Airworthiness Directives; Airbus Airplanes, 532-536 [2013-31527]
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Federal Register / Vol. 79, No. 3 / Monday, January 6, 2014 / Rules and Regulations
students and recent graduates by
allowing talented employees to
participate in Government internships
and similar programs. Similarly,
eligibility to enroll in health benefits is
a valuable tool that can be used as part
of an overall plan to attract students and
recent graduates interested in Federal
careers and to successfully recruit and
retain them. Accordingly, OPM is
proposing to amend the existing Federal
regulations to clarify that eligible
employees in the Pathways Programs
are eligible to elect FEDVIP benefits.
Also, we are proposing to amend the
FEHBP rules to clarify that Pathways
Programs interns are eligible to elect
FEHBP enrollment pursuant to
authorities contained in Schedule D of
the excepted service, a new schedule
created by E.O. 13562 to make necessary
exceptions to the competitive hiring
rules. These changes can be found in 5
CFR 894.302(f) and 5 CFR 890.303(e)(2).
U.S. Office of Personnel Management.
Katherine Archuleta,
Director.
Waiver of Proposed Rulemaking
Subpart C—Enrollment
OPM has determined that it would be
impracticable, unnecessary, and
contrary to the public interest to delay
putting the provisions of this interim
final regulation in place until a public
notice and comment process has been
completed. Under section 553(b) of the
Administrative Procedure Act (APA) (5
U.S.C. 551 et seq.), a general notice of
proposed rulemaking is not required
when an agency, for good cause, finds
that notice and public comment thereon
are impracticable, unnecessary, or
contrary to the public interest. The
expanded FEDVIP elections authorized
by the Pathways Programs final rule
require immediate implementation to
protect available election opportunities
for employees and their eligible
dependents.
Regulatory Flexibility Act
I certify that this regulation will not
have a significant economic impact on
a substantial number of small entities
because the regulation only affects
health insurance benefits of Federal
employees and retirees.
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Executive Order 12866, Regulatory
Review
List of Subjects in 5 CFR Parts 890 and
894
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PART 890—FEDERAL EMPLOYEES
HEALTH BENEFITS PROGRAM
1. The authority citation for part 890
continues to read as follows:
[FR Doc. 2013–31506 Filed 1–3–14; 8:45 am]
BILLING CODE 6325–39–P
■
Authority: 5 U.S.C. 8913; Sec. 890.301
also issued under sec. 311 of Pub. L. 111–3,
123 Stat. 64; Sec. 890.111 also issued under
section 1622(b) of Pub. L. 104–106, 110 Stat.
521; Sec. 890.112 also issued under section
1 of Pub. L. 110–279, 122 Stat. 2604; Sec.
890.803 also issued under 50 U.S.C. 403p, 22
U.S.C. 4069c and 4069c–1; subpart L also
issued under sec. 599C of Pub. L. 101–513,
104 Stat. 2064, as amended; Sec. 890.102 also
issued under sections 11202(f), 11232(e),
11246(b) and (c) of Pub. L. 105–33, 111 Stat.
251; and section 721 of Pub. L. 105–261, 112
Stat. 2061.
2. In § 890.303, revise paragraph (e)(2)
to read as follows:
■
§ 890.303
Continuation of enrollment.
*
*
*
*
*
(e) * * *
(2) However, in the case of an
employee who is employed under an
OPM approved career-related workstudy program under Schedule D of at
least one year’s duration and who is
expected to be in a pay status during not
less than one-third of the total period of
time from the date of the first
appointment to the completion of the
work-study program, his/her enrollment
continues while he/she is in nonpay
status so long as he/she is participating
in the work-study program.
*
*
*
*
*
PART 894—FEDERAL EMPLOYEES
DENTAL AND VISION INSURANCE
PROGRAM
3. The authority citation for part 894
is revised to read as follows:
■
Authority: 5 U.S.C. 8962; 5 U.S.C. 8992;
Subpart C also issued under section 1 of Pub.
L. 110–279, 122 Stat. 2604.
Subpart C—Eligibility
This rule has been reviewed by the
Office of Management and Budget in
accordance with Executive Order 12866.
Administrative practice and
procedure, Government employees,
Health insurance, Retirement.
Accordingly, the Office of Personnel
Management is amending 5 CFR chapter
I as follows:
under § 213.3402(a) of this chapter. To
qualify, you must be expected to be in
a pay status for at least one-third of the
total period of time from the date of the
first appointment to the completion of
the work-study program.
*
*
*
*
*
4. In § 894.302, paragraph (f) is
revised to read as follows:
■
§ 894.302(f)
What is an excluded position?
*
*
*
*
*
(f) Expected to work fewer than six
months in each year. Exception: you are
eligible if you receive an appointment of
at least one year’s duration as an Intern
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0208; Directorate
Identifier 2012–NM–204–AD; Amendment
39–17702; AD 2013–25–06]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for all
Airbus Model A318, A319, A320, and
A321 series airplanes. This AD was
prompted by a determination that
certain maintenance activities, such as
repairs or the accumulation of paint
layers, might cause the weight of an
elevator to exceed the certified limits.
This AD requires checking the weight of
certain elevators, and corrective action
if necessary; and re-identifying the
elevators. We are issuing this AD to
detect and correct elevators that exceed
the certified weight limits, which could
result in reduced control of the airplane.
DATES: This AD becomes effective
February 10, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 10, 2014.
ADDRESSES: You may examine the AD
on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2013-0208; or in
person at the U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC.
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.airwortheas@airbus.com; Internet https://
www.airbus.com. You may view this
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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.
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:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. The
NPRM was published in the Federal
Register on March 11, 2013 (78 FR
15335). The NPRM proposed to correct
an unsafe condition for the specified
products.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2012–0221,
dated October 23, 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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It has been identified that maintenance
activities, such as repairs or the
accumulation of paint layers, may cause the
weight of an elevator to exceed the certified
limits.
This condition, if not detected and corrected,
could result in reduced control of the
aeroplane.
For the reasons described above, this [EASA]
AD requires a onetime weight check of both
left-hand (LH) and right-hand (RH) elevators,
accomplishment of corrective actions, as
applicable, depending on findings, and reidentification of the elevators.
The monitoring of elevator weight evolution
after having complied with this [EASA] AD
is ensured by Airbus A318/A319/A320/A321
ALS Part 2 CDCCL (Critical Design
Configuration Control Limitations),
compliance with which is currently required
by EASA AD 2010–0071R1 (https://
ad.easa.europa.eu/blob/easa_ad_2010_0071_
R1.pdf/AD_2010-0071R1_1), [which
corresponds to FAA AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011)].
Corrective action includes removing the
paint from the elevator surface and
repainting, or replacing the elevator
with a serviceable elevator if the weight
estimate is over the certified weight
limit; and repairing the elevator. You
may examine the MCAI in the AD
docket on the Internet at https://
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www.regulations.gov/
#!documentDetail;D=FAA-2013-02080002.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received.
Support for the NPRM (78 FR 15335,
March 11, 2013)
US Airways stated it agrees with the
NPRM (78 FR 15335, March 11, 2013) to
ensure safety and has been actively
weighing and applying new part
numbers for over a year.
Request To Change Compliance Time
Stipulation
Airbus requested we change
paragraph (i) of the NPRM (78 FR 15335,
March 11, 2013) to specify that the
corrective action for an overweight
elevator is required before further flight
for that elevator and not for the airplane.
We agree with the commenter’s
request because the intent of the final
rule is to prohibit flight with elevators
that exceed the weight limit established
in accordance with Airbus Service
Bulletin A320–55–1034, including
Appendices 1 and 2, dated August 19,
2011. We have changed paragraph (i) in
this final rule to state ‘‘. . . Before
further flight with an elevator that
exceeds the weight limits established in
Airbus Service Bulletin A320–55–1034,
including Appendices 1 and 2, dated
August 19, 2011, repair . . . .’’
Request To Allow Maintenance Record
Check To Identify Affected Elevators
Delta Airlines (DAL) requested we
revise the NPRM (78 FR 15335, March
11, 2013) to allow omitting the elevator
weight check if a review of the airplane
maintenance records shows that an
affected elevator is not installed on the
airplane.
We disagree with the commenter’s
request. This final rule does not specify
a particular method of determining if an
affected elevator is installed. Paragraph
(c) of this final rule identifies the
affected airplanes, and table 1 to
paragraph (g) of this AD lists the
affected elevator part numbers. Once an
operator determines an affected elevator
part number is not installed on an
airplane in its fleet, the operator may
record compliance with this AD for
those airplanes and elevator part
numbers. However, the operator is still
subject to paragraph (l) of this AD,
which prohibits installing the elevator
part numbers listed in table 1 to
paragraph (g) of this AD, unless the
actions required by this AD are
accomplished on the elevator before
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533
installation. We have not changed this
final rule in this regard.
Request To Omit the Elevator Weight
Check Under Certain Conditions
DAL requested we add a note to the
NPRM (78 FR 15335, March 11, 2013)
similar to a note in paragraph 1.E.,
‘‘Compliance,’’ of Airbus Service
Bulletin A320–55–1034, including
Appendices 1 and 2, dated August 19,
2011. DAL stated that elevator
installation requires compliance with a
critical design configuration control
limitation (CDCCL) that requires
weighing the elevator. DAL commented
that the note states it is not necessary to
weigh the elevator again if an elevator
has previously been weighed for the
CDCCL requirement and, since the
elevator was weighed, no maintenance
actions were carried out on it that could
have led to an elevator weight increase.
We disagree with the commenter’s
request to add a note to this final rule.
Paragraph (g)(1) of this AD already
allows a records review if the elevator
weight can be conclusively determined
from review of maintenance records. We
have not changed this final rule in this
regard.
Request To Change Applicability
US Airways requested we change the
applicability of the NPRM (78 FR 15335,
March 11, 2013) from airplanes to all
part numbers of affected elevators. US
Airways stated that the NPRM should be
a component AD, as the elevators are
interchanged among the fleet, and AD
applicability by manufacturer serial
number (MSN) of the airplane could be
confusing.
We disagree with the commenter’s
request. The FAA risk assessment was
performed to determine corrective
action(s) for mitigating the unsafe
condition at an airplane level. Since the
elevator parts are interchanged among
the fleet, this final rule applicability at
an airplane level will ensure discrepant
elevator parts are identified and
corrected. We have not changed this
final rule in this regard.
Request for Clarification of
Applicability
US Airways requested clarification as
to why elevators having ‘‘MPN
D55280002002 & D55280002003’’ are
not included in the NPRM (78 FR
15335, March 11, 2013). US Airways
stated that these elevators have a
requirement for a weight check after any
repair according to Component
Maintenance Manual Manufacturer 55–
21–15, Revision 13, dated January 1,
2013.
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Federal Register / Vol. 79, No. 3 / Monday, January 6, 2014 / Rules and Regulations
We agree to clarify. The purpose of
this AD is to perform a one-time weight
check of all elevators that are in service
with no record of weight at the time of
production. Airbus Modification 150390
installs a placard with the elevator
weight during production. The two part
numbers referenced by US Airways are
installed in production by Airbus
Modification 150390, and the
configuration is maintained by CDCCL
in Airbus A318/A319/A320/A321
Airworthiness Limitations Section Part
2—Damage-Tolerant Airworthiness
Limitation Items. Therefore, the two
part numbers are not included in this
final rule. We have not changed this
final rule in this regard.
Request To Approve Alternative Paints
US Airways requested we change the
corrective actions in the NPRM (78 FR
15335, March 11, 2013) to reflect that
primer paints called out in Structural
Repair Manual 51–23–11, Page 10, Table
6, Sheet 3 (F1 area), are approved as
alternate paints to apply to elevators
that need to be re-painted. US Airways
stated that Appendix 1, step (5)(b) and
step (6) of Airbus Service Bulletin
A320–55–1034, including Appendices 1
and 2, dated August 19, 2011, requires
an external paint scheme and the primer
materials called out in this service
information are not readily available.
We disagree with the commenter’s
request. The commenter did not provide
substantiation for an equivalent
alternative to the primer material
referenced in the service information in
this final rule. The operator may apply
for approval of an alternative method of
compliance under the provisions of
paragraph (m) of this final rule to use
different primer material. We have not
changed this final rule in this regard.
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Request To Correct Typographical
Error
DAL noted an error in paragraph
(h)(2) of the NPRM (78 FR 15335, March
11, 2013), which should state ‘‘than’’
instead of ‘‘that.’’
Paragraph (h)(2) of the NPRM (78 FR
15335, March 11, 2013) stated ‘‘For
elevators other that those identified in
. . . .’’ We agree with the commenter’s
request and have changed paragraph
(h)(2) of this final rule to state ‘‘For
elevators other than those . . . .’’
Request To Revise Certain Terminology
Airbus requested we revise paragraph
(i) of the NPRM (78 FR 15335, March 11,
2013) to use the word ‘‘restore’’ in lieu
of ‘‘repair.’’ Airbus stated it considers
the word ‘‘restore’’ to be more
appropriate for the required actions (i.e.,
removal of paint layers).
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We disagree with the commenter’s
request. The intent of word ‘‘repair’’ is
to restore the structure/part to its
original type design configuration.
Therefore, replacing the word ‘‘repair’’
with ‘‘restore’’ may be misinterpreted.
We have not changed this final rule in
this regard.
Change to This Final Rule
We have changed the first compliance
time specified in paragraph (i) of this
AD from ‘‘before further flight’’ to
‘‘within the applicable time specified in
paragraph (h)(1) or (h)(2) of this AD.’’
We have determined that this change
will provide sufficient time to
adequately address the identified unsafe
condition.
Conclusion
We reviewed the available data,
including the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these changes:
• Are consistent with the intent that
was proposed in the NPRM (78 FR
15335, March 11, 2013) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 15335,
March 11, 2013).
Costs of Compliance
We estimate that this AD affects 755
products of U.S. registry. We estimate
that it will take about 45 work-hours per
product to comply with the basic
requirements of this AD. The average
labor rate is $85 per work-hour. Based
on these figures, we estimate the cost of
this AD to the U.S. operators to be
$2,887,875, or $3,825 per product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
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the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
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 that this AD:
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.
Examining the AD Docket
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/#!documentDetail;
D=FAA-2013-0208-0002; 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 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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 AD:
■
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Federal Register / Vol. 79, No. 3 / Monday, January 6, 2014 / Rules and Regulations
2013–25–06 Airbus: Amendment 39–17702.
Docket No. FAA–2013–0208; Directorate
Identifier 2012–NM–204–AD.
TABLE 1 TO PARAGRAPH (g) OF THIS
AD—AFFECTED PART NUMBERS (P/
N)—Continued
(a) Effective Date
Part name
P/N (first 12
digits only)
Right Hand Elevator ..........
D55280002001
This airworthiness directive (AD) becomes
effective February 10, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes,
certificated in any category, listed in
paragraphs (c)(1) through (c)(4) of this AD, all
serial numbers.
(1) Model A318–111, –112, –121, and –122
airplanes.
(2) Model A319–111, –112, –113, –114,
–115, –131, –132, and –133 airplanes.
(3) Model A320–111, –211, –212, –214,
–231, –232, and –233 airplanes.
(4) Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 55, Stabilizers.
(e) Reason
This AD was prompted by a determination
that certain maintenance activities, such as
repairs or the accumulation of paint layers,
might cause the weight of an elevator to
exceed the certified limits. We are issuing
this AD to detect and correct elevators that
exceed certified weight limits, which could
result in reduced control of the airplane.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Weight Check
At the applicable time specified in
paragraph (h)(1) or (h)(2) of this AD: Do a
weight check on the elevators identified in
table 1 to paragraph (g) of this AD. Do the
weight check in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–55–1034, including
Appendices 1 and 2, dated August 19, 2011,
except as specified in paragraphs (g)(1),
(g)(2), and (g)(3) of this AD.
TABLE 1 TO PARAGRAPH (g) OF THIS
AD—AFFECTED PART NUMBERS (P/N)
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Part name
P/N (first 12
digits only)
Left Hand Elevator .............
Left Hand Elevator .............
Left Hand Elevator .............
Left Hand Elevator .............
Left Hand Elevator .............
Left Hand Elevator .............
Left Hand Elevator .............
Right Hand Elevator ..........
Right Hand Elevator ..........
Right Hand Elevator ..........
Right Hand Elevator ..........
Right Hand Elevator ..........
Right Hand Elevator ..........
D55280001000
D55280001002
D55280001004
D55280001008
D55280001010
D55280001012
D55280002000
D55280001001
D55280001003
D55280001005
D55280001009
D55280001011
D55280001013
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(1) A review of the airplane maintenance
records is acceptable in lieu of the weight
check required by the introductory text of
paragraph (g) of this AD, provided the
elevator weight can be conclusively
determined from that review.
(2) The use of elevator weight data from
production, as specified in Airbus Service
Bulletin A320–55–1034, including
Appendices 1 and 2, dated August 19, 2011,
is acceptable in lieu of the weight check
required by the introductory text of
paragraph (g) of this AD, provided that the
affected elevator has not been subjected to
any maintenance action that could have
modified the weight.
(3) Airplanes on which Airbus
Modification 150390 has been embodied in
production are not required to do the actions
specified in the introductory text of
paragraph (g) of this AD, provided that no
elevator having a part number specified in
table 1 to paragraph (g) of this AD has been
installed on that airplane since the airplane’s
first flight.
(h) Compliance Time for the Actions
Specified in Paragraphs (g) and (i) of This
AD
(1) For an elevator for which, as of the
effective date of this AD, the records show
that no maintenance actions have been
performed since first installation of the
elevator on an airplane, which might have
increased its weight: Within 72 months after
the effective date of this AD.
(2) For elevators other than those identified
in paragraph (h)(1) of this AD: Within 48
months after the effective date of this AD.
(i) Corrective Actions
If the elevator weight, determined as
required by paragraph (g) of this AD, exceeds
the weight limit specified in the
Accomplishment Instructions of Airbus
Service Bulletin A320–55–1034, including
Appendices 1 and 2, dated August 19, 2011:
Within the applicable time specified in
paragraph (h)(1) or (h)(2) of this AD, do the
applicable corrective actions followed by a
new weight check of the elevator, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
55–1034, including Appendices 1 and 2,
dated August 19, 2011. If the elevator weight,
determined as required by the new weight
check, exceeds the weight limit specified in
the Accomplishment Instructions of Airbus
Service Bulletin A320–55–1034, including
Appendices 1 and 2, dated August 19, 2011:
Before further flight with an elevator that
exceeds the weight limits established in
Airbus Service Bulletin A320–55–1034,
including Appendices 1 and 2, dated August
19, 2011, repair the elevator using a method
approved by either the Manager,
International Branch, ANM–116, Transport
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535
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA) (or its
delegated agent).
(j) Elevator Re-Identification
If the elevator weight, determined by the
weight check specified in paragraph (g) or (i)
of this AD, does not exceed the weight limit
specified in the Accomplishment
Instructions of Airbus Service Bulletin A320–
55–1034, including Appendices 1 and 2,
dated August 19, 2011: Within 72 months
after the effective date of this AD, record the
elevator weight and re-identify the elevator,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
55–1042, Revision 01, dated June 29, 2012.
(k) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (j) of this AD, if those
actions were performed before the effective
date of this AD using Airbus Service Bulletin
A320–55–1042, dated August 19, 2011,
which is not incorporated by reference in this
AD.
(l) Parts Installation Limitation
As of the effective date of this AD, no
person may install on any airplane an
elevator with a part number listed in table 1
to paragraph (g) of this AD, unless that
elevator is in compliance with the
requirements 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: 9ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2012–0221, dated
E:\FR\FM\06JAR1.SGM
06JAR1
536
Federal Register / Vol. 79, No. 3 / Monday, January 6, 2014 / Rules and Regulations
October 23, 2012, for related information.
You may examine the MCAI in the AD
docket on the Internet at https://
www.regulations.gov/#!documentDetail;
D=FAA-2013-0208-0002.
(2) Service information identified in this
AD that is not incorporated by reference may
be obtained at the addresses specified in
paragraph (o)(3) and (o)(4) of this AD.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Airbus Service Bulletin A320–55–1034,
including Appendices 1 and 2, dated August
19, 2011.
(ii) Airbus Service Bulletin A320–55–1042,
Revision 01, dated June 29, 2012.
(3) 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.
(4) You may view copies of the 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
December 4, 2013.
John P. Piccola,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–31527 Filed 1–3–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0540; Directorate
Identifier 2012–NM–185–AD; Amendment
39–17721; AD 2013–26–12]
RIN 2120–AA64
sroberts on DSK5SPTVN1PROD with RULES
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: We are superseding
Airworthiness Directive (AD) 2009–14–
02 for certain The Boeing Company
VerDate Mar<15>2010
16:04 Jan 03, 2014
Jkt 232001
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–200C, 747–200F,
747–300, 747–400, 747–400D, 747–
400F, 747SR, and 747SP series
airplanes. AD 2009–14–02 required
repetitive inspections for wear damage
and cracks of the fuselage skin in the
interface area of the vertical stabilizer
seal and fuselage skin, a detailed
inspection for wear damage and cracks
of the surface of any skin repair doubler
in the area, and corrective actions if
necessary. For airplanes on which the
fuselage skin has been blended to
remove wear damage, AD 2009–14–02
also required repetitive external detailed
inspections or high frequency eddy
current inspections for cracks of the
blended area of the fuselage skin, and
corrective actions if necessary. This new
AD reduces the repetitive inspection
interval, changes certain corrective
actions, and expands the applicability.
This AD was prompted by a report of
wear through the fuselage skin that
occurred sooner than the previous
repetitive inspection interval. We are
issuing this AD to detect and correct
wear damage and cracks of the fuselage
skin in the interface area of the vertical
stabilizer seal and fuselage skin in
sections 46 and 48, which could cause
in-flight depressurization of the
airplane.
DATES: This AD is effective February 10,
2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 10, 2014.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P. O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.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–2013–
0540; 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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Bill
Ashforth, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office (ACO), 1601
Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6432; fax: 425–
917–6590; email: Bill.Ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2009–14–02,
Amendment 39–15951 (74 FR 30919,
June 29, 2009). AD 2009–14–02 applied
to the specified products. The NPRM
published in the Federal Register on
July 3, 2013 (78 FR 40050). The NPRM
proposed to continue to require
repetitive inspections for wear damage
and cracks of the fuselage skin in the
interface area of the vertical stabilizer
seal and fuselage skin, a detailed
inspection for wear damage and cracks
of the surface of any skin repair doubler
in the area, and corrective actions if
necessary. For airplanes on which the
fuselage skin has been blended to
remove wear damage, AD 2009–14–02
also required repetitive external detailed
inspections or high frequency eddy
current inspections for cracks of the
blended area of the fuselage skin, and
corrective actions if necessary. That
NPRM also proposed to reduce the
repetitive inspection interval, change
certain corrective actions, and expand
the applicability.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal (78 FR 40050,
July 3, 2013) and the FAA’s response to
each comment.
Request To Modify Paragraph Title
Boeing requested we revise the
terminating action title of paragraph (i)
of the NPRM (78 FR 40050, July 3, 2013)
by removing the word ‘‘Optional.’’
Boeing stated that Boeing Alert Service
Bulletin 747–53A2478, Revision 3,
dated October 17, 2011, specifies that if
any crack is found or if wear damage is
greater than the limit allowed, rub strips
must be installed in accordance with
Boeing Service Bulletin 747–53–2721,
Revision 2, dated March 17, 2011.
Boeing commented that in this case, the
terminating action is not optional.
E:\FR\FM\06JAR1.SGM
06JAR1
]]>Agencies
[Federal Register Volume 79, Number 3 (Monday, January 6, 2014)]
[Rules and Regulations]
[Pages 532-536]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-31527]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0208; Directorate Identifier 2012-NM-204-AD;
Amendment 39-17702; AD 2013-25-06]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A318, A319, A320, and A321 series airplanes. This AD was
prompted by a determination that certain maintenance activities, such
as repairs or the accumulation of paint layers, might cause the weight
of an elevator to exceed the certified limits. This AD requires
checking the weight of certain elevators, and corrective action if
necessary; and re-identifying the elevators. We are issuing this AD to
detect and correct elevators that exceed the certified weight limits,
which could result in reduced control of the airplane.
DATES: This AD becomes effective February 10, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 10,
2014.
ADDRESSES: You may examine the AD on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2013-0208; or in person at the
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC.
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
[[Page 533]]
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.
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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
The NPRM was published in the Federal Register on March 11, 2013 (78 FR
15335). The NPRM proposed to correct an unsafe condition for the
specified products.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2012-0221, dated October 23, 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:
It has been identified that maintenance activities, such as repairs
or the accumulation of paint layers, may cause the weight of an
elevator to exceed the certified limits.
This condition, if not detected and corrected, could result in
reduced control of the aeroplane.
For the reasons described above, this [EASA] AD requires a onetime
weight check of both left-hand (LH) and right-hand (RH) elevators,
accomplishment of corrective actions, as applicable, depending on
findings, and re-identification of the elevators.
The monitoring of elevator weight evolution after having complied
with this [EASA] AD is ensured by Airbus A318/A319/A320/A321 ALS
Part 2 CDCCL (Critical Design Configuration Control Limitations),
compliance with which is currently required by EASA AD 2010-0071R1
(https://ad.easa.europa.eu/blob/easa_ad_2010_0071_R1.pdf/AD_2010-0071R1_1), [which corresponds to FAA AD 2011-14-06, Amendment
39-16741 (76 FR 42024, July 18, 2011)].
Corrective action includes removing the paint from the elevator surface
and repainting, or replacing the elevator with a serviceable elevator
if the weight estimate is over the certified weight limit; and
repairing the elevator. You may examine the MCAI in the AD docket on
the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2013-
0208-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received.
Support for the NPRM (78 FR 15335, March 11, 2013)
US Airways stated it agrees with the NPRM (78 FR 15335, March 11,
2013) to ensure safety and has been actively weighing and applying new
part numbers for over a year.
Request To Change Compliance Time Stipulation
Airbus requested we change paragraph (i) of the NPRM (78 FR 15335,
March 11, 2013) to specify that the corrective action for an overweight
elevator is required before further flight for that elevator and not
for the airplane.
We agree with the commenter's request because the intent of the
final rule is to prohibit flight with elevators that exceed the weight
limit established in accordance with Airbus Service Bulletin A320-55-
1034, including Appendices 1 and 2, dated August 19, 2011. We have
changed paragraph (i) in this final rule to state ``. . . Before
further flight with an elevator that exceeds the weight limits
established in Airbus Service Bulletin A320-55-1034, including
Appendices 1 and 2, dated August 19, 2011, repair . . . .''
Request To Allow Maintenance Record Check To Identify Affected
Elevators
Delta Airlines (DAL) requested we revise the NPRM (78 FR 15335,
March 11, 2013) to allow omitting the elevator weight check if a review
of the airplane maintenance records shows that an affected elevator is
not installed on the airplane.
We disagree with the commenter's request. This final rule does not
specify a particular method of determining if an affected elevator is
installed. Paragraph (c) of this final rule identifies the affected
airplanes, and table 1 to paragraph (g) of this AD lists the affected
elevator part numbers. Once an operator determines an affected elevator
part number is not installed on an airplane in its fleet, the operator
may record compliance with this AD for those airplanes and elevator
part numbers. However, the operator is still subject to paragraph (l)
of this AD, which prohibits installing the elevator part numbers listed
in table 1 to paragraph (g) of this AD, unless the actions required by
this AD are accomplished on the elevator before installation. We have
not changed this final rule in this regard.
Request To Omit the Elevator Weight Check Under Certain Conditions
DAL requested we add a note to the NPRM (78 FR 15335, March 11,
2013) similar to a note in paragraph 1.E., ``Compliance,'' of Airbus
Service Bulletin A320-55-1034, including Appendices 1 and 2, dated
August 19, 2011. DAL stated that elevator installation requires
compliance with a critical design configuration control limitation
(CDCCL) that requires weighing the elevator. DAL commented that the
note states it is not necessary to weigh the elevator again if an
elevator has previously been weighed for the CDCCL requirement and,
since the elevator was weighed, no maintenance actions were carried out
on it that could have led to an elevator weight increase.
We disagree with the commenter's request to add a note to this
final rule. Paragraph (g)(1) of this AD already allows a records review
if the elevator weight can be conclusively determined from review of
maintenance records. We have not changed this final rule in this
regard.
Request To Change Applicability
US Airways requested we change the applicability of the NPRM (78 FR
15335, March 11, 2013) from airplanes to all part numbers of affected
elevators. US Airways stated that the NPRM should be a component AD, as
the elevators are interchanged among the fleet, and AD applicability by
manufacturer serial number (MSN) of the airplane could be confusing.
We disagree with the commenter's request. The FAA risk assessment
was performed to determine corrective action(s) for mitigating the
unsafe condition at an airplane level. Since the elevator parts are
interchanged among the fleet, this final rule applicability at an
airplane level will ensure discrepant elevator parts are identified and
corrected. We have not changed this final rule in this regard.
Request for Clarification of Applicability
US Airways requested clarification as to why elevators having ``MPN
D55280002002 & D55280002003'' are not included in the NPRM (78 FR
15335, March 11, 2013). US Airways stated that these elevators have a
requirement for a weight check after any repair according to Component
Maintenance Manual Manufacturer 55-21-15, Revision 13, dated January 1,
2013.
[[Page 534]]
We agree to clarify. The purpose of this AD is to perform a one-
time weight check of all elevators that are in service with no record
of weight at the time of production. Airbus Modification 150390
installs a placard with the elevator weight during production. The two
part numbers referenced by US Airways are installed in production by
Airbus Modification 150390, and the configuration is maintained by
CDCCL in Airbus A318/A319/A320/A321 Airworthiness Limitations Section
Part 2--Damage-Tolerant Airworthiness Limitation Items. Therefore, the
two part numbers are not included in this final rule. We have not
changed this final rule in this regard.
Request To Approve Alternative Paints
US Airways requested we change the corrective actions in the NPRM
(78 FR 15335, March 11, 2013) to reflect that primer paints called out
in Structural Repair Manual 51-23-11, Page 10, Table 6, Sheet 3 (F1
area), are approved as alternate paints to apply to elevators that need
to be re-painted. US Airways stated that Appendix 1, step (5)(b) and
step (6) of Airbus Service Bulletin A320-55-1034, including Appendices
1 and 2, dated August 19, 2011, requires an external paint scheme and
the primer materials called out in this service information are not
readily available.
We disagree with the commenter's request. The commenter did not
provide substantiation for an equivalent alternative to the primer
material referenced in the service information in this final rule. The
operator may apply for approval of an alternative method of compliance
under the provisions of paragraph (m) of this final rule to use
different primer material. We have not changed this final rule in this
regard.
Request To Correct Typographical Error
DAL noted an error in paragraph (h)(2) of the NPRM (78 FR 15335,
March 11, 2013), which should state ``than'' instead of ``that.''
Paragraph (h)(2) of the NPRM (78 FR 15335, March 11, 2013) stated
``For elevators other that those identified in . . . .'' We agree with
the commenter's request and have changed paragraph (h)(2) of this final
rule to state ``For elevators other than those . . . .''
Request To Revise Certain Terminology
Airbus requested we revise paragraph (i) of the NPRM (78 FR 15335,
March 11, 2013) to use the word ``restore'' in lieu of ``repair.''
Airbus stated it considers the word ``restore'' to be more appropriate
for the required actions (i.e., removal of paint layers).
We disagree with the commenter's request. The intent of word
``repair'' is to restore the structure/part to its original type design
configuration. Therefore, replacing the word ``repair'' with
``restore'' may be misinterpreted. We have not changed this final rule
in this regard.
Change to This Final Rule
We have changed the first compliance time specified in paragraph
(i) of this AD from ``before further flight'' to ``within the
applicable time specified in paragraph (h)(1) or (h)(2) of this AD.''
We have determined that this change will provide sufficient time to
adequately address the identified unsafe condition.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these changes:
Are consistent with the intent that was proposed in the
NPRM (78 FR 15335, March 11, 2013) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 15335, March 11, 2013).
Costs of Compliance
We estimate that this AD affects 755 products of U.S. registry. We
estimate that it will take about 45 work-hours per product to comply
with the basic requirements of this AD. The average labor rate is $85
per work-hour. Based on these figures, we estimate the cost of this AD
to the U.S. operators to be $2,887,875, or $3,825 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will 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 that this AD:
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.
Examining the AD Docket
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2013-0208-0002; 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 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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 adding the following new AD:
[[Page 535]]
2013-25-06 Airbus: Amendment 39-17702. Docket No. FAA-2013-0208;
Directorate Identifier 2012-NM-204-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective February 10,
2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes, certificated in any
category, listed in paragraphs (c)(1) through (c)(4) of this AD, all
serial numbers.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-111, -211, -212, -214, -231, -232, and -233
airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 55, Stabilizers.
(e) Reason
This AD was prompted by a determination that certain maintenance
activities, such as repairs or the accumulation of paint layers,
might cause the weight of an elevator to exceed the certified
limits. We are issuing this AD to detect and correct elevators that
exceed certified weight limits, which could result in reduced
control of the airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Weight Check
At the applicable time specified in paragraph (h)(1) or (h)(2)
of this AD: Do a weight check on the elevators identified in table 1
to paragraph (g) of this AD. Do the weight check in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-55-
1034, including Appendices 1 and 2, dated August 19, 2011, except as
specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
Table 1 to Paragraph (g) of This AD--Affected Part Numbers (P/N)
------------------------------------------------------------------------
Part name P/N (first 12 digits only)
------------------------------------------------------------------------
Left Hand Elevator........................ D55280001000
Left Hand Elevator........................ D55280001002
Left Hand Elevator........................ D55280001004
Left Hand Elevator........................ D55280001008
Left Hand Elevator........................ D55280001010
Left Hand Elevator........................ D55280001012
Left Hand Elevator........................ D55280002000
Right Hand Elevator....................... D55280001001
Right Hand Elevator....................... D55280001003
Right Hand Elevator....................... D55280001005
Right Hand Elevator....................... D55280001009
Right Hand Elevator....................... D55280001011
Right Hand Elevator....................... D55280001013
Right Hand Elevator....................... D55280002001
------------------------------------------------------------------------
(1) A review of the airplane maintenance records is acceptable
in lieu of the weight check required by the introductory text of
paragraph (g) of this AD, provided the elevator weight can be
conclusively determined from that review.
(2) The use of elevator weight data from production, as
specified in Airbus Service Bulletin A320-55-1034, including
Appendices 1 and 2, dated August 19, 2011, is acceptable in lieu of
the weight check required by the introductory text of paragraph (g)
of this AD, provided that the affected elevator has not been
subjected to any maintenance action that could have modified the
weight.
(3) Airplanes on which Airbus Modification 150390 has been
embodied in production are not required to do the actions specified
in the introductory text of paragraph (g) of this AD, provided that
no elevator having a part number specified in table 1 to paragraph
(g) of this AD has been installed on that airplane since the
airplane's first flight.
(h) Compliance Time for the Actions Specified in Paragraphs (g) and (i)
of This AD
(1) For an elevator for which, as of the effective date of this
AD, the records show that no maintenance actions have been performed
since first installation of the elevator on an airplane, which might
have increased its weight: Within 72 months after the effective date
of this AD.
(2) For elevators other than those identified in paragraph
(h)(1) of this AD: Within 48 months after the effective date of this
AD.
(i) Corrective Actions
If the elevator weight, determined as required by paragraph (g)
of this AD, exceeds the weight limit specified in the Accomplishment
Instructions of Airbus Service Bulletin A320-55-1034, including
Appendices 1 and 2, dated August 19, 2011: Within the applicable
time specified in paragraph (h)(1) or (h)(2) of this AD, do the
applicable corrective actions followed by a new weight check of the
elevator, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-55-1034, including Appendices 1 and 2,
dated August 19, 2011. If the elevator weight, determined as
required by the new weight check, exceeds the weight limit specified
in the Accomplishment Instructions of Airbus Service Bulletin A320-
55-1034, including Appendices 1 and 2, dated August 19, 2011: Before
further flight with an elevator that exceeds the weight limits
established in Airbus Service Bulletin A320-55-1034, including
Appendices 1 and 2, dated August 19, 2011, repair the elevator using
a method approved by either the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the European Aviation
Safety Agency (EASA) (or its delegated agent).
(j) Elevator Re-Identification
If the elevator weight, determined by the weight check specified
in paragraph (g) or (i) of this AD, does not exceed the weight limit
specified in the Accomplishment Instructions of Airbus Service
Bulletin A320-55-1034, including Appendices 1 and 2, dated August
19, 2011: Within 72 months after the effective date of this AD,
record the elevator weight and re-identify the elevator, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-55-1042, Revision 01, dated June 29, 2012.
(k) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(j) of this AD, if those actions were performed before the effective
date of this AD using Airbus Service Bulletin A320-55-1042, dated
August 19, 2011, which is not incorporated by reference in this AD.
(l) Parts Installation Limitation
As of the effective date of this AD, no person may install on
any airplane an elevator with a part number listed in table 1 to
paragraph (g) of this AD, unless that elevator is in compliance with
the requirements 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2012-0221, dated
[[Page 536]]
October 23, 2012, for related information. You may examine the MCAI
in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2013-0208-0002.
(2) Service information identified in this AD that is not
incorporated by reference may be obtained at the addresses specified
in paragraph (o)(3) and (o)(4) of this AD.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Airbus Service Bulletin A320-55-1034, including Appendices 1
and 2, dated August 19, 2011.
(ii) Airbus Service Bulletin A320-55-1042, Revision 01, dated
June 29, 2012.
(3) 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.
(4) You may view copies of the 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on December 4, 2013.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-31527 Filed 1-3-14; 8:45 am]
BILLING CODE 4910-13-P
