Nachrichten für Luftfahrer 2008 Teil II (weicht ggf. von Druckversion ab)
AIRWORTHINESS DIRECTIVE Optional Terminating Action
FAA
Aircraft Certification Service www.faa.gov/aircraft/safety/alerts/ (h) Accomplishing the preventive modification specified in Boeing Special Attention Service
www.gpoaccess.gov/fr/advanced.html Bulletin 757-54-0049 or 757-54-0050, both dated July 16, 2007, terminates the repetitive inspections
required by paragraph (f) of this AD.
2008-13-20 Boeing: Amendment 39-15583. Docket No. FAA-2007-0225; Directorate Identifier
2007-NM-210-AD. Concurrent Actions
Effective Date (i) Prior to or concurrently with accomplishing the actions specified in Boeing Special Attention
Service Bulletin 757-54-0049, dated July 16, 2007, accomplish the replacement specified in Boeing
(a) This airworthiness directive (AD) is effective August 6, 2008. Service Bulletin 757-54-0015, Revision 3, dated September 19, 1996.
Affected ADs (j) Actions accomplished before the effective date of this AD in accordance with Boeing Service
Bulletin 757-54-0015, dated February 16, 1989; Revision 1, dated December 20, 1990; or Revision 2,
(b) None. dated April 21, 1994 are considered acceptable for compliance with the corresponding actions
specified in paragraph (i) of this AD.
Applicability
Alternative Methods of Compliance (AMOCs)
(c) This AD applies to Boeing Model 757-200, -200CB, -200PF, and -300 series airplanes,
certificated in any category; equipped with Rolls Royce RB211-535E engines. (k)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to
approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.
Unsafe Condition (2) To request a different method of compliance or a different compliance time for this AD,
follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which
(d) This AD results from reports of several incidents of bolt failure at the aft hinge fittings of the the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards
thrust reversers due to, among other things, high operational loads. We are issuing this AD to prevent District Office (FSDO), or lacking a PI, your local FSDO.
failure of the attachment bolts and consequent separation of a thrust reverser from the airplane during (3) An AMOC that provides an acceptable level of safety may be used for any repair required by
flight, which could result in structural damage to the airplane. this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized by the Manager, Seattle
Compliance ACO, to make those findings. For a repair method to be approved, the repair must meet the
certification basis of the airplane, and the approval must specifically refer to this AD.
(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. Material Incorporated by Reference
Repetitive Inspections/Investigative and Corrective Actions (l) You must use the Boeing service information contained in Table 1 of this AD to do the
actions required by this AD, unless the AD specifies otherwise.
(f) At the time specified in paragraph 1.E. ''Compliance,'' of Boeing Special Attention Service (1) The Director of the Federal Register approved the incorporation by reference of this service
Bulletin 757-54-0049 or 757-54-0050, both dated July 16, 2007, as applicable, except as provided by information under 5 U.S.C. 552(a) and 1 CFR part 51.
paragraph (g) of this AD: Do a detailed inspection for signs of damage of the aft hinge fittings and (2) For service information identified in this AD, contact Boeing Commercial Airplanes, P.O.
attachment bolts of the thrust reversers by doing all the actions, including all applicable related Box 3707, Seattle, Washington 98124-2207.
investigative and corrective actions, as specified in the Accomplishment Instructions of the applicable (3) You may review copies of the service information that is incorporated by reference at the
service bulletin. Do all applicable related investigative and corrective actions at the time specified in FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
paragraph 1.E., ''Compliance,'' of the applicable service bulletin. If any damage is found and the National Archives and Records Administration (NARA). For information on the availability of this
service bulletins specify to contact Boeing for appropriate action: Before further flight, repair using a material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_
method approved in accordance with the procedures specified in paragraph (k) of this AD. of_federal_regulations/ibr_locations.html.
(g) Where Boeing Special Attention Service Bulletins 757-54-0049 and 757-54-0050, both dated
July 16, 2007, specify compliance times relative to the date on the service bulletin, this AD requires
compliance within the specified compliance time after the effective date of this AD.
5 6
Table 1 – Material Incorporated by Reference Lufttüchtigkeitsanweisung
Service Information Revision Date LTA-Nr.: D-2008-273
Boeing Special Attention Service Bulletin 757-54-0015 3 September 19, 1996 Luftfahrt-Bundesamt
Datum der Bekanntgabe: 06.08.2008
Boeing Special Attention Service Bulletin 757-54-0049 Original July 16, 2007
Muster: Boeing AD der ausländischen Behörde:
Boeing Service Bulletin 757-54-0050 Original July 16, 2007 BOEING 767 FAA AD 2008-13-21 Amdt. 39-15584
Geräte-Nr.: Technische Mitteilungen des Herstellers:
Issued in Renton, Washington, on June 8, 2008. 2851, EASA.IM.A.035 Boeing Service Bulletin 767-35-0054 vom 06.07.2006
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. Betroffenes Luftfahrtgerät:
[FR Doc. E8-14190 Filed 7-1-08; 8:45 am]
Boeing
BOEING 767
- Baureihen: 767-200, 767-300 und 767-400ER
- Werk-Nrn.: Gemäß Boeing Service Bulletin 767-35-0054
Betrifft:
SAUERSTOFF (ATA: 35): Sauerstoffanlage in der Passagierkabine - Inspektion der Sauerstoffmasken in den
Passenger-Service-Units (PSU), in den Toiletten/Waschräumen und an den Flugbegleiterplätzen
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 2008-13-21 Amdt. 39-15584
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
***
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AIRWORTHINESS DIRECTIVE information for modifying the oxygen mask assembly by replacing the flow indicator with an
FAA improved flow indicator.
Aircraft Certification Service www.faa.gov/aircraft/safety/alerts/
www.gpoaccess.gov/fr/advanced.html Alternative Methods of Compliance (AMOCs)
2008-13-21 Boeing: Amendment 39-15584. Docket No. FAA-2008-0012; Directorate Identifier (g)(1) The Manager, Seattle Aircraft Certification Office, FAA, has the authority to approve
2007-NM-204-AD. AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different compliance time for this AD,
Effective Date follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which
the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards
(a) This airworthiness directive (AD) is effective August 6, 2008. District Office (FSDO), or lacking a PI, your local FSDO.
Affected ADs Material Incorporated by Reference
(b) None. (h) You must use Boeing Special Attention Service Bulletin 767-35-0054, dated July 6, 2006, to
do the actions required by this AD, unless the AD specifies otherwise.
Applicability (1) The Director of the Federal Register approved the incorporation by reference of this service
information under 5 U.S.C. 552(a) and 1 CFR part 51.
(c) This AD applies to Boeing Model 767-200, -300, and -400ER series airplanes, certificated in (2) For service information identified in this AD, contact Boeing Commercial Airplanes, P.O.
any category; as identified in Boeing Special Attention Service Bulletin 767-35-0054, dated July 6, Box 3707, Seattle, Washington 98124-2207.
2006. (3) You may review copies of the service information incorporated by reference at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National
Unsafe Condition 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/code_of_federal_
(d) This AD results from a report that several passenger masks with broken in-line flow regulations/ibr_locations.html.
indicators were found following a mask deployment. We are issuing this AD to prevent the in-line
flow indicators of the passenger oxygen masks from fracturing and separating, which could inhibit Issued in Renton, Washington, on June 8, 2008.
oxygen flow to the masks and consequently result in exposure of the passengers and cabin attendants Michael Kaszycki,
to hypoxia following a depressurization event. Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. E8-14189 Filed 7-1-08; 8:45 am]
Compliance
(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.
Inspection and Related Investigative/Corrective Actions
(f) Within 60 months after the effective date of this AD, do a general visual inspection to
determine the manufacturer and manufacture date of the oxygen masks in the passenger service units
and the flight attendant and lavatory oxygen boxes, as applicable, and do the applicable related
investigative and corrective actions, by accomplishing all of the applicable actions specified in the
Accomplishment Instructions of Boeing Special Attention Service Bulletin 767-35-0054, dated July
6, 2006; except where the service bulletin specifies installing a new oxygen mask, replace the oxygen
mask with one that was not manufactured by B/E Aerospace between January 1, 2002, and March 1,
2006, or with a modified oxygen mask having an improved flow indicator. The related investigative
and corrective actions must be done before further flight.
Note 1: The Boeing service bulletin refers to B/E Aerospace Service Bulletin 174080-35-01,
dated February 6, 2006; and Revision 1, dated May 1, 2006; as additional sources of service
5 6
Lufttüchtigkeitsanweisung AIRWORTHINESS DIRECTIVE
LTA-Nr.: D-2008-274 FAA
Aircraft Certification Service www.faa.gov/aircraft/safety/alerts/
Luftfahrt-Bundesamt www.gpoaccess.gov/fr/advanced.html
Datum der Bekanntgabe: 06.08.2008
Muster: Boeing AD der ausländischen Behörde: 2008-13-22 Boeing: Amendment 39-15585. Docket No. FAA-2006-26110; Directorate Identifier
BOEING 747 FAA AD 2008-13-22 Amdt. 39-15585
2006-NM-112-AD.
Geräte-Nr.: Technische Mitteilungen des Herstellers:
2832 Boeing Service Bulletin 747-31-2368 Revision 1 vom 24.07.2006 Effective Date
Betroffenes Luftfahrtgerät: (a) This AD becomes effective August 6, 2008.
Boeing Affected ADs
BOEING 747
- Baureihen: 747-400, 747-400D und 747-400F (b) None.
- Werk-Nrn.: Gemäß Boeing Service Bulletin 747-31-2368 Revision 1 Applicability
Betrifft: (c) This AD applies to Boeing Model 747-400, 747-400D, and 747-400F series airplanes,
ANZEIGEN / AUFZEICHNUNGSSYSTEME (ATA: 31): EFIS/EICAS-Anzeigen/Warnsystem - Auswechslung
der EIU-Geräte im E2-6 Gestell des Hauptgeräteraums
certificated in any category; as identified in Boeing Service Bulletin 747-31-2368, Revision 1, dated
July 24, 2006.
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten FAA Unsafe Condition
Airworthiness Directive und der genannten technischen Mitteilung des Herstellers zu entnehmen.
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, (d) This AD results from two instances where all six integrated display units (IDUs) on the flight
vollständig und innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente deck panels went blank in flight. We are issuing this AD to prevent loss of the IDUs due to failure of
durchgeführt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeits-
anweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt. all three electronic flight instrument system/engine indicating and crew alerting system
(EFIS/EICAS) interface units (EIUs), which could result in the inability of the flightcrew to maintain
Fristen: safe flight and landing of the airplane.
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 Compliance
FAA Airworthiness Directive.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der (e) You are responsible for having the actions required by this AD performed within the
FAA AD 2008-13-22 Amdt. 39-15585 compliance times specified, unless the actions have already been done.
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 Replacement
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
Rechtsbehelfsbelehrung: (f) Within 24 months after the effective date of this AD, replace at least one of the three EIUs,
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder part number (P/N) 622-8589-104, located on the E2-6 shelf of the main equipment center with a new
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen.
or modified EIU, P/N 622-8589-105, in accordance with the Accomplishment Instructions of Boeing
LTAs werden auch im Internet unter http://www.lba.de publiziert Service Bulletin 747-31-2368, Revision 1, dated July 24, 2006.
***
Note 1: Boeing Service Bulletin 747-31-2368, Revision 1, dated July 24, 2006, refers to
Rockwell Collins Service Bulletin EIU-7000-31-502, dated March 21, 2006, as an additional source
of service information for modifying an EIU by adding auto restart circuitry, which converts EIU P/N
622-8589-104 to P/N 622-8589-105.
Credit for Actions Done According to Previous Service Bulletin
(g) Actions done before the effective date of this AD in accordance with Boeing Service Bulletin
747-31-2368, dated November 22, 2005 (Revision 1 of the service bulletin specifies that the original
6
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issue is dated December 1, 2005), are acceptable for compliance with the corresponding requirements Issued in Renton, Washington, on June 8, 2008.
of paragraph (f) of this AD. Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
Terminating Action for AD 2004-10-05, Amendment 39-13635 [FR Doc. E8-14188 Filed 7-1-08; 8:45 am]
(h) Replacing an EIU with a new or modified EIU in accordance with paragraph (f) of this AD
constitutes terminating action for the EIU replacement of paragraph (d)(1) of AD 2004-10-05,
provided that the other two EIUs are replaced with EIUs having P/N 622-8589-104 or P/N 622-8589-
105. All other actions required by paragraph (d)(1) of AD 2004-10-05 must be complied with.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Seattle Aircraft Certification Office, FAA, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different compliance time for this AD,
follow the procedures in 14 CFR 39.19. We will only grant a compliance time extension for this AD
if the requestor can show that it is unable to accomplish the minimum requirements of the AD (i.e.,
one modified EIU for each airplane) by the compliance time for reasons beyond its control, such as
the inability to obtain enough parts to comply with the minimum requirements of the AD by the
compliance time. Therefore, requests to extend the compliance time for this AD must include the
following information:
(i) How many airplanes are included in the request,
(ii) An inventory of how many modified EIUs the requestor currently has on hand,
(iii) A forecast inventory showing that the requestor will not have enough modified EIUs
available to accomplish the minimum AD requirements (i.e., one modified EIU for each airplane) by
the AD compliance time, based upon the current inventory on hand and delivery rates from the parts
supplier,
(iv) Documentation of supplier delivery commitments for modified EIUs or conversion kits, as
applicable, including firm delivery commitment dates, that will provide the requestor with an
adequate number of parts to be able to accomplish the minimum AD requirements on its affected
airplanes, and
(v) Documentation of maintenance facility schedule availability for accomplishing the AD
requirements on all airplanes included in the request. We will not approve AMOC requests that
propose replacing or modifying all three EIUs in a time frame longer than 24 months instead of
replacing or modifying one EIU within 24 months. Before using any approved AMOC on any
airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.
Material Incorporated by Reference
(j) You must use Boeing Service Bulletin 747-31-2368, Revision 1, dated July 24, 2006, to do
the actions required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the incorporation by reference of this service
information under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact Boeing Commercial Airplanes, P.O.
Box 3707, Seattle, Washington 98124-2207.
(3) You may review copies of the service information incorporated by reference at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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/code_of_federal_
regulations/ibr_locations.html.
7 8
Lufttüchtigkeitsanweisung [Federal Register: July 10, 2008 (Volume 73, Number 133)]
LTA-Nr.: D-2008-275 [Rules and Regulations]
[Page 39583-39585]
Luftfahrt-Bundesamt From the Federal Register Online via GPO Access [wais.access.gpo.gov]
Datum der Bekanntgabe: 11.08.2008 [DOCID:fr10jy08-8]
Muster: Cirrus Design Corporation AD der ausländischen Behörde:
SR20 / SR22 FAA AD 2008-14-13 Amdt. 39-15608 ––––––––––––––––––––––––––––––––––
Geräte-Nr.: Technische Mitteilungen des Herstellers:
EASA.IM.A.007 Cirrus Design Corporation Service Bulletin 2X-52-07 Revision 4 DEPARTMENT OF TRANSPORTATION
vom 24.01.2008
Federal Aviation Administration
Betroffenes Luftfahrtgerät:
14 CFR Part 39
Cirrus Design Corporation
SR20 / SR22
[Docket No. FAA-2007-28245; Directorate Identifier 2007-CE-047-AD; Amendment 39-15608;
- Baureihen: SR20, SR22 AD 2008-14-13]
- Werk-Nrn.: SR20: RIN 2120-AA64
1423 bis 1906
SR22:
Airworthiness Directives; Cirrus Design Corporation Model SR20 and SR22 Airplanes
0795 und 0820 bis 2912
AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT).
Betrifft:
Möglicher Verlust der Kabinentür im Fluge durch Versagen der Befestigungsbeschläge. ACTION: Final rule.
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, SUMMARY: We are adopting a new airworthiness directive (AD) for certain Cirrus Design
vollständig und innerhalb der vorgesehenen Fristen auf Basis der genannten Bezugsdokumente Corporation (CDC) Models SR20 and SR22 airplanes. This AD requires you to replace the cabin
durchgeführt werden. Alle Abweichungen von den Maßnahmen und Fristen dieser Lufttüchtigkeits- door rod ends with new parts including a redesigned non-binding hinge pin that replaces the existing
anweisung bedürfen der vorherigen Zustimmung durch das Luftfahrt-Bundesamt. pin at the upper door hinge. This AD results from two known occurrences of in-flight cabin door
separation (one total separation and one retained by the door strut). The rod ends, a component of the
Fristen: door hinges, may fail and result in a door separation from the airplane while in flight. We are issuing
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 this AD to prevent in-flight failure of the cabin door, which could result in door separation from the
FAA Airworthiness Directive. airplane.
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der DATES: This AD becomes effective on August 14, 2008.
FAA AD 2008-14-13 Amdt. 39-15608 On August 14, 2008, the Director of the Federal Register approved the incorporation by
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 reference of certain publications listed in this AD.
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.
ADDRESSES: For service information identified in this AD, contact Cirrus Design Corporation,
Rechtsbehelfsbelehrung:
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder
4515 Taylor Circle, Duluth, Minnesota 55811; telephone: (218) 727-2737; Internet address:
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen. www.cirrusdesign.com.
LTAs werden auch im Internet unter http://www.lba.de publiziert
To view the AD docket, go to U.S. Department of Transportation, Docket Operations, M-30,
*** West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC
20590, or on the Internet at http://www.regulations.gov. The docket number is FAA-2007-28245;
Directorate Identifier 2007-CE-047-AD.
FOR FURTHER INFORMATION CONTACT: Wess Rouse, Aerospace Engineer, Chicago
Aircraft Certification Office (ACO), 2300 East Devon Avenue, Room 107, Des Plaines, Illinois
60018; telephone: (847) 294-8113; fax: (847) 294-7834.
1
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SUPPLEMENTARY INFORMATION: Regulatory Findings
Discussion 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
On March 26, 2008, we issued a proposal to amend part 39 of the Federal Aviation Regulations national government and the States, or on the distribution of power and responsibilities among the
(14 CFR part 39) to include an AD that would apply to certain SR20 and SR22 airplanes. This various levels of government.
proposal was published in the Federal Register as a supplemental notice of proposed rulemaking For the reasons discussed above, I certify that this AD:
(NPRM) on April 2, 2008 (73 FR 17935). The NPRM proposed to replace the cabin door rod ends 1. Is not a ''significant regulatory action'' under Executive Order 12866;
with new parts including a redesigned non-binding hinge pin that replaces the existing pin at the 2. Is not a ''significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034,
upper door hinge. February 26, 1979); and
3. Will not have a significant economic impact, positive or negative, on a substantial number of
Comments small entities under the criteria of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD (and other information as included
We provided the public the opportunity to participate in developing this AD. We received no in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary
comments on the proposal or on the determination of the cost to the public. by sending a request to us at the address listed under ADDRESSES. Include ''Docket No. FAA-2007-
28245; Directorate Identifier 2007-CE-047-AD'' in your request.
Conclusion
List of Subjects in 14 CFR Part 39
We have carefully reviewed the available data and determined that air safety and the public
interest require adopting the AD as proposed except for minor editorial corrections. We have Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
determined that these minor corrections:
Are consistent with the intent that was proposed in the NPRM for correcting the unsafe Adoption of the Amendment
condition; and
Do not add any additional burden upon the public than was already proposed in the NPRM. Accordingly, 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:
Costs of Compliance
PART 39–AIRWORTHINESS DIRECTIVES
We estimate that the AD affects 2,308 airplanes in the U.S. registry.
The costs vary from 3.5 work-hours to incorporate Cirrus Kit 70186-004 and 2.5 work-hours to 1. The authority citation for part 39 continues to read as follows:
incorporate Cirrus Kit 70186-005. Parts cost for either kit is $270. For the purposes of this AD, we
will use 3.5 work-hours for all airplanes. Based on this, the cost of this AD is: Authority: 49 U.S.C. 106(g), 40113, 44701.
Labor Cost Parts Cost Total Cost Per Airplane Total Fleet Cost § 39.13 [Amended]
3.5 work-hours X $80 $270 $550 $1,269,400 2. FAA amends § 39.13 by adding the following new AD:
per hour = $280
Note: CDC will provide warranty credit to the extent noted in CDC Service Bulletin 2X-52-07
R4, dated January 24, 2008.
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 AD.
2 3
AIRWORTHINESS DIRECTIVE using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate
FAA principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your
Aircraft Certification Service www.faa.gov/aircraft/safety/alerts/ local FSDO.
www.gpoaccess.gov/fr/advanced.html
Related Information
2008-14-13 Cirrus Design Corporation: Amendment 39-15608; Docket No. FAA-2007-28245;
Directorate Identifier 2007-CE-047-AD. (g) To get copies of the service information referenced in this AD, contact Cirrus Design
Corporation, 4515 Taylor Circle, Duluth, Minnesota 55811, telephone: (218) 788-3000. To view the
Effective Date AD docket, go to the U.S. Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or on the
(a) This AD becomes effective on August 14, 2008. Internet at http://dms.dot.gov. The docket number is Docket No. FAA-2007-28245; Directorate
Identifier 2007-CE-047-AD.
Affected ADs
Material Incorporated by Reference
(b) None.
(h) You must use Cirrus Design Corporation Service Bulletin SB 2X-52-07 R4, dated January
Applicability 24, 2008, to do the actions required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the incorporation by reference of this service
(c) This AD applies to the following airplane models and serial numbers that are certificated in information under 5 U.S.C. 552(a) and 1 CFR part 51.
any category: (2) For service information identified in this AD, contact Cirrus Design Corporation, 4515
Taylor Circle, Duluth, Minnesota 55811; telephone: (218) 727-2737; Internet address:
www.cirrusdesign.com.
Models Serial Nos. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901
SR20 1423 through 1906. Locust, Kansas City, Missouri 64106; or 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:
SR22 0795 and 0820 through 2912. http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Unsafe Condition Issued in Kansas City, Missouri, on July 1, 2008.
John Colomy,
(d) This AD results from two known occurrences of in-flight cabin door separation (one total Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
separation and one retained by the door strut). We are issuing this AD to prevent in-flight failure of [FR Doc. E8-15474 Filed 7-9-08; 8:45 am]
the cabin door, which could result in door separation from the airplane.
Compliance
(e) Unless already done, within the next 50 hours time-in-service (TIS) after August 14, 2008
(the effective date of this AD) or within 180 days after August 14, 2008 (the effective date of this
AD), whichever occurs first, following Cirrus Design Corporation Service Bulletin SB 2X-52-07 R4,
dated January 24, 2008, do one of the following:
(1) If threaded sleeve is installed at the cabin door rod end, install cabin door rod end Kit 70186-
004.
(2) If threaded sleeve is not installed at the cabin door rod end, install cabin door rod end Kit
70186-005.
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Chicago 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. Send
information to ATTN: Wess Rouse, Aerospace Engineer, Chicago ACO, 2300 East Devon Avenue,
Room 107, Des Plaines, Illinois 60018; telephone: (847) 294-8113; fax: (847) 294-7834. Before
4 5
EASA AD No.: 2008-0140
Lufttüchtigkeitsanweisung EASA AIRWORTHINESS DIRECTIVE
LTA-Nr.: D-2008-276
AD No.: 2008 - 0140
Luftfahrt-Bundesamt
Datum der Bekanntgabe: 11.08.2008
Muster: Airbus AD der ausländischen Behörde:
A340 EASA AD 2008-0140 vom 28.07.2008 Date: 28 July 2008
Geräte-Nr.: Technische Mitteilungen des Herstellers: Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with
2850, EASA.A.015 Airbus Service Bulletin A340-54-4010 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
Airbus may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of that
A340 Airworthiness 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: A340-211, A340-212, A340-213, A340-311, A340-312 und A340-313
Type Approval Holder’s Name : Type/Model designation(s) :
- Werk-Nrn.: Alle
AIRBUS A340-200/-300 aircraft
-----------------------------------------------------------------------------------------------------------------------
Ausgenommen sind die bei der Flugzeugherstellung bereits modifizierten Flugzeuge TCDS Number : EASA A.015
gemäß Airbus Modifikation 49203 (Production-Mod.) .
-----------------------------------------------------------------------------------------------------------------------
Foreign AD : Not applicable
Betrifft:
GONDELN / PYLON (ATA: 54): Pylon-Pyramid-Befestigungsbereich hinter der Rippe Nr. 1 - Inspektion Supersedure : None
Maßnahmen:
Detaillierte Informationen über die durchzuführenden Maßnahmen sind der oben genannten EASA
Airworthiness Directive und der genannten technischen Mitteilung des Herstellers zu entnehmen. Nacelles/Pylons – Pylon Pyramid Attachment Areas aft of Rib1
ATA 54
Alle erforderlichen Maßnahmen zur Abstellung des technischen Mangels müssen ordnungsgemäß, - Inspection
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. Manufacturer(s): AIRBUS (formerly AIRBUS INDUSTRIE)
Fristen: Applicability: AIRBUS A340 aircraft, models -211, -212, -213, - 311, - 312 and -313, all
Alle anzuwendenden Fristen sind der oben genannten EASA Airworthiness Directive zu entnehmen. serial numbers except those on which AIRBUS Modification 49203 has
Die Laufzeit aller anzuwendenden Fristen beginnt mit dem Datum der Inkraftsetzung der genannten been embodied in production.
EASA Airworthiness Directive.
Reason: Further to accomplishment of A340 ALI tasks 545104, which require a
Diese Lufttüchtigkeitsanweisung entspricht hinsichtlich der durchzuführenden Maßnahmen und Fristen der rototest inspection as per Non Destructive Testing Manual (NTM) 54-51-
EASA AD 2008-0140 vom 28.07.2008 04 of engine pylon pyramid attachment areas at aft end of lower arms
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 between Rib1 and Rib2 (2 fastener locations/pylon), four findings have
Sicherheit des Luftverkehrs, das in diesem Fall das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es been reported and repaired.
erforderlich, die sofortige Vollziehung dieser LTA anzuordnen.
Further investigations made on performances of High Frequency Eddy
Rechtsbehelfsbelehrung: Current (HFEC) inspection techniques in steel led to the conclusion that
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder existing NTM procedure 54-51-04 by rototest is not reliable because this
zur Niederschrift beim Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen.
method is not adapted to the ferromagnetic materials and therefore
LTAs werden auch im Internet unter http://www.lba.de publiziert findings reported up to now using this procedure can be considered as
*** uncertain.
Therefore, a new inspection procedure using Ultra Sonic (US) testing
without fastener removal has been developed.
In order to comply with certification requirements, this Airworthiness
Directive (AD) requires performing the new US inspection on all A340-
200/-300 pre-modification 49203 (reinforcements of pylon primary
structure for enhanced A340).
EASA Form 110 Page 1/3
Aktenzeichen: (01)T231-502.1/D-2008-276 Seite 1 von 1
EASA AD No.: 2008-0140 EASA AD No.: 2008-0140
Effective Date: 11 August 2008 3. Enquiries regarding this AD should be referred to the Airworthiness
Directives, Safety Management & Research Section, Certification
Directorate, EASA. E-mail ADs@easa.europa.eu
Required action(s) Required as indicated:
and Compliance 4. For any question concerning the technical content of the requirements
1. Unless already accomplished, perform a special detailed inspection of
Time(s): pylon pyramid attachment areas at aft end of lower arms between Rib 1
in this AD, please contact:
and Rib 2 without fastener removal (2 fastener locations/pylon) in AIRBUS SAS – Airworthiness Office - EAL Fax: +33 5 61 93 45 80.
accordance with instructions given in AIRBUS Service Bulletin (SB) A340-
54-4010, with the following threshold :
x Pending on Weight Variant (WV), before accumulation of threshold X1
Flight Cycles (FC) or X2 Flight Hours (FH), whichever occurs first:
Threshold X1 FC Threshold X2 FH WV
13 000 60 000 000 thru 004
11 470 77 400 020, 021, 023 thru 026,
028 thru 030, PRE 49203
11 000 30 000 027
x For aircraft belonging to WV 000 thru 004 already inspected in
accordance with ALI task 545104-01-01 (using rototest procedure):
within 2 680 FC or 19 200 FH from this rototest inspection, whichever
occurs first, without exceeding 15 280 FC or 76 400 FH since first flight
whichever occurs first.
2. If any fatigue crack has been detected, before next flight contact AIRBUS
to get the repair instructions and apply the associated corrective actions.
3. If no fatigue crack has been detected, repeat this inspection at interval not
exceeding Y1 FC or Y2 FH whichever occurs first, pending on WV:
Interval Y1 FC Interval Y2 FH WV
1 900 9 500 000 thru 004
1 700 8 500 020, 021, 023 thru 026,
028 thru 030, PRE
49203
1 700 8 500 027
Note: This AD cancels A340 ALI tasks 545104-01-01 and 545104-01-02 and
545104-01-06.
Ref. Publications: AIRBUS Service Bulletin A340-54-4010 at original issue.
The use of later approved revisions of this document 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. The required actions and the risk allowance have granted the
issuance of a Final AD with Request for Comments, postponing the
public consultation process after publication.
EASA Form 110 Page 2/3 EASA Form 110 Page 3/3
