Airworthiness Directives; Airbus Airplanes, 62928-62932 [2014-25023]
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Federal Register / Vol. 79, No. 203 / Tuesday, October 21, 2014 / Proposed Rules
including any personal information
provided in the comments (except
information deemed to be exempt from
public disclosure).
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C. Issues on Which DOE Seeks
Comment
Although DOE welcomes comments
on any aspect of this proposed
determination, DOE is particularly
interested in receiving comments and
views of interested parties concerning
the following issues:
1. The HID lamps selected for and
excluded from analysis of economic
justification for standards;
2. The technology options analyzed
and in particular the elimination of
sapphire arc tubes and starting method
as technology option(s);
3. The equipment classes analyzed in
this NOPD;
4. The design options identified in the
screening analysis;
5. The representative equipment
classes analyzed in this NOPD;
6. The baseline lamps selected,
including the inclusion of a 150 W MH
lamp;
7. The selection of more efficacious
substitute lamps analyzed in this NOPD;
8. The decision to analyze equal
wattage replacement lamps, as well as
the methodology used to select the
equal wattage replacement lamps;
9. The methodology used to
determine ELs, as well as the resulting
ELs analyzed in this NOPD;
10. The factors used in this NOPD to
scale to equipment classes not directly
analyzed;
11. The decision to include
replacement pathways other than full
fixture replacement in this NOPD;
12. The results and methodology from
the equipment price determination;
13. Methods to improve DOE’s energy
use analysis, as well as any data
supporting alternate operating hour
estimates or assumptions regarding
dimming of HID lamp-and-ballast
systems;
14. The assumptions and
methodology for estimating annual
operating hours, which were based on
data from the 2010 U.S. Lighting Market
Characterization;
15. Methods to improve DOE’s
equipment price projections beyond the
assumption of constant real prices, as
well as any data supporting alternate
methods;
16. The reasonableness of assuming a
zero percent rebound effect (the
potential tendency for customers to
increase HID lamp usage in response to
more efficient lamp-and-ballast
systems);
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17. Whether the shipment scenarios
under various policy scenarios are
reasonable and likely to occur;
18. The impediments that prevent
users of HID lamps from switching to
LED lighting to garner further energy
savings;
19. The expected impact of potential
standards on the rate at which HID lamp
customers transition to non-HID
technology;
20. The methodology used in the MIA
and the results of the MIA;
21. The proposal of a negative
determination stating that standards for
HID lamps are not justified.
[Docket No. FAA–2014–0753; Directorate
Identifier 2014–NM–128–AD]
have been installed and may have the
potential of cracks in the rod eye-end.
This proposed AD would also require an
inspection to determine if certain
elevator servo-control parts are
installed, and replacement if necessary.
We are proposing this AD to detect and
correct rod eye-end cracking, which
could result in an uncontrolled elevator
surface and consequent reduced control
of the airplane.
DATES: We must receive comments on
this proposed AD by December 5, 2014.
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—EIAS, 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 view this 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.
RIN 2120–AA64
Examining the AD Docket
VIII. Approval of the Office of the
Secretary
The Secretary of Energy has approved
publication of this NOPD.
List of Subjects in 10 CFR Part 431
Administrative practice and
procedure, Confidential business
information, Energy conservation, and
Reporting and recordkeeping
requirements.
Issued in Washington, DC, on October 10,
2014.
Kathleen B. Hogan,
Deputy Assistant Secretary for Energy
Efficiency, Energy Efficiency and Renewable
Energy.
[FR Doc. 2014–24971 Filed 10–20–14; 8:45 am]
BILLING CODE 6450–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2011–19–
04, for all Airbus Model A318, A319,
A320, and A321 series airplanes. AD
2011–19–04 currently requires
repetitive inspections of the left-hand
and right-hand inboard and outboard
elevator servo-control rod eye-ends for
cracking, and corrective actions if
necessary. Since we issued AD 2011–
19–04, we have determined that certain
elevator servo-control parts that do not
conform to the approved type design
SUMMARY:
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You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0753; 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 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
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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–2014–0753; Directorate Identifier
2014–NM–128–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.
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Discussion
On September 7, 2011, we issued AD
2011–19–04, Amendment 39–16809 (76
FR 57630, September 16, 2011). AD
2011–19–04 requires actions intended to
address an unsafe condition on all
Airbus Model A318, A319, A320, and
A321 series airplanes. AD 2011–19–04
superseded AD 2009–17–04,
Amendment 39–15995 (74 FR 41611,
August 18, 2009).
Since we issued AD 2011–19–04,
Amendment 39–16809 (76 FR 57630,
September 16, 2011), the European
Aviation Safety Agency (EASA), which
is the Technical Agent for the Member
States of the European Community, has
issued EASA Airworthiness Directive
2014–0137, dated May 28, 2014
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for all Model A318, A319,
A320, and Model A321 series airplanes.
The MCAI states:
One case of elevator servo-control
disconnection was reported on an A320
family aeroplane. Investigation results
revealed that the failure occurred at the
servo-control rod eye-end. Prompted by this
finding, additional inspections revealed
cracking at the same location on a number of
other servo-control rod eye-ends. In several
cases, both actuators of the same elevator
surface were affected.
It was determined that the detected rod
end cracks are caused by fatigue, induced by
a bending effect which is linked to the
spherical bearing rotational torque. As the
elevator surface is neither actuated nor
damped, a dual servo-control disconnection
on the same elevator would result in an
uncontrolled surface.
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This condition, if not corrected, could
result in reduced control of the aeroplane.
To address this potential unsafe condition,
EASA issued [an airworthiness directive
(later revised)] [which corresponds to FAA
AD 2009–17–04, Amendment 39–5995 (74
FR 41611, August 18, 2009)] to require a onetime inspection of the elevator servo-control
rod eye-ends for aeroplanes which had
accumulated more than 10,000 flight cycles
(FC) since aeroplane first flight and, in case
of findings, accomplishment of corrective
actions.
As a result of EASA AD 2008–0149, a
significant number of rod eye-ends were
found cracked. In addition, some cracks were
reported on rod eye-ends that had not yet
accumulated the 10,000 FC of the established
threshold.
Prompted by these findings, EASA issued
[an airworthiness directive (later revised)]
[which corresponds to FAA AD 2011–19–04,
Amendment 39–16809 (76 FR 57630,
September 16, 2011)], which partially
retained the initial inspection requirement of
EASA AD 2008–0149, which was
superseded, reduced the compliance time of
the initial inspection and introduced a
repetitive inspection programme.
After EASA AD 2010–0046R1 (https://
ad.easa.europa.eu/blob/easa_ad_2010_0046_
R1_superseded.pdf/AD_2010-0046R1_1) was
issued, a new elevator servo-control rod eyeend was developed, incorporating a regreasable roller bearing.
Consequently, EASA issued [EASA] AD
2013–0309 (later corrected) (https://
ad.easa.europa.eu/blob/easa_ad_2013_0309_
superseded.pdf/AD_2013-0309_1), retaining
the requirements of EASA AD 2010–0046R1,
which was superseded, and introduced an
optional terminating action for the repetitive
inspections by replacing the existing elevator
servo-control rod eye-ends with the new
elevator servo-control rod eye-end. In
addition, that [EASA] AD prohibited, for
aeroplanes that incorporate this optional
modification, (re)installation of unmodified
elevator servo-controls.
At the time that EASA AD 2013–0309 was
issued, it was planned that Airbus would
proceed with the certification of certain
elevator servo-controls, Part Number (P/N)
31075–0xx, P/N 31075–1xx and P/N 31075–
3xx (originally certified only for installation
on Model A320–111 aeroplanes, which are
no longer in service), to allow installation of
those parts on other A320 family aeroplane
Models.
Since that [EASA] AD was issued, Airbus
decided not to progress with certification of
the affected elevator servo-controls for
installation on other Models.
For the reason described above, and
because of evidence that such parts remain
available as spares in the field, this [EASA]
AD retains the requirements of EASA AD
2013–0309, which is superseded, and adds a
prohibition to install the affected elevator
servo-controls that were only intended for
A320–111 aeroplanes.
This proposed AD would require an
inspection to determine whether any
elevator control part having P/N 31075–
0xx, 31075–1xx, or 31075–3xx is
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installed and replacement if necessary.
You may examine the MCAI in the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0753.
Relevant Service Information
Airbus has issued Service Bulletin
A320–27–1223, dated September 3,
2013. The actions described in this
service information are intended to
correct the unsafe condition identified
in the MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This Proposed AD
and the MCAI or Service Information
The MCAI does not include an action
for airplanes installed with elevator
control parts having part number (P/N)
31075–0xx, 31075–1xx, or 31075–3xx.
This proposed AD would require an
inspection to determine if those elevator
servo-control parts are installed, and
replacement if necessary.
Costs of Compliance
We estimate that this proposed AD
affects 851 airplanes of U.S. registry.
The actions that are required by AD
2011–19–04, Amendment 39–16809 (76
FR 57630, September 16, 2011), and
retained in this proposed AD take about
25 work-hours per product, at an
average labor rate of $85 per work-hour.
Based on these figures, the estimated
cost of the actions that are required by
AD 2011–19–04 is $2,125 per product.
We also estimate that it would take
about 14 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
this proposed AD on U.S. operators to
be $1,012,690, or $1,190 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 2 work-hours and require parts
costing $4,000, for a cost of $4,170 per
product. We have no way of
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determining the number of aircraft that
might need this action.
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.
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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:
■
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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2011–19–04, Amendment 39–16809 (76
FR 57630, September 16, 2011), and
adding the following new AD:
■
Airbus: Docket No. FAA–2014–0753;
Directorate Identifier 2014–NM–128–AD.
(a) Comments Due Date
We must receive comments by December 5,
2014.
(b) Affected ADs
This AD replaces AD 2011–19–04,
Amendment 39–16809 (76 FR 57630,
September 16, 2011).
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(4)
of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A318–111, –112, –121,
and –122 airplanes.
(2) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes.
(3) Airbus Model A320–211, –212, –214,
–231, –232, and –233 airplanes.
(4) Airbus Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight Controls.
(e) Reason
This AD was prompted by a determination
that certain elevator servo-control parts that
do not conform to the approved type design
have been installed and may have the
potential of cracks in the rod eye-end. We are
issuing this AD to detect and correct rod eyeend cracking, which could result in
uncontrolled elevator surface and consequent
reduced control of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspections
This paragraph restates the requirements of
paragraph (g) of AD 2011–19–04,
Amendment 39–16809 (76 FR 57630,
September 16, 2011), with no changes.
(1) At the applicable times specified in
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD:
Inspect both the left-hand and right-hand
inboard elevator servo-control rod eye-ends
for cracking, in accordance with the
instructions of Airbus All Operators Telex
(AOT) A320–27A1186, Revision 04, dated
April 3, 2009; or the Accomplishment
Instructions of Airbus Service Bulletin A320–
27A1186, Revision 07, dated March 2, 2011.
As of October 21, 2011 (the effective date of
AD 2011–19–04, Amendment 39–16809 (76
FR 57630, September 16, 2011)), use Airbus
Service Bulletin A320–27A1186, Revision 07,
dated March 2, 2011.
(i) For airplanes that have accumulated
10,000 total flight cycles or more as of
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September 22, 2009 (the effective date of AD
2009–17–04, Amendment 39–15995 (74 FR
41611, August 18, 2009)): At the later of the
times specified in paragraphs (g)(1)(i)(A) and
(g)(1)(i)(B) of this AD.
(A) Within 1,500 flight cycles after
September 22, 2009 (the effective date of AD
2009–17–04, Amendment 39–15995 (74 FR
41611, August 18, 2009)).
(B) Within 1,500 flight cycles after
accumulating 10,000 total flight cycles since
first flight of the airplane.
(ii) For airplanes that have accumulated
less than 10,000 total flight cycles as of
September 22, 2009 (the effective date of AD
2009–17–04, Amendment 39–15995 (74 FR
41611, August 18, 2009)): At the later of the
times specified in paragraphs (g)(1)(ii)(A) and
(g)(1)(ii)(B) of this AD.
(A) Before the accumulation of 5,000 total
flight cycles.
(B) Within 20 months after October 21,
2011 (the effective date of AD 2011–19–04,
Amendment 39–16809 (76 FR 57630,
September 16, 2011)) but no later than before
the accumulation of 11,500 total flight cycles.
(2) At the applicable time specified in
paragraphs (g)(2)(i) and (g)(2)(ii) of this AD:
Inspect both the left-hand and right-hand
outboard elevator servo-control rod eye-ends
for cracking, in accordance with the
instructions of Airbus AOT A320–27A1186,
Revision 04, dated April 3, 2009; or the
Accomplishment Instructions of Airbus
Service Bulletin A320–27A1186, Revision 07,
dated March 2, 2011. As of October 21, 2011
(the effective date of AD 2011–19–04,
Amendment 39–16809 (76 FR 57630,
September 16, 2011)), use Airbus Service
Bulletin A320–27A1186, Revision 07, dated
March 2, 2011.
(i) For airplanes that have accumulated
10,000 total flight cycles or more as of
September 22, 2009 (the effective date of AD
2009–17–04, Amendment 39–15995 (74 FR
41611, August 18, 2009)): At the later of the
times specified in paragraphs (g)(2)(i)(A) and
(g)(2)(i)(B) of this AD.
(A) Within 3,000 flight cycles after
September 22, 2009 (the effective date of AD
2009–17–04, Amendment 39–15995 (74 FR
41611, August 18, 2009)).
(B) Within 3,000 flight cycles after
accumulating 10,000 total flight cycles since
first flight of the airplane.
(ii) For airplanes that have accumulated
less than 10,000 total flight cycles as of
September 22, 2009 (the effective date of AD
2009–17–04, Amendment 39–15995 (74 FR
41611, August 18, 2009)): At the later of the
times specified in paragraphs (g)(2)(ii)(A) and
(g)(2)(ii)(B) of this AD.
(A) Before the accumulation of 7,500 total
flight cycles.
(B) Within 40 months after October 21,
2011 (the effective date of AD 2011–19–04,
Amendment 39–16809 (76 FR 57630,
September 16, 2011)) but no later than before
the accumulation of 13,000 total flight cycles.
(h) Retained Repetitive Inspections
This paragraph restates the requirements of
paragraph (h) of AD 2011–19–04,
Amendment 39–16809 (76 FR 57630,
September 16, 2011), with no changes.
Repeat the inspections of the left-hand and
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right-hand inboard and outboard elevator
servo-control rod eye-ends for cracking as
required by paragraphs (g)(1) and (g)(2) of
this AD at the later of the times specified in
paragraph (h)(1) or (h)(2) of this AD. Repeat
the inspections thereafter at intervals not to
exceed 5,000 flight cycles.
(1) Within 5,000 flight cycles after the last
inspection required by paragraph (g)(1) or
(g)(2) of this AD as applicable.
(2) Within 6 months after October 21, 2011
(the effective date of AD 2011–19–04,
Amendment 39–16809 (76 FR 57630,
September 16, 2011)).
(k)(1) and (k)(2) of this AD, do an inspection
to determine whether any elevator control
part having part number (P/N) 31075–0xx,
31075–1xx, or 31075–3xx is installed. A
review of airplane maintenance records is
acceptable in lieu of this inspection if the
part numbers of the elevator control parts can
be conclusively determined from that review.
(1) Concurrently with the accomplishment
of the next inspection required by paragraph
(g) or (h) of this AD.
(2) Within 30 days after the effective date
of this AD.
(i) Retained Corrective Actions
This paragraph restates the requirements of
paragraph (i) of AD 2011–19–04, Amendment
39–16809 (76 FR 57630, September 16, 2011),
with no changes. If any cracking is found
during any inspection required by paragraph
(g) or (h) of this AD, before further flight,
accomplish all applicable corrective actions,
in accordance with the Accomplishment
Instructions and figures of Airbus Service
Bulletin A320–27A1186, Revision 07, dated
March 2, 2011.
(l) New Requirement of This AD:
Replacement of Certain Parts
(j) Retained Parts Limitation for Elevator
Servo-Control Rod Eye-Ends
This paragraph restates the requirements of
paragraph (j) of AD 2011–19–04, Amendment
39–16809 (76 FR 57630, September 16, 2011),
with a new exception. As of October 21, 2011
(the effective date of AD 2011–19–04,
Amendment 39–16809 (76 FR 57360,
September 16, 2011)), and except as required
by paragraph (p) of this AD, no person may
install on any airplane an elevator servocontrol rod eye-end unless it is new or has
been inspected in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–27A1186, Revision 07,
dated March 2, 2011, with no crack findings.
(k) New Requirement of This AD: Inspection
To Determine Part Numbers
As of the effective date of this AD: At the
later of the times specified in paragraphs
If the inspection required by paragraph (k)
of this AD reveals that any elevator servocontrols having P/Ns 31075–0xx, 31075–1xx,
or 31075–3xx are installed: Before further
flight, do the actions specified in paragraph
(l)(1) or (l)(2) of this AD.
(1) Replace all elevator servo-controls
having P/N 31075–0xx, 31075–1xx, or
31075–3xx with parts having P/N 31075–2xx
or 31075–4xx, as applicable, using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or the European Aviation
Safety Agency (EASA); or Airbus’s EASA
Design Organization Approval (DOA).
(2) Replace all elevator servo-controls
having P/N 31075–0xx, 31075–1xx, or
31075–3xx with serviceable parts having
P/N 31075–6xx or 31075–8xx, as applicable,
in accordance with the Accomplishment
Instruction of Airbus Service Bulletin A320–
27–1223, dated September 3, 2013, or
Goodrich Service Bulletin 31075–27–22,
dated July 2, 2013. Serviceable parts are
those that have been inspected for cracks in
the rod eye-ends without any crack findings
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
27A1186, Revision 07, dated March 2, 2011.
(m) New Optional Terminating Action for
Certain Inspections
Modification of an airplane by replacing all
4 elevator servo-control rod eye-ends with
modified (i.e. re-greasable) parts, and reidentification of those elevator servo-controls
to P/N 31075–6xx or P/N 31075–8xx, as
applicable, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–27–1223, dated
September 3, 2013; constitutes terminating
action for the requirements of paragraphs (g),
(h), (k), and (l) of this AD.
Note 1 to paragraph (m) of this AD:
Maintenance Review Board Report task
reference 27.34.00/06 is applicable to
elevator servo-controls having P/N 31075–
6xx or P/N 31075–8xx.
(n) New Exception to Certain Inspections
Airplanes on which Airbus modification
154554 (installation of servo-controls having
P/N 31075–6xx or P/N 31075–8xx, fitted with
modified rod eye-end roller bearing) has been
embodied in production are not affected by
the requirements of paragraphs (g), (h), (k),
and (l) of this AD, provided that no elevator
servo-control having P/N 31075–0xx, or P/N
31075–1xx, or P/N 31075–2xx, or P/N 31075–
3xx, or P/N 31075–4xx, fitted with rod-end
assembly P/N 341203-xxx, has been
reinstalled since first flight.
(o) Credit for Previous Actions
(1) This paragraph restates the credit
specified in paragraph (k) of AD 2011–19–04,
Amendment 39–16809 (76 FR 57630,
September 16, 2011).
(i) This paragraph provides credit for
actions required by paragraphs (g)(1) and
(g)(2) of this AD, if those actions were
performed before October 21, 2011 (the
effective date of AD 2011–19–04,
Amendment 39–16809 (76 FR 57630,
September 16, 2011)), using the service
information specified in table 1 to paragraph
(o)(1)(i) of this AD.
TABLE 1 TO PARAGRAPH (o)(1)(i) OF THIS AD—CREDIT SERVICE INFORMATION FOR PARAGRAPH (g) OF THIS AD
Airbus AOT—
Revision—
mstockstill on DSK4VPTVN1PROD with PROPOSALS
A320–27A1186
A320–27A1186
A320–27A1186
A320–27A1186
A320–27A1186
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
(ii) This paragraph provides credit for
actions required by paragraph (h) of this AD,
if those actions were performed before
October 21, 2011 (the effective date of AD
2011–19–04, Amendment 39–16809 (76 FR
57630, September 16, 2011)), using Airbus
Service Bulletin A320–27A1186, Revision 05,
dated March 10, 2010; or Airbus Service
Bulletin A320–27A1186, Revision 06, dated
December 14, 2010.
(2) This paragraph provides credit for
actions required by paragraph (i) of this AD,
if those actions were performed before
October 21, 2011 (the effective date of AD
2011–19–04, Amendment 39–16809 (76 FR
VerDate Sep<11>2014
17:11 Oct 20, 2014
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57630, September 16, 2011)), using Airbus
Service Bulletin A320–27A1186, Revision 06,
dated December 14, 2010.
(p) New Parts Installation Prohibition
(1) As of the effective date of this AD, no
person may install on any airplane an
elevator servo-control having P/N 31075–0xx,
31075–1xx, or 31075–3xx.
(2) No person may install on any airplane
an elevator servo-control having P/N 31075–
2xx or P/N 31075–4xx, or an elevator servocontrol rod eye-end having P/N 341203 or P/
N 341203–XXX, as required by paragraphs
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Dated—
Original ...............
01 .......................
02 .......................
03 .......................
04 .......................
June 23, 2008.
August 11, 2008.
March 30, 2009.
April 1, 2009.
April 3, 2009.
(p)(2)(i) and (p)(2)(ii) of this AD, as
applicable.
(i) For airplanes that do not have Airbus
Modification 154554 embodied in
production: After optional modification of
the airplane as specified in paragraph (m) of
this AD.
(ii) For airplanes on which Airbus
Modification 154554 has been embodied in
production: As of the effective date of this
AD.
(q) Other FAA AD Provisions
The following provisions also apply to this
AD:
E:\FR\FM\21OCP1.SGM
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Federal Register / Vol. 79, No. 203 / Tuesday, October 21, 2014 / Proposed Rules
(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: 9-ANM-116AMOC-REQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD
2011–19–04, Amendment 39–16809 (76 FR
57630, September 16, 2011), are approved as
AMOCs for the corresponding provisions of
this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
(r) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0137, dated
May 28, 2014, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2014–0753.
(2) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 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 view this 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.
DEPARTMENT OF HEALTH AND
HUMAN SERVICES
ENVIRONMENTAL PROTECTION
AGENCY
Food and Drug Administration
40 CFR Part 52
21 CFR Part 73
[EPA–R09–OAR–2014–0711; FRL–9917–80–
Region 9]
[Docket No. FDA–2014–C–1616]
EMD Millipore Corp.; Filing of Color
Additive Petition
AGENCY:
Food and Drug Administration,
HHS.
ACTION:
Notice of petition.
The Food and Drug
Administration (FDA or we) is
announcing that we have filed a
petition, submitted by EMD Millipore
Corp., proposing that the color additive
regulations be amended to expand the
safe use of mica-based pearlescent
pigments in alcoholic beverages to
include cordials, liqueurs, cocktails, and
certain other alcoholic beverages, and
non-alcoholic mixers and mixes.
SUMMARY:
The color additive petition was
filed on August 21, 2014.
DATES:
FOR FURTHER INFORMATION CONTACT:
Ellen Anderson, Center for Food Safety
and Applied Nutrition (HFS–265), Food
and Drug Administration, 5100 Paint
Branch Pkwy., College Park, MD 20740–
3835, 240–402–1309.
Under
section 721(d)(1) of the Federal Food,
Drug, and Cosmetic Act (21 U.S.C.
379e(d)(1)), we are giving notice that we
have filed a color additive petition (CAP
4C0299), submitted by EMD Millipore
Corp., c/o Hyman, Phelps & McNamara,
P.C., 700 13th Street NW., Suite 1200,
Washington, DC 20005. The petition
proposes to amend the color additive
regulations in 21 CFR 73.350, Micabased pearlescent pigments, to expand
the safe use of mica-based pearlescent
pigments in alcoholic beverages to
include cordials, liqueurs, cocktails, and
certain other alcoholic beverages, and
non-alcoholic mixers and mixes.
We have determined under 21 CFR
25.32(k) that this action is of a type that
does not individually or cumulatively
have a significant effect on the human
environment. Therefore, neither an
environmental assessment nor an
environmental impact statement is
required.
SUPPLEMENTARY INFORMATION:
Issued in Renton, Washington, on October
13, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
Dated: October 16, 2014.
Dennis M. Keefe,
Director, Office of Food Additive Safety,
Center for Food Safety and Applied Nutrition.
[FR Doc. 2014–25023 Filed 10–20–14; 8:45 am]
[FR Doc. 2014–24962 Filed 10–20–14; 8:45 am]
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BILLING CODE 4164–01–P
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17:11 Oct 20, 2014
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Approval and Promulgation of
Implementation Plans; Revisions to the
Nevada State Implementation Plan;
Stationary Source Permits
Environmental Protection
Agency (EPA).
ACTION: Proposed rule.
AGENCY:
The Environmental Protection
Agency (EPA) is proposing to approve
revisions to the applicable state
implementation plan for the State of
Nevada submitted by the Nevada
Division of Environmental Protection.
The revisions include amended State
rules related to applications for, and
issuance of, permits for stationary
sources, but not including review and
permitting of major sources and major
modifications under parts C and D of
title I of the Clean Air Act. EPA is taking
action under the Clean Air Act
obligation to take action on State
submittals of revisions to state
implementation plans. The intended
effect of the proposed approval is to fix
deficiencies in the previously-approved
version of the permitting rules and to
ensure that new or modified stationary
sources do not interfere with attainment
or maintenance of the national ambient
air quality standards.
DATES: Any comments must arrive by
November 20, 2014.
ADDRESSES: Submit comments,
identified by docket number EPA–R09–
OAR–2014–0711, by one of the
following methods:
1. Federal eRulemaking Portal:
www.regulations.gov. Follow the on-line
instructions.
2. Email: R9airpermits@epa.gov.
3. Mail or deliver: Laura Yannayon
(AIR–3), U.S. Environmental Protection
Agency Region IX, 75 Hawthorne Street,
San Francisco, CA 94105–3901.
Instructions: All comments will be
included in the public docket without
change and may be made available
online at www.regulations.gov,
including any personal information
provided, unless the comment includes
Confidential Business Information (CBI)
or other information whose disclosure is
restricted by statute. Information that
you consider CBI or otherwise protected
should be clearly identified as such and
should not be submitted through
www.regulations.gov or email.
www.regulations.gov is an ‘‘anonymous
access’’ system, and EPA will not know
SUMMARY:
E:\FR\FM\21OCP1.SGM
21OCP1
]]>Agencies
[Federal Register Volume 79, Number 203 (Tuesday, October 21, 2014)]
[Proposed Rules]
[Pages 62928-62932]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-25023]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0753; Directorate Identifier 2014-NM-128-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) 2011-19-
04, for all Airbus Model A318, A319, A320, and A321 series airplanes.
AD 2011-19-04 currently requires repetitive inspections of the left-
hand and right-hand inboard and outboard elevator servo-control rod
eye-ends for cracking, and corrective actions if necessary. Since we
issued AD 2011-19-04, we have determined that certain elevator servo-
control parts that do not conform to the approved type design have been
installed and may have the potential of cracks in the rod eye-end. This
proposed AD would also require an inspection to determine if certain
elevator servo-control parts are installed, and replacement if
necessary. We are proposing this AD to detect and correct rod eye-end
cracking, which could result in an uncontrolled elevator surface and
consequent reduced control of the airplane.
DATES: We must receive comments on this proposed AD by December 5,
2014.
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--EIAS, 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 view this 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 by searching for and locating Docket No. FAA-2014-
0753; 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
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
[[Page 62929]]
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-2014-0753;
Directorate Identifier 2014-NM-128-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 September 7, 2011, we issued AD 2011-19-04, Amendment 39-16809
(76 FR 57630, September 16, 2011). AD 2011-19-04 requires actions
intended to address an unsafe condition on all Airbus Model A318, A319,
A320, and A321 series airplanes. AD 2011-19-04 superseded AD 2009-17-
04, Amendment 39-15995 (74 FR 41611, August 18, 2009).
Since we issued AD 2011-19-04, Amendment 39-16809 (76 FR 57630,
September 16, 2011), the European Aviation Safety Agency (EASA), which
is the Technical Agent for the Member States of the European Community,
has issued EASA Airworthiness Directive 2014-0137, dated May 28, 2014
(referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''), to correct an unsafe condition for all
Model A318, A319, A320, and Model A321 series airplanes. The MCAI
states:
One case of elevator servo-control disconnection was reported on
an A320 family aeroplane. Investigation results revealed that the
failure occurred at the servo-control rod eye-end. Prompted by this
finding, additional inspections revealed cracking at the same
location on a number of other servo-control rod eye-ends. In several
cases, both actuators of the same elevator surface were affected.
It was determined that the detected rod end cracks are caused by
fatigue, induced by a bending effect which is linked to the
spherical bearing rotational torque. As the elevator surface is
neither actuated nor damped, a dual servo-control disconnection on
the same elevator would result in an uncontrolled surface.
This condition, if not corrected, could result in reduced
control of the aeroplane.
To address this potential unsafe condition, EASA issued [an
airworthiness directive (later revised)] [which corresponds to FAA
AD 2009-17-04, Amendment 39-5995 (74 FR 41611, August 18, 2009)] to
require a one-time inspection of the elevator servo-control rod eye-
ends for aeroplanes which had accumulated more than 10,000 flight
cycles (FC) since aeroplane first flight and, in case of findings,
accomplishment of corrective actions.
As a result of EASA AD 2008-0149, a significant number of rod
eye-ends were found cracked. In addition, some cracks were reported
on rod eye-ends that had not yet accumulated the 10,000 FC of the
established threshold.
Prompted by these findings, EASA issued [an airworthiness
directive (later revised)] [which corresponds to FAA AD 2011-19-04,
Amendment 39-16809 (76 FR 57630, September 16, 2011)], which
partially retained the initial inspection requirement of EASA AD
2008-0149, which was superseded, reduced the compliance time of the
initial inspection and introduced a repetitive inspection programme.
After EASA AD 2010-0046R1 (https://ad.easa.europa.eu/blob/easa_ad_2010_0046_R1_superseded.pdf/AD_2010-0046R1_1) was issued, a
new elevator servo-control rod eye-end was developed, incorporating
a re-greasable roller bearing.
Consequently, EASA issued [EASA] AD 2013-0309 (later corrected)
(https://ad.easa.europa.eu/blob/easa_ad_2013_0309_superseded.pdf/AD_2013-0309_1), retaining the requirements of EASA AD 2010-0046R1,
which was superseded, and introduced an optional terminating action
for the repetitive inspections by replacing the existing elevator
servo-control rod eye-ends with the new elevator servo-control rod
eye-end. In addition, that [EASA] AD prohibited, for aeroplanes that
incorporate this optional modification, (re)installation of
unmodified elevator servo-controls.
At the time that EASA AD 2013-0309 was issued, it was planned
that Airbus would proceed with the certification of certain elevator
servo-controls, Part Number (P/N) 31075-0xx, P/N 31075-1xx and P/N
31075-3xx (originally certified only for installation on Model A320-
111 aeroplanes, which are no longer in service), to allow
installation of those parts on other A320 family aeroplane Models.
Since that [EASA] AD was issued, Airbus decided not to progress
with certification of the affected elevator servo-controls for
installation on other Models.
For the reason described above, and because of evidence that
such parts remain available as spares in the field, this [EASA] AD
retains the requirements of EASA AD 2013-0309, which is superseded,
and adds a prohibition to install the affected elevator servo-
controls that were only intended for A320-111 aeroplanes.
This proposed AD would require an inspection to determine whether any
elevator control part having P/N 31075-0xx, 31075-1xx, or 31075-3xx is
installed and replacement if necessary. You may examine the MCAI in the
AD docket on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2014-0753.
Relevant Service Information
Airbus has issued Service Bulletin A320-27-1223, dated September 3,
2013. The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This Proposed AD and the MCAI or Service
Information
The MCAI does not include an action for airplanes installed with
elevator control parts having part number (P/N) 31075-0xx, 31075-1xx,
or 31075-3xx. This proposed AD would require an inspection to determine
if those elevator servo-control parts are installed, and replacement if
necessary.
Costs of Compliance
We estimate that this proposed AD affects 851 airplanes of U.S.
registry.
The actions that are required by AD 2011-19-04, Amendment 39-16809
(76 FR 57630, September 16, 2011), and retained in this proposed AD
take about 25 work-hours per product, at an average labor rate of $85
per work-hour. Based on these figures, the estimated cost of the
actions that are required by AD 2011-19-04 is $2,125 per product.
We also estimate that it would take about 14 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $1,012,690, or
$1,190 per product.
In addition, we estimate that any necessary follow-on actions would
take about 2 work-hours and require parts costing $4,000, for a cost of
$4,170 per product. We have no way of
[[Page 62930]]
determining the number of aircraft that might need this action.
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.
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)
2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011), and
adding the following new AD:
Airbus: Docket No. FAA-2014-0753; Directorate Identifier 2014-NM-
128-AD.
(a) Comments Due Date
We must receive comments by December 5, 2014.
(b) Affected ADs
This AD replaces AD 2011-19-04, Amendment 39-16809 (76 FR 57630,
September 16, 2011).
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes.
(2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(3) Airbus Model A320-211, -212, -214, -231, -232, and -233
airplanes.
(4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Controls.
(e) Reason
This AD was prompted by a determination that certain elevator
servo-control parts that do not conform to the approved type design
have been installed and may have the potential of cracks in the rod
eye-end. We are issuing this AD to detect and correct rod eye-end
cracking, which could result in uncontrolled elevator surface and
consequent reduced control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspections
This paragraph restates the requirements of paragraph (g) of AD
2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011),
with no changes.
(1) At the applicable times specified in paragraphs (g)(1)(i)
and (g)(1)(ii) of this AD: Inspect both the left-hand and right-hand
inboard elevator servo-control rod eye-ends for cracking, in
accordance with the instructions of Airbus All Operators Telex (AOT)
A320-27A1186, Revision 04, dated April 3, 2009; or the
Accomplishment Instructions of Airbus Service Bulletin A320-27A1186,
Revision 07, dated March 2, 2011. As of October 21, 2011 (the
effective date of AD 2011-19-04, Amendment 39-16809 (76 FR 57630,
September 16, 2011)), use Airbus Service Bulletin A320-27A1186,
Revision 07, dated March 2, 2011.
(i) For airplanes that have accumulated 10,000 total flight
cycles or more as of September 22, 2009 (the effective date of AD
2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At
the later of the times specified in paragraphs (g)(1)(i)(A) and
(g)(1)(i)(B) of this AD.
(A) Within 1,500 flight cycles after September 22, 2009 (the
effective date of AD 2009-17-04, Amendment 39-15995 (74 FR 41611,
August 18, 2009)).
(B) Within 1,500 flight cycles after accumulating 10,000 total
flight cycles since first flight of the airplane.
(ii) For airplanes that have accumulated less than 10,000 total
flight cycles as of September 22, 2009 (the effective date of AD
2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At
the later of the times specified in paragraphs (g)(1)(ii)(A) and
(g)(1)(ii)(B) of this AD.
(A) Before the accumulation of 5,000 total flight cycles.
(B) Within 20 months after October 21, 2011 (the effective date
of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16,
2011)) but no later than before the accumulation of 11,500 total
flight cycles.
(2) At the applicable time specified in paragraphs (g)(2)(i) and
(g)(2)(ii) of this AD: Inspect both the left-hand and right-hand
outboard elevator servo-control rod eye-ends for cracking, in
accordance with the instructions of Airbus AOT A320-27A1186,
Revision 04, dated April 3, 2009; or the Accomplishment Instructions
of Airbus Service Bulletin A320-27A1186, Revision 07, dated March 2,
2011. As of October 21, 2011 (the effective date of AD 2011-19-04,
Amendment 39-16809 (76 FR 57630, September 16, 2011)), use Airbus
Service Bulletin A320-27A1186, Revision 07, dated March 2, 2011.
(i) For airplanes that have accumulated 10,000 total flight
cycles or more as of September 22, 2009 (the effective date of AD
2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At
the later of the times specified in paragraphs (g)(2)(i)(A) and
(g)(2)(i)(B) of this AD.
(A) Within 3,000 flight cycles after September 22, 2009 (the
effective date of AD 2009-17-04, Amendment 39-15995 (74 FR 41611,
August 18, 2009)).
(B) Within 3,000 flight cycles after accumulating 10,000 total
flight cycles since first flight of the airplane.
(ii) For airplanes that have accumulated less than 10,000 total
flight cycles as of September 22, 2009 (the effective date of AD
2009-17-04, Amendment 39-15995 (74 FR 41611, August 18, 2009)): At
the later of the times specified in paragraphs (g)(2)(ii)(A) and
(g)(2)(ii)(B) of this AD.
(A) Before the accumulation of 7,500 total flight cycles.
(B) Within 40 months after October 21, 2011 (the effective date
of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16,
2011)) but no later than before the accumulation of 13,000 total
flight cycles.
(h) Retained Repetitive Inspections
This paragraph restates the requirements of paragraph (h) of AD
2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011),
with no changes. Repeat the inspections of the left-hand and
[[Page 62931]]
right-hand inboard and outboard elevator servo-control rod eye-ends
for cracking as required by paragraphs (g)(1) and (g)(2) of this AD
at the later of the times specified in paragraph (h)(1) or (h)(2) of
this AD. Repeat the inspections thereafter at intervals not to
exceed 5,000 flight cycles.
(1) Within 5,000 flight cycles after the last inspection
required by paragraph (g)(1) or (g)(2) of this AD as applicable.
(2) Within 6 months after October 21, 2011 (the effective date
of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16,
2011)).
(i) Retained Corrective Actions
This paragraph restates the requirements of paragraph (i) of AD
2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011),
with no changes. If any cracking is found during any inspection
required by paragraph (g) or (h) of this AD, before further flight,
accomplish all applicable corrective actions, in accordance with the
Accomplishment Instructions and figures of Airbus Service Bulletin
A320-27A1186, Revision 07, dated March 2, 2011.
(j) Retained Parts Limitation for Elevator Servo-Control Rod Eye-Ends
This paragraph restates the requirements of paragraph (j) of AD
2011-19-04, Amendment 39-16809 (76 FR 57630, September 16, 2011),
with a new exception. As of October 21, 2011 (the effective date of
AD 2011-19-04, Amendment 39-16809 (76 FR 57360, September 16,
2011)), and except as required by paragraph (p) of this AD, no
person may install on any airplane an elevator servo-control rod
eye-end unless it is new or has been inspected in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-
27A1186, Revision 07, dated March 2, 2011, with no crack findings.
(k) New Requirement of This AD: Inspection To Determine Part Numbers
As of the effective date of this AD: At the later of the times
specified in paragraphs (k)(1) and (k)(2) of this AD, do an
inspection to determine whether any elevator control part having
part number (P/N) 31075-0xx, 31075-1xx, or 31075-3xx is installed. A
review of airplane maintenance records is acceptable in lieu of this
inspection if the part numbers of the elevator control parts can be
conclusively determined from that review.
(1) Concurrently with the accomplishment of the next inspection
required by paragraph (g) or (h) of this AD.
(2) Within 30 days after the effective date of this AD.
(l) New Requirement of This AD: Replacement of Certain Parts
If the inspection required by paragraph (k) of this AD reveals
that any elevator servo-controls having P/Ns 31075-0xx, 31075-1xx,
or 31075-3xx are installed: Before further flight, do the actions
specified in paragraph (l)(1) or (l)(2) of this AD.
(1) Replace all elevator servo-controls having P/N 31075-0xx,
31075-1xx, or 31075-3xx with parts having P/N 31075-2xx or 31075-
4xx, as applicable, using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the European Aviation Safety Agency (EASA); or Airbus's EASA
Design Organization Approval (DOA).
(2) Replace all elevator servo-controls having P/N 31075-0xx,
31075-1xx, or 31075-3xx with serviceable parts having P/N 31075-6xx
or 31075-8xx, as applicable, in accordance with the Accomplishment
Instruction of Airbus Service Bulletin A320-27-1223, dated September
3, 2013, or Goodrich Service Bulletin 31075-27-22, dated July 2,
2013. Serviceable parts are those that have been inspected for
cracks in the rod eye-ends without any crack findings in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-27A1186, Revision 07, dated March 2, 2011.
(m) New Optional Terminating Action for Certain Inspections
Modification of an airplane by replacing all 4 elevator servo-
control rod eye-ends with modified (i.e. re-greasable) parts, and
re-identification of those elevator servo-controls to P/N 31075-6xx
or P/N 31075-8xx, as applicable, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-27-1223,
dated September 3, 2013; constitutes terminating action for the
requirements of paragraphs (g), (h), (k), and (l) of this AD.
Note 1 to paragraph (m) of this AD: Maintenance Review Board
Report task reference 27.34.00/06 is applicable to elevator servo-
controls having P/N 31075-6xx or P/N 31075-8xx.
(n) New Exception to Certain Inspections
Airplanes on which Airbus modification 154554 (installation of
servo-controls having P/N 31075-6xx or P/N 31075-8xx, fitted with
modified rod eye-end roller bearing) has been embodied in production
are not affected by the requirements of paragraphs (g), (h), (k),
and (l) of this AD, provided that no elevator servo-control having
P/N 31075-0xx, or P/N 31075-1xx, or P/N 31075-2xx, or P/N 31075-3xx,
or P/N 31075-4xx, fitted with rod-end assembly P/N 341203-xxx, has
been reinstalled since first flight.
(o) Credit for Previous Actions
(1) This paragraph restates the credit specified in paragraph
(k) of AD 2011-19-04, Amendment 39-16809 (76 FR 57630, September 16,
2011).
(i) This paragraph provides credit for actions required by
paragraphs (g)(1) and (g)(2) of this AD, if those actions were
performed before October 21, 2011 (the effective date of AD 2011-19-
04, Amendment 39-16809 (76 FR 57630, September 16, 2011)), using the
service information specified in table 1 to paragraph (o)(1)(i) of
this AD.
Table 1 to Paragraph (o)(1)(i) of This AD--Credit Service Information for Paragraph (g) of This AD
----------------------------------------------------------------------------------------------------------------
Airbus AOT-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
A320-27A1186............................. Original.......................... June 23, 2008.
A320-27A1186............................. 01................................ August 11, 2008.
A320-27A1186............................. 02................................ March 30, 2009.
A320-27A1186............................. 03................................ April 1, 2009.
A320-27A1186............................. 04................................ April 3, 2009.
----------------------------------------------------------------------------------------------------------------
(ii) This paragraph provides credit for actions required by
paragraph (h) of this AD, if those actions were performed before
October 21, 2011 (the effective date of AD 2011-19-04, Amendment 39-
16809 (76 FR 57630, September 16, 2011)), using Airbus Service
Bulletin A320-27A1186, Revision 05, dated March 10, 2010; or Airbus
Service Bulletin A320-27A1186, Revision 06, dated December 14, 2010.
(2) This paragraph provides credit for actions required by
paragraph (i) of this AD, if those actions were performed before
October 21, 2011 (the effective date of AD 2011-19-04, Amendment 39-
16809 (76 FR 57630, September 16, 2011)), using Airbus Service
Bulletin A320-27A1186, Revision 06, dated December 14, 2010.
(p) New Parts Installation Prohibition
(1) As of the effective date of this AD, no person may install
on any airplane an elevator servo-control having P/N 31075-0xx,
31075-1xx, or 31075-3xx.
(2) No person may install on any airplane an elevator servo-
control having P/N 31075-2xx or P/N 31075-4xx, or an elevator servo-
control rod eye-end having P/N 341203 or P/N 341203-XXX, as required
by paragraphs (p)(2)(i) and (p)(2)(ii) of this AD, as applicable.
(i) For airplanes that do not have Airbus Modification 154554
embodied in production: After optional modification of the airplane
as specified in paragraph (m) of this AD.
(ii) For airplanes on which Airbus Modification 154554 has been
embodied in production: As of the effective date of this AD.
(q) Other FAA AD Provisions
The following provisions also apply to this AD:
[[Page 62932]]
(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: 9-ANM-116-AMOC-REQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD 2011-19-04, Amendment 39-
16809 (76 FR 57630, September 16, 2011), are approved as AMOCs for
the corresponding provisions of this AD.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA Design Organization Approval (DOA). If approved by the
DOA, the approval must include the DOA-authorized signature.
(r) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0137, dated May 28, 2014,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2014-0753.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 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 view this 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 October 13, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-25023 Filed 10-20-14; 8:45 am]
BILLING CODE 4910-13-P
