[Federal Register Volume 75, Number 149 (Wednesday, August 4, 2010)]
[Proposed Rules]
[Pages 46873-46877]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-19144]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0670; Directorate Identifier 2007-NM-339-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A318-111 and A318-112
Airplanes and Model A319, A320, and A321 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
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SUMMARY: We are revising an earlier NPRM for the products listed above.
This action revises the earlier NPRM by expanding the scope. 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:
Damage to the lower lateral fittings of the 80VU rack, typically
elongated holes, migrated bushes [bushings], and/or missing bolts
have been reported in-service. In addition damage to the lower
central support fitting (including cracking) has been reported.
In the worst case scenario a complete failure of the 80VU
fittings in combination with a high load factor or strong vibration
could lead to failure of the rack structure and/or computers or
rupture/disconnection of the cable harnesses to one or more
computers located in the 80VU. This rack contains computers for
Flight Controls, Communication and Radio-navigation. These functions
are duplicated across other racks but during critical phases of
flight the multiple system failures/re-configuration may constitute
an unsafe condition.
* * * * *
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 30, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://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, Airworthiness Office--EAS, 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: [email protected]; Internet http://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 http://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this 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: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2141; 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-2008-0670;
Directorate Identifier 2007-NM-339-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 http://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.
[[Page 46874]]
Discussion
We proposed to amend 14 CFR part 39 with an earlier NPRM for the
specified products, which was published in the Federal Register on June
24, 2008 (73 FR 35601). That earlier NPRM proposed to require actions
intended to address the unsafe condition for the products listed above.
Since that NPRM was issued, the European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, has issued EASA Airworthiness Directive 2007-
0276R1, dated March 18, 2010 (corrected April 12, 2010) (referred to
after this as ``the MCAI''), to revise EASA AD 2007-0276, dated October
26, 2007, which we referred to in the NPRM. The MCAI adds an optional
terminating action to the repetitive inspections. The MCAI states:
Damage to the lower lateral fittings of the 80VU rack, typically
elongated holes, migrated bushes [bushings], and/or missing bolts
have been reported in-service. In addition damage to the lower
central support fitting (including cracking) has been reported.
In the worst case scenario a complete failure of the 80VU
fittings in combination with a high load factor or strong vibration
could lead to failure of the rack structure and/or computers or
rupture/disconnection of the cable harnesses to one or more
computers located in the 80VU. This rack contains computers for
Flight Controls, Communication and Radio-navigation. These functions
are duplicated across other racks but during critical phases of
flight the multiple system failures/re-configuration may constitute
an unsafe condition.
For the reasons described above, EASA AD 2007-0276 was issued to
require repetitive [detailed] inspection of the lower lateral 80VU
fittings for damage and [repetitive detailed] inspection of the
lower central 80VU support for damage and cracking, and the
accomplishment of associated corrective actions, depending on
findings.
Since AD 2007-0276 was issued, Airbus introduced a new
reinforced lower central support for the 80VU.
This [EASA] AD has been revised to introduce the new reinforced
lower central support as an optional terminating action to the
repetitive inspections.
* * * * *
The associated corrective actions include repair or replacement of the
lower lateral fittings and/or replacement of the lower central support.
Modifying the 80VU lower lateral fittings (the modification includes
replacing the 80VU lower lateral fittings) eliminates the need for the
repetitive inspection of the lower lateral fittings. Replacing the 80VU
lower central support (i.e., replacing the pyramid fitting on the 80VU
rack with a new, reinforced fitting) eliminates the need for the
repetitive inspection of the lower central support. You may obtain
further information by examining the MCAI in the AD docket.
Also, we have determined that for any cracking found during an
inspection specified in paragraph (i) of this supplemental NPRM
(referred to as paragraph (f)(3) in the NPRM), the corrective action
specified in paragraph (j) of this supplemental NPRM (referred to as
paragraph (f)(4) in the NPRM) must be done before further flight. Our
policy specifies the requirement to repair known cracks before further
flight (though we might make exceptions to this policy in certain cases
of unusual need, as discussed below). This policy is based on the fact
that such damaged airplanes do not conform to the FAA-certificated type
design and, therefore, are not airworthy until a properly approved
repair is made. We consider the compliance times in this AD to be
adequate to allow operators to acquire parts to have on hand in the
event that a crack is detected during inspection. Therefore, we have
determined that, due to the safety implications and consequences
associated with such cracking, any subject 80VU rack lower central
support that is found to be cracked must be replaced or modified before
further flight.
Also, since the NPRM 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 supplemental
NPRM.
Comments
We have considered the following comments received on the earlier
NPRM.
Requests To Include Optional Terminating Action
Northwest Airlines, and Air Transport Association (ATA) on behalf
of its members United Airlines and US Airways, request that we refer to
a new Airbus service bulletin under development that provides a
permanent terminating action for the central support fitting. United
points out that the terminating action is preferable because the
inspection proposed in the NPRM is intrusive to aircraft systems and
very time consuming.
We agree with the commenters' request to refer to the new Airbus
service information as the appropriate source of service information
for modification of the central support. Since issuance of the NPRM,
Airbus has issued Service Bulletin A320-53-1215, dated November 5,
2008. That service bulletin describes procedures for replacing the
lower central support of the 80VU rack with a new, reinforced support.
We have added paragraph (k) to this supplemental NPRM to specify that
doing this replacement terminates the requirements of paragraphs (g)
and (i) of this AD. We have also revised paragraph (d) of this
supplemental NPRM to include reference to the ATA Code 53: Fuselage,
which is the subject of Airbus Service Bulletin A320-53-1215, dated
November 5, 2008.
Explanation of Additional Revised Service Information
Since we issued the NPRM, Airbus has issued Mandatory Service
Bulletin A320-25A1555, Revision 01, including Appendix 1, dated
February 18, 2008; and Mandatory Service Bulletin A320-25A1555,
Revision 02, including Appendix 1, dated November 5, 2008. Airbus has
also issued Service Bulletin A320-25-1557, Revision 01, dated February
7, 2008; and Service Bulletin A320-25-1557, Revision 02, dated November
5, 2008. (We referred to Airbus Service Bulletins A320-25A1555 and
A320-25-1557, both dated June 14, 2007, in the NPRM as the appropriate
source of service information for doing the proposed actions.) Airbus
issued Revision 01 of those service bulletins to include minor
improvements in the procedures. Airbus issued Revision 02 of those
service bulletins to include a reference to the terminating action
specified in Airbus Service Bulletin A320-53-1215, dated November 5,
2008.
No additional work is necessary for airplanes on which any revision
of these service bulletins has been accomplished before the effective
date of this AD; therefore, we have revised paragraphs (g) and (n) of
this supplemental NPRM to refer to Revision 02 of Airbus Service
Bulletins A320-25A1555 and A320-25-1557. We have also revised
paragraphs (h) and (i) of this supplemental NPRM to refer to Revision
02 of Airbus Mandatory Service Bulletin A320-25A1555. We have also
revised this supplemental NPRM to include a new paragraph (l) to give
credit for actions accomplished before the effective date of this AD in
accordance with the Airbus service bulletins listed in Table 1 of this
AD.
Clarification of Repetitive Interval
We have revised the repetitive interval specified in paragraph
(g)(2) of this supplemental NPRM (referred to as paragraph (f)(1)(i) in
the NRPM) to specify that the next inspection must be done within
24,000 flight cycles after doing the replacement and thereafter the
[[Page 46875]]
inspection must be done at intervals not to exceed 4,500 flight cycles.
Paragraph (f)(1)(ii) of the NPRM specified a repetitive interval of
24,000 flight cycles for airplanes on which the repair (replacement)
had been done. However, after exceeding 24,000 flight cycles since the
replacement, the inspections must be done at intervals not to exceed
4,500 flight cycles in order to adequately address the identified
unsafe condition.
We have also revised the repetitive interval specified in paragraph
(i)(2) of this supplemental NPRM (referred to as paragraph (f)(3)(ii)
in the NRPM) to specify that the next inspection must be done within
24,000 flight cycles after doing the repair or replacement and
thereafter the inspection must be done at the applicable intervals
specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD. Paragraph
(f)(3)(ii) of the NPRM specified a repetitive interval of 24,000 flight
cycles for airplanes on which the repair or replacement had been done.
However, after exceeding 24,000 flight cycles since the repair or
replacement, the inspections must be done within the applicable
intervals specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD in
order to address the identified unsafe condition.
We have also revised paragraphs (i)(1)(i) and (i)(1)(ii) of this AD
(referred to as paragraphs (f)(3)(i)(A) and (f)(3)(i)(B) of the NPRM)
by removing the phrase ``as of the effective date of the AD.'' The
repetitive intervals specified in those paragraphs are not dependent on
how many flight cycles the support has accumulated as of the effective
date of the AD, e.g., for a lower central support that has accumulated
23,000 total flight cycles (at the time the inspection specified in
paragraph (i) is done), the inspection should be repeated at intervals
not to exceed 4,500 flight cycles until the lower central support has
accumulated 30,000 total flight cycles and then the inspection should
be repeated at intervals not to exceed 500 flight cycles.
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.
Certain changes described above expand the scope of the earlier
NPRM. As a result, we have determined that it is necessary to reopen
the comment period to provide additional opportunity for the public to
comment on this proposed AD.
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 678 products of U.S. registry. We also estimate that
it would take about 82 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $85 per
work-hour. Required parts would cost about $2,592 per product. Where
the service information lists required parts costs that are covered
under warranty, we have assumed that there will be no charge for these
costs. As we do not control warranty coverage for affected parties,
some parties may incur costs higher than estimated here. Based on these
figures, we estimate the cost of the proposed AD on U.S. operators to
be $6,483,036, or $9,562 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this 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 adding the following new AD:
Airbus: Docket No. FAA-2008-0670; Directorate Identifier 2007-NM-
339-AD.
Comments Due Date
(a) We must receive comments by August 30, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A318-111, A318-112, A319-
111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-
[[Page 46876]]
132, A319-133, A320-111, A320-211, A320-212, A320-214, A320-231,
A320-232, A320-233, A321-111, A321-112, A321-131, A321-211, A321-
212, A321-213, A321-231, and A321-232 airplanes, certificated in any
category, all manufacturer serial numbers, except airplanes on which
Airbus Modification 34804 has been embodied in production or on
which Airbus Service Bulletins A320-25-1557 and A320-53-1215 have
been done in service.
Subject
(d) Air Transport Association (ATA) of America Code 25:
Equipment/Furnishings, and Code 53: Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Damage to the lower lateral fittings of the 80VU rack, typically
elongated holes, migrated bushes [bushings], and/or missing bolts
have been reported in-service. In addition damage to the lower
central support fitting (including cracking) has been reported.
In the worst case scenario a complete failure of the 80VU
fittings in combination with a high load factor or strong vibration
could lead to failure of the rack structure and/or computers or
rupture/disconnection of the cable harnesses to one or more
computers located in the 80VU. This rack contains computers for
Flight Controls, Communication and Radio-navigation. These functions
are duplicated across other racks but during critical phases of
flight the multiple system failures/re-configuration may constitute
an unsafe condition.
* * * * *
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.
Repetitive Inspections of the 80V Rack Lower Lateral Fittings
(g) Prior to the accumulation of 24,000 total flight cycles, or
within 500 flight cycles after the effective date of this AD,
whichever occurs later: Do a special detailed inspection of the 80VU
rack lower lateral fittings for damage (e.g., broken fitting,
missing bolts, migrated bushings, material burr, or rack in contact
with the fitting) of the 80VU rack lower lateral fittings, in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A320-25A1555, Revision 02, dated November 5, 2008.
Repeat the inspection thereafter at the interval specified in
paragraph (g)(1) or (g)(2) of this AD, as applicable. Modifying the
80VU lower lateral fittings, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-25-1557, Revision 02,
dated November 5, 2008, terminates the inspection requirements of
this paragraph.
(1) For airplanes on which the 80VU rack lower lateral fittings
have not been replaced in accordance with the Airbus Mandatory
Service Bulletin A320-25A1555: Repeat the inspection thereafter at
intervals not to exceed 4,500 flight cycles.
(2) For airplanes on which the 80VU rack lower lateral fittings
have been replaced in accordance with Airbus Mandatory Service
Bulletin A320-25A1555: Do the next inspection within 24,000 flight
cycles after doing the replacement and repeat the inspection
thereafter at intervals not to exceed 4,500 flight cycles.
(h) If any damage is found during any inspection required by
paragraph (g) of this AD, do all applicable corrective actions
(inspection and/or repair) in accordance with the Accomplishment
Instructions and timeframes given in Airbus Mandatory Service
Bulletin A320-25A1555, Revision 02, dated November 5, 2008.
Repetitive Inspections of the 80V Rack Lower Central Support
(i) Prior to the accumulation of 24,000 total flight cycles, or
within 500 flight cycles after the effective date of this AD,
whichever occurs later: Do a special detailed inspection of the 80VU
rack lower central support for cracking, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A320-25A1555, Revision 02, dated November 5, 2008. Repeat the
inspection thereafter at the interval specified in paragraph (i)(1)
or (i)(2) of this AD, as applicable. Replacing the pyramid fitting
on the 80VU rack with a new, reinforced fitting, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1215, dated November 5, 2008, terminates the inspection requirements
of this paragraph.
(1) For airplanes on which the 80VU rack lower central support
has not been repaired or replaced in accordance with Airbus
Mandatory Service Bulletin A320-25A1555 or Airbus Service Bulletin
A320-25-1557: Repeat the inspection thereafter at the interval
specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD, as
applicable.
(i) For airplanes on which the lower central support has
accumulated 30,000 total flight cycles or more: At intervals not to
exceed 500 flight cycles.
(ii) For airplanes on which the lower central support has
accumulated less than 30,000 total flight cycles: At intervals not
to exceed 4,500 flight cycles, without exceeding 30,750 total flight
cycles on the support for the first repetitive inspection.
(2) For airplanes on which the 80VU rack lower central support
has been repaired or replaced in accordance with Airbus Mandatory
Service Bulletin A320-25A1555 or Airbus Service Bulletin A320-25-
1557: Do the next inspection within 24,000 flight cycles after the
repair or replacement and thereafter repeat the inspection at the
interval specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD,
as applicable.
(j) If any crack is found during any inspection required by
paragraph (i) of this AD, before further flight, replace the pyramid
fitting on the 80VU rack with a new, reinforced fitting, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-53-1215, dated November 5, 2008. Doing this
replacement terminates the inspection requirements of paragraph (i)
of this AD.
Optional Terminating Action
(k) Doing the actions specified in paragraphs (k)(1) and (k)(2)
of this AD terminates the requirements of paragraphs (g) and (i) of
this AD.
(1) Replacing the pyramid fitting on the 80VU rack with a new,
reinforced fitting, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1215, dated November
5, 2008.
(2) Modifying the 80VU lower lateral fittings, in accordance
with Airbus Service Bulletin A320-25-1557, Revision 02, dated
November 5, 2008.
Credit Service Bulletins
(l) Actions done before the effective date of this AD in
accordance with the service information identified in Table 1 of
this AD are acceptable for compliance with the corresponding
requirements of this AD.
Table 1--Previous Revisions of Service Information
------------------------------------------------------------------------
Service information Revision level Date
------------------------------------------------------------------------
Airbus Mandatory Service 01.............. February 18, 2008.
Bulletin A320-25A1555.
Airbus Service Bulletin A320- Original........ June 14, 2007.
25A1555.
Airbus Service Bulletin A320- Original........ June 14, 2007.
25-1557.
Airbus Service Bulletin A320- 01.............. February 7, 2008.
25-1557.
------------------------------------------------------------------------
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service
information as follows:
(1) Although the MCAI or service information allows further
flight after cracks are found during compliance with the required
action, (j) of this AD requires that you do a corrective action
before further flight.
(2) Although the MCAI specifies doing a repair or replacement
and repetitive inspections after the repair or replacement is done
if cracking is found in the 80VU rack lower central support,
paragraph (j) of this AD requires that you perform a replacement,
which eliminates the need for further repetitive inspections of the
part.
[[Page 46877]]
Other FAA AD Provisions
(m) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, ANM-
116, International Branch, 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: Tim
Dulin, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 227-2141; 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) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(n) Refer to MCAI EASA Airworthiness Directive 2007-0276R1,
dated March 18, 2010 (corrected April 12, 2010), and the service
information identified in Table 2 of this AD, for related
information.
Table 2--Related Service Information
------------------------------------------------------------------------
Service information Revision level Date
------------------------------------------------------------------------
Airbus Mandatory Service 02.............. November 5, 2008.
Bulletin A320-25A1555.
Airbus Service Bulletin A320- 02.............. November 5, 2008.
25-1557.
Airbus Service Bulletin A320- Original........ November 5, 2008.
53-1215.
------------------------------------------------------------------------
Issued in Renton, Washington, on July 27, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-19144 Filed 8-3-10; 8:45 am]
BILLING CODE 4910-13-P