to Model 369D helicopters; SB369E-102 applies to Model 369E
helicopters; and SB369F-087 applies to Model 369F and FF helicopters.
(2) If either the No. 1 or No. 2 aft rivet at a frame-ring-to-tailboom-longeron location is more
than 0.50 inches (12.7 millimeters) from the aft face of the station 209.78 frame ring, before further
flight, modify that location by fabricating and installing a doubler over the location as depicted in
Figures 3 and 4 and by following the Accomplishment Instructions, paragraph 2.C., of the SB for
your model helicopter.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles Aircraft Certification Office, FAA, may approve AMOCs for this
AD. Send your proposal to: John Cecil, Aerospace Engineer, FAA, Los Angeles Certification Office,
5
Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712-4137, telephone (562) 627-
5228, fax (562) 627-5210, email john.cecil@faa.gov.
(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part
91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or certificate holding district office before
operating any aircraft complying with this AD through an AMOC.
(g) Subject
Joint Aircraft Service Component (JASC) Code 5302: Rotorcraft Tailboom.
(h) 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.
(i) MD Helicopters, Inc., Service Bulletin (SB) No. SB369D-207, dated July 20, 2010.
(ii) MD Helicopters, Inc., SB No. SB369E-102, dated July 20, 2010.
(iii) MD Helicopters, Inc., SB No. SB369F-087, dated July 20, 2010.
Note 1 to paragraph (h)(2) of this AD: MD Helicopters, Inc., issued one service bulletin with
three numbers, SB369D-207, SB369E-102, and SB369F-087, all dated July 20, 2010.
(3) You may view this service information at FAA, Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the
availability of this material at the FAA, call (817) 222-5110.
(4) 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 Fort Worth, Texas, on March 6, 2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
6
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
38144 Braunschweig
D-2013-125 Fax: +49-531-2355-5298
email: ad@LBA.de
EUROCOPTER Datum der Bekanntgabe: 29.04.2013
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: EUROCOPTER
Hersteller: Eurocopter, Eurocopter France
Muster: EC 120,
EC 130
Baureihen: EC 120 B und EC 130 B4
Werknummern: Alle
Für EC 120 B Hubschrauber:
Alle Seriennummern unterhalb 1368, ausgestattet mit Schiebetüren der
Teilenummer P/N C526A2370101.
Für EC 130 B4 Hubschrauber:
Alle Seriennummern, ausgestattet mit Schiebetüren der Teilennummer P/N
C526S1101051.
Ausgenommen sind Hubschrauber, an denen die Eurocopter Modifikation MOD
07 3796 oder MOD 072921 bei der Herstellung durchgeführt worden ist.
Gerätenummer: 3048, 3065, EASA.R.008, EASA.R.508, DGAC TCDS 189
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
EASA AD 2013-0093 (Correction: 17.04.2013) vom 15.04.2013
Betrifft:
(ATA 52) Doors - Sliding Door Star Support - Modification
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 2013-0093 (Correction: 17.04.2013) vom 15.04.2013.
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.
Eurocopter Alert Service Bulletin No. EC120-52A014 Revision 0 vom 16.01.2004
Eurocopter Alert Service Bulletin No. EC120-52A014 Revision 1 vom 25.01.2013
Eurocopter Alert Service Bulletin No. EC130-52A009 Revision 0 vom 30.03.2010
Eurocopter Alert Service Bulletin No. EC130-52A009 Revision 1 vom 25.01.2013
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.
D-2013-125 Seite 1 von 2 251/2013
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-2013-125 Seite 2 von 2 251/2013
EASA AD No.: 2013-0093
EASA AIRWORTHINESS DIRECTIVE
AD No.: 2013-0093
[Correction: 17 April 2013]
Date: 15 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 21.A.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):
EUROCOPTER EC 120 B and EC 130 B4 Helicopters
TCDS Number: DGAC France No.189 and EASA.R.008
Foreign AD: Not applicable
Supersedure: None
ATA 52 Doors – Sliding Door Star Support – Modification
Manufacturer(s): Eurocopter (formerly Eurocopter-France)
Applicability: EC 120 B helicopters, all Serial Numbers (S/N) below 1368, equipped with
sliding door P/N C526A2370101, and
EC 130 B4 helicopters, all S/N, equipped with sliding door P/N
C526S1101051,
except those helicopters that have incorporated Eurocopter modification
(MOD) 07 3796 (reinforcement of the sliding door star support attachment) in
production, or have incorporated Eurocopter MOD 07 2921 (industrialized
sliding door) in production.
Reason: A case has been reported where, after landing, the passengers of an
Eurocopter helicopter could not open the sliding door from inside. The
passengers had to leave the helicopter through the pilot door.
The investigation revealed a sliding door star axle support failure.
This condition, if not corrected, could delay the evacuation from the helicopter
in case of emergency, possibly resulting in injury to the occupants.
For the reason described above, this AD requires modification of the sliding
door star support.
This AD was republished to correct one typo in the header and another one in
Ref. publication.
Effective Date: 29 April 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.
EASA AD No.: 2013-0093
Required Action(s) Required as indicated, unless accomplished previously:
and Compliance
(1) Within 165 flight hours or 24 months, whichever occurs first after the
Time(s):
effective date of this AD, modify the sliding door star support attachment
in accordance with the instructions of § 3 of Eurocopter Alert Service
Bulletin (ASB) EC120 No 52A014 Revision 1, or ASB EC130 No 52A009
Revision 1, depending on the helicopter type.
(2) Accomplishment of Eurocopter SB EC120 No 52A014 original issue or
SB EC130 No 52A009 original issue before the effective date of this AD is
acceptable to comply with the requirements of paragraph (1) of this AD.
(3) From the effective date of this AD, do not install any sliding door P/N
C526A2370101 on an EC 120 helicopter, or a sliding door P/N
C526S1101051 on an EC 130 B4 helicopter, unless in compliance with
the requirements of this AD.
Ref. Publications: Eurocopter ASB EC120 No 52A014 original issue dated 16 January 2004, or
Revision 1 dated 25 January 2013;
Eurocopter ASB EC130 No 52A009 original issue dated 30 March 2010, or
Revision 1 dated 25 January 2013;
The use of later approved revisions of these documents is acceptable for
compliance with the requirements of this AD.
Remarks: 1. If requested and appropriately substantiated, EASA can approve
Alternative Methods of Compliance for this AD.
2. This AD was posted on 21 February 2013 as PAD 13-037 for consultation
until 21 March 2013. No comments were received during the consultation
period.
3. Enquiries regarding this AD should be referred to the Safety Information
Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu.
4. For any question concerning the technical content of the requirements in
this AD, please contact:
EUROCOPTER (STDI) – Aéroport de Marseille Provence, 13725
Marignane Cedex, France; telephone +33 (4) 12 85 97 97; facsimile +33
(4) 85 99 66; E-mail: Directive.technical-support@eurocopter.com.
TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
38144 Braunschweig
D-2013-126 Fax: +49-531-2355-5298
email: ad@LBA.de
ROBINSON Datum der Bekanntgabe: 29.04.2013
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Drehflügler
Inhaber der Musterzulassung: Robinson Helicopter Company
Hersteller: Robinson Helicopter Company
Muster: R44
Baureihen: R44 und R44 II
Werknummern: Alle
Betroffen sind Hubschrauber mit Emergency floats, die mit einer Inflation valve
assembly der Teilenummer P/N D757-1 ausgerüstet sind, welche nicht die
Bezeichnung "D758-4" trägt oder mit der Modifikation B900-8 geändert wurde,
und welche eine Housing assembly der Teilenummer P/N D758-1, Revision C
oder früher, enthält.
Gerätenummer: 3063, EASA.IM.R.121
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
FAA AD 2013-05-15 - Amdt. 39-17387
Betrifft:
(ATA 32) Landing Gear - Emergency Floats - Inflation Valve Assembly - Replacement
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 2013-05-15 - Amdt. 39-17387.
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.
Robinson R44 Service Bulletin SB-80 vom 07.09.2011
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-2013-126 Seite 1 von 1 253/2013
[Federal Register Volume 78, Number 58 (Tuesday, March 26, 2013)]
[Rules and Regulations]
[Pages 18224-18226]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-06297]
––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1088; Directorate Identifier 2012-SW-005-AD; Amendment 39-17387;
AD 2013-05-15]
RIN 2120-AA64
Airworthiness Directives; Robinson Helicopter Company Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
––––––––––––––––––––––––––––––––––
SUMMARY: We are adopting a new airworthiness directive (AD) for Robinson Helicopter
Company (Robinson) Model R44 and R44 II helicopters equipped with emergency floats. This AD
requires replacing the inflation valve assembly. This AD was prompted by the failure of the
emergency floats to deploy during a factory test because a needle was binding within the inflation
valve assembly. The actions are intended to prevent the failure of the floats to inflate during an
emergency landing.
DATES: This AD is effective April 30, 2013.
ADDRESSES: For service information identified in this AD, contact Robinson Helicopter Company,
2901 Airport Drive, Torrance, CA 90505; telephone (310) 539-0508; fax (310) 539-5198; or at
http://www.robinsonheli.com. You may review a copy of the referenced service information at the
FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137.
Examining the AD Docket
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, any incorporated-by-reference service information, the
economic evaluation, any comments received, and other information. The street address for the
Docket Operations Office (phone: 800-647-5527) is U.S. Department of Transportation, Docket
Operations Office, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue
SE., Washington, DC 20590.
1
FOR FURTHER INFORMATION CONTACT: Venessa Stiger, Aerospace Engineer, Cabin
Safety/Mechanical & Environmental Systems, Los Angeles Aircraft Certification Office, Transport
Airplane Directorate, FAA, 3960 Paramount Blvd., Lakewood, CA 90712-4137; telephone (562)
627-5337; email venessa.stiger@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On October 16, 2012, at 77 FR 63260, the Federal Register published our notice of proposed
rulemaking (NPRM), which proposed to amend 14 CFR part 39 to include an AD that would apply to
Robinson Helicopter Company (Robinson) Model R44 and R44 II helicopters with emergency floats
equipped with an inflation valve assembly, part number (P/N) D757-1, not engraved with ''D758-4''
or modified with modification B900-8, and containing a housing assembly, P/N D758-1, Revision C
or prior. That NPRM proposed to require replacing the inflation valve assembly because the
emergency floats failed to deploy during a factory test. The proposed requirements were intended to
prevent the failure of the floats to inflate during an emergency landing.
Comments
We gave the public the opportunity to participate in developing this AD, but we received no
comments on the NPRM (77 FR 63260, October 16, 2012).
FAA's Determination
We have reviewed the relevant information and determined that an unsafe condition exists and is
likely to exist or develop on other products of these same type designs and that air safety and the
public interest require adopting the AD requirements as proposed.
Related Service Information
We have reviewed Robinson R44 Service Bulletin SB-80, dated September 7, 2011 (SB), which
describes procedures for upgrading certain valve assemblies within the next 250 flight hours or by
June 30, 2012, whichever occurs first. The SB reports that during a factory test of pop-out emergency
floats the floats failed to inflate because of a stuck cylinder valve.
Differences Between This AD and the Service Information
This AD requires replacing the inflation valve assembly within 1 year or 500 hours TIS,
whichever occurs first. The SB specifies replacing the assembly within 250 flight hours or by June
30, 2012, whichever occurs first. We used the Monitor Safety/Analyze Data (MSAD) process and
were able to predict when the next occurrence would likely occur if no repairs were completed.
Costs of Compliance
We estimate that this AD affects 165 helicopters of U.S. Registry and that the labor cost averages
$85 per work-hour. Based on these assumptions, we estimate that replacing the inflation valve
assembly takes 2.5 work-hours for a labor cost of about $213. Parts cost $850 to $955 for a total cost
per helicopter of $1,063 to $1,168.
According to Robinson's service information, some or all of the costs of this AD may be covered
under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty
coverage. Accordingly, we have included all costs in our cost estimate.
2
