Airworthiness Directives; Airbus Model A310 Series Airplanes, 39863-39868 [2010-17061]
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39863
Proposed Rules
Federal Register
Vol. 75, No. 133
Tuesday, July 13, 2010
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0680; Directorate
Identifier 2008–NM–195–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310 Series Airplanes
jlentini on DSKJ8SOYB1PROD with PROPOSALS
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: Analysis
performed in the frame of the Extended
Service Goal has led Airbus to modify
the inspection programme [modification
of thresholds, intervals and associated
configurations] which is currently
´ ´
required by DGAC (Direction Generale
de l’Aviation Civile) France AD F–
2005–001. This modified inspection
programme is necessary to detect and
prevent damage associated with a
structural fatigue phenomenon of the
rear spar internal angle and the tee
fitting located in the centre wing box.
This condition, if not corrected, could
affect the structural integrity of the
centre wing box. The unsafe condition
is reduced structural integrity of the
wings. 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 August 27, 2010.
ADDRESSES: You may send comments by
any of the following methods:
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• 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—
EAW (Airworthiness Office), 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone: +33 5 61 93
36 96; fax: +33 5 61 93 44 51; e-mail:
account.airworth-eas@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: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2125;
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.
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FAA–2010–0680; Directorate Identifier
2008–NM–195–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 have lengthened the 30-day
comment period for proposed ADs that
address MCAI originated by aviation
authorities of other countries to provide
adequate time for interested parties to
submit comments. The comment period
for these proposed ADs is now typically
45 days, which is consistent with the
comment period for domestic transport
ADs.
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 April 20, 2006, we issued AD
2006–09–05, Amendment 39–14575 (71
FR 25921, May 3, 2006). That AD
required actions intended to address an
unsafe condition on the products listed
above.
Since we issued AD 2006–09–05, the
manufacturer has modified the
inspection program currently required
by AD 2006–09–05 by reducing certain
compliance times. The European
Aviation Safety Agency (EASA), which
is the Technical Agent for the Member
States of the European Community, has
issued EASA Airworthiness Directive
2008–0187, dated October 10, 2008
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
Analysis performed in the frame of the
Extended Service Goal has led Airbus to
modify the inspection programme
[modification of thresholds, intervals and
associated configurations] which is currently
´ ´
required by DGAC (Direction Generale de
l’Aviation Civile) France AD F–2005–001
[which corresponds to FAA AD 2006–09–05].
This modified inspection programme is
necessary to detect and prevent damage
associated with a structural fatigue
phenomenon of the rear spar internal angle
and the tee fitting located in the centre wing
box. This condition, if not corrected, could
affect the structural integrity of the centre
wing box.
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Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Proposed Rules
For the reason stated above, this new
EASA AD retains the requirements of DGAC
France AD F–2005–001, which is
superseded, and refers to the latest revision
of Airbus Service Bulletin (SB) A310–57–
2047.
The unsafe condition is reduced
structural integrity of the wings. This
AD retains the requirements of AD
2006–09–05, but with certain reduced
compliance times. The required actions
include doing repetitive rotating probe
inspections for any crack of the rear spar
internal angle and the left and right
sides of the tee fitting, and doing related
investigative/corrective actions if
necessary. The actions also include
modifying the holes in the internal
angle and tee fitting by cold expansion.
You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Service Bulletin
A310–57–2047, Revision 08, dated July
2, 2009; and Mandatory Service Bulletin
A310–57–2035, Revision 10, dated
March 25, 2008. 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.
jlentini on DSKJ8SOYB1PROD with PROPOSALS
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.
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Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 66 products of U.S. registry.
The actions that are required by AD
2006–09–05 and retained in this
proposed AD take up to 600 work-hours
per product, at an average labor rate of
$85 per work hour. Required parts cost
up to $38,900 per product. Based on
these figures, the estimated cost of the
currently required actions is up to
$89,900 per product.
This new AD adds no new costs to
affected operators; the manufacturer has
modified the inspection program
currently required by AD 2006–09–05,
this proposed AD reduces the
compliance times required by the
existing AD.
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.
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.
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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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–14575 (71 FR
25921, May 3, 2006) and adding the
following new AD:
Airbus: Docket No. FAA–2010–0680;
Directorate Identifier 2008–NM–195–AD.
Comments Due Date
(a) We must receive comments by August
27, 2010.
Affected ADs
(b) This AD supersedes AD 2006–09–05,
Amendment 39–14575. This AD also affects
certain requirements of AD 98–26–01,
Amendment 39–10942.
Applicability
(c) This AD applies to all Airbus Model
A310–203, –204, –221, –222, –304, –322,
–324, and –325 airplanes, certificated in any
category.
Subject
(d) Air Transport Association (ATA) of
America Code 57: Wings.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Analysis performed in the frame of the
Extended Service Goal has led Airbus to
modify the inspection programme
[modification of thresholds, intervals and
associated configurations] which is currently
´ ´
required by DGAC (Direction Generale de
l’Aviation Civile) France AD F–2005–001
[which corresponds to FAA AD 2006–09–05].
This modified inspection programme is
necessary to detect and prevent damage
associated with a structural fatigue
phenomenon of the rear spar internal angle
and the tee fitting located in the centre wing
box. This condition, if not corrected, could
affect the structural integrity of the centre
wing box.
The unsafe condition is reduced structural
integrity of the wings.
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Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Proposed Rules
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.
05), modify the holes in the internal angle
and tee fitting and do all applicable related
investigative and corrective actions by
accomplishing all the actions specified in the
Accomplishment Instructions of Airbus
Service Bulletin A310–57–2035, Revision 08,
dated September 19, 2005; or Airbus
Mandatory Service Bulletin A310–57–2035,
Revision 10, dated March 25, 2008; except as
required by paragraph (h) of this AD. Do all
applicable related investigative and
corrective actions before further flight. As of
the effective date of this AD, use only Airbus
RESTATEMENT OF CERTAIN
REQUIREMENTS OF AD 2006–09–05
MODIFICATION
(g) For all airplanes except those that are
modified by Airbus Modifications
06672S6812, 06673S6813, and 07387S7974
in production: Within 60 months after June
7, 2006 (the effective date of AD 2006–09–
Mandatory Service Bulletin A310–57–2035,
Revision 10, dated March 25, 2008.
Contact the FAA
(h) Where the service information specified
in Table 1 of this AD specifies to contact the
manufacturer if certain cracks are found,
before further flight, repair those conditions
according to a method approved by either the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
´ ´
Direction Generale de l’Aviation Civile
(DGAC) (or its delegated agent); or EASA (or
its delegated agent).
TABLE 1—SERVICE INFORMATION
Document
Revision
Airbus Mandatory Service Bulletin A310–57–2035 .........................................................................................
Airbus Service Bulletin A310–57–2035 ...........................................................................................................
Actions Accomplished According to
Previous Issues of Airbus Service Bulletin
A310–57–2035
(i) Actions accomplished before June 7,
2006, in accordance with the service
Date
10
08
March 25, 2008.
September 19, 2005.
information specified in Table 2 of this AD,
are considered acceptable for compliance
with the corresponding actions specified in
paragraph (g) of this AD.
TABLE 2—PREVIOUS ISSUES OF SERVICE BULLETIN A310–57–2035
Document
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Service
Service
Service
Service
Service
Service
Service
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
A310–57–2035
A310–57–2035
A310–57–2035
A310–57–2035
A310–57–2035
A310–57–2035
A310–57–2035
Revision
...........................................................................................................
...........................................................................................................
...........................................................................................................
...........................................................................................................
...........................................................................................................
...........................................................................................................
...........................................................................................................
NEW REQUIREMENTS OF THIS AD—
REVISED COMPLIANCE TIMES FOR
INSPECTIONS REQUIRED BY AD 2006–09–
05
Initial and Repetitive Inspections of the Rear
Spar Internal Angle
(j) For airplanes on which an inspection of
the rear spar internal angle has not been done
in accordance with Airbus Service Bulletin
A310–57–2047 as of the effective date of this
AD: At the later of the times specified in
paragraphs (j)(1) and (j)(2) of this AD, do a
rotating probe inspection for any crack of the
rear spar internal angle located in the center
wing box and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A310–
57–2047, Revision 08, dated July 2, 2009;
except as required by paragraphs (n) and (o)
of this AD. Do all applicable related
investigative and corrective actions before
further flight. Repeat the inspection
thereafter at the applicable time specified in
Table 4 of this AD. Certain compliance times
are applicable to short range use, average
flight time (AFT) equal to or less than 4
hours, or long range use, AFT exceeding 4
hours.
Note 1: To establish the AFT, divide the
accumulated flight time (counted from the
take-off up to the landing) by the number of
accumulated flight cycles. This gives the
average flight time per flight cycle.
Date
1
2
3
4
5
6
7
October 13, 1989.
February 26, 1990.
May 23, 1990.
April 15, 1992.
May 27, 1992.
March 8, 1994.
April 17, 1996.
(1) Within the applicable time specified in
Table 3 of this AD.
(2) Within the applicable time specified in
paragraph (j)(2)(i), (j)(2)(ii), or (j)(2)(iii) of this
AD:
(i) For A310–203, –204, –221, and –222
airplanes: Within 700 flight cycles or 1,500
flight hours after the effective date of this AD,
whichever occurs first.
(ii) For A310–304, –322, –324, and –325
short range airplanes: Within 700 flight
cycles or 1,900 flight hours after the effective
date of this AD, whichever occurs first.
(iii) For A310–304, –322, –324, and –325
long range airplanes: Within 500 flight cycles
or 2,500 flight hours after the effective date
of this AD, whichever occurs first.
TABLE 3—INITIAL INSPECTION INTERNAL ANGLE
jlentini on DSKJ8SOYB1PROD with PROPOSALS
Model and configuration
Compliance time (whichever occurs first)
A310–203, –204, –221, and –222 airplanes on
which Mod 6672S6812 and Mod 7387S7974
are not done.
A310–203, –204, –221, and –222 airplanes on
which Mod 6672S6812 and Mod 7387S7974
are done in production.
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Before the accumulation of 9,200 total flight
cycles.
Before the accumulation of 18,500 total flight
hours.
Before the accumulation of 19,800 total flight
cycles.
Before the accumulation of 39,600 total flight
hours.
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TABLE 3—INITIAL INSPECTION INTERNAL ANGLE—Continued
A310–203, –204, –221, and –222 airplanes on
which Mod 6672S6812 and Mod 7387S7974
are done in accordance with Airbus Service
Bulletin A310–57–2035 and before the accumulation of 6,200 total flight cycles and
12,500 total flight hours.
A310–203, –204, –221, and –222 airplanes on
which Mod 6672S6812 and Mod 7387S7974
are done in accordance with Airbus Service
Bulletin A310–57–2035 and are not done before the accumulation of 6,200 total flight cycles and 12,500 total flight hours.
A310–304, –322, –324, and –325 short range
airplanes on which Mod 6672S6812 and Mod
7387S7974 are not done.
A310–304, –322, –324, and –325 long range
airplanes on which Mod 6672S6812 and Mod
7387S7974 are not done.
A310–304, –322, –324, and –325 short range
airplanes on which Mod 6672S6812 and Mod
7387S7974 are done.
A310–304, –322, –324, and –325 long range
airplanes on which Mod 6672S6812 and Mod
7387S7974 are done in production.
A310–304, –322, –324, and –325 short range
airplanes on which Mod 6672S6812 and Mod
7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 and before the accumulation of 4,700 total flight cycles and 13,100 total flight hours.
A310–304, –322, –324, and –325 short range
airplanes on which Mod 6672S6812 and Mod
7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 and not
done before the accumulation of 4,700 total
flight cycles and 13,100 total flight hours.
A310–304, –322, –324, and –325 long range
airplanes on which Mod 6672S6812 and Mod
7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 before
the accumulation of 3,300 total flight cycles
and 16,700 total flight hours.
A310–304, –322, –324, and –325 long range
airplanes on which Mod 6672S6812 and Mod
7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 and not
done before the accumulation of 3,300 total
flight cycles and 16,700 total flight hours.
Within 19,800 flight cycles after the effective
date of this AD.
Within 39,600 flight hours after the effective
date of this AD.
Within 8,200 flight cycles after the effective
date of this AD.
Within 16,400 flight hours after the effective
date of this AD.
Before the accumulation of 7,500 total flight
cycles.
Before the accumulation of 21,100 total flight
hours.
Before the accumulation of 5,300 total flight
cycles.
Before the accumulation of 26,900 total flight
hours.
Before the accumulation of 15,900 total flight
cycles.
Before the accumulation of 44,700 total flight
hours.
Before the accumulation of 11,300 total flight
cycles.
Before the accumulation of 56,900 total flight
hours.
Within 15,900 flight cycles after the effective
date of this AD.
Within 44,700 flight hours after the effective
date of this AD.
Within 8,500 flight cycles after the effective
date of this AD.
Within 23,800 flight hours after the effective
date of this AD.
Within 11,300 flight cycles after the effective
date of this AD.
Within 56,900 flight hours after the effective
date of this AD.
Within 6,000 flight cycles after the effective
date of this AD.
Within 30,300 flight hours after the effective
date of this AD.
TABLE 4—REPETITIVE INTERVALS
Model and configuration
Interval (not to exceed)
jlentini on DSKJ8SOYB1PROD with PROPOSALS
A310–203, –204, –221, and –222 airplanes ............................
A310–304, –322, –324, and –325 short range airplanes ........
A310–304, –322, –324, and –325 long range airplanes .........
(k) For airplanes on which an inspection of
the rear spar internal angle has been done in
accordance with Airbus Service Bulletin
A310–57–2047 as of the effective date of this
AD: At the applicable time specified in
paragraphs (k)(1), (k)(2), and (k)(3) of this AD,
do a rotating probe inspection for any crack
of the rear spar internal angle located in the
center wing box and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A310–
57–2047, Revision 08, dated July 2, 2009;
except as required by paragraphs (n) and (o)
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Within 7,200 flight cycles or 14,400 flight hours, whichever occurs first.
Within 6,800 flight cycles or 19,100 flight hours, whichever occurs first.
Within 4,800 flight cycles or 24,300 flight hours, whichever occurs first.
of this AD. Do all applicable related
investigative and corrective actions before
further flight. Repeat the inspection
thereafter at the applicable time specified in
Table 4 of this AD. Certain compliance times
are applicable to short range use, AFT equal
to or less than 4 hours, or long range use,
AFT exceeding 4 hours.
(1) For A310–203, –204, –221, and –222
airplanes: At the earlier of the times specified
in paragraphs (k)(1)(i) and (k)(1)(ii) of this
AD.
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(i) Within 7,940 flight cycles or 15,880
flight hours after the most recent inspection,
whichever occurs first.
(ii) At the later of the times specified in
paragraphs (k)(1)(ii)(A) and (k)(1)(ii)(B) of
this AD.
(A) Within the applicable interval specified
in Table 4 of this AD.
(B) Within 740 flight cycles or 1,480 flight
hours after the effective date of this AD,
whichever occurs first.
(2) For A310–304, –322, –324, and –325
short range airplanes: At the later of the times
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specified in paragraphs (k)(2)(i) and (k)(2)(ii)
of this AD.
(i) Within the applicable interval specified
in Table 4 of this AD.
(ii) Within 700 flight cycles or 1,900 flight
hours after the effective date of this AD,
whichever occurs first.
(3) For A310–304, –322, –324, and –325
long range airplanes: At the later of the times
specified in paragraphs (k)(3)(i) and (k)(3)(ii)
of this AD.
(i) Within the applicable interval specified
in Table 4 of this AD.
(ii) Within 500 flight cycles or 2,500 flight
hours after the effective date of this AD,
whichever occurs first.
Initial and Repetitive Inspections of the Tee
Fitting
(l) For airplanes on which an inspection of
the left and right sides of the tee fitting has
not been done in accordance with Airbus
Service Bulletin A310–57–2047 as of the
effective date of this AD: At the later of the
times specified in paragraphs (l)(1) and (l)(2)
of this AD, do a rotating probe inspection for
any crack of the left and right sides of the tee
fitting, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A310–
57–2047, Revision 08, dated July 2, 2009;
except as required by paragraphs (n) and (o)
of this AD. Do all applicable related
investigative and corrective actions before
further flight. Repeat the inspection
39867
thereafter at the applicable time specified in
Table 6 of this AD. Certain compliance times
are applicable to short range use, AFT equal
to or less than 4 hours, or long range use,
AFT exceeding 4 hours.
(1) Within the applicable time specified in
Table 5 of this AD.
(2) Within the applicable time in paragraph
(l)(2)(i), (l)(2)(ii), or (l)(2)(iii) of this AD.
(i) For A310–203, –204, –221, and –222
airplanes: Within 800 flight cycles or 1,600
flight hours, whichever occurs first.
(ii) For A310–304, –322, –324, and –325
short range airplanes: Within 800 flight
cycles or 2,200 flight hours, whichever
occurs first.
(iii) For A310–304, –322, –324, and –325
long range airplanes: Within 600 flight cycles
or 3,100 flight hours, whichever occurs first.
TABLE 5—INITIAL INSPECTION TEE FITTING
jlentini on DSKJ8SOYB1PROD with PROPOSALS
Model and configuration
Compliance time (whichever occurs first)
A310–203, –204, –221, and –222 airplanes on
which Mod 6673S6813 is not done.
A310–203, –204, –221, and –222 airplanes on
which Mod 6673S6813 is done in production.
A310–203, –204, –221, and –222 airplanes on
which Mod 6673S6813 is done in accordance
with Airbus Service Bulletin A310–57–2035
and before the accumulation of 8,100 total
flight cycles and 16,200 total flight hours.
A310–203, –204, –221, and –222 airplanes on
which Mod 6673S6813 is done in accordance
with Airbus Service Bulletin A310–57–2035
and not before the accumulation of 8,100
total flight cycles and 16,200 total flight hours.
A310–304, –322, –324, and –325 short range
airplanes on which Mod 6673S6813 is not
done.
A310–304, –322, –324, and –325 long range
airplanes on which Mod 6673S6813 is not
done.
A310–304, –322, –324, and –325 short range
airplanes on which Mod 6673S6813 is done
in production.
A310–304, –322, –324, and –325 long range
airplanes on which Mod 6673S6813 is done
in production.
A310–304, –322, –324, and –325 short range
airplanes on which Mod 6673S6813 is done
in accordance with Airbus Service Bulletin
A310–57–2035 and before the accumulation
of 5,800 total flight cycles and 16,400 total
flight hours.
A310–304, –322, –324, and –325 short range
airplanes on which Mod 6673S6813 is done
in accordance with Airbus Service Bulletin
A310–57–2035 and not before the accumulation of 5,800 total flight cycles and 16,400
total flight hours.
A310–304, –322, –324, and –325 long range
airplanes on which Mod 6673S6813 is done
in accordance with Airbus Service Bulletin
A310–57–2035 and before the accumulation
of 4,600 total flight cycles and 23,100 total
flight hours.
A310–304, –322, –324, and –325 long range
airplanes on which Mod 6673S6813 is done
in accordance with Airbus Service Bulletin
A310–57–2035 and not before the accumulation of 4,600 total flight cycles and 23,100
total flight hours.
VerDate Mar<15>2010
16:13 Jul 12, 2010
Jkt 220001
Before the accumulation of 14,300 flight cycles.
Before the accumulation of 17,500 total flight
cycles.
Within 17,500 flight cycles after the effective
date of this AD.
Within 28,700 flight hours after the effective
date of this AD.
Before the accumulation of 35,000 total flight
hours.
Within 35,000 flight hours after the effective
date of this AD.
Within 9,600 flight cycles after the effective
date of this AD.
Within 19,200 flight hours after the effective
date of this AD.
Within 10,800 flight cycles after the effective
date of this AD.
Within 30,400 flight hours after the effective
date of this AD.
Before the accumulation of 8,500 total flight
cycles.
Before the accumulation of 42,800 total flight
hours.
Before the accumulation of 13,100 total flight
cycles.
Before the accumulation of 36,700 total flight
hours.
Before the accumulation of 10,300 total flight
cycles.
Before the accumulation of 51,600 total flight
hours.
Within 13,100 flight cycles after the effective
date of this AD.
Within 36,700 flight hours after the effective
date of this AD.
Within 7,400 flight cycles after the effective
date of this AD.
Within 20,900 flight hours after the effective
date of this AD.
Within 10,300 flight cycles after the effective
date of this AD.
Within 51,600 flight hours after the effective
date of this AD.
Within 6,000 flight cycles after the effective
date of this AD.
Within 30,300 flight hours after the effective
date of this AD.
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39868
Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Proposed Rules
TABLE 6—REPETITIVE INTERVALS
Model and configuration
Interval (not to exceed)
A310–203, –204, –221, and –222 airplanes ............................................
A310–304, –322, –324, and –325 short range airplanes ........................
A310–304, –322, –324, and –325 long range airplanes .........................
(m) For airplanes on which an inspection
of the rear left and right sides of the tee
fitting has been done in accordance with
Airbus Service Bulletin A310–57–2047 as of
the effective date of this AD: At the
applicable time specified in paragraphs
(m)(1) or (m)(2) of this AD, do a rotating
probe inspection for any crack of the left and
right sides of the tee fitting, and do all
applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A310–57–2047, Revision 08,
dated July 2, 2009; except as required by
paragraphs (n) and (o) of this AD. Do all
applicable related investigative and
corrective actions before further flight.
Repeat the inspection thereafter at the
applicable time specified in Table 6 of this
AD. Certain compliance times are applicable
to short range use, AFT equal to or less than
4 hours, or long range use, AFT exceeding 4
hours.
(1) For A310–203, –204, –221, and –222
airplanes: At the earlier of the times specified
in paragraphs (m)(1)(i) and (m)(1)(ii) of this
AD.
9,100 flight cycles or 18,300 flight hours, whichever occurs first.
7,300 flight cycles or 20,400 flight hours, whichever occurs first.
5,900 flight cycles or 29,600 flight hours, whichever occurs first
(i) Within 10,800 flight cycles or 17,400
flight hours after the most recent inspection,
whichever occurs first.
(ii) At the later of the times specified in
paragraphs (m)(1)(ii)(A) and (m)(1)(ii)(B) of
this AD.
(A) Within the applicable interval specified
in Table 6 of this AD.
(B) Within 700 flight cycles or 1,500 flight
hours after the effective date of this AD,
whichever occurs first.
(2) For A310–304, –322, –324, and –325
airplanes: At the later of the times specified
in paragraphs (m)(2)(i) and (m)(2)(ii) of this
AD.
(i) Within the applicable interval specified
in Table 6 of this AD.
(ii) Within 700 flight cycles or 1,900 flight
hours after the effective date of this AD,
whichever occurs first.
Contact the FAA
(n) Where Airbus Service Bulletin A310–
57–2047, Revision 08, dated July 2, 2009,
specifies to contact the manufacturer if
certain cracks are found, before further flight,
repair those conditions according to a
method approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA (or its
delegated agent).
No Reporting Required
(o) Although Airbus Service Bulletin
A310–57–2047, Revision 06, dated July 13,
2004; and Revision 08, dated July 2, 2009;
specify to submit certain information to the
manufacturer, this AD does not include that
requirement.
(p) Actions accomplished before the
effective date of this AD in accordance with
Airbus Mandatory Service Bulletin A310–57–
2035, Revision 09, dated September 27, 2007,
are considered acceptable for compliance
with the corresponding actions specified in
paragraph (g) of this AD.
(q) Actions accomplished before the
effective date of this AD in accordance with
the service information specified in Table 7
of this AD, are considered acceptable for
compliance with the corresponding actions
specified in paragraphs (j) through (m) of this
AD.
TABLE 7—PREVIOUS ISSUES OF SERVICE BULLETIN A310–57–2047
Document
Airbus
Airbus
Airbus
Airbus
Airbus
Service
Service
Service
Service
Service
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
A310-57-2047 .........................................................................................................
A310–57–2047 .......................................................................................................
A310–57–2047 .......................................................................................................
A310–57–2047 .......................................................................................................
A310–57–2047 .......................................................................................................
Related AD
(r) Accomplishing a rotating probe
inspection of the rear spar internal angle and
the tee fitting in accordance with Airbus
Service Bulletin A310–57–2047, Revision 08,
dated July 2, 2009, or a service bulletin listed
in Table 7 of this AD, terminates the
requirements specified in paragraph (o) of
AD 98–26–01.
FAA AD Differences
jlentini on DSKJ8SOYB1PROD with PROPOSALS
Note 2: This AD differs from the MCAI
and/or service information as follows:
Although the MCAI or service information
tells you to contact the manufacturer for
repair information, paragraph (n) of this AD
requires that you contact the FAA or EASA
(or its delegated agent) instead. Although the
MCAI or service information tells you to
submit information to the manufacturer,
paragraph (o) of this AD specifies that such
submittal is not required.
Other FAA AD Provisions
(s) The following provisions also apply to
this AD:
VerDate Mar<15>2010
Revision
16:13 Jul 12, 2010
Jkt 220001
(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: Dan Rodina,
Aerospace Engineer, International Branch,
ANM–116, FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone (425)
227–2125; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
The AMOC approval letter must specifically
reference this AD.
(2) AMOCs approved previously in
accordance with AD 2006–09–05,
Amendment 39–14575, are approved as
AMOCs for the corresponding provisions of
this AD.
(3) Airworthy Product: For any
requirement in this AD to obtain corrective
PO 00000
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Fmt 4702
Sfmt 9990
Date
03
04
05
06
07
November 26, 1997.
March 5, 1999.
August 3, 2000.
July 13, 2004.
March 14, 2008.
actions from a manufacturer or other source,
use these actions if they are FAA-approved.
Corrective actions are considered FAAapproved 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
(t) Refer to MCAI EASA Airworthiness
Directive 2008–0187, dated October 10, 2008;
and Airbus Service Bulletins A310–57–2047,
Revision 08, dated July 2, 2009; and Airbus
Mandatory Service Bulletin A310–57–2035,
Revision 10, dated March 25, 2008; for
related information.
Issued in Renton, Washington, on June 30,
2010.
Todd G. Dixon,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–17061 Filed 7–12–10; 8:45 am]
BILLING CODE 4910–13–P
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]]>Agencies
[Federal Register Volume 75, Number 133 (Tuesday, July 13, 2010)]
[Proposed Rules]
[Pages 39863-39868]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-17061]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 /
Proposed Rules
[[Page 39863]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0680; Directorate Identifier 2008-NM-195-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 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: Analysis performed in the frame
of the Extended Service Goal has led Airbus to modify the inspection
programme [modification of thresholds, intervals and associated
configurations] which is currently required by DGAC (Direction
G[eacute]n[eacute]rale de l'Aviation Civile) France AD F-2005-001. This
modified inspection programme is necessary to detect and prevent damage
associated with a structural fatigue phenomenon of the rear spar
internal angle and the tee fitting located in the centre wing box. This
condition, if not corrected, could affect the structural integrity of
the centre wing box. The unsafe condition is reduced structural
integrity of the wings. 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 August 27, 2010.
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--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5
61 93 44 51; e-mail: account.airworth-eas@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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; 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-2010-0680;
Directorate Identifier 2008-NM-195-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 have lengthened the 30-day comment period for proposed ADs that
address MCAI originated by aviation authorities of other countries to
provide adequate time for interested parties to submit comments. The
comment period for these proposed ADs is now typically 45 days, which
is consistent with the comment period for domestic transport ADs.
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 April 20, 2006, we issued AD 2006-09-05, Amendment 39-14575 (71
FR 25921, May 3, 2006). That AD required actions intended to address an
unsafe condition on the products listed above.
Since we issued AD 2006-09-05, the manufacturer has modified the
inspection program currently required by AD 2006-09-05 by reducing
certain compliance times. The European Aviation Safety Agency (EASA),
which is the Technical Agent for the Member States of the European
Community, has issued EASA Airworthiness Directive 2008-0187, dated
October 10, 2008 (referred to after this as ``the MCAI''), to correct
an unsafe condition for the specified products. The MCAI states:
Analysis performed in the frame of the Extended Service Goal has
led Airbus to modify the inspection programme [modification of
thresholds, intervals and associated configurations] which is
currently required by DGAC (Direction G[eacute]n[eacute]rale de
l'Aviation Civile) France AD F-2005-001 [which corresponds to FAA AD
2006-09-05].
This modified inspection programme is necessary to detect and
prevent damage associated with a structural fatigue phenomenon of
the rear spar internal angle and the tee fitting located in the
centre wing box. This condition, if not corrected, could affect the
structural integrity of the centre wing box.
[[Page 39864]]
For the reason stated above, this new EASA AD retains the
requirements of DGAC France AD F-2005-001, which is superseded, and
refers to the latest revision of Airbus Service Bulletin (SB) A310-
57-2047.
The unsafe condition is reduced structural integrity of the wings. This
AD retains the requirements of AD 2006-09-05, but with certain reduced
compliance times. The required actions include doing repetitive
rotating probe inspections for any crack of the rear spar internal
angle and the left and right sides of the tee fitting, and doing
related investigative/corrective actions if necessary. The actions also
include modifying the holes in the internal angle and tee fitting by
cold expansion. You may obtain further information by examining the
MCAI in the AD docket.
Relevant Service Information
Airbus has issued Service Bulletin A310-57-2047, Revision 08, dated
July 2, 2009; and Mandatory Service Bulletin A310-57-2035, Revision 10,
dated March 25, 2008. 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.
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 66 products of U.S. registry.
The actions that are required by AD 2006-09-05 and retained in this
proposed AD take up to 600 work-hours per product, at an average labor
rate of $85 per work hour. Required parts cost up to $38,900 per
product. Based on these figures, the estimated cost of the currently
required actions is up to $89,900 per product.
This new AD adds no new costs to affected operators; the
manufacturer has modified the inspection program currently required by
AD 2006-09-05, this proposed AD reduces the compliance times required
by the existing AD.
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.
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 39-14575 (71 FR
25921, May 3, 2006) and adding the following new AD:
Airbus: Docket No. FAA-2010-0680; Directorate Identifier 2008-NM-
195-AD.
Comments Due Date
(a) We must receive comments by August 27, 2010.
Affected ADs
(b) This AD supersedes AD 2006-09-05, Amendment 39-14575. This
AD also affects certain requirements of AD 98-26-01, Amendment 39-
10942.
Applicability
(c) This AD applies to all Airbus Model A310-203, -204, -221, -
222, -304, -322, -324, and -325 airplanes, certificated in any
category.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Analysis performed in the frame of the Extended Service Goal has
led Airbus to modify the inspection programme [modification of
thresholds, intervals and associated configurations] which is
currently required by DGAC (Direction G[eacute]n[eacute]rale de
l'Aviation Civile) France AD F-2005-001 [which corresponds to FAA AD
2006-09-05].
This modified inspection programme is necessary to detect and
prevent damage associated with a structural fatigue phenomenon of
the rear spar internal angle and the tee fitting located in the
centre wing box. This condition, if not corrected, could affect the
structural integrity of the centre wing box.
The unsafe condition is reduced structural integrity of the wings.
[[Page 39865]]
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 CERTAIN REQUIREMENTS OF AD 2006-09-05 MODIFICATION
(g) For all airplanes except those that are modified by Airbus
Modifications 06672S6812, 06673S6813, and 07387S7974 in production:
Within 60 months after June 7, 2006 (the effective date of AD 2006-
09-05), modify the holes in the internal angle and tee fitting and
do all applicable related investigative and corrective actions by
accomplishing all the actions specified in the Accomplishment
Instructions of Airbus Service Bulletin A310-57-2035, Revision 08,
dated September 19, 2005; or Airbus Mandatory Service Bulletin A310-
57-2035, Revision 10, dated March 25, 2008; except as required by
paragraph (h) of this AD. Do all applicable related investigative
and corrective actions before further flight. As of the effective
date of this AD, use only Airbus Mandatory Service Bulletin A310-57-
2035, Revision 10, dated March 25, 2008.
Contact the FAA
(h) Where the service information specified in Table 1 of this
AD specifies to contact the manufacturer if certain cracks are
found, before further flight, repair those conditions according to a
method approved by either the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated
agent); or EASA (or its delegated agent).
Table 1--Service Information
------------------------------------------------------------------------
Document Revision Date
------------------------------------------------------------------------
Airbus Mandatory Service 10 March 25, 2008.
Bulletin A310-57-2035.
Airbus Service Bulletin A310- 08 September 19, 2005.
57-2035.
------------------------------------------------------------------------
Actions Accomplished According to Previous Issues of Airbus Service
Bulletin A310-57-2035
(i) Actions accomplished before June 7, 2006, in accordance with
the service information specified in Table 2 of this AD, are
considered acceptable for compliance with the corresponding actions
specified in paragraph (g) of this AD.
Table 2--Previous Issues of Service Bulletin A310-57-2035
------------------------------------------------------------------------
Document Revision Date
------------------------------------------------------------------------
Airbus Service Bulletin A310- 1 October 13, 1989.
57-2035.
Airbus Service Bulletin A310- 2 February 26, 1990.
57-2035.
Airbus Service Bulletin A310- 3 May 23, 1990.
57-2035.
Airbus Service Bulletin A310- 4 April 15, 1992.
57-2035.
Airbus Service Bulletin A310- 5 May 27, 1992.
57-2035.
Airbus Service Bulletin A310- 6 March 8, 1994.
57-2035.
Airbus Service Bulletin A310- 7 April 17, 1996.
57-2035.
------------------------------------------------------------------------
NEW REQUIREMENTS OF THIS AD--REVISED COMPLIANCE TIMES FOR INSPECTIONS
REQUIRED BY AD 2006-09-05
Initial and Repetitive Inspections of the Rear Spar Internal Angle
(j) For airplanes on which an inspection of the rear spar
internal angle has not been done in accordance with Airbus Service
Bulletin A310-57-2047 as of the effective date of this AD: At the
later of the times specified in paragraphs (j)(1) and (j)(2) of this
AD, do a rotating probe inspection for any crack of the rear spar
internal angle located in the center wing box and do all applicable
related investigative and corrective actions, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A310-57-2047,
Revision 08, dated July 2, 2009; except as required by paragraphs
(n) and (o) of this AD. Do all applicable related investigative and
corrective actions before further flight. Repeat the inspection
thereafter at the applicable time specified in Table 4 of this AD.
Certain compliance times are applicable to short range use, average
flight time (AFT) equal to or less than 4 hours, or long range use,
AFT exceeding 4 hours.
Note 1: To establish the AFT, divide the accumulated flight
time (counted from the take-off up to the landing) by the number of
accumulated flight cycles. This gives the average flight time per
flight cycle.
(1) Within the applicable time specified in Table 3 of this AD.
(2) Within the applicable time specified in paragraph (j)(2)(i),
(j)(2)(ii), or (j)(2)(iii) of this AD:
(i) For A310-203, -204, -221, and -222 airplanes: Within 700
flight cycles or 1,500 flight hours after the effective date of this
AD, whichever occurs first.
(ii) For A310-304, -322, -324, and -325 short range airplanes:
Within 700 flight cycles or 1,900 flight hours after the effective
date of this AD, whichever occurs first.
(iii) For A310-304, -322, -324, and -325 long range airplanes:
Within 500 flight cycles or 2,500 flight hours after the effective
date of this AD, whichever occurs first.
Table 3--Initial Inspection Internal Angle
------------------------------------------------------------------------
------------------------------------------------------------------------
Model and configuration Compliance time (whichever occurs first)
------------------------------------------------------------------------
A310-203, -204, -221, and - Before the Before the
222 airplanes on which Mod accumulation of accumulation of
6672S6812 and Mod 7387S7974 9,200 total flight 18,500 total flight
are not done. cycles. hours.
A310-203, -204, -221, and - Before the Before the
222 airplanes on which Mod accumulation of accumulation of
6672S6812 and Mod 7387S7974 19,800 total flight 39,600 total flight
are done in production. cycles. hours.
[[Page 39866]]
A310-203, -204, -221, and - Within 19,800 flight Within 39,600 flight
222 airplanes on which Mod cycles after the hours after the
6672S6812 and Mod 7387S7974 effective date of effective date of
are done in accordance with this AD. this AD.
Airbus Service Bulletin
A310-57-2035 and before the
accumulation of 6,200 total
flight cycles and 12,500
total flight hours.
A310-203, -204, -221, and - Within 8,200 flight Within 16,400 flight
222 airplanes on which Mod cycles after the hours after the
6672S6812 and Mod 7387S7974 effective date of effective date of
are done in accordance with this AD. this AD.
Airbus Service Bulletin
A310-57-2035 and are not
done before the
accumulation of 6,200 total
flight cycles and 12,500
total flight hours.
A310-304, -322, -324, and - Before the Before the
325 short range airplanes accumulation of accumulation of
on which Mod 6672S6812 and 7,500 total flight 21,100 total flight
Mod 7387S7974 are not done. cycles. hours.
A310-304, -322, -324, and - Before the Before the
325 long range airplanes on accumulation of accumulation of
which Mod 6672S6812 and Mod 5,300 total flight 26,900 total flight
7387S7974 are not done. cycles. hours.
A310-304, -322, -324, and - Before the Before the
325 short range airplanes accumulation of accumulation of
on which Mod 6672S6812 and 15,900 total flight 44,700 total flight
Mod 7387S7974 are done. cycles. hours.
A310-304, -322, -324, and - Before the Before the
325 long range airplanes on accumulation of accumulation of
which Mod 6672S6812 and Mod 11,300 total flight 56,900 total flight
7387S7974 are done in cycles. hours.
production.
A310-304, -322, -324, and - Within 15,900 flight Within 44,700 flight
325 short range airplanes cycles after the hours after the
on which Mod 6672S6812 and effective date of effective date of
Mod 7387S7974 are done in this AD. this AD.
accordance with Airbus
Service Bulletin A310-57-
2035 and before the
accumulation of 4,700 total
flight cycles and 13,100
total flight hours.
A310-304, -322, -324, and - Within 8,500 flight Within 23,800 flight
325 short range airplanes cycles after the hours after the
on which Mod 6672S6812 and effective date of effective date of
Mod 7387S7974 are done in this AD. this AD.
accordance with Airbus
Service Bulletin A310-57-
2035 and not done before
the accumulation of 4,700
total flight cycles and
13,100 total flight hours.
A310-304, -322, -324, and - Within 11,300 flight Within 56,900 flight
325 long range airplanes on cycles after the hours after the
which Mod 6672S6812 and Mod effective date of effective date of
7387S7974 are done in this AD. this AD.
accordance with Airbus
Service Bulletin A310-57-
2035 before the
accumulation of 3,300 total
flight cycles and 16,700
total flight hours.
A310-304, -322, -324, and - Within 6,000 flight Within 30,300 flight
325 long range airplanes on cycles after the hours after the
which Mod 6672S6812 and Mod effective date of effective date of
7387S7974 are done in this AD. this AD.
accordance with Airbus
Service Bulletin A310-57-
2035 and not done before
the accumulation of 3,300
total flight cycles and
16,700 total flight hours.
------------------------------------------------------------------------
Table 4--Repetitive Intervals
------------------------------------------------------------------------
Model and configuration Interval (not to exceed)
------------------------------------------------------------------------
A310-203, -204, -221, and -222 Within 7,200 flight cycles or
airplanes. 14,400 flight hours, whichever
occurs first.
A310-304, -322, -324, and -325 short Within 6,800 flight cycles or
range airplanes. 19,100 flight hours, whichever
occurs first.
A310-304, -322, -324, and -325 long Within 4,800 flight cycles or
range airplanes. 24,300 flight hours, whichever
occurs first.
------------------------------------------------------------------------
(k) For airplanes on which an inspection of the rear spar
internal angle has been done in accordance with Airbus Service
Bulletin A310-57-2047 as of the effective date of this AD: At the
applicable time specified in paragraphs (k)(1), (k)(2), and (k)(3)
of this AD, do a rotating probe inspection for any crack of the rear
spar internal angle located in the center wing box and do all
applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-57-2047, Revision 08, dated July 2, 2009; except as
required by paragraphs (n) and (o) of this AD. Do all applicable
related investigative and corrective actions before further flight.
Repeat the inspection thereafter at the applicable time specified in
Table 4 of this AD. Certain compliance times are applicable to short
range use, AFT equal to or less than 4 hours, or long range use, AFT
exceeding 4 hours.
(1) For A310-203, -204, -221, and -222 airplanes: At the earlier
of the times specified in paragraphs (k)(1)(i) and (k)(1)(ii) of
this AD.
(i) Within 7,940 flight cycles or 15,880 flight hours after the
most recent inspection, whichever occurs first.
(ii) At the later of the times specified in paragraphs
(k)(1)(ii)(A) and (k)(1)(ii)(B) of this AD.
(A) Within the applicable interval specified in Table 4 of this
AD.
(B) Within 740 flight cycles or 1,480 flight hours after the
effective date of this AD, whichever occurs first.
(2) For A310-304, -322, -324, and -325 short range airplanes: At
the later of the times
[[Page 39867]]
specified in paragraphs (k)(2)(i) and (k)(2)(ii) of this AD.
(i) Within the applicable interval specified in Table 4 of this
AD.
(ii) Within 700 flight cycles or 1,900 flight hours after the
effective date of this AD, whichever occurs first.
(3) For A310-304, -322, -324, and -325 long range airplanes: At
the later of the times specified in paragraphs (k)(3)(i) and
(k)(3)(ii) of this AD.
(i) Within the applicable interval specified in Table 4 of this
AD.
(ii) Within 500 flight cycles or 2,500 flight hours after the
effective date of this AD, whichever occurs first.
Initial and Repetitive Inspections of the Tee Fitting
(l) For airplanes on which an inspection of the left and right
sides of the tee fitting has not been done in accordance with Airbus
Service Bulletin A310-57-2047 as of the effective date of this AD:
At the later of the times specified in paragraphs (l)(1) and (l)(2)
of this AD, do a rotating probe inspection for any crack of the left
and right sides of the tee fitting, and do all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A310-57-2047,
Revision 08, dated July 2, 2009; except as required by paragraphs
(n) and (o) of this AD. Do all applicable related investigative and
corrective actions before further flight. Repeat the inspection
thereafter at the applicable time specified in Table 6 of this AD.
Certain compliance times are applicable to short range use, AFT
equal to or less than 4 hours, or long range use, AFT exceeding 4
hours.
(1) Within the applicable time specified in Table 5 of this AD.
(2) Within the applicable time in paragraph (l)(2)(i),
(l)(2)(ii), or (l)(2)(iii) of this AD.
(i) For A310-203, -204, -221, and -222 airplanes: Within 800
flight cycles or 1,600 flight hours, whichever occurs first.
(ii) For A310-304, -322, -324, and -325 short range airplanes:
Within 800 flight cycles or 2,200 flight hours, whichever occurs
first.
(iii) For A310-304, -322, -324, and -325 long range airplanes:
Within 600 flight cycles or 3,100 flight hours, whichever occurs
first.
Table 5--Initial Inspection Tee Fitting
------------------------------------------------------------------------
------------------------------------------------------------------------
Model and configuration Compliance time (whichever occurs first)
------------------------------------------------------------------------
A310-203, -204, -221, and - Before the Within 28,700 flight
222 airplanes on which Mod accumulation of hours after the
6673S6813 is not done. 14,300 flight effective date of
cycles. this AD.
A310-203, -204, -221, and - Before the Before the
222 airplanes on which Mod accumulation of accumulation of
6673S6813 is done in 17,500 total flight 35,000 total flight
production. cycles. hours.
A310-203, -204, -221, and - Within 17,500 flight Within 35,000 flight
222 airplanes on which Mod cycles after the hours after the
6673S6813 is done in effective date of effective date of
accordance with Airbus this AD. this AD.
Service Bulletin A310-57-
2035 and before the
accumulation of 8,100 total
flight cycles and 16,200
total flight hours.
A310-203, -204, -221, and - Within 9,600 flight Within 19,200 flight
222 airplanes on which Mod cycles after the hours after the
6673S6813 is done in effective date of effective date of
accordance with Airbus this AD. this AD.
Service Bulletin A310-57-
2035 and not before the
accumulation of 8,100 total
flight cycles and 16,200
total flight hours.
A310-304, -322, -324, and - Within 10,800 flight Within 30,400 flight
325 short range airplanes cycles after the hours after the
on which Mod 6673S6813 is effective date of effective date of
not done. this AD. this AD.
A310-304, -322, -324, and - Before the Before the
325 long range airplanes on accumulation of accumulation of
which Mod 6673S6813 is not 8,500 total flight 42,800 total flight
done. cycles. hours.
A310-304, -322, -324, and - Before the Before the
325 short range airplanes accumulation of accumulation of
on which Mod 6673S6813 is 13,100 total flight 36,700 total flight
done in production. cycles. hours.
A310-304, -322, -324, and - Before the Before the
325 long range airplanes on accumulation of accumulation of
which Mod 6673S6813 is done 10,300 total flight 51,600 total flight
in production. cycles. hours.
A310-304, -322, -324, and - Within 13,100 flight Within 36,700 flight
325 short range airplanes cycles after the hours after the
on which Mod 6673S6813 is effective date of effective date of
done in accordance with this AD. this AD.
Airbus Service Bulletin
A310-57-2035 and before the
accumulation of 5,800 total
flight cycles and 16,400
total flight hours.
A310-304, -322, -324, and - Within 7,400 flight Within 20,900 flight
325 short range airplanes cycles after the hours after the
on which Mod 6673S6813 is effective date of effective date of
done in accordance with this AD. this AD.
Airbus Service Bulletin
A310-57-2035 and not before
the accumulation of 5,800
total flight cycles and
16,400 total flight hours.
A310-304, -322, -324, and - Within 10,300 flight Within 51,600 flight
325 long range airplanes on cycles after the hours after the
which Mod 6673S6813 is done effective date of effective date of
in accordance with Airbus this AD. this AD.
Service Bulletin A310-57-
2035 and before the
accumulation of 4,600 total
flight cycles and 23,100
total flight hours.
A310-304, -322, -324, and - Within 6,000 flight Within 30,300 flight
325 long range airplanes on cycles after the hours after the
which Mod 6673S6813 is done effective date of effective date of
in accordance with Airbus this AD. this AD.
Service Bulletin A310-57-
2035 and not before the
accumulation of 4,600 total
flight cycles and 23,100
total flight hours.
------------------------------------------------------------------------
[[Page 39868]]
Table 6--Repetitive Intervals
------------------------------------------------------------------------
Model and configuration Interval (not to exceed)
------------------------------------------------------------------------
A310-203, -204, -221, and -222 9,100 flight cycles or 18,300
airplanes. flight hours, whichever occurs
first.
A310-304, -322, -324, and -325 short 7,300 flight cycles or 20,400
range airplanes. flight hours, whichever occurs
first.
A310-304, -322, -324, and -325 long 5,900 flight cycles or 29,600
range airplanes. flight hours, whichever occurs
first
------------------------------------------------------------------------
(m) For airplanes on which an inspection of the rear left and
right sides of the tee fitting has been done in accordance with
Airbus Service Bulletin A310-57-2047 as of the effective date of
this AD: At the applicable time specified in paragraphs (m)(1) or
(m)(2) of this AD, do a rotating probe inspection for any crack of
the left and right sides of the tee fitting, and do all applicable
related investigative and corrective actions, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A310-57-2047,
Revision 08, dated July 2, 2009; except as required by paragraphs
(n) and (o) of this AD. Do all applicable related investigative and
corrective actions before further flight. Repeat the inspection
thereafter at the applicable time specified in Table 6 of this AD.
Certain compliance times are applicable to short range use, AFT
equal to or less than 4 hours, or long range use, AFT exceeding 4
hours.
(1) For A310-203, -204, -221, and -222 airplanes: At the earlier
of the times specified in paragraphs (m)(1)(i) and (m)(1)(ii) of
this AD.
(i) Within 10,800 flight cycles or 17,400 flight hours after the
most recent inspection, whichever occurs first.
(ii) At the later of the times specified in paragraphs
(m)(1)(ii)(A) and (m)(1)(ii)(B) of this AD.
(A) Within the applicable interval specified in Table 6 of this
AD.
(B) Within 700 flight cycles or 1,500 flight hours after the
effective date of this AD, whichever occurs first.
(2) For A310-304, -322, -324, and -325 airplanes: At the later
of the times specified in paragraphs (m)(2)(i) and (m)(2)(ii) of
this AD.
(i) Within the applicable interval specified in Table 6 of this
AD.
(ii) Within 700 flight cycles or 1,900 flight hours after the
effective date of this AD, whichever occurs first.
Contact the FAA
(n) Where Airbus Service Bulletin A310-57-2047, Revision 08,
dated July 2, 2009, specifies to contact the manufacturer if certain
cracks are found, before further flight, repair those conditions
according to a method approved by either the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or
its delegated agent).
No Reporting Required
(o) Although Airbus Service Bulletin A310-57-2047, Revision 06,
dated July 13, 2004; and Revision 08, dated July 2, 2009; specify to
submit certain information to the manufacturer, this AD does not
include that requirement.
(p) Actions accomplished before the effective date of this AD in
accordance with Airbus Mandatory Service Bulletin A310-57-2035,
Revision 09, dated September 27, 2007, are considered acceptable for
compliance with the corresponding actions specified in paragraph (g)
of this AD.
(q) Actions accomplished before the effective date of this AD in
accordance with the service information specified in Table 7 of this
AD, are considered acceptable for compliance with the corresponding
actions specified in paragraphs (j) through (m) of this AD.
Table 7--Previous Issues of Service Bulletin A310-57-2047
------------------------------------------------------------------------
Document Revision Date
------------------------------------------------------------------------
Airbus Service Bulletin 03 November 26, 1997.
A310[dash]57[dash]2047.
Airbus Service Bulletin A310- 04 March 5, 1999.
57-2047.
Airbus Service Bulletin A310- 05 August 3, 2000.
57-2047.
Airbus Service Bulletin A310- 06 July 13, 2004.
57-2047.
Airbus Service Bulletin A310- 07 March 14, 2008.
57-2047.
------------------------------------------------------------------------
Related AD
(r) Accomplishing a rotating probe inspection of the rear spar
internal angle and the tee fitting in accordance with Airbus Service
Bulletin A310-57-2047, Revision 08, dated July 2, 2009, or a service
bulletin listed in Table 7 of this AD, terminates the requirements
specified in paragraph (o) of AD 98-26-01.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service
information as follows:
Although the MCAI or service information tells you to contact the
manufacturer for repair information, paragraph (n) of this AD
requires that you contact the FAA or EASA (or its delegated agent)
instead. Although the MCAI or service information tells you to
submit information to the manufacturer, paragraph (o) of this AD
specifies that such submittal is not required.
Other FAA AD Provisions
(s) 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: Dan
Rodina, Aerospace Engineer, International Branch, ANM-116, FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056; telephone (425) 227-2125; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(2) AMOCs approved previously in accordance with AD 2006-09-05,
Amendment 39-14575, are approved as AMOCs for the corresponding
provisions of this AD.
(3) 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
(t) Refer to MCAI EASA Airworthiness Directive 2008-0187, dated
October 10, 2008; and Airbus Service Bulletins A310-57-2047,
Revision 08, dated July 2, 2009; and Airbus Mandatory Service
Bulletin A310-57-2035, Revision 10, dated March 25, 2008; for
related information.
Issued in Renton, Washington, on June 30, 2010.
Todd G. Dixon,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-17061 Filed 7-12-10; 8:45 am]
BILLING CODE 4910-13-P
