Airworthiness Directives; Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 Airplanes; and Model A340-200 and -300 Series Airplanes, 42602-42607 [2011-18131]
Download as PDF
<![CDATA[
42602
Federal Register / Vol. 76, No. 138 / Tuesday, July 19, 2011 / Proposed Rules
presented by the importer to an
authorized inspector at the port of
arrival, upon arrival of the birds,
poultry, hatching eggs, or poultry meat
and products at the port.
PART 95—SANITARY CONTROL OF
ANIMAL BYPRODUCTS (EXCEPT
CASINGS), AND HAY AND STRAW,
OFFERED FOR ENTRY INTO THE
UNITED STATES
23. The authority citation for part 95
continues to read as follows:
Authority: 7 U.S.C. 8301–8317; 21 U.S.C.
136 and 136a; 31 U.S.C. 9701; 7 CFR 2.22,
2.80, and 371.4.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above that would
supersede an existing AD. This
proposed 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:
24. In § 95.5, paragraph (c) is
amended by removing the words
‘‘exotic’’ and ‘‘subtype H5N1’’.
During A330 and A340 aeroplanes fatigue
tests, cracks appeared on the right (RH) and
left (LH) sides between the crossing area of
the keel beam fitting and the front spar of the
Centre Wing Box (CWB). This condition, if
not corrected, could lead to keel beam
rupture which would affect the area
structural integrity.
§ 95.6
*
§ 95.5
[Amended]
[Amended]
25. In § 95.6, paragraph (c) is
amended by removing the word
‘‘exotic’’.
PART 104—PERMITS FOR
BIOLOGICAL PRODUCTS
26. The authority citation for part 104
continues to read as follows:
Authority: 21 U.S.C. 151–159; 7 CFR 2.22,
2.80, and 371.4.
§ 104.2
[Amended]
27. In § 104.2, paragraph (b) is
amended by removing the words ‘‘fowl
pest (fowl plague)’’ and adding the
words ‘‘highly pathogenic avian
influenza’’ in their place.
Done in Washington, DC, this 13th day of
July 2011.
Kevin Shea,
Acting Administrator, Animal and Plant
Health Inspection Service.
[FR Doc. 2011–18108 Filed 7–18–11 8:45 am]
BILLING CODE 3410–34–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0717; Directorate
Identifier 2010–NM–108–AD]
srobinson on DSK4SPTVN1PROD with PROPOSALS
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–201, –202, –203, –223, –243,
–301, –302, –303, –321, –322, –323,
–341, –342, and –343 Airplanes; and
Model A340–200 and –300 Series
Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
VerDate Mar<15>2010
17:35 Jul 18, 2011
Jkt 223001
*
*
*
*
The proposed AD would require actions
that are intended to address the unsafe
condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by September 2, 2011.
ADDRESSES: You may send comments by
any of the following methods:
• 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 W12–40, 1200 New Jersey
Avenue, SE., Washington, DC, between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Airbus SAS—
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; e-mail
airworthiness.A330–A340@airbus.com;
Internet https://www.airbus.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
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,
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
except Federal holidays. The AD docket
contains this proposed AD, 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.
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:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2011–0717; Directorate Identifier
2010–NM–108–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On July 24, 2007, we issued AD 2007–
16–02, Amendment 39–15141 (72 FR
44731, August 9, 2007). That AD
required actions intended to address an
unsafe condition on the products listed
above.
Since we issued AD 2007–16–02, the
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2010–0024,
dated February 12, 2010 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
During A330 and A340 aeroplanes fatigue
tests, cracks appeared on the right (RH) and
left (LH) sides between the crossing area of
the keel beam fitting and the front spar of the
Centre Wing Box (CWB). This condition, if
not corrected, could lead to keel beam
rupture which would affect the area
structural integrity.
In order to maintain the structural integrity
of the aeroplane, EASA AD 2006–0315R1
required repetitive special detailed
E:\FR\FM\19JYP1.SGM
19JYP1
42603
Federal Register / Vol. 76, No. 138 / Tuesday, July 19, 2011 / Proposed Rules
inspections on the horizontal flange of the
keel beam in the area of first fastener hole aft
of FR40.
This AD, which supersedes EASA AD
2006–0315R1:
—Retains the inspection requirements of
EASA AD 2006–0315R1,
—Extends the AD applicability to aeroplanes
which have embodied Airbus modification
49202, and
—Modifies the inspection thresholds and
intervals.
You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued the following
service information.
TABLE—SERVICE INFORMATION
Document
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Mandatory Service Bulletin A330–57–3081, including Appendix 1 ...................................
Mandatory Service Bulletin A340–57–4089, including Appendix 1 ...................................
Service Bulletin A330–57–3090 .........................................................................................
Service Bulletin A330–57–3098, including Appendix 1 .....................................................
Service Bulletin A340–57–4106, including Appendix 1 .....................................................
Service Bulletin A340–57–4098 .........................................................................................
Airbus Mandatory Service Bulletins
A330–57–3081, Revision 03, dated July
31, 2009; and A340–57–4089, Revision
03, dated July 31, 2009; reduce certain
compliance times. The compliance time
for the initial special detailed inspection
ranges from 10,350 flight cycles or
69,870 flight hours, to 21,180 flight
cycles or 63,560 flight hours, depending
on airplane configuration. The
compliance times for the repetitive
interval range from 7,780 flight cycles or
52,510 flight hours, to 12,360 flight
cycles or 37,080 flight hours, depending
on airplane configuration. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Change to Existing AD
srobinson on DSK4SPTVN1PROD with PROPOSALS
Revision
This proposed AD would retain all
requirements of AD 2007–16–02. Since
AD 2007–16–02 was issued, the AD
format has been revised, and certain
paragraphs have been rearranged. As a
result, the corresponding paragraph
identifiers have changed in this
proposed AD, as listed in the following
table:
VerDate Mar<15>2010
17:35 Jul 18, 2011
Jkt 223001
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD
2007–16–02
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
(e)(1)
(e)(2)
(e)(3)
(e)(4)
(e)(5)
(e)(6)
Corresponding
requirement in this
proposed AD
paragraph (h)
paragraph (i)
paragraph (j)
paragraph (k)
paragraph (l)
paragraph (m)
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 proposed
different actions in this AD from those
in the MCAI in order to follow FAA
policies. Any such differences are
highlighted in a Note within the
proposed AD.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 35 products of U.S. registry.
For the 9 airplanes affected by the
existing AD, the actions that are
required by AD 2007–16–02 and
retained in this proposed AD take about
41 work-hours per product, at an
average labor rate of $85 per work hour.
Required parts cost about $191 per
product. Based on these figures, the
estimated cost of the currently required
actions is $3,676 per product.
For the 26 additional airplanes added
in this AD, we estimate the actions in
this proposed AD would take about 41
work-hours per product, at an average
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
03 .................................
03 .................................
Original ........................
01 .................................
01 .................................
Original ........................
Date
July 31, 2009.
July 31, 2009.
March 27, 2006.
July 31, 2009.
July 31, 2009.
March 27, 2006.
labor rate of $85 per work hour.
Required parts would cost about $191
per product. Based on these figures, the
estimated cost of the proposed AD is
$3,676 per product.
In addition, because the proposed AD
advises to contact the manufacturer for
repair instructions, we cannot estimate
the parts or labor costs for any necessary
follow-on actions. We have no way of
determining the number of products
that may need these actions.
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 proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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.
E:\FR\FM\19JYP1.SGM
19JYP1
42604
Federal Register / Vol. 76, No. 138 / Tuesday, July 19, 2011 / Proposed Rules
For the reasons discussed above, I
certify this proposed regulation:
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 proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Subject
(d) Air Transport Association (ATA) of
America Code 57: Wings.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
During A330 and A340 aeroplanes fatigue
tests, cracks appeared on the right (RH) and
left (LH) sides between the crossing area of
the keel beam fitting and the front spar of the
Centre Wing Box (CWB). This condition, if
not corrected, could lead to keel beam
rupture which would affect the area
structural integrity.
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 39–15141 (72 FR
44731, August 9, 2007) and adding the
following new AD:
Airbus: Docket No. FAA–2011–0717;
Directorate Identifier 2010–NM–108–AD.
Comments Due Date
(a) We must receive comments by
September 2, 2011.
Affected ADs
(b) This AD supersedes AD 2007–16–02,
Amendment 39–15141.
Applicability
(c) This AD applies to the airplanes
identified in paragraphs (c)(1) and (c)(2) of
this AD; certificated in any category; except
as provided by paragraph (c)(3) of this AD.
(1) Airbus Model A330–201, –202, –203,
–223, –243, –301, –302, –303, –321, –322,
–323, –341, –342, and –343 airplanes, all
serial numbers, except those on which
Airbus modification 55306 or 55792 has been
embodied in production.
(2) Airbus Model A340–211, –212, –213,
–311, –312, and –313 airplanes, all serial
numbers, except those on which Airbus
modification 55306 or 55792 has been
embodied in production.
(3) This AD is not applicable to Airbus
Model A340–211, –212, –213, –311, –312,
and –313 airplanes that have been repaired
in accordance with Airbus Repair Drawing
R57115053, R57115051, or R57115047
(installation of titanium doubler on both
sides). AD 2007–12–08, Amendment 39–
15086 (72 FR 31171, June 6, 2007), applies
to these airplanes.
*
*
*
*
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2007–
16–02, With Revised Service Information
(g) For Model A330–201, –202, –203, –223,
–243, –301, –321, –322, –323, –341, –342,
and –343 airplanes, except those on which
Airbus modification 49202 has been
embodied in production, or Airbus Service
Bulletin A330–57–3090 has been embodied
in service, and Model A340–200 and –300
series airplanes, except those on which
Airbus modification 49202 has been
embodied in production or Airbus Service
Bulletin A340–57–4098 has been embodied
in service, and except Model A340–211,
–212, –213, –311, –312, and –313 airplanes
that have been repaired in accordance with
Airbus Repair Drawing R57115053,
R57115051, or R57115047: Do the actions
required by paragraphs (h), (l), and (m) of this
AD.
(h) For airplanes identified in paragraph (g)
of this AD, within the mandatory threshold
(flight cycles or flight hours) mentioned in
the paragraph 1.E.(2) of Airbus Mandatory
Service Bulletin A340–57–4089, Revision 02;
or A330–57–3081, Revision 02; both dated
January 24, 2006; depending on the
configuration of the aircraft model; or within
3 months after September 13, 2007 (the
effective date of AD 2007–16–02); whichever
occurs later: Carry out the NDT (nondestructive test) inspection of the hole(s) of
the horizontal flange of the keel beam located
on FR 40 datum on RH (right-hand) and/or
LH (left-hand) side of the fuselage, in
accordance with the instructions of the
applicable service bulletin listed in table 1 of
this AD. After the effective date of this AD,
use only Airbus Mandatory Service Bulletin
A330–57–3081, Revision 03, dated July 31,
2009; or Airbus Mandatory Service Bulletin
A340–57–4089, Revision 03, dated July 31,
2009; as applicable. Inspection in accordance
with Airbus A330/A340 200–300 Technical
Disposition F57D03012810, Issue B, dated
August 18, 2003; or 582.0651/2002, Issue A,
dated October 17, 2002; satisfies the
inspection requirements for the first rotating
probe inspection which is specified at the
inspection threshold of this AD. Doing the
inspection required by paragraph (n) of this
AD terminates the requirements of this
paragraph of this AD.
Note 1: In order to prevent large repairs or
heavy maintenance, Airbus recommends to
perform the above inspection according to
recommended thresholds mentioned in
paragraph 1.E.(2) of Airbus Mandatory
Service Bulletin A340–57–4089, Revision 02;
or Airbus Mandatory Service Bulletin A330–
57–3081, Revision 02; both dated January 24,
2006.
TABLE 1—ACCEPTABLE SERVICE INFORMATION FOR CERTAIN REQUIREMENTS OF PARAGRAPH (H)
Document
srobinson on DSK4SPTVN1PROD with PROPOSALS
Airbus
Airbus
Airbus
Airbus
Mandatory
Mandatory
Mandatory
Mandatory
Service
Service
Service
Service
Bulletin
Bulletin
Bulletin
Bulletin
A330–57–3081
A330–57–3081
A340–57–4089
A340–57–4089
(i) In case of any crack finding during the
inspection required by paragraph (h) of this
AD, before further flight, contact Airbus in
order to get repair instructions before next
flight, and repair before further flight.
(j) Should no crack be detected during the
inspection required by paragraph (h) of this
AD:
VerDate Mar<15>2010
17:35 Jul 18, 2011
Jkt 223001
Revision
.....................................................................................
.....................................................................................
.....................................................................................
.....................................................................................
(1) Before further flight: Follow up the
actions indicated in the flow charts, Figure
7, 8, or 9, of Airbus Mandatory Service
Bulletin A340–57–4089, including Appendix
01, Revision 02, dated January 24, 2006, or
Revision 03, dated July 31, 2009; or Figure
5, 6, or 7, of Airbus Mandatory Service
Bulletin A330–57–3081, including Appendix
01, Revision 02, dated January 24, 2006, or
PO 00000
Frm 00015
Fmt 4702
Sfmt 4702
Date
02
03
02
03
January 24, 2006.
July 31, 2009.
January 24, 2006.
July 31, 2009.
Revision 03, dated July 31, 2009; in
accordance with the instructions of Airbus
Mandatory Service Bulletin A340–57–4089,
including Appendix 01, Revision 02, dated
January 24, 2006, or Revision 03, dated July
31, 2009; or Airbus Mandatory Service
Bulletin A330–57–3081, including Appendix
01, Revision 02, dated January 24, 2006, or
E:\FR\FM\19JYP1.SGM
19JYP1
srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 138 / Tuesday, July 19, 2011 / Proposed Rules
Revision 03, dated July 31, 2009; as
applicable.
(2) Within 30 days after September 13,
2007, or within 30 days after doing the
inspection required by paragraph (h) of this
AD, whichever occurs later: Send the report
of actions carried out in paragraph (j)(1) of
this AD to Airbus.
(3) Renew the inspection at mandatory
intervals given in paragraph 1.E.(2) of Airbus
Mandatory Service Bulletin A340–57–4089,
Revision 02, dated January 24, 2006; or
Airbus Mandatory Service Bulletin A330–57–
3081, Revision 02, dated January 24, 2006; as
applicable; in accordance with the
instructions of Airbus Mandatory Service
Bulletin A340–57–4089, Revision 02, dated
January 24, 2006, or Revision 03, dated July
31, 2009, or Airbus Mandatory Service
Bulletin A330–57–3081, Revision 02, dated
January 24, 2006, or Revision 03, dated July
31, 2009; as applicable, and send the
inspection results to Airbus. Doing the
inspection required by paragraph (n) of this
AD terminates the requirements of this
paragraph of this AD.
Note 2: In order to prevent large repairs or
heavy maintenance, Airbus recommends to
perform the above repetitive inspection
according to recommended intervals
mentioned in paragraph 1.E.(2) of Airbus
Mandatory Service Bulletin A340–57–4089,
Revision 02, dated January 24, 2006; or
Airbus Mandatory Service Bulletin A330–57–
3081, Revision 02, dated January 24, 2006.
(k) Upon detection of a crack during a
repetitive inspection required by paragraph
(j)(3) of this AD, before further flight, contact
Airbus to get repair instructions, and repair
before further flight.
(l) For airplanes identified in paragraph (g)
of this AD: No additional work is required for
compliance with paragraph (h) of this AD for
aircraft inspected in accordance with the
instructions of Airbus Service Bulletin A330–
57–3081, dated October 30, 2003, or Revision
01, dated May 18, 2004; or Airbus Service
Bulletin A340–57–4089, dated October 30,
2003, or Revision 01, dated March 2, 2004.
Nevertheless, the operators must check that
their inspection program is in accordance
with paragraph 1.E.(2) of Airbus Mandatory
Service Bulletin A340–57–4089, Revision 02,
dated January 24, 2006; or Airbus Mandatory
Service Bulletin A330–57–3081, Revision 02,
dated January 24, 2006; as applicable; for the
repetitive inspection.
(m) For airplanes identified in paragraph
(g) of this AD on which Airbus Modification
41652 is not embodied: When the aircraft has
been modified in accordance with Airbus
Service Bulletin A330–57–3090, dated March
27, 2006; or Airbus Service Bulletin A340–
57–4098, dated March 27, 2006; as
applicable; the repetitive inspections
required by this AD are cancelled. In case of
any crack finding during the modification:
Where the applicable service bulletin
specifies to contact Airbus, before further
flight, contact Airbus to get repair
instructions, and repair.
New Requirements of This AD
(n) At the applicable time in paragraph
(n)(1) or (n)(2) of this AD: Do an NDT
inspection of the hole(s) of the horizontal
VerDate Mar<15>2010
17:35 Jul 18, 2011
Jkt 223001
flange of the keel beam located on FR 40
datum on RH and/or LH side of the fuselage,
in accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A330–57–3081, Revision 03, dated
July 31, 2009; or Airbus Mandatory Service
Bulletin A340–57–4089, Revision 03, dated
July 31, 2009; as applicable. Inspection in
accordance with Airbus A330/A340
Technical Disposition F57D03012810, Issue
B, dated August 18, 2003; or 582.0651/2002,
Issue A, dated October 17, 2002; is acceptable
for compliance with the inspection
requirements for the first rotating probe
inspection required by this paragraph. Doing
the inspection required by this paragraph
terminates the requirements of paragraphs (h)
and (j)(3) of this AD.
(1) For airplanes on which an inspection
required by paragraph (h) of this AD has not
been done as of the effective date of this AD:
At the applicable time specified in paragraph
(n)(1)(i) or (n)(1)(ii) of this AD.
(i) For all airplanes except those identified
in paragraph (g) of this AD: Within the
‘‘Mandatory Threshold’’ (flight cycles or
flight hours) specified in table 1 of paragraph
1.E.(2) of the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A330–57–
3081, Revision 03, dated July 31, 2009; or
Airbus Mandatory Service Bulletin A340–57–
4089, Revision 03, dated July 31, 2009; as
applicable; or within 3 months after the
effective date of this AD; whichever occurs
later. The compliance times for configuration
02 through 06 specified in the ‘‘Mandatory
Threshold’’ column in table 1 of paragraph
1.E., ‘‘Compliance,’’ are total flight cycles and
total flight hours.
(ii) For airplanes identified in paragraph (g)
of this AD: At the earlier of the times
specified in paragraphs (n)(1)(ii)(A) and
(n)(1)(ii)(B) of this AD.
(A) Within the ‘‘Mandatory Threshold’’
(flight cycles or flight hours) specified in
table 1 of paragraph 1.E.(2) of Airbus
Mandatory Service Bulletin A340–57–4089,
Revision 02, dated January 24, 2006; or
Airbus Mandatory Service Bulletin A330–57–
3081, Revision 02, dated January 24, 2006;
depending on the configuration of the aircraft
model; or within 3 months after September
13, 2007; whichever occurs later. The
compliance times for Model A330 post-mod.
No. 41652 and pre-mod. No. 44360, postmod. No. 44360, and pre-mod. No. 49202
(specified in Airbus Mandatory Service
Bulletin A330–57–3081, Revision 02, dated
January 24, 2006); and Model A340 postmod. No. 41652, post-mod. No. 43500 and
pre-mod. No. 44360, post-mod. No. 44360
and pre-mod. No. 49202, and Weight Variant
027 (specified in Airbus Mandatory Service
Bulletin A340–57–4089, Revision 02, dated
January 24, 2006); specified in the
‘‘Mandatory Threshold’’ column in table 1 of
paragraph 1.E., ‘‘Compliance,’’ are total flight
cycles and total flight hours.
(B) Within the ‘‘Mandatory Threshold’’
(flight cycles or flight hours) specified in
table 1 of paragraph 1.E.(2) of the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330–57–3081,
Revision 03, dated July 31, 2009; or Airbus
Mandatory Service Bulletin A340–57–4089,
Revision 03, dated July 31, 2009; as
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
42605
applicable; or within 3 months after the
effective date of this AD; whichever occurs
later. The compliance times for configuration
02 through 06 specified in the ‘‘Mandatory
Threshold’’ column in table 1 of paragraph
1.E., ‘‘Compliance,’’ are total flight cycles and
total flight hours.
(2) For airplanes on which an inspection
required by paragraph (h) of this AD has been
done as of the effective date of this AD: At
the earlier of the times specified in
paragraphs (n)(2)(i) and (n)(2)(ii) of this AD.
(i) Within the ‘‘Mandatory Intervals’’ given
in table 1 of paragraph 1.E.(2) of Airbus
Mandatory Service Bulletin A340–57–4089,
Revision 02, dated January 24, 2006; or
Airbus Mandatory Service Bulletin A330–57–
3081, Revision 02, dated January 24, 2006; as
applicable.
(ii) Within the applicable ‘‘Mandatory
Interval’’ specified in table 1 of Paragraph
1.E.(2). of Airbus Mandatory Service Bulletin
A330–57–3081, Revision 03, dated July 31,
2009; or Airbus Mandatory Service Bulletin
A340–57–4089, Revision 03, dated July 31,
2009; as applicable; or within 3 months after
the effective date of this AD; whichever
occurs later.
Note 3: To prevent large repairs or heavy
maintenance, Airbus recommends to perform
the above inspection according to
recommended thresholds specified in
paragraph 1.E.(2) of Airbus Mandatory
Service Bulletin A330–57–3081, Revision 03,
dated July 31, 2009; or Airbus Mandatory
Service Bulletin A340–57–4089, Revision 03,
dated July 31, 2009; as applicable.
(o) If any cracking is found during any
inspection required by paragraph (n) of this
AD, before further flight, repair in accordance
with a method approved by the International
Branch, ANM–116, Transport Airplane
Directorate, FAA, or EASA (or its delegated
agent).
(p) If no cracking is found during any
inspection required by paragraph (n) of this
AD, do the actions required by paragraphs
(p)(1) and (p)(2) of this AD.
(1) Before further flight: Install new or
oversized fastener, as applicable; seal the
fastener; and do all other applicable actions;
in accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A330–57–3081, Revision 03, dated
July 31, 2009; or Airbus Mandatory Service
Bulletin A340–57–4089, Revision 03, dated
July 31, 2009; as applicable.
(2) Repeat the inspection required by
paragraph (n) of this AD thereafter at
intervals not to exceed the mandatory
intervals specified in Paragraph 1.E.(2). of
Airbus Mandatory Service Bulletin A330–57–
3081, Revision 03, dated July 31, 2009; or
Airbus Mandatory Service Bulletin A340–57–
4089, Revision 03, dated July 31, 2009; as
applicable.
Note 4: To prevent large repairs or heavy
maintenance, Airbus recommends to perform
the above repetitive inspection according to
recommended intervals mentioned in
paragraph 1.E.(2) of Airbus Mandatory
Service Bulletin A330–57–3081, Revision 03,
dated July 31, 2009; or Airbus Mandatory
Service Bulletin A340–57–4089, Revision 03,
dated July 31, 2009; as applicable.
E:\FR\FM\19JYP1.SGM
19JYP1
42606
Federal Register / Vol. 76, No. 138 / Tuesday, July 19, 2011 / Proposed Rules
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(q) Inspections done before the effective
date of this AD in accordance with the
service information specified in table 2 of
this AD are acceptable for compliance with
the corresponding inspection required by
paragraph (n) of this AD.
TABLE 2—CREDIT SERVICE INFORMATION FOR CERTAIN ACTIONS
Document
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Revision
Mandatory Service Bulletin A330–57–3081 .......................................................................
Mandatory Service Bulletin A340–57–4089 .......................................................................
Service Bulletin A330–57–3081 .........................................................................................
Service Bulletin A330–57–3081 .........................................................................................
Service Bulletin A340–57–4089 .........................................................................................
Service Bulletin A340–57–4089 .........................................................................................
(r) Modifying the fasteners installation in
the junction keel beam fitting at FR 40, in
accordance with Airbus Service Bulletin
A330–57–3098, dated August 30, 2007; or
Airbus Service Bulletin A340–57–4106,
dated August 30, 2007; as applicable; before
the effective date of this AD terminates the
requirements of this AD; except for airplanes
on which a crack was detected at hole 5
before oversizing of the keel beam (in
accordance with step 3.B.(1)(b)3 of the
Accomplishment Instructions of Airbus
Service Bulletin A330–57–3098 or Airbus
Service Bulletin A340–57–4106), before
further flight, repair in accordance with a
method approved by the International
Branch, ANM–116, Transport Airplane
Directorate, FAA, or EASA (or its delegated
agent).
(s) Modifying the fasteners installation in
the junction keel beam fitting at FR 40, in
accordance with Airbus Service Bulletin
A330–57–3098, Revision 01, dated July 31,
2009; or Airbus Service Bulletin A340–57–
4106, Revision 01, dated July 31, 2009; as
applicable; terminates the requirements of
this AD.
(t) Modifying the fasteners installation in
the junction keel beam fitting at FR 40, in
accordance with Airbus Service Bulletin
A330–57–3090, dated March 27, 2006; or
02 .................................
02 .................................
Original ........................
01 .................................
Original ........................
01 .................................
Airbus Service Bulletin A340–57–4098,
dated March 27, 2006; as applicable;
terminates the requirements of this AD.
(u) In case of any crack finding during any
modification specified paragraphs (r), (s), and
(t) of this AD: Where the applicable service
bulletin specifies to contact Airbus, before
further flight, repair in accordance with a
method approved by the International
Branch, FAA, or EASA (or its delegated
agent).
Date
January 24, 2006.
January 24, 2006.
October 30, 2003.
May 18, 2004.
October 30, 2003.
March 2, 2004.
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 227–1138; fax (425)
227–1149. Information may be e-mailed to:
9-ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(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.
FAA AD Differences
Note 5: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(v) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
Related Information
(w) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2010–
0024, dated February 12, 2010, and the
applicable service information specified/
identified in table 3 of this AD, for related
information.
TABLE 3—RELATED SERVICE INFORMATION
Document
srobinson on DSK4SPTVN1PROD with PROPOSALS
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Revision
Mandatory Service Bulletin A330–57–3081 .......................................................................
Mandatory Service Bulletin A330–57–3081 .......................................................................
Mandatory Service Bulletin A340–57–4089 .......................................................................
Mandatory Service Bulletin A340–57–4089 .......................................................................
Service Bulletin A330–57–3090 .........................................................................................
Service Bulletin A330–57–3098 .........................................................................................
Service Bulletin A340–57–4106 .........................................................................................
Service Bulletin A340–57–4098 .........................................................................................
A330/A340 200–300 Technical Disposition F57D03012810 .............................................
A330/A340 Technical Disposition 582.0651/2002 .............................................................
VerDate Mar<15>2010
17:35 Jul 18, 2011
Jkt 223001
PO 00000
Frm 00017
Fmt 4702
Sfmt 9990
02 .................................
03 .................................
02 .................................
03 .................................
Original ........................
01 .................................
01 .................................
Original ........................
Issue B ........................
Issue A ........................
E:\FR\FM\19JYP1.SGM
19JYP1
Date
January 24, 2006.
July 31, 2009.
January 24, 2006.
July 31, 2009.
March 27, 2006.
July 31, 2009.
July 31, 2009.
March 27, 2006.
August 18, 2003.
October 17, 2002.
Federal Register / Vol. 76, No. 138 / Tuesday, July 19, 2011 / Proposed Rules
Issued in Renton, Washington, on July 7,
2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2011–18131 Filed 7–18–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0719; Directorate
Identifier 2010–NM–087–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 767–200, –300, and
–400ER Series Airplanes
srobinson on DSK4SPTVN1PROD with PROPOSALS
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to supersede an
existing airworthiness directive (AD)
that applies to the products listed above.
The existing AD currently requires
replacing the separation link assembly
on the applicable entry and service
doors with an improved separation link
assembly, and doing related
investigative and corrective actions if
necessary. Since we issued that AD, we
have received a report that an additional
airplane is subject to the unsafe
condition. This proposed AD would add
that airplane to the applicability and
also remove certain other airplanes from
the applicability. We are proposing this
AD to prevent failure of an entry or
service door to open fully in the event
of an emergency evacuation, which
could impede exit from the airplane.
This condition could result in injury to
passengers or crewmembers.
DATES: We must receive comments on
this proposed AD by September 2, 2011.
ADDRESSES: You may send comments by
any of the following methods:
• 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: Deliver to Mail
address above between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
VerDate Mar<15>2010
17:35 Jul 18, 2011
Jkt 223001
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207;
telephone 206–544–5000, extension 1,
fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Stephen Styskal, Aerospace Engineer,
Cabin Safety and Environmental
Systems Branch, ANM–150S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; phone: (425)
917–6439; fax: (425) 917–6590; e-mail:
stephen.styskal@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2011–0719; Directorate Identifier
2010–NM–087–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On January 22, 2009, we issued AD
2009–04–12, Amendment 39–15818 (74
PO 00000
Frm 00018
Fmt 4702
Sfmt 4702
42607
FR 8717, February 26, 2009), for certain
Model 767–200, –300, and –400ER
series airplanes. That AD requires
replacing the separation link assembly
on the applicable entry and service
doors with an improved separation link
assembly, and doing related
investigative and corrective actions if
necessary. That AD resulted from
reports that entry and service doors did
not open fully during deployment of
emergency escape slides, and additional
reports of missing snap rings. We issued
that AD to prevent failure of an entry or
service door to open fully in the event
of an emergency evacuation, which
could impede exit from the airplane.
This condition could result in injury to
passengers or crewmembers.
Actions Since Existing AD Was Issued
Since we issued AD 2009–04–12, we
have received a report indicating that an
additional airplane is subject to the
unsafe condition. In addition, four
airplanes were converted to freighter
configurations without the affected
slides, and, therefore, are no longer
subject to the unsafe condition.
Relevant Service Information
We reviewed Boeing Special
Attention Service Bulletin 767–25–
0428, Revision 3, dated October 21,
2010. This service bulletin describes the
same procedures that are described in
Boeing Special Attention Service
Bulletin 767–25–0428, Revision 1, dated
May 8, 2008 (which was referenced in
AD 2009–04–12 as the appropriate
source of service information). Revision
3 of Boeing Special Attention Service
Bulletin 767–25–0428 adds a step to the
entry/service door bustle installation
process, and contains information on
airplanes identified in the revised
Effectivity section and a changed part
number for a cap screw.
Boeing Special Attention Service
Bulletin 767–25–0428, Revision 2, dated
February 4, 2010, included an
additional airplane in the Effectivity
section and removed four airplanes from
the Effectivity section.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would retain all
the requirements of AD 2009–04–12
using the revised service information
described previously. This proposed AD
would add an airplane to the
E:\FR\FM\19JYP1.SGM
19JYP1
]]>Agencies
[Federal Register Volume 76, Number 138 (Tuesday, July 19, 2011)]
[Proposed Rules]
[Pages 42602-42607]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-18131]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0717; Directorate Identifier 2010-NM-108-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-201, -202, -203, -
223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343
Airplanes; and Model A340-200 and -300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above that would supersede an existing AD. This
proposed 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:
During A330 and A340 aeroplanes fatigue tests, cracks appeared
on the right (RH) and left (LH) sides between the crossing area of
the keel beam fitting and the front spar of the Centre Wing Box
(CWB). This condition, if not corrected, could lead to keel beam
rupture which would affect the area structural integrity.
* * * * *
The proposed AD would require actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by September 2,
2011.
ADDRESSES: You may send comments by any of the following methods:
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 W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 45 80; e-mail airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington. For information on the availability of
this material at the FAA, call 425-227-1221.
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 this proposed AD, 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.
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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-0717;
Directorate Identifier 2010-NM-108-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On July 24, 2007, we issued AD 2007-16-02, Amendment 39-15141 (72
FR 44731, August 9, 2007). That AD required actions intended to address
an unsafe condition on the products listed above.
Since we issued AD 2007-16-02, the European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, has issued EASA Airworthiness Directive 2010-0024,
dated February 12, 2010 (referred to after this as ``the MCAI''), to
correct an unsafe condition for the specified products. The MCAI
states:
During A330 and A340 aeroplanes fatigue tests, cracks appeared
on the right (RH) and left (LH) sides between the crossing area of
the keel beam fitting and the front spar of the Centre Wing Box
(CWB). This condition, if not corrected, could lead to keel beam
rupture which would affect the area structural integrity.
In order to maintain the structural integrity of the aeroplane,
EASA AD 2006-0315R1 required repetitive special detailed
[[Page 42603]]
inspections on the horizontal flange of the keel beam in the area of
first fastener hole aft of FR40.
This AD, which supersedes EASA AD 2006-0315R1:
--Retains the inspection requirements of EASA AD 2006-0315R1,
--Extends the AD applicability to aeroplanes which have embodied
Airbus modification 49202, and
--Modifies the inspection thresholds and intervals.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Airbus has issued the following service information.
Table--Service Information
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A330-57- 03.......................... July 31, 2009.
3081, including Appendix 1.
Airbus Mandatory Service Bulletin A340-57- 03.......................... July 31, 2009.
4089, including Appendix 1.
Airbus Service Bulletin A330-57-3090..... Original.................... March 27, 2006.
Airbus Service Bulletin A330-57-3098, 01.......................... July 31, 2009.
including Appendix 1.
Airbus Service Bulletin A340-57-4106, 01.......................... July 31, 2009.
including Appendix 1.
Airbus Service Bulletin A340-57-4098..... Original.................... March 27, 2006.
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletins A330-57-3081, Revision 03, dated
July 31, 2009; and A340-57-4089, Revision 03, dated July 31, 2009;
reduce certain compliance times. The compliance time for the initial
special detailed inspection ranges from 10,350 flight cycles or 69,870
flight hours, to 21,180 flight cycles or 63,560 flight hours, depending
on airplane configuration. The compliance times for the repetitive
interval range from 7,780 flight cycles or 52,510 flight hours, to
12,360 flight cycles or 37,080 flight hours, depending on airplane
configuration. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Change to Existing AD
This proposed AD would retain all requirements of AD 2007-16-02.
Since AD 2007-16-02 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in this
Requirement in AD 2007-16-02 proposed AD
------------------------------------------------------------------------
paragraph (e)(1) paragraph (h)
paragraph (e)(2) paragraph (i)
paragraph (e)(3) paragraph (j)
paragraph (e)(4) paragraph (k)
paragraph (e)(5) paragraph (l)
paragraph (e)(6) paragraph (m)
------------------------------------------------------------------------
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 proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a Note within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 35 products of U.S. registry.
For the 9 airplanes affected by the existing AD, the actions that
are required by AD 2007-16-02 and retained in this proposed AD take
about 41 work-hours per product, at an average labor rate of $85 per
work hour. Required parts cost about $191 per product. Based on these
figures, the estimated cost of the currently required actions is $3,676
per product.
For the 26 additional airplanes added in this AD, we estimate the
actions in this proposed AD would take about 41 work-hours per product,
at an average labor rate of $85 per work hour. Required parts would
cost about $191 per product. Based on these figures, the estimated cost
of the proposed AD is $3,676 per product.
In addition, because the proposed AD advises to contact the
manufacturer for repair instructions, we cannot estimate the parts or
labor costs for any necessary follow-on actions. We have no way of
determining the number of products that may need these actions.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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.
[[Page 42604]]
For the reasons discussed above, I certify this proposed
regulation:
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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing Amendment 39-15141 (72 FR
44731, August 9, 2007) and adding the following new AD:
Airbus: Docket No. FAA-2011-0717; Directorate Identifier 2010-NM-
108-AD.
Comments Due Date
(a) We must receive comments by September 2, 2011.
Affected ADs
(b) This AD supersedes AD 2007-16-02, Amendment 39-15141.
Applicability
(c) This AD applies to the airplanes identified in paragraphs
(c)(1) and (c)(2) of this AD; certificated in any category; except
as provided by paragraph (c)(3) of this AD.
(1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes, all serial
numbers, except those on which Airbus modification 55306 or 55792
has been embodied in production.
(2) Airbus Model A340-211, -212, -213, -311, -312, and -313
airplanes, all serial numbers, except those on which Airbus
modification 55306 or 55792 has been embodied in production.
(3) This AD is not applicable to Airbus Model A340-211, -212, -
213, -311, -312, and -313 airplanes that have been repaired in
accordance with Airbus Repair Drawing R57115053, R57115051, or
R57115047 (installation of titanium doubler on both sides). AD 2007-
12-08, Amendment 39-15086 (72 FR 31171, June 6, 2007), applies to
these airplanes.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
During A330 and A340 aeroplanes fatigue tests, cracks appeared
on the right (RH) and left (LH) sides between the crossing area of
the keel beam fitting and the front spar of the Centre Wing Box
(CWB). This condition, if not corrected, could lead to keel beam
rupture which would affect the area structural integrity.
* * * * *
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2007-16-02, With Revised Service
Information
(g) For Model A330-201, -202, -203, -223, -243, -301, -321, -
322, -323, -341, -342, and -343 airplanes, except those on which
Airbus modification 49202 has been embodied in production, or Airbus
Service Bulletin A330-57-3090 has been embodied in service, and
Model A340-200 and -300 series airplanes, except those on which
Airbus modification 49202 has been embodied in production or Airbus
Service Bulletin A340-57-4098 has been embodied in service, and
except Model A340-211, -212, -213, -311, -312, and -313 airplanes
that have been repaired in accordance with Airbus Repair Drawing
R57115053, R57115051, or R57115047: Do the actions required by
paragraphs (h), (l), and (m) of this AD.
(h) For airplanes identified in paragraph (g) of this AD, within
the mandatory threshold (flight cycles or flight hours) mentioned in
the paragraph 1.E.(2) of Airbus Mandatory Service Bulletin A340-57-
4089, Revision 02; or A330-57-3081, Revision 02; both dated January
24, 2006; depending on the configuration of the aircraft model; or
within 3 months after September 13, 2007 (the effective date of AD
2007-16-02); whichever occurs later: Carry out the NDT (non-
destructive test) inspection of the hole(s) of the horizontal flange
of the keel beam located on FR 40 datum on RH (right-hand) and/or LH
(left-hand) side of the fuselage, in accordance with the
instructions of the applicable service bulletin listed in table 1 of
this AD. After the effective date of this AD, use only Airbus
Mandatory Service Bulletin A330-57-3081, Revision 03, dated July 31,
2009; or Airbus Mandatory Service Bulletin A340-57-4089, Revision
03, dated July 31, 2009; as applicable. Inspection in accordance
with Airbus A330/A340 200-300 Technical Disposition F57D03012810,
Issue B, dated August 18, 2003; or 582.0651/2002, Issue A, dated
October 17, 2002; satisfies the inspection requirements for the
first rotating probe inspection which is specified at the inspection
threshold of this AD. Doing the inspection required by paragraph (n)
of this AD terminates the requirements of this paragraph of this AD.
Note 1: In order to prevent large repairs or heavy maintenance,
Airbus recommends to perform the above inspection according to
recommended thresholds mentioned in paragraph 1.E.(2) of Airbus
Mandatory Service Bulletin A340-57-4089, Revision 02; or Airbus
Mandatory Service Bulletin A330-57-3081, Revision 02; both dated
January 24, 2006.
Table 1--Acceptable Service Information for Certain Requirements of
Paragraph (h)
------------------------------------------------------------------------
Document Revision Date
------------------------------------------------------------------------
Airbus Mandatory Service 02 January 24, 2006.
Bulletin A330-57-3081.
Airbus Mandatory Service 03 July 31, 2009.
Bulletin A330-57-3081.
Airbus Mandatory Service 02 January 24, 2006.
Bulletin A340-57-4089.
Airbus Mandatory Service 03 July 31, 2009.
Bulletin A340-57-4089.
------------------------------------------------------------------------
(i) In case of any crack finding during the inspection required
by paragraph (h) of this AD, before further flight, contact Airbus
in order to get repair instructions before next flight, and repair
before further flight.
(j) Should no crack be detected during the inspection required
by paragraph (h) of this AD:
(1) Before further flight: Follow up the actions indicated in
the flow charts, Figure 7, 8, or 9, of Airbus Mandatory Service
Bulletin A340-57-4089, including Appendix 01, Revision 02, dated
January 24, 2006, or Revision 03, dated July 31, 2009; or Figure 5,
6, or 7, of Airbus Mandatory Service Bulletin A330-57-3081,
including Appendix 01, Revision 02, dated January 24, 2006, or
Revision 03, dated July 31, 2009; in accordance with the
instructions of Airbus Mandatory Service Bulletin A340-57-4089,
including Appendix 01, Revision 02, dated January 24, 2006, or
Revision 03, dated July 31, 2009; or Airbus Mandatory Service
Bulletin A330-57-3081, including Appendix 01, Revision 02, dated
January 24, 2006, or
[[Page 42605]]
Revision 03, dated July 31, 2009; as applicable.
(2) Within 30 days after September 13, 2007, or within 30 days
after doing the inspection required by paragraph (h) of this AD,
whichever occurs later: Send the report of actions carried out in
paragraph (j)(1) of this AD to Airbus.
(3) Renew the inspection at mandatory intervals given in
paragraph 1.E.(2) of Airbus Mandatory Service Bulletin A340-57-4089,
Revision 02, dated January 24, 2006; or Airbus Mandatory Service
Bulletin A330-57-3081, Revision 02, dated January 24, 2006; as
applicable; in accordance with the instructions of Airbus Mandatory
Service Bulletin A340-57-4089, Revision 02, dated January 24, 2006,
or Revision 03, dated July 31, 2009, or Airbus Mandatory Service
Bulletin A330-57-3081, Revision 02, dated January 24, 2006, or
Revision 03, dated July 31, 2009; as applicable, and send the
inspection results to Airbus. Doing the inspection required by
paragraph (n) of this AD terminates the requirements of this
paragraph of this AD.
Note 2: In order to prevent large repairs or heavy maintenance,
Airbus recommends to perform the above repetitive inspection
according to recommended intervals mentioned in paragraph 1.E.(2) of
Airbus Mandatory Service Bulletin A340-57-4089, Revision 02, dated
January 24, 2006; or Airbus Mandatory Service Bulletin A330-57-3081,
Revision 02, dated January 24, 2006.
(k) Upon detection of a crack during a repetitive inspection
required by paragraph (j)(3) of this AD, before further flight,
contact Airbus to get repair instructions, and repair before further
flight.
(l) For airplanes identified in paragraph (g) of this AD: No
additional work is required for compliance with paragraph (h) of
this AD for aircraft inspected in accordance with the instructions
of Airbus Service Bulletin A330-57-3081, dated October 30, 2003, or
Revision 01, dated May 18, 2004; or Airbus Service Bulletin A340-57-
4089, dated October 30, 2003, or Revision 01, dated March 2, 2004.
Nevertheless, the operators must check that their inspection program
is in accordance with paragraph 1.E.(2) of Airbus Mandatory Service
Bulletin A340-57-4089, Revision 02, dated January 24, 2006; or
Airbus Mandatory Service Bulletin A330-57-3081, Revision 02, dated
January 24, 2006; as applicable; for the repetitive inspection.
(m) For airplanes identified in paragraph (g) of this AD on
which Airbus Modification 41652 is not embodied: When the aircraft
has been modified in accordance with Airbus Service Bulletin A330-
57-3090, dated March 27, 2006; or Airbus Service Bulletin A340-57-
4098, dated March 27, 2006; as applicable; the repetitive
inspections required by this AD are cancelled. In case of any crack
finding during the modification: Where the applicable service
bulletin specifies to contact Airbus, before further flight, contact
Airbus to get repair instructions, and repair.
New Requirements of This AD
(n) At the applicable time in paragraph (n)(1) or (n)(2) of this
AD: Do an NDT inspection of the hole(s) of the horizontal flange of
the keel beam located on FR 40 datum on RH and/or LH side of the
fuselage, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A330-57-3081, Revision 03, dated
July 31, 2009; or Airbus Mandatory Service Bulletin A340-57-4089,
Revision 03, dated July 31, 2009; as applicable. Inspection in
accordance with Airbus A330/A340 Technical Disposition F57D03012810,
Issue B, dated August 18, 2003; or 582.0651/2002, Issue A, dated
October 17, 2002; is acceptable for compliance with the inspection
requirements for the first rotating probe inspection required by
this paragraph. Doing the inspection required by this paragraph
terminates the requirements of paragraphs (h) and (j)(3) of this AD.
(1) For airplanes on which an inspection required by paragraph
(h) of this AD has not been done as of the effective date of this
AD: At the applicable time specified in paragraph (n)(1)(i) or
(n)(1)(ii) of this AD.
(i) For all airplanes except those identified in paragraph (g)
of this AD: Within the ``Mandatory Threshold'' (flight cycles or
flight hours) specified in table 1 of paragraph 1.E.(2) of the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A330-57-3081, Revision 03, dated July 31, 2009; or Airbus Mandatory
Service Bulletin A340-57-4089, Revision 03, dated July 31, 2009; as
applicable; or within 3 months after the effective date of this AD;
whichever occurs later. The compliance times for configuration 02
through 06 specified in the ``Mandatory Threshold'' column in table
1 of paragraph 1.E., ``Compliance,'' are total flight cycles and
total flight hours.
(ii) For airplanes identified in paragraph (g) of this AD: At
the earlier of the times specified in paragraphs (n)(1)(ii)(A) and
(n)(1)(ii)(B) of this AD.
(A) Within the ``Mandatory Threshold'' (flight cycles or flight
hours) specified in table 1 of paragraph 1.E.(2) of Airbus Mandatory
Service Bulletin A340-57-4089, Revision 02, dated January 24, 2006;
or Airbus Mandatory Service Bulletin A330-57-3081, Revision 02,
dated January 24, 2006; depending on the configuration of the
aircraft model; or within 3 months after September 13, 2007;
whichever occurs later. The compliance times for Model A330 post-
mod. No. 41652 and pre-mod. No. 44360, post-mod. No. 44360, and pre-
mod. No. 49202 (specified in Airbus Mandatory Service Bulletin A330-
57-3081, Revision 02, dated January 24, 2006); and Model A340 post-
mod. No. 41652, post-mod. No. 43500 and pre-mod. No. 44360, post-
mod. No. 44360 and pre-mod. No. 49202, and Weight Variant 027
(specified in Airbus Mandatory Service Bulletin A340-57-4089,
Revision 02, dated January 24, 2006); specified in the ``Mandatory
Threshold'' column in table 1 of paragraph 1.E., ``Compliance,'' are
total flight cycles and total flight hours.
(B) Within the ``Mandatory Threshold'' (flight cycles or flight
hours) specified in table 1 of paragraph 1.E.(2) of the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A330-57-3081, Revision 03, dated July 31, 2009; or Airbus Mandatory
Service Bulletin A340-57-4089, Revision 03, dated July 31, 2009; as
applicable; or within 3 months after the effective date of this AD;
whichever occurs later. The compliance times for configuration 02
through 06 specified in the ``Mandatory Threshold'' column in table
1 of paragraph 1.E., ``Compliance,'' are total flight cycles and
total flight hours.
(2) For airplanes on which an inspection required by paragraph
(h) of this AD has been done as of the effective date of this AD: At
the earlier of the times specified in paragraphs (n)(2)(i) and
(n)(2)(ii) of this AD.
(i) Within the ``Mandatory Intervals'' given in table 1 of
paragraph 1.E.(2) of Airbus Mandatory Service Bulletin A340-57-4089,
Revision 02, dated January 24, 2006; or Airbus Mandatory Service
Bulletin A330-57-3081, Revision 02, dated January 24, 2006; as
applicable.
(ii) Within the applicable ``Mandatory Interval'' specified in
table 1 of Paragraph 1.E.(2). of Airbus Mandatory Service Bulletin
A330-57-3081, Revision 03, dated July 31, 2009; or Airbus Mandatory
Service Bulletin A340-57-4089, Revision 03, dated July 31, 2009; as
applicable; or within 3 months after the effective date of this AD;
whichever occurs later.
Note 3: To prevent large repairs or heavy maintenance, Airbus
recommends to perform the above inspection according to recommended
thresholds specified in paragraph 1.E.(2) of Airbus Mandatory
Service Bulletin A330-57-3081, Revision 03, dated July 31, 2009; or
Airbus Mandatory Service Bulletin A340-57-4089, Revision 03, dated
July 31, 2009; as applicable.
(o) If any cracking is found during any inspection required by
paragraph (n) of this AD, before further flight, repair in
accordance with a method approved by the International Branch, ANM-
116, Transport Airplane Directorate, FAA, or EASA (or its delegated
agent).
(p) If no cracking is found during any inspection required by
paragraph (n) of this AD, do the actions required by paragraphs
(p)(1) and (p)(2) of this AD.
(1) Before further flight: Install new or oversized fastener, as
applicable; seal the fastener; and do all other applicable actions;
in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330-57-3081, Revision 03, dated July 31,
2009; or Airbus Mandatory Service Bulletin A340-57-4089, Revision
03, dated July 31, 2009; as applicable.
(2) Repeat the inspection required by paragraph (n) of this AD
thereafter at intervals not to exceed the mandatory intervals
specified in Paragraph 1.E.(2). of Airbus Mandatory Service Bulletin
A330-57-3081, Revision 03, dated July 31, 2009; or Airbus Mandatory
Service Bulletin A340-57-4089, Revision 03, dated July 31, 2009; as
applicable.
Note 4: To prevent large repairs or heavy maintenance, Airbus
recommends to perform the above repetitive inspection according to
recommended intervals mentioned in paragraph 1.E.(2) of Airbus
Mandatory Service Bulletin A330-57-3081, Revision 03, dated July 31,
2009; or Airbus Mandatory Service Bulletin A340-57-4089, Revision
03, dated July 31, 2009; as applicable.
[[Page 42606]]
Credit for Actions Accomplished in Accordance With Previous Service
Information
(q) Inspections done before the effective date of this AD in
accordance with the service information specified in table 2 of this
AD are acceptable for compliance with the corresponding inspection
required by paragraph (n) of this AD.
Table 2--Credit Service Information for Certain Actions
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A330-57- 02.......................... January 24, 2006.
3081.
Airbus Mandatory Service Bulletin A340-57- 02.......................... January 24, 2006.
4089.
Airbus Service Bulletin A330-57-3081..... Original.................... October 30, 2003.
Airbus Service Bulletin A330-57-3081..... 01.......................... May 18, 2004.
Airbus Service Bulletin A340-57-4089..... Original.................... October 30, 2003.
Airbus Service Bulletin A340-57-4089..... 01.......................... March 2, 2004.
----------------------------------------------------------------------------------------------------------------
(r) Modifying the fasteners installation in the junction keel
beam fitting at FR 40, in accordance with Airbus Service Bulletin
A330-57-3098, dated August 30, 2007; or Airbus Service Bulletin
A340-57-4106, dated August 30, 2007; as applicable; before the
effective date of this AD terminates the requirements of this AD;
except for airplanes on which a crack was detected at hole 5 before
oversizing of the keel beam (in accordance with step 3.B.(1)(b)3 of
the Accomplishment Instructions of Airbus Service Bulletin A330-57-
3098 or Airbus Service Bulletin A340-57-4106), before further
flight, repair in accordance with a method approved by the
International Branch, ANM-116, Transport Airplane Directorate, FAA,
or EASA (or its delegated agent).
(s) Modifying the fasteners installation in the junction keel
beam fitting at FR 40, in accordance with Airbus Service Bulletin
A330-57-3098, Revision 01, dated July 31, 2009; or Airbus Service
Bulletin A340-57-4106, Revision 01, dated July 31, 2009; as
applicable; terminates the requirements of this AD.
(t) Modifying the fasteners installation in the junction keel
beam fitting at FR 40, in accordance with Airbus Service Bulletin
A330-57-3090, dated March 27, 2006; or Airbus Service Bulletin A340-
57-4098, dated March 27, 2006; as applicable; terminates the
requirements of this AD.
(u) In case of any crack finding during any modification
specified paragraphs (r), (s), and (t) of this AD: Where the
applicable service bulletin specifies to contact Airbus, before
further flight, repair in accordance with a method approved by the
International Branch, FAA, or EASA (or its delegated agent).
FAA AD Differences
Note 5: This AD differs from the MCAI and/or service
information as follows: No differences.
Other FAA AD Provisions
(v) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, FAA, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your request to your principal
inspector or local Flight Standards District Office, as appropriate.
If sending information directly to the International Branch, send it
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. Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your
appropriate principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office/
certificate holding district office. The AMOC approval letter must
specifically reference this AD.
(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.
Related Information
(w) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2010-0024, dated February 12, 2010, and the applicable
service information specified/identified in table 3 of this AD, for
related information.
Table 3--Related Service Information
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A330-57- 02.......................... January 24, 2006.
3081.
Airbus Mandatory Service Bulletin A330-57- 03.......................... July 31, 2009.
3081.
Airbus Mandatory Service Bulletin A340-57- 02.......................... January 24, 2006.
4089.
Airbus Mandatory Service Bulletin A340-57- 03.......................... July 31, 2009.
4089.
Airbus Service Bulletin A330-57-3090..... Original.................... March 27, 2006.
Airbus Service Bulletin A330-57-3098..... 01.......................... July 31, 2009.
Airbus Service Bulletin A340-57-4106..... 01.......................... July 31, 2009.
Airbus Service Bulletin A340-57-4098..... Original.................... March 27, 2006.
Airbus A330/A340 200-300 Technical Issue B..................... August 18, 2003.
Disposition F57D03012810.
Airbus A330/A340 Technical Disposition Issue A..................... October 17, 2002.
582.0651/2002.
----------------------------------------------------------------------------------------------------------------
[[Page 42607]]
Issued in Renton, Washington, on July 7, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-18131 Filed 7-18-11; 8:45 am]
BILLING CODE 4910-13-P
