Airworthiness Directives; Airbus Airplanes, 32060-32064 [2012-13191]
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Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules
777–53A0054, Revision 1, dated November 4,
2010; specify to contact Boeing for
appropriate action, accomplish applicable
actions using a method approved in
accordance with the procedures specified in
paragraph (q) of this AD.
(j) Retained Exception to Service Bulletin
Specifications, Contact for Inspection
Requirements
This paragraph restates the requirements of
paragraph (j) of AD 2009–24–08, Amendment
39–16096 (74 FR 62217, November 27, 2009).
Where paragraph 1.E. ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 777–53A0054,
dated August 7, 2008, specifies to ‘‘contact
Boeing for inspection requirements for
operation beyond 60,000 total flight-cycles
after first repaint,’’ for those airplanes, this
AD requires contacting the Manager, Seattle
Aircraft Certification Office (ACO), for all
inspection requirements of this AD and doing
the requirements.
(k) Retained Reporting
This paragraph restates the requirements of
paragraph (k) of AD 2009–24–08,
Amendment 39–16096 (74 FR 62217,
November 27, 2009). At the applicable time
specified in paragraph (k)(1) or (k)(2) of this
AD: Submit a report of positive findings of
cracks found during the inspection required
by paragraphs (g) and (m) of this AD to the
Boeing Commercial Airplane Group, P.O.
Box 3707, Seattle, Washington 98124–2207.
Alternatively, operators may submit reports
to their Boeing field service representatives.
The report must contain, at a minimum, the
inspection results, a description of any
discrepancies found, the airplane serial
number, and the number of flight cycles and
flight hours on the airplane. 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 contained in this AD and has
assigned OMB Control Number 2120–0056.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
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(l) New Inspection for External Decals
Within 24 months after the effective date
of this AD: Inspect to determine the locations
where external decals have been applied or
removed across affected lap joints, large
cargo door hinges, and external doublers, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 777–
53A0054, Revision 1, dated November 4,
2010.
(m) New Inspection for Scribe Lines and
Related Investigative and Corrective Actions
If, during the inspection required by
paragraph (l) of this AD, any location is
found where external decals have been
applied or removed across lap joints, large
cargo door hinges, or external doublers:
Before further flight, do a detailed
exploratory inspection for scribe lines at all
affected locations, in accordance with the
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Accomplishment Instructions of Boeing
Service Bulletin 777–53A0054, Revision 1,
dated November 4, 2010. Do all applicable
related investigative and corrective actions at
the times specified in Boeing Service Bulletin
777–53A0054, Revision 1, dated November 4,
2010, by accomplishing all actions specified
in the Accomplishment Instructions of
Boeing Service Bulletin 777–53A0054,
Revision 1, dated November 4, 2010, except
as provided by paragraph (i) of this AD.
(n) Exceptions to Service Information
(1) Where Boeing Service Bulletin 777–
53A0054, Revision 1, dated November 4,
2010, specifies a compliance time after the
date on that service bulletin, paragraphs (l)
and (m) of this AD require compliance within
the specified compliance time after the
effective date of this AD.
(2) Where paragraph 1.E., ‘‘Compliance,’’ of
Boeing Service Bulletin 777–53A0054,
Revision 1, dated November 4, 2010,
specifies to ‘‘contact Boeing for inspection
requirements for operation beyond 60,000
total flight-cycles after first repaint,’’ for
those airplanes, this AD requires contacting
the Manager, Seattle ACO, for all inspection
requirements of this AD and doing the
requirements.
(o) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (m) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Alert
Service Bulletin 777–53A0054, dated August
7, 2008.
(p) Paperwork Reduction Act Burden
Statement
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 5 minutes per
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave. SW., Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
(q) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
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Information may be emailed to: 9–ANM–
Seattle–ACO–AMOC–Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO
to make those findings. For a repair method
to be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2009–24–08,
Amendment 39–16096 (74 FR 62217,
November 27, 2009), are approved as AMOCs
for the corresponding provisions of this AD,
except that AMOCs approved for AD 2009–
24–08 are not approved for fuselage areas
where any decals may have been installed or
removed on airplanes that have never been
stripped or repainted since they left the
factory.
(r) Related Information
(1) For more information about this AD,
contact Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone: 425–917–
6577; fax: 425–917–6590; email:
Berhane.Alazar@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; phone:
206–544–5000, extension 1; fax: 206–766–
5680; email: me.boecom@boeing.com;
Internet: https://www.myboeingfleet.com.
You may review copies of the referenced
service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW.,
Renton, Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
Issued in Renton, Washington, on May 21,
2012.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–13169 Filed 5–30–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0493; Directorate
Identifier 2011–NM–180–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules
Notice of proposed rulemaking
(NPRM).
ACTION:
We propose to supersede an
existing airworthiness directive (AD) for
all Airbus Model A318–111 and –112
airplanes; and all Model A319, A320,
and A321 series airplanes. The existing
AD currently requires revising the
Airworthiness Limitations Section
(ALS) of the Instructions for Continued
Airworthiness to incorporate new
limitations for fuel tank systems. Since
we issued that AD, Airbus has issued
more restrictive maintenance
requirements and/or airworthiness
limitations. This proposed AD would
revise the maintenance program to
incorporate revised fuel maintenance
and inspection tasks, and add airplanes
to the applicability. We are proposing
this AD to prevent the potential of
ignition sources inside fuel tanks,
which, in combination with flammable
fuel vapors, could result in a fuel tank
explosion and consequent loss of the
airplane.
SUMMARY:
We must receive comments on
this proposed AD by July 16, 2012.
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
W12–140, 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; email
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.
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DATES:
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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone
(425) 227–1405; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
The Fuel Airworthiness Limitations (FAL)
are specified in Airbus A318/A319/A320/
A321 FAL Document reference 95A.1931/05,
which is approved by the European Aviation
Safety Agency (EASA) and referenced in the
Airbus A318/A319/A320/A321 ALS Part 5.
The issue 4 of Airbus A318/A319/A320/
A321 FAL Document introduces more
restrictive maintenance requirements and/or
airworthiness limitations. Failure to comply
with these more restrictive maintenance
requirements and airworthiness limitations
contained in this document constitutes an
unsafe condition.
This [EASA] AD retains the requirement of
EASA AD 2006–0203, which is superseded,
and requires the implementation of the new
or more restrictive maintenance requirements
and/or airworthiness limitations as specified
in Airbus A318/A319/A320/A321 FAL
Document issue 4.
Comments Invited
We are proposing this AD to prevent the
potential of ignition sources inside fuel
tanks, which, in combination with
flammable fuel vapors, could result in a
fuel tank explosion and consequent loss
of the airplane. You may obtain further
information by examining the MCAI in
the AD docket.
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–2012–0493; Directorate Identifier
2011–NM–180–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
Examining the AD Docket
On November 16, 2009, we issued AD
2007–15–06 R1, Amendment 39–16097
(74 FR 62219, November 27, 2009). That
AD required actions intended to address
an unsafe condition on the products
listed above.
Since we issued AD 2007–15–06 R1,
Amendment 39–16097 (74 FR 62219,
November 27, 2009), Airbus has issued
A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document
95A.1931/05, Issue 4, dated August 26,
2010. The European Aviation Safety
Agency (EASA), which is the Technical
Agent for the Member States of the
European Community, has issued EASA
Airworthiness Directive 2011–0155,
dated August 25, 2011 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
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.
The airworthiness limitations are currently
published in the Airbus A318/A319/A320/
A321 Airworthiness Limitations Section
(ALS).
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Relevant Service Information
Airbus has issued A318/A319/A320/
A321 Fuel Airworthiness Limitations,
Document 95A.1931/05, Issue 4, dated
August 26, 2010. The actions described
in this service information are intended
to correct the unsafe condition
identified in the MCAI.
Explanation of Changes Made to This
NPRM
We have changed Note 1 and Note 2
of the restated requirements of AD
2007–15–06 R1, Amendment 39–16097
(74 FR 62219, November 27, 2009), to
lettered paragraphs (i) and (j),
respectively, in this NPRM. These
changes do not add any additional
burden upon the public than was
required in the existing AD.
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.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
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Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules
affect about 745 products of U.S.
registry.
The actions that are required by AD
2007–15–06 R1, Amendment 39–16097
(74 FR 62219, November 27, 2009), and
retained in this proposed AD take about
2 work-hours per product, at an average
labor rate of $85 per work hour.
Required parts cost about $0 per
product. Based on these figures, the
estimated cost of the currently required
actions is $170 per product.
We estimate that it would take about
2 work-hours per product to comply
with the new basic requirements of this
proposed AD. The average labor rate is
$85 per work-hour. Based on these
figures, we estimate the cost of the
proposed AD on U.S. operators to be
$126,650, or $170 per product.
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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);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
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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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2007–15–06 R1, Amendment 39–16097
(74 FR 62219, November 27, 2009), and
adding the following new AD:
Airbus: Docket No. FAA–2012–0493;
Directorate Identifier 2011–NM–180–AD.
(a) Comments Due Date
We must receive comments by July 16,
2012.
(b) Affected ADs
This AD supersedes AD 2007–15–06 R1,
Amendment 39–16097 (74 FR 62219,
November 27, 2009).
(c) Applicability
(1) This AD applies to Airbus Model A318–
111, –112, –121, and –122 airplanes; Model
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; Model A320–111,
–211, –212, –214, –231, –232, and –233
airplanes; Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes;
certificated in any category; all serial
numbers.
(2) This AD requires revisions to certain
operator maintenance documents to include
new actions (e.g., inspections and/or Critical
Design Configuration Control Limitations
(CDCCLs). Compliance with these actions is
required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered,
or repaired in the areas addressed by these
inspections, the operator may not be able to
accomplish the inspections described in the
revisions. In this situation, to comply with 14
CFR 91.403(c), the operator must request
approval for an alternative method of
compliance (AMOC) according to paragraph
(l)(1) of this AD. The request should include
a description of changes to the required
actions that will ensure the continued
operational safety of the airplane.
(d) Subject
Air Transport Association (ATA) of
America Code 05, Periodic Inspections.
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(e) Reason
This AD was prompted by Airbus issuing
more restrictive maintenance requirements
and/or airworthiness limitations. We are
issuing this AD to prevent the potential of
ignition sources inside fuel tanks, which, in
combination with flammable fuel vapors,
could result in a fuel tank explosion and
consequent loss of the airplane.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Retained Revision of the Airworthiness
Limitations Section (ALS) To Incorporate
Fuel Maintenance and Inspection Tasks
This paragraph restates the requirements of
paragraph (f) of AD 2007–15–06 R1,
Amendment 39–16097 (74 FR 62219,
November 27, 2009). For Model A318–111
and –112 airplanes, and Model A319, A320,
and A321 airplanes: Within 3 months after
August 28, 2007 (the effective date of AD
2007–15–06), revise the ALS of the
Instructions for Continued Airworthiness to
incorporate Airbus A318/A319/A320/A321
ALS Part 5—Fuel Airworthiness Limitations,
dated February 28, 2006, as defined in Airbus
A318/A319/A320/A321 Fuel Airworthiness
Limitations, Document 95A.1931/05, Issue 1,
dated December 19, 2005 (approved by the
European Aviation Safety Agency (EASA) on
March 14, 2006), Section 1, ‘‘Maintenance/
Inspection Tasks;’’ or Airbus A318/A319/
A320/A321 Fuel Airworthiness Limitations,
Document 95A.1931/05, Issue 2, dated July 8,
2008 (approved by the EASA on December
19, 2008), Section 1, ’’Maintenance/
Inspection Tasks.’’ For all tasks identified in
Section 1 of Airbus A318/A319/A320/A321
Fuel Airworthiness Limitations, Document
95A.1931/05, Issue 1, dated December 19,
2005; or Issue 2, dated July 8, 2008; the
initial compliance times start from August
28, 2007, and the repetitive inspections must
be accomplished thereafter at the intervals
specified in Section 1, ’’Maintenance/
Inspection Tasks,’’ of Airbus A318/A319/
A320/A321 Fuel Airworthiness Limitations,
Document 95A.1931/05, Issue 1, dated
December 19, 2005; or Issue 2, dated July 8,
2008.
Note 1 to paragraph (g) of this AD: Airbus
Operator Information Telex (OIT) SE
999.0076/06, dated June 20, 2006, provides
guidance on identifying the applicable
sections of the Airbus A318/A319/A320/
A321 Airplane Maintenance Manual
necessary for accomplishing the tasks
specified in Section 1 ’’Maintenance/
Inspection Tasks,’’ of Airbus A318/A319/
A320/A321 Fuel Airworthiness Limitations,
Document 95A.1931/05, Issue 1, dated
December 19, 2005; or Issue 2, dated July 8,
2008.
(h) Retained Revision of the ALS To
Incorporate CDCCLs
This paragraph restates the requirements of
paragraph (g) of AD 2007–15–06 R1,
Amendment 39–16097 (74 FR 62219,
November 27, 2009). For Airbus Model
A318–111 and –112 airplanes, and Model
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Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules
A319, A320, and A321 airplanes: Within 12
months after August 28, 2007 (the effective
date of AD 2007–15–06), revise the ALS of
the Instructions for Continued Airworthiness
to incorporate Airbus A318/A319/A320/
A321 ALS Part 5–Fuel Airworthiness
Limitations, dated February 28, 2006, as
defined in Airbus A318/A319/A320/A321
Fuel Airworthiness Limitations, Document
95A.1931/05, Issue 1, dated December 19,
2005 (approved by the EASA on March 14,
2006), Section 2, ‘‘Critical Design
Configuration Control Limitations;’’ or
Airbus A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document
95A.1931/05, Issue 2, dated July 8, 2008
(approved by EASA on December 19, 2008),
Section 2, ’’Critical Design Configuration
Control Limitations.’’
(i) Retained No Alternative Inspections,
Inspection Intervals, or CDCCLs
(1) This paragraph restates the
requirements of paragraph (h) of AD 2007–
15–06 R1, Amendment 39–16097 (74 FR
62219, November 27, 2009). Except as
provided by paragraph (l) of this AD: After
accomplishing the actions specified in
paragraphs (g) and (h) of this AD, no
alternative inspections, inspection intervals,
or CDCCLs may be used.
(2) Notwithstanding any other maintenance
or operational requirements, components that
have been identified as airworthy or installed
on the affected airplanes before the revision
of the ALS, as required by paragraphs (g) and
(h) of this AD, do not need to be reworked
in accordance with the CDCCLs. However,
once the ALS has been revised, future
maintenance actions on these components
must be done in accordance with the
CDCCLs.
(j) Revise Maintenance Program
Within 6 months after the effective date of
this AD: Revise the maintenance program to
incorporate the new or revised tasks, life
limits, and CDCCLs specified in Airbus
A318/A319/A320/A321 Fuel Airworthiness
Limitations, Document 95A.1931/05, Issue 4,
dated August 26, 2010, except as required in
paragraph (j)(4) of this AD. The initial
compliance times and intervals are stated in
these documents, except as required in
paragraphs (j)(1) through (j)(4) of this AD, or
within 6 months after the effective date of
this AD, whichever occurs later. For certain
tasks, the compliance times depend on the
pre-modification and post-modification
status of the airplane. Incorporating the
requirements of this paragraph terminates the
corresponding requirements of paragraphs (g)
and (h) of this AD.
(1) For airplanes whose first flight occurred
before August 28, 2007 (the effective date of
AD 2007–15–06 R1, Amendment 39–16097
(74 FR 62219, November 27, 2009)), the first
accomplishment of tasks 281800–01–1,
Functional Check of Tank Vapour Seal and
Vent Drain System; and 281800–02–1,
Detailed Inspection of Vapour Seal; must be
performed no later than 11 months after the
effective date of this AD.
(2) The first accomplishment of Tasks
470000–01–1, Operational Check of DFSOV,
Dual Flapper Check Valves and NEA Line for
Leaks; 470000–02–1, Operational Check of
both Dual Flapper Check Valves for Leaks;
470000–03–1, Operational Check of Dual
Flapper Check Valves for Reverse Flow and
NEA Line for Leaks; 470000–04–1,
Operational Check of Dual Flapper Check
Valves for Reverse Flow; and 470000–05–1,
Remove Air Separation Module (ASM) and
Return to Vendor for Workshop Check; must
be calculated, in accordance with paragraphs
(j)(2)(i) or (j)(2)(ii) of this AD.
(i) From the airplane first flight for
airplanes on which Airbus modification
38062 or 38195 has been embodied in
production, or
(ii) From the in-service installation of the
fuel tank inerting system specified in Airbus
Service Bulletin A320–47–1001, Airbus
Service Bulletin A320–47–1002, Airbus
Service Bulletin A320–47–1003, Airbus
Service Bulletin A320–47–1004, Airbus
Service Bulletin A320–47–1006, or Airbus
Service Bulletin A320–47–1007.
(3) Although Airbus A318/A319/A320/
A321 Fuel Airworthiness Limitations,
Document 95A.1931/05, Issue 4, dated
32063
August 26, 2010, does not refer to Airbus
Service Bulletin A320–47–1006 and Airbus
Service Bulletin A320–47–1007, the tasks
apply as follows:
(i) Tasks 470000–01–1, Operational Check
of DFSOV, Dual Flapper Check Valves and
NEA Line for Leaks; and 470000–02–1,
Operational Check of both Dual Flapper
Check Valves for leaks; apply to airplanes
that have previously accomplished the
actions specified in Airbus Service Bulletin
A320–47–1007.
(ii) Task 470000–03–1, Operational Check
of Dual Flapper Check Valves for Reverse
Flow and NEA Line for Leaks; applies to
airplanes that have previously accomplished
the actions specified in Airbus Service
Bulletin A320–47–1006, and that have not
accomplished the actions specified in Airbus
Service Bulletin A320–47–1007.
(iii) Task 470000–04–1, Operational Check
of Dual Flapper Check Valves for Reverse
Flow; applies to airplanes in postmodification 38195 configuration and that
have not accomplished the actions specified
in Airbus Service Bulletin A320–47–1007.
(iv) Task 470000–05–1, Remove ASM and
return to Vendor for workshop check; applies
to airplanes that have previously
accomplished the actions specified in Airbus
Service Bulletin A320–47–1007, and are in
pre-modification 151529 configuration.
(4) Replace each ASM identified in table 1
of this AD in accordance with a method
approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA) (or its
delegated agent). The compliance time for the
replacement is before the accumulation of
27,000 flight hours (component time)—i.e.,
the life limitation.
Note 2 to paragraph (g)(4) of this AD:
Airbus A318/A319/A320/A321 Maintenance
Manual Task 47–10–43–920–001–A, Air
Separation Module Replacement, is an
additional source of guidance for
accomplishment of the removal and
replacement of the ASM.
TABLE 1—ASM REPLACEMENT
ASM Part No.
Affected airplane configuration
2060017–101 ..............................................................................................................................
2060017–102 ..............................................................................................................................
mstockstill on DSK4VPTVN1PROD with PROPOSALS
(k) No Alternative Actions Intervals, and/or
CDCCLs
After accomplishing the revisions required
by paragraph (j) of this AD, no alternative
actions (e.g., inspections), intervals, and/or
CDCCLs may be used other than those
specified in Airbus A318/A319/A320/A321
ALS Part 5—Fuel Airworthiness Limitations,
dated February 28, 2006, as defined in Airbus
A318/A319/A320/A321 Fuel Airworthiness
Limitations, Document 95A.1931/05, Issue 4,
VerDate Mar<15>2010
17:48 May 30, 2012
Jkt 226001
Post-modification 38062, or
Post-Airbus Service Bulletin A320–47–1002, or
Post-Airbus Service Bulletin A320–47–1004, or
Post-Airbus Service Bulletin A320–47–1007
Post-modification 152033, or
Post-Airbus Service Bulletin A320–47–1011
dated August 26, 2010, unless the actions,
intervals, and/or CDCCLs are approved as an
AMOC in accordance with the procedures
specified in paragraph (l)(1) of this AD.
(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, has the authority to
approve AMOCs for this AD, if requested
PO 00000
Frm 00026
Fmt 4702
Sfmt 4702
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–1405; fax (425)
227–1149. Information may be emailed to:
E:\FR\FM\31MYP1.SGM
31MYP1
32064
Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules
9-ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(m) Related Information
(1) Refer to MCAI EASA Airworthiness
Directive 2011–0155, dated August 25, 2011,
and the following service information, for
related information.
(i) Airbus A318/A319/A320/A321 ALS Part
5—Fuel Airworthiness Limitations, dated
February 28, 2006.
(ii) Airbus A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document
95A.1931/05, Issue 1, dated December 19,
2005.
(iii) A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document
95A.1931/05, Issue 2, dated July 8, 2008.
(iv) Airbus A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document
95A.1931/05, Issue 4, dated August 26, 2010.
(2) For service information identified in
this 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; email
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.
Issued in Renton, Washington, on May 18,
2012.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–13191 Filed 5–30–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
mstockstill on DSK4VPTVN1PROD with PROPOSALS
14 CFR Part 39
[Docket No. FAA–2012–0492; Directorate
Identifier 2010–NM–126–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 747 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
VerDate Mar<15>2010
17:48 May 30, 2012
Jkt 226001
Notice of proposed rulemaking
(NPRM).
ACTION:
We propose to supersede an
existing airworthiness directive (AD)
that applies to certain The Boeing
Company Model 747 airplanes. The
existing AD currently requires repetitive
visual inspections around the bushings
of the wing landing gear (WLG) beam
outboard end fittings for corrosion, and
rework if necessary; and ultrasonic
inspections for cracks of the outboard
end fittings of the WLG support beams,
and rework if necessary. Since we
issued that AD, there have been new
reports of corrosion damage to the end
fittings of the WLG support beams, and
one report of subsequent cracking in the
end fittings. This proposed AD would
add airplanes and repetitive inspections
of the outboard end fitting of the left
and right WLG support beams for cracks
and corrosion, and corrective actions if
necessary. We are proposing this AD to
detect and correct corrosion and
subsequent cracking in the outboard end
fittings, which could result in
separation of the fitting and damage to
adjacent flight control cables and
hydraulic systems and consequent
reduced controllability of the airplane.
DATES: We must receive comments on
this proposed AD by July 16, 2012.
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 W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1, fax 206–766–5680; email
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
SUMMARY:
PO 00000
Frm 00027
Fmt 4702
Sfmt 4702
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Bill
Ashforth, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, Washington
98057–3356; phone: (425) 917–6432;
fax: (425) 917–6590; email:
bill.ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2012–0492; Directorate Identifier
2010–NM–126–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On July 7, 1989, we issued AD 89–15–
07, amendment 39–6267 (54 FR 30009,
July 18, 1989), for certain Model 747
airplanes. That AD requires visual
inspections around the bushings of the
wing landing gear for corrosion, and
repair if necessary, and ultrasonic
inspections for cracks of the outboard
end fittings of the WLG support beams,
and overhaul if necessary. That AD
resulted from a report of a fracture of the
outboard end fitting of a left WLG beam.
We issued that AD to prevent failure of
the outboard end fitting of a WLG beam
with possible damage to control cables
or hydraulic lines in the area of the
landing gear beam.
E:\FR\FM\31MYP1.SGM
31MYP1
]]>Agencies
[Federal Register Volume 77, Number 105 (Thursday, May 31, 2012)]
[Proposed Rules]
[Pages 32060-32064]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-13191]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0493; Directorate Identifier 2011-NM-180-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
[[Page 32061]]
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) for all Airbus Model A318-111 and -112 airplanes; and all Model
A319, A320, and A321 series airplanes. The existing AD currently
requires revising the Airworthiness Limitations Section (ALS) of the
Instructions for Continued Airworthiness to incorporate new limitations
for fuel tank systems. Since we issued that AD, Airbus has issued more
restrictive maintenance requirements and/or airworthiness limitations.
This proposed AD would revise the maintenance program to incorporate
revised fuel maintenance and inspection tasks, and add airplanes to the
applicability. We are proposing this AD to prevent the potential of
ignition sources inside fuel tanks, which, in combination with
flammable fuel vapors, could result in a fuel tank explosion and
consequent loss of the airplane.
DATES: We must receive comments on this proposed AD by July 16, 2012.
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 W12-140, 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; email 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: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-1405; 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-2012-0493;
Directorate Identifier 2011-NM-180-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On November 16, 2009, we issued AD 2007-15-06 R1, Amendment 39-
16097 (74 FR 62219, November 27, 2009). That AD required actions
intended to address an unsafe condition on the products listed above.
Since we issued AD 2007-15-06 R1, Amendment 39-16097 (74 FR 62219,
November 27, 2009), Airbus has issued A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document 95A.1931/05, Issue 4, dated August
26, 2010. The European Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Community, has
issued EASA Airworthiness Directive 2011-0155, dated August 25, 2011
(referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:
The airworthiness limitations are currently published in the
Airbus A318/A319/A320/A321 Airworthiness Limitations Section (ALS).
The Fuel Airworthiness Limitations (FAL) are specified in Airbus
A318/A319/A320/A321 FAL Document reference 95A.1931/05, which is
approved by the European Aviation Safety Agency (EASA) and
referenced in the Airbus A318/A319/A320/A321 ALS Part 5.
The issue 4 of Airbus A318/A319/A320/A321 FAL Document
introduces more restrictive maintenance requirements and/or
airworthiness limitations. Failure to comply with these more
restrictive maintenance requirements and airworthiness limitations
contained in this document constitutes an unsafe condition.
This [EASA] AD retains the requirement of EASA AD 2006-0203,
which is superseded, and requires the implementation of the new or
more restrictive maintenance requirements and/or airworthiness
limitations as specified in Airbus A318/A319/A320/A321 FAL Document
issue 4.
We are proposing this AD to prevent the potential of ignition sources
inside fuel tanks, which, in combination with flammable fuel vapors,
could result in a fuel tank explosion and consequent loss of the
airplane. You may obtain further information by examining the MCAI in
the AD docket.
Relevant Service Information
Airbus has issued A318/A319/A320/A321 Fuel Airworthiness
Limitations, Document 95A.1931/05, Issue 4, dated August 26, 2010. The
actions described in this service information are intended to correct
the unsafe condition identified in the MCAI.
Explanation of Changes Made to This NPRM
We have changed Note 1 and Note 2 of the restated requirements of
AD 2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27, 2009),
to lettered paragraphs (i) and (j), respectively, in this NPRM. These
changes do not add any additional burden upon the public than was
required in the existing AD.
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.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would
[[Page 32062]]
affect about 745 products of U.S. registry.
The actions that are required by AD 2007-15-06 R1, Amendment 39-
16097 (74 FR 62219, November 27, 2009), and retained in this proposed
AD take about 2 work-hours per product, at an average labor rate of $85
per work hour. Required parts cost about $0 per product. Based on these
figures, the estimated cost of the currently required actions is $170
per product.
We estimate that it would take about 2 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of the proposed AD on U.S. operators to be $126,650, or $170
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);
3. Will not affect intrastate aviation in Alaska; and
4. 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 airworthiness directive
(AD) 2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27,
2009), and adding the following new AD:
Airbus: Docket No. FAA-2012-0493; Directorate Identifier 2011-NM-
180-AD.
(a) Comments Due Date
We must receive comments by July 16, 2012.
(b) Affected ADs
This AD supersedes AD 2007-15-06 R1, Amendment 39-16097 (74 FR
62219, November 27, 2009).
(c) Applicability
(1) This AD applies to Airbus Model A318-111, -112, -121, and -
122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232,
and -233 airplanes; Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes; certificated in any category; all serial
numbers.
(2) This AD requires revisions to certain operator maintenance
documents to include new actions (e.g., inspections and/or Critical
Design Configuration Control Limitations (CDCCLs). Compliance with
these actions is required by 14 CFR 91.403(c). For airplanes that
have been previously modified, altered, or repaired in the areas
addressed by these inspections, the operator may not be able to
accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance (AMOC)
according to paragraph (l)(1) of this AD. The request should include
a description of changes to the required actions that will ensure
the continued operational safety of the airplane.
(d) Subject
Air Transport Association (ATA) of America Code 05, Periodic
Inspections.
(e) Reason
This AD was prompted by Airbus issuing more restrictive
maintenance requirements and/or airworthiness limitations. We are
issuing this AD to prevent the potential of ignition sources inside
fuel tanks, which, in combination with flammable fuel vapors, could
result in a fuel tank explosion and consequent loss of the airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Retained Revision of the Airworthiness Limitations Section (ALS) To
Incorporate Fuel Maintenance and Inspection Tasks
This paragraph restates the requirements of paragraph (f) of AD
2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27, 2009).
For Model A318-111 and -112 airplanes, and Model A319, A320, and
A321 airplanes: Within 3 months after August 28, 2007 (the effective
date of AD 2007-15-06), revise the ALS of the Instructions for
Continued Airworthiness to incorporate Airbus A318/A319/A320/A321
ALS Part 5--Fuel Airworthiness Limitations, dated February 28, 2006,
as defined in Airbus A318/A319/A320/A321 Fuel Airworthiness
Limitations, Document 95A.1931/05, Issue 1, dated December 19, 2005
(approved by the European Aviation Safety Agency (EASA) on March 14,
2006), Section 1, ``Maintenance/Inspection Tasks;'' or Airbus A318/
A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05,
Issue 2, dated July 8, 2008 (approved by the EASA on December 19,
2008), Section 1, ''Maintenance/Inspection Tasks.'' For all tasks
identified in Section 1 of Airbus A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document 95A.1931/05, Issue 1, dated
December 19, 2005; or Issue 2, dated July 8, 2008; the initial
compliance times start from August 28, 2007, and the repetitive
inspections must be accomplished thereafter at the intervals
specified in Section 1, ''Maintenance/Inspection Tasks,'' of Airbus
A318/A319/A320/A321 Fuel Airworthiness Limitations, Document
95A.1931/05, Issue 1, dated December 19, 2005; or Issue 2, dated
July 8, 2008.
Note 1 to paragraph (g) of this AD: Airbus Operator Information
Telex (OIT) SE 999.0076/06, dated June 20, 2006, provides guidance
on identifying the applicable sections of the Airbus A318/A319/A320/
A321 Airplane Maintenance Manual necessary for accomplishing the
tasks specified in Section 1 ''Maintenance/Inspection Tasks,'' of
Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations, Document
95A.1931/05, Issue 1, dated December 19, 2005; or Issue 2, dated
July 8, 2008.
(h) Retained Revision of the ALS To Incorporate CDCCLs
This paragraph restates the requirements of paragraph (g) of AD
2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27, 2009).
For Airbus Model A318-111 and -112 airplanes, and Model
[[Page 32063]]
A319, A320, and A321 airplanes: Within 12 months after August 28,
2007 (the effective date of AD 2007-15-06), revise the ALS of the
Instructions for Continued Airworthiness to incorporate Airbus A318/
A319/A320/A321 ALS Part 5-Fuel Airworthiness Limitations, dated
February 28, 2006, as defined in Airbus A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document 95A.1931/05, Issue 1, dated
December 19, 2005 (approved by the EASA on March 14, 2006), Section
2, ``Critical Design Configuration Control Limitations;'' or Airbus
A318/A319/A320/A321 Fuel Airworthiness Limitations, Document
95A.1931/05, Issue 2, dated July 8, 2008 (approved by EASA on
December 19, 2008), Section 2, ''Critical Design Configuration
Control Limitations.''
(i) Retained No Alternative Inspections, Inspection Intervals, or
CDCCLs
(1) This paragraph restates the requirements of paragraph (h) of
AD 2007-15-06 R1, Amendment 39-16097 (74 FR 62219, November 27,
2009). Except as provided by paragraph (l) of this AD: After
accomplishing the actions specified in paragraphs (g) and (h) of
this AD, no alternative inspections, inspection intervals, or CDCCLs
may be used.
(2) Notwithstanding any other maintenance or operational
requirements, components that have been identified as airworthy or
installed on the affected airplanes before the revision of the ALS,
as required by paragraphs (g) and (h) of this AD, do not need to be
reworked in accordance with the CDCCLs. However, once the ALS has
been revised, future maintenance actions on these components must be
done in accordance with the CDCCLs.
(j) Revise Maintenance Program
Within 6 months after the effective date of this AD: Revise the
maintenance program to incorporate the new or revised tasks, life
limits, and CDCCLs specified in Airbus A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document 95A.1931/05, Issue 4, dated
August 26, 2010, except as required in paragraph (j)(4) of this AD.
The initial compliance times and intervals are stated in these
documents, except as required in paragraphs (j)(1) through (j)(4) of
this AD, or within 6 months after the effective date of this AD,
whichever occurs later. For certain tasks, the compliance times
depend on the pre-modification and post-modification status of the
airplane. Incorporating the requirements of this paragraph
terminates the corresponding requirements of paragraphs (g) and (h)
of this AD.
(1) For airplanes whose first flight occurred before August 28,
2007 (the effective date of AD 2007-15-06 R1, Amendment 39-16097 (74
FR 62219, November 27, 2009)), the first accomplishment of tasks
281800-01-1, Functional Check of Tank Vapour Seal and Vent Drain
System; and 281800-02-1, Detailed Inspection of Vapour Seal; must be
performed no later than 11 months after the effective date of this
AD.
(2) The first accomplishment of Tasks 470000-01-1, Operational
Check of DFSOV, Dual Flapper Check Valves and NEA Line for Leaks;
470000-02-1, Operational Check of both Dual Flapper Check Valves for
Leaks; 470000-03-1, Operational Check of Dual Flapper Check Valves
for Reverse Flow and NEA Line for Leaks; 470000-04-1, Operational
Check of Dual Flapper Check Valves for Reverse Flow; and 470000-05-
1, Remove Air Separation Module (ASM) and Return to Vendor for
Workshop Check; must be calculated, in accordance with paragraphs
(j)(2)(i) or (j)(2)(ii) of this AD.
(i) From the airplane first flight for airplanes on which Airbus
modification 38062 or 38195 has been embodied in production, or
(ii) From the in-service installation of the fuel tank inerting
system specified in Airbus Service Bulletin A320-47-1001, Airbus
Service Bulletin A320-47-1002, Airbus Service Bulletin A320-47-1003,
Airbus Service Bulletin A320-47-1004, Airbus Service Bulletin A320-
47-1006, or Airbus Service Bulletin A320-47-1007.
(3) Although Airbus A318/A319/A320/A321 Fuel Airworthiness
Limitations, Document 95A.1931/05, Issue 4, dated August 26, 2010,
does not refer to Airbus Service Bulletin A320-47-1006 and Airbus
Service Bulletin A320-47-1007, the tasks apply as follows:
(i) Tasks 470000-01-1, Operational Check of DFSOV, Dual Flapper
Check Valves and NEA Line for Leaks; and 470000-02-1, Operational
Check of both Dual Flapper Check Valves for leaks; apply to
airplanes that have previously accomplished the actions specified in
Airbus Service Bulletin A320-47-1007.
(ii) Task 470000-03-1, Operational Check of Dual Flapper Check
Valves for Reverse Flow and NEA Line for Leaks; applies to airplanes
that have previously accomplished the actions specified in Airbus
Service Bulletin A320-47-1006, and that have not accomplished the
actions specified in Airbus Service Bulletin A320-47-1007.
(iii) Task 470000-04-1, Operational Check of Dual Flapper Check
Valves for Reverse Flow; applies to airplanes in post-modification
38195 configuration and that have not accomplished the actions
specified in Airbus Service Bulletin A320-47-1007.
(iv) Task 470000-05-1, Remove ASM and return to Vendor for
workshop check; applies to airplanes that have previously
accomplished the actions specified in Airbus Service Bulletin A320-
47-1007, and are in pre-modification 151529 configuration.
(4) Replace each ASM identified in table 1 of this AD in
accordance with a method approved by either the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the European Aviation Safety Agency (EASA) (or its delegated
agent). The compliance time for the replacement is before the
accumulation of 27,000 flight hours (component time)--i.e., the life
limitation.
Note 2 to paragraph (g)(4) of this AD: Airbus A318/A319/A320/
A321 Maintenance Manual Task 47-10-43-920-001-A, Air Separation
Module Replacement, is an additional source of guidance for
accomplishment of the removal and replacement of the ASM.
Table 1--ASM Replacement
----------------------------------------------------------------------------------------------------------------
ASM Part No. Affected airplane configuration
----------------------------------------------------------------------------------------------------------------
2060017-101............................ Post-modification 38062, or
Post-Airbus Service Bulletin A320-47-1002, or
Post-Airbus Service Bulletin A320-47-1004, or
Post-Airbus Service Bulletin A320-47-1007
2060017-102............................ Post-modification 152033, or
Post-Airbus Service Bulletin A320-47-1011
----------------------------------------------------------------------------------------------------------------
(k) No Alternative Actions Intervals, and/or CDCCLs
After accomplishing the revisions required by paragraph (j) of
this AD, no alternative actions (e.g., inspections), intervals, and/
or CDCCLs may be used other than those specified in Airbus A318/
A319/A320/A321 ALS Part 5--Fuel Airworthiness Limitations, dated
February 28, 2006, as defined in Airbus A318/A319/A320/A321 Fuel
Airworthiness Limitations, Document 95A.1931/05, Issue 4, dated
August 26, 2010, unless the actions, intervals, and/or CDCCLs are
approved as an AMOC in accordance with the procedures specified in
paragraph (l)(1) of this AD.
(l) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, has the authority to approve AMOCs
for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the International
Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-1405; fax (425) 227-1149. Information may be emailed to:
[[Page 32064]]
9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC,
notify your appropriate principal inspector, or lacking a principal
inspector, the manager of the local flight standards district
office/certificate holding district office. The AMOC approval letter
must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(m) Related Information
(1) Refer to MCAI EASA Airworthiness Directive 2011-0155, dated
August 25, 2011, and the following service information, for related
information.
(i) Airbus A318/A319/A320/A321 ALS Part 5--Fuel Airworthiness
Limitations, dated February 28, 2006.
(ii) Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations,
Document 95A.1931/05, Issue 1, dated December 19, 2005.
(iii) A318/A319/A320/A321 Fuel Airworthiness Limitations,
Document 95A.1931/05, Issue 2, dated July 8, 2008.
(iv) Airbus A318/A319/A320/A321 Fuel Airworthiness Limitations,
Document 95A.1931/05, Issue 4, dated August 26, 2010.
(2) For service information identified in this 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; email 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.
Issued in Renton, Washington, on May 18, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-13191 Filed 5-30-12; 8:45 am]
BILLING CODE 4910-13-P
