Airworthiness Directives; Airbus Airplanes, 51117-51121 [2013-20251]
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Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Proposed Rules
Eurocopter or UTC Actuation Systems/
Goodrich Actuation Systems.
Accordingly, we have included all costs
in our cost estimate.
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 proposed
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
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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, 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 to the extent that it justifies
making a regulatory distinction; 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 an economic 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,
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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 adding
the following new airworthiness
directive (AD):
■
Eurocopter France (Eurocopter) Helicopters:
Docket No. FAA–2013–0737; Directorate
Identifier 2012–SW–111–AD.
(a) Applicability
This AD applies to the following model
helicopters, certificated in any category, with
a part-numbered main servo-control listed
below: overhauled or repaired by UTC
Actuation Systems/Goodrich Actuation
Systems between June 1, 2008, and
September 15, 2012, inclusive; or with a
serial number listed in Appendix 1 of
Eurocopter Emergency Alert Service Bulletin
Nos. 67.00.45 or 67.19, both Revision 1, and
both dated December 5, 2012 (EASB):
(1) Model AS332C, AS332L, AS332L1, and
AS332L2 helicopters with main servocontrol, part number (P/N) SC7202, SC7202–
(all dash numbers), SC7203, SC7203–(all
dash numbers), SC7221, or SC7221–(all dash
numbers), installed; and
(2) Model SA330J helicopters with main
servo-control P/N SC7111, SC7111–(all dash
numbers) SC7112, or SC7112–(all dash
numbers), installed.
(b) Unsafe Condition
This AD defines the unsafe condition as
missing crimping on a ball joint of a main
servo-control end-fitting. This condition
could result in failure of a main servo-control
upper end fitting, failure of the flight
controls, and loss of control of the helicopter.
51117
(ii) Using a light source, inspect the ball
joint of the lower end-fitting of the main
servo-control for crimping in accordance
with Detail A and Detail B, Figure 1, of the
EASB applicable to your model helicopter. If
the lower ball joint is not crimped, crimp the
ball joint.
(2) Prior to installing any servo-control that
is affected by this AD, perform the required
actions in accordance with paragraphs (e)(1)
of this AD.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Matt Wilbanks,
Aviation Safety Engineer, Rotorcraft
Certification Office, Rotorcraft Directorate,
FAA, 2601 Meacham Blvd., Fort Worth,
Texas 76137; telephone (817) 222–5110;
email matt.wilbanks@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2012–0248, dated November 20, 2012.
You may view the EASA AD on the Internet
at https://www.regulations.gov in Docket No.
FAA–2013–0737.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6730, Rotor Flight Control—Rotorcraft
Servo System.
Issued in Fort Worth, Texas, on August 12,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
(c) Comments Due Date
We must receive comments by October 21,
2013.
[FR Doc. 2013–20312 Filed 8–19–13; 8:45 am]
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
DEPARTMENT OF TRANSPORTATION
(e) Required Actions
(1) Within 85 hours time-in-service (TIS):
(i) Using a light source, inspect the ball
joint of the upper end-fitting of the main
servo control for crimping in accordance
with Detail A and Detail B, Figure 1, of the
EASB applicable to your model helicopter.
(A) If the upper ball joint is not crimped
and the ball joint slips a distance of 1
millimeter (mm) or greater, replace the servocontrol with an airworthy servo-control.
(B) If the upper ball joint is not crimped
and the ball joint slips a distance of less than
1mm, either crimp the ball joint or replace
the servo-control with an airworthy servocontrol.
[Docket No. FAA–2013–0698; Directorate
Identifier 2012–NM–136–AD]
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BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
airworthiness directive (AD) 2006–06–
14, that applies to certain Airbus Model
SUMMARY:
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A318–100 and A319–100 series
airplanes, A320–111 airplanes, A320–
200 series airplanes, and A321–100 and
A321–200 series airplanes. AD 2006–
06–14 requires operators to review the
airplane’s maintenance records to
determine the part numbers of the
magnetic fuel level indicators (MFLIs) of
the wing fuel tanks, and related
investigative and corrective actions if
necessary. Since we issued AD 2006–
06–14, we received information that the
related investigative actions of the
existing AD are not fully effective and
that an affected MFLI could still be
installed on airplanes on which the
related investigative actions were
accomplished. This proposed AD would
also require an inspection (improved
method) to determine the part numbers
of the MFLIs, and, if necessary,
replacement of the MFLI or repair. We
are proposing this AD to prevent an
ignition source in the wing fuel tank in
the event of a lightning strike, which
could result in a fire or explosion.
DATES: We must receive comments on
this proposed AD by October 4, 2013.
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, WA. 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
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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, WA
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–2013–0698; Directorate Identifier
2012–NM–136–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 March 10, 2006, we issued AD
2006–06–14, Amendment 39–14523 (71
FR 15023, March 27, 2006), (‘‘AD 2006–
06–14’’). That AD required actions
intended to address an unsafe condition
on Airbus Model A318–111 and –112
airplanes; Model A319–111, –112, –113,
–114, –115, –131, –132, and –133
airplanes; A320–111 airplanes; Model
A320–211, –212, –214, –231, –232, and
–233 airplanes; Model A321–111, –112,
and –131 airplanes; and Model A321–
211, –212, –213, –231, and –232
airplanes.
Since we issued AD 2006–06–14, the
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2012–0119,
dated July 4, 2012 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
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In 2005, several in-service occurrences
were reported of finding wear and/or
detachment of the top stop of magnetic fuel
level indicators (MFLI), either observed
during tank maintenance activities, or on
MFLI returned to the MFLI manufacturer.
The investigation results indicated that the
wear of the top stop retaining ‘S’ shaped wire
had been caused by repetitive impact with
the float, resulting in complete detachment of
the top stop.
This condition, if not detected and
corrected, could lead an MFLI top stop to
come into contact with a probe, which could,
in the event of a lightning strike, create an
ignition source in the fuel tank vapour space,
possibly resulting in a fuel tank explosion
and consequent loss of the aeroplane.
DGAC France issued AD F–2005–108
(EASA approval 2005–6026) [https://
ad.easa.europa.eu/ad/F–2005–108]
[corresponding FAA AD 2006–06–14] to
require identification (by inspection) and
replacement of the affected metallic MFLI
(3508802-xx series with the ‘S’ shaped
retaining wire) with a metallic MFLI with the
top stop retained by a ‘trapped wire’, or with
a composite MFLI.
Since that [French] AD was issued, it has
been identified that the inspection procedure
(visual check) detailed in Airbus Service
Bulletin (SB) A320–28–1138 was not fully
effective, and that affected MFLI could still
be fitted on aeroplanes which have passed
the inspection in accordance with the
instructions of this SB.
For the reasons described above, this
[EASA] AD, which supersedes DGAC France
AD F–2005–108, requires a one-time
inspection (improved method) to identify the
type of MFLI installed and, depending on
findings, replacement or repair, as
applicable. This [EASA] AD also prohibits
the installation of the affected MFLI on any
aeroplane as replacement parts.
The repair may also include locating
and removing any missing top stop, and
inspecting for any damage caused to the
fuel tank by a missing top stop. You
may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Service Bulletin
A320–28–1209, dated December 12,
2011. The actions described in this
service information are intended to
correct the unsafe condition identified
in the MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
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condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This AD and the
MCAI or Service Information
Where the MCAI states in the
compliance time ‘‘whichever occurs
later,’’ this proposed AD would require
‘‘whichever occurs earlier.’’ We have
determined that this compliance time
would address the unsafe condition in
a more timely manner. We considered
the manufacturer’s recommendation,
and the overall risk to the fleet,
including the severity of the failure and
the likelihood of the failure’s
occurrence. Therefore, we find that a
compliance time of 49,000 flight hours
after May 1, 2006, or at the next
scheduled fuel tank entry after the
effective date of this AD, whichever
occurs first, to complete the required
actions to be warranted.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 755 products of U.S.
registry.
ESTIMATED COSTS
Action
Labor cost
Parts numbers review [retained actions Between 1 and 8
from AD 2006–06–14, Amendment 39–
work-hours × $85
14523 (71 FR 15023, March 27, 2006)].
per hour = Between $85 and
$680.
Inspection for part numbers [new pro- 21 work-hours ×
posed action].
$85 per hour =
$1,785.
We estimate the following costs to do
any necessary replacement or repair that
would be required based on the results
Parts cost
Cost per product
Cost on U.S. operators
None ......
Between $85 and
$680.
Between $64,175 and $513,400
$0 ...........
$1,785 ....................
$1,347,675
of the proposed inspection. We have no
way of determining the number of
aircraft that might need the replacement
or repair:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per
product
Replace or repair ..........................................................
4 work-hours × $85 per hour = $340 ...........................
$0
$340
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According to the manufacturer, some
of the costs of this proposed AD may be
covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all costs in our
cost estimate.
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 proposed
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.
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Regulatory Findings
List of Subjects in 14 CFR Part 39
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.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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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)
2006–06–14, Amendment 39–14523 (71
FR 15023, March 27, 2006), and adding
the following new AD:
■
Airbus: Docket No. FAA–2013–0698;
Directorate Identifier 2012–NM–136–AD.
(a) Comments Due Date
We must receive comments by October 4,
2013.
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(b) Affected ADs
This AD supersedes AD 2006–06–14,
Amendment 39–14523 (71 FR 15023, March
27, 2006).
(c) Applicability
This AD applies to Airbus Model A318–
111, A318–112, A318–121, A318–122, A319–
111, A319–112, A319–113, A319–114, A319–
115, A319–131, A319–132, A319–133, A320–
111, A320–211, A320–212, A320–214, A320–
215, A320–216, 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.
(d) Subject
Air Transport Association (ATA) of
America Code 28: Fuel.
(e) Reason
This AD was prompted by a report of
several in-service incidents of wear and
detachment of the top-stops from magnetic
fuel level indicators (MFLI) in a wing fuel
tank. We are issuing this AD to prevent an
ignition source in the wing fuel tank in the
event of a lighting strike, which could result
in a fire or explosion.
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(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 Review of Airplane
Maintenance Records/Investigative and
Corrective Actions
This paragraph restates the requirements of
paragraph (f) of AD 2006–06–14, Amendment
39–14523 (71 FR 15023, March 27, 2006). For
Model A318–111 and –112 airplanes; Model
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; A320–111
airplanes; Model A320–211, –212, –214,
–231, –232, and –233 airplanes; Model
A321–111, –112, and –131 airplanes; and
Model A321–211, –212, –213, –231, and –232
airplanes; on which Airbus Modification
27496 has not been installed in production:
Within 65 months or 6,500 flight hours after
May 1, 2006 (the effective date of AD 2006–
06–14), whichever is first, review the
airplane’s maintenance records to determine
the part number (P/N) of each MFLI of the
wing fuel tanks in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–28–1138, dated March
18, 2005. If the P/N cannot be identified, or
the P/N is identified in the ‘‘old P/N’’ column
of the table in paragraph 1.L.,
‘‘Interchangeability/Mixability,’’ of Airbus
Service Bulletin A320–28–1138, dated March
18, 2005, before further flight, do the
applicable related investigative and
corrective actions by accomplishing all of the
actions in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–28–1138, dated March
18, 2005.
(h) Retained Parts Installation Prohibition
This paragraph restates the requirements
paragraph (g) of AD 2006–06–14,
Amendment 39–14523 (71 FR 15023, March
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27, 2006). For Model A318–111 and –112
airplanes; Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes;
A320–111 airplanes; Model A320–211, –212,
–214, –231, –232, and –233 airplanes; Model
A321–111, –112, and –131 airplanes; and
Model A321–211, –212, –213, –231, and –232
airplanes; on which Airbus Modification
27496 has not been installed in production:
As of May 1, 2006 (the effective date of AD
2006–06–14), no person may install on any
airplane any MFLI of the wing fuel tanks
with a P/N identified in the ‘‘old P/N’’
column of the table in paragraph 1.L.,
‘‘Interchangeability/Mixability,’’ of Airbus
Service Bulletin A320–28–1138, dated March
18, 2005.
(i) New Requirement of This AD: Inspection
For all airplanes, except as provided by
paragraph (k) of this AD: At the next
scheduled fuel tank entry after the effective
date of this AD, or within 49,000 flight hours
after May 1, 2006 (the effective date of AD
2006–06–14, Amendment 39–14523 (71 FR
15023, March 27, 2006), whichever occurs
first, perform a special detailed inspection of
the wing tank to determine which type of
magnetic fuel level indicators (MFLI) are
installed, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–28–1209, dated
December 12, 2011. A review of airplane
maintenance records is acceptable in lieu of
this inspection, if the part number and the
type of the installed MFLI can be
conclusively determined from that review.
Paragraphs (i)(1) through (i)(11) of this AD
identify the affected MLFI part numbers.
(1) 3508802–24
(2) 3508802–25
(3) 3508802–26
(4) 3508802–27
(5) 3508802–28
(6) 3508802–34
(7) 3508802–39
(8) 3508802–74
(9) 3508802–75
(10) 3508802–76
(11) 3508802–91
Note 1 to paragraph (i) of this AD: The
affected MFLI have the ‘S’-shaped lock-wire
design.
(j) New Requirement of This AD:
Replacement or Repair
If, during the inspection required by
paragraph (i) of this AD, a MFLI with the ‘S’
shaped lock-wire design (Part Number (P/N)
listed in paragraphs (i)(1) through (i)(11) of
this AD) is found, then at the next scheduled
fuel tank entry after the effective date of this
AD, or within 49,000 flight hours after May
1, 2006 (the effective date of AD 2006–06–14,
Amendment 39–14523 (71 FR 15023, March
27, 2006), whichever occurs first, replace the
affected MFLI with a serviceable part and
accomplish the corrective actions (repair), as
applicable, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–28–1209, dated
December 12, 2011. For the purpose of this
AD, a serviceable part is a composite MFLI,
or a metallic MFLI with the top stop retained
by a ‘trapped wire,’ as applicable to the
location identified in Table 1 of paragraph (j)
of this AD.
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TABLE 1 OF PARAGRAPH (J) OF THIS
AD—METALLIC MFLI WITH THE TOP
STOP RETAINED BY A ‘TRAPPED
WIRE,’ INCLUDING APPLICABLE LOCATION (FIN)
MFLI P/N
3508802–35
3508802–36
3508802–37
3508802–38
Applicable location (FIN)
56/57QM
58/59QM
60/61QM
62/63QM
(k) New Requirement of This AD: Exception
for Paragraph (i) of This AD
Airplanes on which Airbus modification
(mod) 27496 has been embodied in
production, and on which no wing tank
MFLI replacement with a part number listed
in paragraph (i)(1) through (i)(11) of this AD
has been made since first flight, are not
affected by the requirement of paragraph (i)
of this AD.
(l) New Requirement of This AD: Parts
Installation Prohibition
As of the effective date of this AD, do not
install on any airplane a MFLI with a part
number listed in paragraph (i)(1) through
(i)(11) of this AD.
(m) Other FAA AD Provisions
The following provisions also apply to
This AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
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, WA 98057–3356;
telephone (425) 227–1405; fax (425) 227–
1149. Information may be emailed to: M-116AMOC-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 its delegated agent, or by the Design
Approval Holder with a State of Design
Authority’s design organization approval).
For a repair method to be approved, the
repair approval must specifically refer to this
AD. You are required to assure the product
is airworthy before it is returned to service.
(n) Special Flight Permits
Special flight permits, as described in
Section 21.197 and Section 21.199 of the
E:\FR\FM\20AUP1.SGM
20AUP1
Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Proposed Rules
Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency (EASA)
Airworthiness Directive 2012–0119, dated
July 4, 2012, for related information, which
can be found in the AD docket on the
Internet at https://www.regulations.gov.
(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, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on August
9, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–20251 Filed 8–19–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this AD, contact Piper Aircraft, Inc.,
2926 Piper Drive, Vero Beach, Florida
32960; telephone: (772) 567–4361; fax:
(772) 978–6573; email:
customer.service@piper.com; Internet:
www.piper.com/home/pages/
Publications.cfm. You may review
copies of the referenced service
information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA,
call (816) 329–4148.
ADDRESSES:
Federal Aviation Administration
Examining the AD Docket
14 CFR Part 39
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Gary
Wechsler, Aerospace Engineer, Atlanta
Aircraft Certification Office, FAA, 1701
Columbia Avenue, College Park, Georgia
30337; telephone: (404) 474–5575; fax:
(404) 474–5606; email: gary.wechsler@
faa.gov.
[Docket No. FAA–2013–0742; Directorate
Identifier 2013–CE–012–AD]
RIN 2120–AA64
Airworthiness Directives; Piper
Aircraft, Inc.
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to certain Piper Aircraft,
Inc. Models PA–28–140, PA–28–150,
PA–28–160, PA–28–180, PA–28R–180,
and PA–28R–200 airplanes. AD 71–21–
08, Amendment 39–1312 (36 FR 19572,
October 8, 1971) currently requires
replacement of the fuel selector valve
cover. Since we issued AD 71–21–08, it
has been found that a similar fuel
selector valve issue exists in additional
serial numbered airplanes not identified
in the existing AD. This proposed AD
would add additional airplanes to the
AD’s applicability section and changes
the compliance time of the required
actions. We are proposing this AD to
correct the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by October 4, 2013.
sroberts on DSK5SPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Mar<15>2010
17:51 Aug 19, 2013
Jkt 229001
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–2013–0742; Directorate Identifier
2013–CE–012–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
PO 00000
Frm 00024
Fmt 4702
Sfmt 4702
51121
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 September 29, 1971, we issued AD
71–21–08, Amendment 39–1312 (36 FR
19572, October 8, 1971), for certain
Piper Aircraft, Inc. Models PA–28–140,
PA–28–180, PA–28R–180, and PA–28R–
200 airplanes. That AD requires a
replacement of the fuel selector valve
cover to prevent possible binding of the
fuel selector handle.
Actions Since Existing AD Was Issued
Since we issued AD 71–21–08,
Amendment 39–1312 (36 FR 19572,
October 8, 1971), a safety event in 2011
caused the loss of a Model PA–28–180C
airplane and the serious injury to one
occupant. A subsequent FAA
investigation revealed eight additional
PA–28 series events dating from 1999 to
the present were the result of a similar
fuel selector valve assembly issue.
Additionally, the FAA was unable to
determine and locate records of
notification when Piper Service Letter
(SL) 590, dated May 25, 1972, and Piper
Service Bulletin (SB) 840, dated June 19,
1986, were released indicating a similar
fuel selector valve issue existed in
additional serial numbered airplanes
not identified in AD 71–21–08.
Although reliable FAA records do not
exist for events prior to 1995, it is likely
that the AD and Piper service
information referenced above was
released due to the frequency of similar
events occurring during the periods in
which the documents were released.
Piper has indicated the majority of the
airplanes added to the applicability of
this NPRM have likely already complied
with the proposed action.
Relevant Service Information
The 2011 safety event prompted us to
review the Piper Aircraft, Inc. service
information history, specifically Piper
Mandatory Service Bulletin No. 840,
dated June 19, 1986. The service
information describes applicability and
where to find procedures for
replacement of the fuel selector valve
cover.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
E:\FR\FM\20AUP1.SGM
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]]>Agencies
[Federal Register Volume 78, Number 161 (Tuesday, August 20, 2013)]
[Proposed Rules]
[Pages 51117-51121]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-20251]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0698; Directorate Identifier 2012-NM-136-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede airworthiness directive (AD) 2006-06-
14, that applies to certain Airbus Model
[[Page 51118]]
A318-100 and A319-100 series airplanes, A320-111 airplanes, A320-200
series airplanes, and A321-100 and A321-200 series airplanes. AD 2006-
06-14 requires operators to review the airplane's maintenance records
to determine the part numbers of the magnetic fuel level indicators
(MFLIs) of the wing fuel tanks, and related investigative and
corrective actions if necessary. Since we issued AD 2006-06-14, we
received information that the related investigative actions of the
existing AD are not fully effective and that an affected MFLI could
still be installed on airplanes on which the related investigative
actions were accomplished. This proposed AD would also require an
inspection (improved method) to determine the part numbers of the
MFLIs, and, if necessary, replacement of the MFLI or repair. We are
proposing this AD to prevent an ignition source in the wing fuel tank
in the event of a lightning strike, which could result in a fire or
explosion.
DATES: We must receive comments on this proposed AD by October 4, 2013.
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, WA. 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, WA 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-2013-0698;
Directorate Identifier 2012-NM-136-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 March 10, 2006, we issued AD 2006-06-14, Amendment 39-14523 (71
FR 15023, March 27, 2006), (``AD 2006-06-14''). That AD required
actions intended to address an unsafe condition on Airbus Model A318-
111 and -112 airplanes; Model A319-111, -112, -113, -114, -115, -131, -
132, and -133 airplanes; A320-111 airplanes; Model A320-211, -212, -
214, -231, -232, and -233 airplanes; Model A321-111, -112, and -131
airplanes; and Model A321-211, -212, -213, -231, and -232 airplanes.
Since we issued AD 2006-06-14, the European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, has issued EASA Airworthiness Directive 2012-0119,
dated July 4, 2012 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:
In 2005, several in-service occurrences were reported of finding
wear and/or detachment of the top stop of magnetic fuel level
indicators (MFLI), either observed during tank maintenance
activities, or on MFLI returned to the MFLI manufacturer. The
investigation results indicated that the wear of the top stop
retaining `S' shaped wire had been caused by repetitive impact with
the float, resulting in complete detachment of the top stop.
This condition, if not detected and corrected, could lead an
MFLI top stop to come into contact with a probe, which could, in the
event of a lightning strike, create an ignition source in the fuel
tank vapour space, possibly resulting in a fuel tank explosion and
consequent loss of the aeroplane.
DGAC France issued AD F-2005-108 (EASA approval 2005-6026)
[https://ad.easa.europa.eu/ad/F-2005-108] [corresponding FAA AD 2006-
06-14] to require identification (by inspection) and replacement of
the affected metallic MFLI (3508802-xx series with the `S' shaped
retaining wire) with a metallic MFLI with the top stop retained by a
`trapped wire', or with a composite MFLI.
Since that [French] AD was issued, it has been identified that
the inspection procedure (visual check) detailed in Airbus Service
Bulletin (SB) A320-28-1138 was not fully effective, and that
affected MFLI could still be fitted on aeroplanes which have passed
the inspection in accordance with the instructions of this SB.
For the reasons described above, this [EASA] AD, which
supersedes DGAC France AD F-2005-108, requires a one-time inspection
(improved method) to identify the type of MFLI installed and,
depending on findings, replacement or repair, as applicable. This
[EASA] AD also prohibits the installation of the affected MFLI on
any aeroplane as replacement parts.
The repair may also include locating and removing any missing top stop,
and inspecting for any damage caused to the fuel tank by a missing top
stop. You may obtain further information by examining the MCAI in the
AD docket.
Relevant Service Information
Airbus has issued Service Bulletin A320-28-1209, dated December 12,
2011. The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe
[[Page 51119]]
condition exists and is likely to exist or develop on other products of
the same type design.
Differences Between This AD and the MCAI or Service Information
Where the MCAI states in the compliance time ``whichever occurs
later,'' this proposed AD would require ``whichever occurs earlier.''
We have determined that this compliance time would address the unsafe
condition in a more timely manner. We considered the manufacturer's
recommendation, and the overall risk to the fleet, including the
severity of the failure and the likelihood of the failure's occurrence.
Therefore, we find that a compliance time of 49,000 flight hours after
May 1, 2006, or at the next scheduled fuel tank entry after the
effective date of this AD, whichever occurs first, to complete the
required actions to be warranted.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 755 products of U.S. registry.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Parts numbers review [retained Between 1 and 8 None............... Between $85 and Between $64,175 and $513,400
actions from AD 2006-06-14, work-hours x $85 $680.
Amendment 39-14523 (71 FR per hour = Between
15023, March 27, 2006)]. $85 and $680.
Inspection for part numbers [new 21 work-hours x $85 $0................. $1,785............. $1,347,675
proposed action]. per hour = $1,785.
--------------------------------------------------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacement or
repair that would be required based on the results of the proposed
inspection. We have no way of determining the number of aircraft that
might need the replacement or repair:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replace or repair............................ 4 work-hours x $85 per hour = $0 $340
$340.
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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 proposed 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
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2006-06-14, Amendment 39-14523 (71 FR 15023, March 27, 2006), and
adding the following new AD:
Airbus: Docket No. FAA-2013-0698; Directorate Identifier 2012-NM-
136-AD.
(a) Comments Due Date
We must receive comments by October 4, 2013.
[[Page 51120]]
(b) Affected ADs
This AD supersedes AD 2006-06-14, Amendment 39-14523 (71 FR
15023, March 27, 2006).
(c) Applicability
This AD applies to Airbus Model A318-111, A318-112, A318-121,
A318-122, A319-111, A319-112, A319-113, A319-114, A319-115, A319-
131, A319-132, A319-133, A320-111, A320-211, A320-212, A320-214,
A320-215, A320-216, 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.
(d) Subject
Air Transport Association (ATA) of America Code 28: Fuel.
(e) Reason
This AD was prompted by a report of several in-service incidents
of wear and detachment of the top-stops from magnetic fuel level
indicators (MFLI) in a wing fuel tank. We are issuing this AD to
prevent an ignition source in the wing fuel tank in the event of a
lighting strike, which could result in a fire or explosion.
(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 Review of Airplane Maintenance Records/Investigative and
Corrective Actions
This paragraph restates the requirements of paragraph (f) of AD
2006-06-14, Amendment 39-14523 (71 FR 15023, March 27, 2006). For
Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114,
-115, -131, -132, and -133 airplanes; A320-111 airplanes; Model
A320-211, -212, -214, -231, -232, and -233 airplanes; Model A321-
111, -112, and -131 airplanes; and Model A321-211, -212, -213, -231,
and -232 airplanes; on which Airbus Modification 27496 has not been
installed in production: Within 65 months or 6,500 flight hours
after May 1, 2006 (the effective date of AD 2006-06-14), whichever
is first, review the airplane's maintenance records to determine the
part number (P/N) of each MFLI of the wing fuel tanks in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-28-1138, dated March 18, 2005. If the P/N cannot be identified,
or the P/N is identified in the ``old P/N'' column of the table in
paragraph 1.L., ``Interchangeability/Mixability,'' of Airbus Service
Bulletin A320-28-1138, dated March 18, 2005, before further flight,
do the applicable related investigative and corrective actions by
accomplishing all of the actions in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-28-1138,
dated March 18, 2005.
(h) Retained Parts Installation Prohibition
This paragraph restates the requirements paragraph (g) of AD
2006-06-14, Amendment 39-14523 (71 FR 15023, March 27, 2006). For
Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114,
-115, -131, -132, and -133 airplanes; A320-111 airplanes; Model
A320-211, -212, -214, -231, -232, and -233 airplanes; Model A321-
111, -112, and -131 airplanes; and Model A321-211, -212, -213, -231,
and -232 airplanes; on which Airbus Modification 27496 has not been
installed in production: As of May 1, 2006 (the effective date of AD
2006-06-14), no person may install on any airplane any MFLI of the
wing fuel tanks with a P/N identified in the ``old P/N'' column of
the table in paragraph 1.L., ``Interchangeability/Mixability,'' of
Airbus Service Bulletin A320-28-1138, dated March 18, 2005.
(i) New Requirement of This AD: Inspection
For all airplanes, except as provided by paragraph (k) of this
AD: At the next scheduled fuel tank entry after the effective date
of this AD, or within 49,000 flight hours after May 1, 2006 (the
effective date of AD 2006-06-14, Amendment 39-14523 (71 FR 15023,
March 27, 2006), whichever occurs first, perform a special detailed
inspection of the wing tank to determine which type of magnetic fuel
level indicators (MFLI) are installed, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-28-1209,
dated December 12, 2011. A review of airplane maintenance records is
acceptable in lieu of this inspection, if the part number and the
type of the installed MFLI can be conclusively determined from that
review. Paragraphs (i)(1) through (i)(11) of this AD identify the
affected MLFI part numbers.
(1) 3508802-24
(2) 3508802-25
(3) 3508802-26
(4) 3508802-27
(5) 3508802-28
(6) 3508802-34
(7) 3508802-39
(8) 3508802-74
(9) 3508802-75
(10) 3508802-76
(11) 3508802-91
Note 1 to paragraph (i) of this AD: The affected MFLI have the
`S'-shaped lock-wire design.
(j) New Requirement of This AD: Replacement or Repair
If, during the inspection required by paragraph (i) of this AD,
a MFLI with the `S' shaped lock-wire design (Part Number (P/N)
listed in paragraphs (i)(1) through (i)(11) of this AD) is found,
then at the next scheduled fuel tank entry after the effective date
of this AD, or within 49,000 flight hours after May 1, 2006 (the
effective date of AD 2006-06-14, Amendment 39-14523 (71 FR 15023,
March 27, 2006), whichever occurs first, replace the affected MFLI
with a serviceable part and accomplish the corrective actions
(repair), as applicable, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-28-1209, dated December
12, 2011. For the purpose of this AD, a serviceable part is a
composite MFLI, or a metallic MFLI with the top stop retained by a
`trapped wire,' as applicable to the location identified in Table 1
of paragraph (j) of this AD.
Table 1 of Paragraph (j) of this AD--Metallic MFLI With the Top Stop
Retained by a `Trapped Wire,' Including Applicable Location (FIN)
------------------------------------------------------------------------
MFLI P/N Applicable location (FIN)
------------------------------------------------------------------------
3508802-35.......................... 56/57QM
3508802-36.......................... 58/59QM
3508802-37.......................... 60/61QM
3508802-38.......................... 62/63QM
------------------------------------------------------------------------
(k) New Requirement of This AD: Exception for Paragraph (i) of This AD
Airplanes on which Airbus modification (mod) 27496 has been
embodied in production, and on which no wing tank MFLI replacement
with a part number listed in paragraph (i)(1) through (i)(11) of
this AD has been made since first flight, are not affected by the
requirement of paragraph (i) of this AD.
(l) New Requirement of This AD: Parts Installation Prohibition
As of the effective date of this AD, do not install on any
airplane a MFLI with a part number listed in paragraph (i)(1)
through (i)(11) of this AD.
(m) Other FAA AD Provisions
The following provisions also apply to This AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. 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, WA 98057-
3356; telephone (425) 227-1405; fax (425) 227-1149. Information may
be emailed to: M-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 its delegated agent, or by the Design Approval Holder with a
State of Design Authority's design organization approval). For a
repair method to be approved, the repair approval must specifically
refer to this AD. You are required to assure the product is
airworthy before it is returned to service.
(n) Special Flight Permits
Special flight permits, as described in Section 21.197 and
Section 21.199 of the
[[Page 51121]]
Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not
allowed.
(o) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency (EASA) Airworthiness
Directive 2012-0119, dated July 4, 2012, for related information,
which can be found in the AD docket on the Internet at https://www.regulations.gov.
(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, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on August 9, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-20251 Filed 8-19-13; 8:45 am]
BILLING CODE 4910-13-P
