Airworthiness Directives; Airbus Model A330-200, A330-300, A340-300, A340-500, and A340-600 Series Airplanes, 72323-72326 [E8-27940]
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Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations
TABLE 1—MATERIAL INCORPORATED BY REFERENCE FOR ACTIONS REQUIRED IN THIS AD—Continued
Service Bulletin
Revision
Date
Boeing Special Attention Service Bulletin 737–25–1475 .....................................
BFGoodrich Service Bulletin 25–308 ...................................................................
Original ..................................................
Original ..................................................
November 26, 2002.
January 21, 2000.
TABLE 2—MATERIAL INCORPORATED BY REFERENCE FOR THE OPTIONAL TERMINATING ACTION IN THIS AD
Service Bulletin
Revision
Boeing Service Bulletin 737–25–1404 .................................................................
Boeing Special Attention Service Bulletin 737–25–1403 .....................................
Goodrich Service Bulletin 25–338 ........................................................................
1 ............................................................
1 ............................................................
1 ............................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information listed in Table 3 of
Date
April 18, 2002.
November 29, 2001.
March 31, 2004.
this AD under 5 U.S.C. 552(a) and 1 CFR part
51.
TABLE 3—NEW MATERIAL INCORPORATED BY REFERENCE
Service Bulletin
Revision
Boeing Service Bulletin 737–25–1404 .................................................................
Boeing Service Bulletin 737–25–1491 .................................................................
Boeing Special Attention Service Bulletin 737–25–1475 .....................................
Goodrich Service Bulletin 25–308 ........................................................................
1 ............................................................
Original ..................................................
Original ..................................................
Original ..................................................
(2) The Director of the Federal Register
previously approved the incorporation by
reference of Boeing Service Bulletin 737–25–
1404, dated May 25, 2000, on August 28,
2001 (66 FR 38361, July 24, 2001).
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207; telephone (206)
544–9990; fax (206) 766–5682; e-mail
DDCS@boeing.com; Internet https://
www.myboeingfleet.com.
(4) You may review copies of the service
information that is 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: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
November 16, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–27926 Filed 11–26–08; 8:45 am]
dwashington3 on PROD1PC60 with RULES
BILLING CODE 4910–13–P
VerDate Aug<31>2005
14:57 Nov 26, 2008
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0910; Directorate
Identifier 2008–NM–033–AD; Amendment
39–15749; AD 2008–24–09]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–200, A330–300, A340–300, A340–
500, and A340–600 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are superseding an
existing airworthiness directive (AD) for
the products listed above. This AD
results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
An A330 operator reported a shroud box
bottom panel missing during a routine
inspection. The same panel detached from an
A330 aircraft during take-off, causing damage
to the surrounding structure and to the
Trimmable Horizontal Stabilizer (THS) tip
fairing.
The inspection indicated the blind rivets
used to attach the panel worked loose
causing fatigue damage with crack
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Date
April 18, 2002.
April 23, 2007.
November 26, 2002.
January 21, 2000.
propagation through the fastener line
resulting in panel detachment * * *.
* * * Three additional events of panel loss
have been experienced on in service aircraft
already inspected in accordance with the AD
requirements * * *.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
January 2, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 2, 2009.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on August 26, 2008 (73 FR
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72324
Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations
50256) and proposed to supersede AD
2007–08–05, Amendment 39–15022 (72
FR 18563, April 13, 2007). That NPRM
proposed to correct an unsafe condition
for the specified products. The MCAI
states:
An A330 operator reported a shroud box
bottom panel missing during a routine
inspection. The same panel detached from an
A330 aircraft during take-off, causing damage
to the surrounding structure and to the
Trimmable Horizontal Stabilizer (THS) tip
fairing.
The inspection indicated the blind rivets
used to attach the panel worked loose
causing fatigue damage with crack
propagation through the fastener line
resulting in panel detachment.
To avoid potential injuries to persons on
ground, Airworthiness Directive (AD) 2006–
0107 [which corresponds with FAA AD
2007–08–05] mandated a one time detailed
visual inspection of the shroud box bottom
panel.
Further to issuance of AD 2006–0107, three
additional events of panel loss have been
experienced on in service aircraft already
inspected in accordance with the AD
requirements and no findings. Thus, it has
been decided to delete this one time detailed
visual inspection and to mandate a
modification which prevents such unsafe
condition. Therefore, the present AD
supersedes EASA AD 2006–0107 and
mandates the installation of a bolted shroud
box bottom panel instead of blind riveted
metallic design.
The modification includes doing all
applicable related investigative and
corrective actions. The related
investigative action is an inspection to
detect cracks of the shroud box hole.
The corrective action is repairing any
cracked shroud box hole. The
applicability of the MCAI has been
revised; certain airplanes have been
removed and others added. You may
obtain further information by examining
the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
dwashington3 on PROD1PC60 with RULES
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
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14:57 Nov 26, 2008
Jkt 217001
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
about 34 products of U.S. registry. We
also estimate that it will take about 20
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $80 per work-hour.
Required parts will cost about $990 per
product. Where the service information
lists required parts costs that are
covered under warranty, we have
assumed that there will be no charge for
these parts. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here. Based on these
figures, we estimate the cost of this AD
to the U.S. operators to be $88,060, or
$2,590 per product.
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 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 this AD:
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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 regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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 the NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
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:
■
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 39–15022 (72 FR
18563, April 13, 2007) and adding the
following new AD:
■
2008–24–09 Airbus: Amendment 39–15749.
Docket No. FAA–2008–0910; Directorate
Identifier 2008–NM–033–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective January 2, 2009.
Affected ADs
(b) This AD supersedes AD 2007–08–05,
Amendment 39–15022.
Applicability
(c) This AD applies to Airbus airplanes
identified in Table 1 of this AD; certificated
in any category.
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Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations
72325
TABLE 1—APPLICABILITY
For model—
On which—
Except for those airplanes on which—
(1) A330–200, A330–300, and
A340–300 series, all certified
models, all serial numbers.
(2) Airbus A340–500 and A340–
600 series, all certified models,
all serial numbers.
Airbus modification 46077 has
been embodied in production.
Airbus Modification 55568 has been done in production, or Airbus
Mandatory Service Bulletin A330–57–3100 or Airbus Mandatory
Service Bulletin A340–57–4109 has been embodied in service.
Airbus Modification 55568 has been embodied in production, or Airbus Mandatory Service Bulletin A340–57–5018 has been embodied
in service.
None ..............................................
Subject
(d) Air Transport Association (ATA) of
America Code 57: Wings.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
An A330 operator reported a shroud box
bottom panel missing during a routine
inspection. The same panel detached from an
A330 aircraft during take-off, causing damage
to the surrounding structure and to the
Trimmable Horizontal Stabilizer (THS) tip
fairing.
The inspection indicated the blind rivets
used to attach the panel worked loose
causing fatigue damage with crack
propagation through the fastener line
resulting in panel detachment.
To avoid potential injuries to persons on
ground, Airworthiness Directive (AD) 2006–
0107 [which corresponds with FAA AD
2007–08–05] mandated a one time detailed
visual inspection of the shroud box bottom
panel.
Further to issuance of AD 2006–0107, three
additional events of panel loss have been
experienced on in service aircraft already
inspected in accordance with the AD
requirements and no findings. Thus, it has
been decided to delete this one time detailed
visual inspection and to mandate a
modification which prevents such unsafe
condition. Therefore, the present AD
supersedes EASA AD 2006–0107 and
mandates the installation of a bolted shroud
box bottom panel instead of blind riveted
metallic design.
The modification includes doing all
applicable related investigative and
corrective actions. The related investigative
action is an inspection to detect cracks of the
shroud box hole. The corrective action is
repairing any cracked shroud box hole.
New Requirements of This AD: Actions and
Compliance
(f) Unless already done: Within 69 months
after the effective date of this AD, modify the
shroud box bottom skin panel on both wings,
and do all applicable related investigative
and corrective actions, by accomplishing all
the actions in the applicable service bulletins
identified in Table 2 of this AD. Do all
applicable related investigative and
corrective actions before further flight.
TABLE 2—SERVICE BULLETINS
Service Bulletin—
Date—
Airbus Mandatory Service Bulletin A330–57–3100 ....................................................................................................................
Airbus Mandatory Service Bulletin A340–57–4109 ....................................................................................................................
Airbus Mandatory Service Bulletin A340–57–5018 ....................................................................................................................
October 1, 2007.
October 1, 2007.
October 1, 2007.
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
dwashington3 on PROD1PC60 with RULES
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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: Vladimir
Ulyanov, Aerospace Engineer, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149. 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.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2008–
0002, dated January 7, 2008, and the service
bulletins identified in Table 2 of this AD for
related information.
Material Incorporated by Reference
(i) You must use the service information
specified in Table 3 of this AD 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 Airbus SAS—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; fax +33 5 61
93 45 80, e-mail airworthiness.A330–
A340@airbus.com; Internet https://
www.airbus.com.
(3) You may review copies 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: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
TABLE 3—MATERIAL INCORPORATED BY REFERENCE
Service Bulletin—
Date—
Airbus Mandatory Service Bulletin A330–57–3100 ....................................................................................................................
Airbus Mandatory Service Bulletin A340–57–4109 ....................................................................................................................
October 1, 2007.
October 1, 2007.
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Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations
TABLE 3—MATERIAL INCORPORATED BY REFERENCE—Continued
Service Bulletin—
Date—
Airbus Mandatory Service Bulletin A340–57–5018 ....................................................................................................................
October 1, 2007.
Issued in Renton, Washington, on
November 16, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–27940 Filed 11–26–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1244; Directorate
Identifier 2008–SW–59–AD; Amendment 39–
15752; AD 2008–22–52]
RIN 2120–AA64
Airworthiness Directives; MD
Helicopters, Inc. Model 500N and 600N
Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule; request for
comments.
dwashington3 on PROD1PC60 with RULES
AGENCY:
SUMMARY: This document supersedes
AD 2008–18–52 and publishes in the
Federal Register an amendment
adopting Emergency Airworthiness
Directive (AD) 2008–22–52 which was
sent previously to all known U.S.
owners and operators of MD
Helicopters, Inc. (MDHI) Model 500N
and 600N helicopters by individual
letters. This AD requires turning OFF
the Yaw Stability Augmentation System
(YSAS); installing a placard that limits
airspeed to 100 KTS or VNE, whichever
is less; and revising the limitations
section of the Rotorcraft Flight Manual
(RFM) to reflect that limitation. Finally,
replacing the adapter tubes with
airworthy adapter tubes that have a
production date code stamp is required.
This AD is prompted by several
occurrences of failed adapter tubes on
the Model MD900 helicopter which uses
the same adapter tubes. The actions
specified by this AD are intended to
prevent loss of yaw control and
subsequent loss of control of the
helicopter.
Effective December 15, 2008, to
all persons except those persons to
whom it was made immediately
effective by Emergency AD 2008–22–52,
issued on October 23, 2008, which
DATES:
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14:57 Nov 26, 2008
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contained the requirements of this
amendment.
Comments for inclusion in the Rules
Docket must be received on or before
January 27, 2009.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
You may get the service information
identified in this AD from MD
Helicopters Inc., Attn: Customer
Support Division, 4555 E. McDowell
Rd., Mail Stop M615, Mesa, Arizona
85215–9734, telephone 1–800–388–
3378, fax 480–346–6813, or on the Web
at https://www.mdhelicopters.com.
Examining the Docket: You may
examine the docket that contains the
AD, any comments, and other
information on the Internet at https://
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 Docket
Operations office (telephone (800) 647–
5527) is located in Room W12–140 on
the ground floor of the West Building at
the street address stated in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Eric
D. Schrieber, FAA, Los Angeles Aircraft
Certification Office, Aviation Safety
Engineer, Airframe Branch, 3960
Paramount Blvd., Lakewood, California
90712, telephone 562–627–5348, fax
562–627–5210.
SUPPLEMENTARY INFORMATION: On August
20, 2008, we issued Emergency AD
2008–18–51 for 500N, 600N, and
MD900 helicopters. Emergency AD
2008–18–51 was prompted by reports
that 2 MD900 helicopters experienced
failed vertical stabilizer control system
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(VSCS) adapter tubes. In one case, the
helicopter experienced an
uncommanded yaw, resulting in loss of
a window and a door. The Emergency
AD required several actions related to
the YSAS for the Model 500N and 600N
helicopters and to the vertical stabilizer
control system (VSCS) for the Model
MD900 helicopters.
After we issued Emergency AD 2008–
18–51, we discovered that pulling the
circuit breaker per the Emergency AD
caused impaired directional control,
which could result in loss of control of
the helicopter. Therefore, on August 27,
2008, we issued superseding Emergency
AD 2008–18–52, which requires, for
Model 500N, 600N and MD900
helicopters, turning OFF the VSCS or
YSAS switches instead of pulling the
circuit breakers and installing placards
that limit airspeed to 100 KIAS or VNE,
whichever is less. For the Model MD900
helicopters, limiting flight to VFR,
prohibiting use of the autopilot, and
making changes to the Emergency
Procedures and Airworthiness (sic)
Limitations sections of the RFM are also
required. For all of the helicopter
models, Emergency AD 2008–18–52
requires, within 45 days, terminating
action by replacing the adapter tube
with an airworthy adapter tube that has
a date stamp of August 15, 2008 or later,
and then removing the placards,
removing the AD limitation changes
from the RFM, and returning all
switches and circuit breakers to their
normal positions.
Since the issuance of Emergency AD
2008–18–52, we have had additional
occurrences of failed adapter tubes on
the MD900 helicopters. The
replacement adapter tube that was
terminating action for the requirements
of Emergency AD 2008–18–52 failed on
2 of the MD900 helicopters.
Furthermore, adapter tubes without a
production date code stamp remain a
safety concern on the 500N and 600N
helicopters because they may not
conform to the FAA-approved design.
Therefore, we separated the AD actions
and issued 2 superseding Emergency
ADs; 2008–22–52 for the 500N and
600N helicopters, and 2008–22–53 for
the MD900 helicopters.
Emergency AD 2008–22–52 applies to
the 500N and 600N helicopters and
continues to require the same actions as
Emergency AD 2008–18–52; however,
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]]>Agencies
[Federal Register Volume 73, Number 230 (Friday, November 28, 2008)]
[Rules and Regulations]
[Pages 72323-72326]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-27940]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0910; Directorate Identifier 2008-NM-033-AD;
Amendment 39-15749; AD 2008-24-09]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-200, A330-300, A340-
300, A340-500, and A340-600 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. This AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
An A330 operator reported a shroud box bottom panel missing
during a routine inspection. The same panel detached from an A330
aircraft during take-off, causing damage to the surrounding
structure and to the Trimmable Horizontal Stabilizer (THS) tip
fairing.
The inspection indicated the blind rivets used to attach the
panel worked loose causing fatigue damage with crack propagation
through the fastener line resulting in panel detachment * * *.
* * * Three additional events of panel loss have been
experienced on in service aircraft already inspected in accordance
with the AD requirements * * *.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective January 2, 2009.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 2,
2009.
ADDRESSES: You may examine the AD docket on the Internet at https://
www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1138; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on August 26, 2008 (73
FR
[[Page 72324]]
50256) and proposed to supersede AD 2007-08-05, Amendment 39-15022 (72
FR 18563, April 13, 2007). That NPRM proposed to correct an unsafe
condition for the specified products. The MCAI states:
An A330 operator reported a shroud box bottom panel missing
during a routine inspection. The same panel detached from an A330
aircraft during take-off, causing damage to the surrounding
structure and to the Trimmable Horizontal Stabilizer (THS) tip
fairing.
The inspection indicated the blind rivets used to attach the
panel worked loose causing fatigue damage with crack propagation
through the fastener line resulting in panel detachment.
To avoid potential injuries to persons on ground, Airworthiness
Directive (AD) 2006-0107 [which corresponds with FAA AD 2007-08-05]
mandated a one time detailed visual inspection of the shroud box
bottom panel.
Further to issuance of AD 2006-0107, three additional events of
panel loss have been experienced on in service aircraft already
inspected in accordance with the AD requirements and no findings.
Thus, it has been decided to delete this one time detailed visual
inspection and to mandate a modification which prevents such unsafe
condition. Therefore, the present AD supersedes EASA AD 2006-0107
and mandates the installation of a bolted shroud box bottom panel
instead of blind riveted metallic design.
The modification includes doing all applicable related
investigative and corrective actions. The related investigative action
is an inspection to detect cracks of the shroud box hole. The
corrective action is repairing any cracked shroud box hole. The
applicability of the MCAI has been revised; certain airplanes have been
removed and others added. You may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect about 34 products of U.S.
registry. We also estimate that it will take about 20 work-hours per
product to comply with the basic requirements of this AD. The average
labor rate is $80 per work-hour. Required parts will cost about $990
per product. Where the service information lists required parts costs
that are covered under warranty, we have assumed that there will be no
charge for these parts. As we do not control warranty coverage for
affected parties, some parties may incur costs higher than estimated
here. Based on these figures, we estimate the cost of this AD to the
U.S. operators to be $88,060, or $2,590 per product.
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 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 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 regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
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 the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-15022 (72 FR
18563, April 13, 2007) and adding the following new AD:
2008-24-09 Airbus: Amendment 39-15749. Docket No. FAA-2008-0910;
Directorate Identifier 2008-NM-033-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective January
2, 2009.
Affected ADs
(b) This AD supersedes AD 2007-08-05, Amendment 39-15022.
Applicability
(c) This AD applies to Airbus airplanes identified in Table 1 of
this AD; certificated in any category.
[[Page 72325]]
Table 1--Applicability
------------------------------------------------------------------------
Except for those
For model-- On which-- airplanes on which--
------------------------------------------------------------------------
(1) A330-200, A330-300, and Airbus Airbus Modification
A340-300 series, all modification 55568 has been done
certified models, all serial 46077 has been in production, or
numbers. embodied in Airbus Mandatory
production. Service Bulletin
A330-57-3100 or
Airbus Mandatory
Service Bulletin
A340-57-4109 has
been embodied in
service.
(2) Airbus A340-500 and A340- None............. Airbus Modification
600 series, all certified 55568 has been
models, all serial numbers. embodied in
production, or
Airbus Mandatory
Service Bulletin
A340-57-5018 has
been embodied in
service.
------------------------------------------------------------------------
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
An A330 operator reported a shroud box bottom panel missing
during a routine inspection. The same panel detached from an A330
aircraft during take-off, causing damage to the surrounding
structure and to the Trimmable Horizontal Stabilizer (THS) tip
fairing.
The inspection indicated the blind rivets used to attach the
panel worked loose causing fatigue damage with crack propagation
through the fastener line resulting in panel detachment.
To avoid potential injuries to persons on ground, Airworthiness
Directive (AD) 2006-0107 [which corresponds with FAA AD 2007-08-05]
mandated a one time detailed visual inspection of the shroud box
bottom panel.
Further to issuance of AD 2006-0107, three additional events of
panel loss have been experienced on in service aircraft already
inspected in accordance with the AD requirements and no findings.
Thus, it has been decided to delete this one time detailed visual
inspection and to mandate a modification which prevents such unsafe
condition. Therefore, the present AD supersedes EASA AD 2006-0107
and mandates the installation of a bolted shroud box bottom panel
instead of blind riveted metallic design.
The modification includes doing all applicable related
investigative and corrective actions. The related investigative
action is an inspection to detect cracks of the shroud box hole. The
corrective action is repairing any cracked shroud box hole.
New Requirements of This AD: Actions and Compliance
(f) Unless already done: Within 69 months after the effective
date of this AD, modify the shroud box bottom skin panel on both
wings, and do all applicable related investigative and corrective
actions, by accomplishing all the actions in the applicable service
bulletins identified in Table 2 of this AD. Do all applicable
related investigative and corrective actions before further flight.
Table 2--Service Bulletins
------------------------------------------------------------------------
Service Bulletin-- Date--
------------------------------------------------------------------------
Airbus Mandatory Service Bulletin October 1, 2007.
A330-57-3100.
Airbus Mandatory Service Bulletin October 1, 2007.
A340-57-4109.
Airbus Mandatory Service Bulletin October 1, 2007.
A340-57-5018.
------------------------------------------------------------------------
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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:
Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149.
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.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(h) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2008-0002, dated January 7, 2008, and the service
bulletins identified in Table 2 of this AD for related information.
Material Incorporated by Reference
(i) You must use the service information specified in Table 3 of
this AD 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
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; fax +33 5 61 93 45 80, e-mail
airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com.
(3) You may review copies 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: https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html.
Table 3--Material Incorporated by Reference
------------------------------------------------------------------------
Service Bulletin-- Date--
------------------------------------------------------------------------
Airbus Mandatory Service Bulletin October 1, 2007.
A330-57-3100.
Airbus Mandatory Service Bulletin October 1, 2007.
A340-57-4109.
[[Page 72326]]
Airbus Mandatory Service Bulletin October 1, 2007.
A340-57-5018.
------------------------------------------------------------------------
Issued in Renton, Washington, on November 16, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E8-27940 Filed 11-26-08; 8:45 am]
BILLING CODE 4910-13-P
