Airworthiness Directives; Airbus Airplanes, 57753-57757 [2014-22469]
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Federal Register / Vol. 79, No. 187 / Friday, September 26, 2014 / Rules and Regulations
envelope, which could result in loss of
control of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Replacement of Fuse Pins and Access
Cover Assemblies
Within 48 months after the effective date
of this AD: Replace the fuse pins for the
outboard aft upper spar and the access cover
assemblies on struts Nos. 1 and 4, with new
fuse pins and access cover assemblies, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–54A2238, dated January 31, 2014.
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(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (i) of this AD. Information may be
emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO
to make those findings. For a repair method
to be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) If the service information contains steps
that are labeled as RC (Required for
Compliance), those steps must be done to
comply with this AD; any steps that are not
labeled as RC are recommended. Those steps
that are not labeled as RC may be deviated
from, done as part of other actions, or done
using accepted methods different from those
identified in the specified service
information without obtaining approval of an
AMOC, provided the steps labeled as RC can
be done and the airplane can be put back in
a serviceable condition. Any substitutions or
changes to steps labeled as RC require
approval of an AMOC.
(i) Related Information
For more information about this AD,
contact Narinder Luthra, Aerospace Engineer,
Airframe Branch, ANM–120S, Seattle
Aircraft Certification Office (ACO), FAA,
1601 Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6513; fax: 425–917–
6590; email: narinder.luthra@faa.gov.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
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(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) Boeing Alert Service Bulletin 747–
54A2238, dated January 31, 2014.
(ii) Reserved.
(3) 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.
(4) You may view this service information
at FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA 98057–3356.
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
September 12, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–22468 Filed 9–25–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0291; Directorate
Identifier 2013–NM–137–AD; Amendment
39–17972; AD 2014–19–04]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2004–03–
19, which applies to certain Airbus
Model A320–111, –211 and –231 series
airplanes. AD 2004–03–19 required
repetitive inspections for cracking in the
transition and pick-up angles in the
lower part of the center fuselage area,
and corrective action if necessary. AD
2004–03–19 also provided for an
optional terminating modification for
the repetitive inspection requirements.
This new AD requires accomplishing
the modification by installing washers
between the transition pick-up angle
SUMMARY:
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57753
and the pin nuts, and doing related
investigative and corrective actions if
necessary. This new AD also adds
airplanes to the applicability of AD
2004–03–19. This AD was prompted by
a determination that the optional
terminating modification must be
required in order to address the unsafe
condition. We are issuing this AD to
prevent fatigue cracking in the
transition and pick-up angles of the
lower part of the center fuselage, which
could result in reduced structural
integrity of the wing-fuselage support
and fuselage pressure vessel.
DATES: This AD becomes effective
October 31, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 15, 2004 (69 FR 5922,
February 9, 2004).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0291; or in
person at the 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.
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
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 supersede AD 2004–03–19,
Amendment 39–13463 (69 FR 5922,
February 9, 2004). AD 2004–03–19
applied to certain Airbus Model A320–
111, –211, and –231 series airplanes.
The NPRM published in the Federal
Register on May 30, 2014 (79 FR 31057).
The NPRM was prompted by a
determination that the optional
terminating modification must be
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required in order to address the unsafe
condition. The NPRM proposed to
require repetitive inspections for
cracking in the transition and pick-up
angles in the lower part of the center
fuselage area, and corrective action if
necessary. The NPRM also proposed to
require a terminating modification for
the repetitive inspection requirements.
The NPRM also proposed to add
airplanes to the applicability. We are
issuing this AD to prevent fatigue
cracking in the transition and pick-up
angles of the lower part of the center
fuselage, which could result in reduced
structural integrity of the wing-fuselage
support and fuselage pressure vessel.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2013–0137,
dated July 9, 2013 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus Model A320–111,
–211, and –231 series airplanes. The
MCAI states:
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During the A320 fatigue test campaign, it
has been determined that fatigue damage
could appear on the transition and pick-up
angle between Frame (FR) 35 and FR36.
This condition, if not detected and
corrected, could affect the structural integrity
of the aeroplane.
To address this potential unsafe condition,
´ ´
DGAC [Direction Generale de l’Aviation
Civile] France issued AD 2002–183 [related
to FAA AD 2004–03–19, Amendment 39–
13463 (69 FR 5922, February 9, 2004)], to
require repetitive inspections of the center
fuselage pick-up angle between FR35 and
FR36, below stringer 30, left hand (LH) and
right hand (RH) sides, and, depending on
findings, accomplishment of applicable
corrective action(s).
Since that [DGAC] AD [2002–183] was
issued, a modification was developed, which
has been published through Airbus Service
Bulletin (SB) A320–53–1027 for in-service
application, introducing additional washers
below the riveting, which constitutes
terminating action for the repetitive
inspections.
For the reasons described above, this
[EASA] AD retains the requirements of DGAC
France AD 2002–183, which is superseded,
and requires modification of the transition
and pick-up angle between FR35 and FR36.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-02910002.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (79
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FR 31057, May 30, 2014) or on the
determination of the cost to the public.
‘‘Contacting the Manufacturer’’
Paragraph in this AD
Since late 2006, we have included a
standard paragraph titled ‘‘Airworthy
Product’’ in all MCAI ADs in which the
FAA develops an AD based on a foreign
authority’s AD.
The MCAI or referenced service
information in an FAA AD often directs
the owner/operator to contact the
manufacturer for corrective actions,
such as a repair. Briefly, the Airworthy
Product paragraph allowed owners/
operators to use corrective actions
provided by the manufacturer if those
actions were FAA-approved. In
addition, the paragraph stated that any
actions approved by the State of Design
Authority (or its delegated agent) are
considered to be FAA-approved.
In the NPRM (79 FR 11016, February
27, 2014), we proposed to prevent the
use of repairs that were not specifically
developed to correct the unsafe
condition, by requiring that the repair
approval provided by the State of
Design Authority or its delegated agent
specifically refer to this FAA AD. This
change was intended to clarify the
method of compliance and to provide
operators with better visibility of repairs
that are specifically developed and
approved to correct the unsafe
condition. In addition, for certain new
requirements, we proposed to change
the phrase ‘‘its delegated agent’’ to
include a design approval holder (DAH)
with State of Design Authority design
organization approval (DOA), as
applicable, to refer to a DAH authorized
to approve required repairs for the
proposed AD.
No comments were provided to the
NPRM (79 FR 11016, February 27, 2014)
about these proposed changes. However,
a comment was provided for an NPRM
having Directorate Identifier 2012–NM–
101–AD (78 FR 78285, December 26,
2013). The commenter stated the
following: ‘‘The proposed wording,
being specific to repairs, eliminates the
interpretation that Airbus messages are
acceptable for approving minor
deviations (corrective actions) needed
during accomplishment of an AD
mandated Airbus service bulletin.’’
This comment has made the FAA
aware that some operators have
misunderstood or misinterpreted the
Airworthy Product paragraph to allow
the owner/operator to use messages
provided by the manufacturer as
approval of deviations during the
accomplishment of an AD-mandated
action. The Airworthy Product
paragraph does not approve messages or
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other information provided by the
manufacturer for deviations to the
requirements of the AD-mandated
actions. The Airworthy Product
paragraph only addresses the
requirement to contact the manufacturer
for corrective actions for the identified
unsafe condition and does not cover
deviations from other AD requirements.
However, deviations to AD-required
actions are addressed in 14 CFR 39.17,
and anyone may request the approval
for an alternative method of compliance
to the AD-required actions using the
procedures found in 14 CFR 39.19.
To address this misunderstanding and
misinterpretation of the Airworthy
Product paragraph, we have changed the
paragraph and retitled it ‘‘Contacting the
Manufacturer.’’ This paragraph now
clarifies that for any requirement in this
AD to obtain corrective actions from a
manufacturer, the actions must be
accomplished using a method approved
by the FAA, the European Aviation
Safety Agency (EASA), or Airbus’s
EASA Design Organization Approval
(DOA).
The Contacting the Manufacturer
paragraph also clarifies that, if approved
by the DOA, the approval must include
the DOA-authorized signature. The DOA
signature indicates that the data and
information contained in the document
are EASA-approved, which is also FAAapproved. Messages and other
information provided by the
manufacturer that do not contain the
DOA-authorized signature approval are
not EASA-approved, unless EASA
directly approves the manufacturer’s
message or other information.
This clarification does not remove
flexibility previously afforded by the
Airworthy Product paragraph.
Consistent with long-standing FAA
policy, such flexibility was never
intended for required actions. This is
also consistent with the
recommendation of the Airworthiness
Directive Implementation Aviation
Rulemaking Committee to increase
flexibility in complying with ADs by
identifying those actions in
manufacturers’ service instructions that
are ‘‘Required for Compliance’’ with
ADs. We continue to work with
manufacturers to implement this
recommendation. But once we
determine that an action is required, any
deviation from the requirement must be
approved as an alternative method of
compliance.
Other commenters to the NPRM
having Directorate Identifier 2012–NM–
101–AD (78 FR 78285, December 26,
2013) pointed out that in many cases the
foreign manufacturer’s service bulletin
and the foreign authority’s MCAI might
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have been issued some time before the
FAA AD. Therefore, the DOA might
have provided U.S. operators with an
approved repair, developed with full
awareness of the unsafe condition,
before the FAA AD is issued. Under
these circumstances, to comply with the
FAA AD, the operator would be
required to go back to the
manufacturer’s DOA and obtain a new
approval document, adding time and
expense to the compliance process with
no safety benefit.
Based on these comments, we
removed the requirement that the DAHprovided repair specifically refer to this
AD. Before adopting such a
requirement, the FAA will coordinate
with affected DAHs and verify they are
prepared to implement means to ensure
57755
that their repair approvals consider the
unsafe condition addressed in this AD.
Any such requirements will be adopted
through the normal AD rulemaking
process, including notice-and-comment
procedures, when appropriate.
We also have decided not to include
a generic reference to either the
‘‘delegated agent’’ or ‘‘DAH with State of
Design Authority design organization
approval,’’ but instead we have
provided the specific delegation
approval granted by EASA for the DAH.
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
31057, May 30, 2014) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 31057,
May 30, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Conclusion
Costs of Compliance
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
We estimate that this AD affects 482
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Inspection [retained action
9 work-hours × $85 per hour =
from AD 2004–03–19,
$765 per inspection cycle.
Amendment 39–13463 (69
FR 5922, February 9, 2004)].
Inspection for Model A320–212 9 work-hours × $85 per hour =
airplanes [new action].
$765 per inspection cycle.
Terminating modification [new
28 work-hours × $85 per hour
action].
= $2,380.
Authority for This Rulemaking
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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
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Parts cost
$0
$765 per inspection cycle .......
$18,360 per inspection cycle
(24 airplanes).
$0
$765 per inspection cycle .......
$1,837
$4,217 .....................................
$32,130 per inspection cycle
(42 airplanes).
$2,032,594.
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.
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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0291; 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 street address for the
Docket Operations office (telephone
800–647–5527) is in the ADDRESSES
section.
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Cost on U.S.
operators
Cost per product
Fmt 4700
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2004–03–19, Amendment 39–13463 (69
FR 5922, February 9, 2004), and adding
the following new AD:
■
2014–19–04 Airbus: Amendment 39–17972.
Docket No. FAA–2014–0291; Directorate
Identifier 2013–NM–137–AD.
(a) Effective Date
This AD becomes effective October 31,
2014.
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(b) Affected ADs
This AD replaces AD 2004–03–19,
Amendment 39–13463 (69 FR 5922, February
9, 2004).
(c) Applicability
This AD applies to Airbus Model A320–
111, –211, –212, and –231 airplanes,
certificated in any category, all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by the
determination that the modification must be
accomplished in order to address the unsafe
condition. We are issuing this AD to prevent
fatigue cracking in the transition and pick-up
angles of the lower part of the center
fuselage, which could result in reduced
structural integrity of the wing-fuselage
support and fuselage pressure vessel.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Detailed and Rotating Probe
Inspections
This paragraph restates the requirements of
paragraph (b) of AD 2004–03–19,
Amendment 39–13463 (69 FR 5922, February
9, 2004). For Model A320–111, –211, and
–231 airplanes on which the modification
specified in AD 98–12–18, Amendment 39–
10573 (63 FR 31345, June 9, 1998), has not
been done: Do the applicable inspections
specified in paragraphs (g)(1) and (g)(2) of
this AD, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1028, Revision 01,
dated February 12, 2002.
(1) For airplanes on which the inspections
required by AD 98–12–18, Amendment 39–
10573 (63 FR 31345, June 9, 1998), have been
done: Within 12,000 flight cycles after
accomplishment of the last inspection
required by AD 98–12–18, do a detailed
inspection of the transition angle and a
rotating probe inspection of the pick-up angle
in the lower part of the center fuselage area
for cracking.
(2) For airplanes on which the inspections
required by AD 98–12–18, Amendment 39–
10573 (63 FR 31345, June 9, 1998), have not
been done: At the later of the times specified
in paragraphs (g)(2)(i) and (g)(2)(ii) of this
AD, do a detailed inspection of the transition
angle and a rotating probe inspection of the
pick-up angle in the lower part of the center
fuselage area for cracking.
(i) Before the accumulation of 10,400 total
flight cycles, or 24,600 total flight hours,
whichever is first.
(ii) Before the accumulation of 16,000 total
flight cycles, or within 3,500 flight cycles
after March 15, 2004 (the effective date of AD
2004–03–19, Amendment 39–13463 (69 FR
5922, February 9, 2004), whichever is first.
(h) Retained Repetitive Inspections
This paragraph restates the requirements of
paragraph (c) of AD 2004–03–19,
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Amendment 39–13463 (69 FR 5922, February
9, 2004). For Model A320–111, –211, and
–231 airplanes: Repeat the detailed and
rotating probe inspections specified in
paragraphs (g)(1) and (g)(2) of this AD at
intervals not to exceed 10,400 flight cycles or
24,600 flight hours, whichever is first, until
the modification specified in paragraph (m)
of this AD has been done.
(i) Retained Corrective Action for
Paragraphs (g) and (h) of This AD
This paragraph restates the requirements of
paragraph (d) of AD 2004–03–19,
Amendment 39–13463 (69 FR 5922, February
9, 2004), with specific delegation approval
language. For Model A320–111, –211, and
–231 airplanes: If any cracking is found
during any inspection required by paragraph
(g) or (h) of this AD, prior to further flight,
either repair the cracking per the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1028, Revision 01,
dated February 12, 2002; or do the
modification specified in paragraph (m) of
this AD. Where Airbus Service Bulletin
A320–53–1028, Revision 01, dated February
12, 2002, specifies to contact the
manufacturer for repair instructions, prior to
further flight, repair the cracking in
accordance with 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); or the Direction Generale
de l’Aviation Civile (or its delegated agent).
If the cracking is repaired, repeat the
inspections as required by paragraph (h) of
this AD.
(j) New Detailed and Rotating Probe
Inspections for Model A320–212 Airplanes
For Model A320–212 airplanes on which
the modification specified in Airbus Service
Bulletin A320–53–1027 has not been done as
of the effective date of this AD: Do the
applicable inspections specified in paragraph
(j)(1) or (j)(2) of this AD, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A320–53–1028, Revision 01,
dated February 12, 2002.
(1) For airplanes on which the inspections
specified in Airbus Service Bulletin A320–
53–1028 have been done as of the effective
date of this AD: At the later of the times
specified in paragraphs (j)(1)(i) and (j)(1)(ii)
of this AD, do a detailed inspection of the
transition angle and a rotating probe
inspection of the pick-up angle in the lower
part of the center fuselage area for cracking.
(i) Within 10,400 flight cycles or 24,600
flight hours, whichever occurs first after
accomplishing the most recent inspection
specified in Airbus Service Bulletin A320–
53–1028.
(ii) Within 90 days after the effective date
of this AD.
(2) For airplanes on which the inspections
specified in Airbus Service Bulletin A320–
53–1028 have not been done as of the
effective date of this AD: At the later of the
times specified in paragraphs (j)(2)(i) and
(j)(2)(ii) of this AD, do a detailed inspection
of the transition angle and a rotating probe
inspection of the pick-up angle in the lower
part of the center fuselage area for cracking.
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(i) Before the accumulation of 10,400 total
flight cycles, or 24,600 total flight hours,
whichever occurs first.
(ii) Within 90 days after the effective date
of this AD.
(k) New Repetitive Inspections for Model
A320–212 Airplanes
For Model A320–212 airplanes: Repeat the
detailed and rotating probe inspections
specified in paragraphs (j)(1) and (j)(2) of this
AD at intervals not to exceed 10,400 flight
cycles or 24,600 flight hours, whichever
occurs first, until the modification specified
in paragraph (m) of this AD has been done.
(l) New Corrective Action for Model A320–
212 Airplanes
For Model A320–212 airplanes: If any
cracking is found during any inspection
required by paragraph (j) or (k) of this AD,
before further flight, do the actions specified
in either paragraph (l)(1) or (l)(2) of this AD.
(1) Repair the crack in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1028, Revision 01,
dated February 12, 2002, except where
Airbus Service Bulletin A320–53–1028,
Revision 01, dated February 12, 2002,
specifies to contact the manufacturer, before
further flight, repair 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). After
the cracking is repaired, repeat the
inspections required by paragraph (k) of this
AD.
(2) Do the modification specified in
paragraph (m) of this AD.
(m) New Terminating Modification for All
Airplanes
For all airplanes: Before the accumulation
of 40,000 flight cycles since first flight, or
within 1,500 flight cycles after the effective
date of this AD, whichever occurs later, but
not exceeding 48,000 flight cycles since first
flight, modify by doing rotating probe
inspections for cracking of certain fastener
holes, replacing transition angles if any
cracking is found in the transition angles,
repairing if any pick-up angles cracking is
found, and installing washers between the
transition pick-up angle and the pin nuts; in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1027, Revision 03, dated February 12,
2002, except where Airbus Service Bulletin
A320–53–1027, Revision 03, dated February
12, 2001, specifies to contact Airbus, before
further flight, repair 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).
Accomplishment of this modification
terminates the repetitive inspections required
by paragraphs (h) and (k) of this AD.
(n) Terminating Modification
For airplanes on which Airbus
Modification 21202 has been embodied in
production: No actions are required by this
AD.
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(o) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraph (j) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A320–53–1028, dated March 1,
1994, which was incorporated by reference in
AD 98–12–18, Amendment 39–10573 (63 FR
31345, June 9, 1998).
(2) This paragraph provides credit for the
action specified in paragraph (m) of this AD,
if that action was performed before the
effective date of this AD using the service
information specified in paragraph (o)(2)(i),
(o)(2)(ii), or (o)(2)(iii) of this AD, which is not
incorporated by reference in this AD.
(i) Airbus Service Bulletin A320–53–1027,
dated March 1, 1994.
(ii) Airbus Service Bulletin A320–53–1027,
Revision 1, dated September 5, 1994.
(iii) Airbus Service Bulletin A320–53–
1027, Revision 2, dated June 8, 1995 (which
was incorporated by reference in AD 98–12–
18, Amendment 39–10573 (63 FR 31345,
June 9, 1998)).
(p) 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-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 in
accordance with AD 2004–03–19,
Amendment 39–13463 (69 FR 5922, February
9, 2004), are approved as AMOCs for the
corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, 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
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(q) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency Airworthiness
VerDate Sep<11>2014
17:52 Sep 25, 2014
Jkt 232001
Directive 2013–0137, dated July 9, 2013, for
related information. You may examine the
MCAI in the AD docket on the Internet at
https://www.regulations.gov/
#!documentDetail;D=FAA-2014-0291-0002.
(2) Service information identified in this
AD that is not incorporated by reference in
this AD is available at the addresses specified
in paragraphs (r)(4) and (r)(5) of this AD.
(r) 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 this AD specifies otherwise.
(3) The following service information was
approved for IBR on March 15, 2004 (69 FR
5922, February 9, 2004).
(i) Airbus Service Bulletin A320–53–1027,
Revision 03, dated February 12, 2002.
(ii) Airbus Service Bulletin A320–53–1028,
Revision 01, dated February 12, 2002.
(4) 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.
(5) 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.
(6) 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
September 12, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
57757
Tri-Area Class B airspace area to include
exclusion of restricted area R–4001C
from the Class B airspace when the
restricted area is active. The remainder
of the Class B description is not affected
by this change.
DATES: Effective date: 0901 UTC
September 26, 2014. The Director of the
Federal Register approves this
incorporation by reference action under
1 CFR part 51, subject to the annual
revision of FAA Order 7400.9 and
publication of conforming amendments.
ADDRESSES: FAA Order 7400.9Y,
Airspace Designations and Reporting
Points, and subsequent amendments can
be viewed online at https://www.faa.gov/
air_traffic/publications/. The Order is
also available for inspection 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://archives.gov/federal_
register/code_of_federal-regulations/ibr_
locations.html.
FAA Order 7400.9, Airspace
Designations and Reporting Points, is
published yearly and effective on
September 15. For further information,
you can contact the Airspace Policy and
Regulations Group, Federal Aviation
Administration, 800 Independence
Avenue SW., Washington, DC 20591;
telephone: 202–267–8783.
FOR FURTHER INFORMATION CONTACT: Paul
Gallant, Airspace Policy and
Regulations Group, Office of Airspace
Services, Federal Aviation
Administration, 800 Independence
Avenue SW., Washington, DC 20591;
telephone: (202) 267–8783.
SUPPLEMENTARY INFORMATION:
AGENCY:
Background
On May 23, 2014, the FAA published
a final rule establishing restricted area
R–4001C at Aberdeen Proving Ground,
MD (79 FR 29661). R–4001C was formed
by further subdividing small sections of
existing restricted areas R–4001A and
R–4001B that currently extend into Area
D of the Washington, DC, Tri-Area Class
B airspace area. The description of Area
D excludes the airspace in restricted
areas R–4001A and B from the Class B
airspace. This change simply updates
that description to add R–4001C (which
is imbedded within R–4001A and R–
4001B) to the exclusionary language.
Aeronautical charts have been updated
to reflect this information.
This action amends the
description of Area D of the Washington
The Rule
The FAA is amending Title 14 Code
of Federal Regulations (14 CFR) part 71
to update the description of Area D in
the Washington Tri-Area Class B
[FR Doc. 2014–22469 Filed 9–25–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2014–0713; Airspace
Docket No. 14–AWA–1]
RIN 2120–AA66
Amendment of Class B Airspace;
Washington Tri-Area, DC
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; technical
amendment.
SUMMARY:
PO 00000
Frm 00055
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]]>Agencies
[Federal Register Volume 79, Number 187 (Friday, September 26, 2014)]
[Rules and Regulations]
[Pages 57753-57757]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-22469]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0291; Directorate Identifier 2013-NM-137-AD;
Amendment 39-17972; AD 2014-19-04]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2004-03-19,
which applies to certain Airbus Model A320-111, -211 and -231 series
airplanes. AD 2004-03-19 required repetitive inspections for cracking
in the transition and pick-up angles in the lower part of the center
fuselage area, and corrective action if necessary. AD 2004-03-19 also
provided for an optional terminating modification for the repetitive
inspection requirements. This new AD requires accomplishing the
modification by installing washers between the transition pick-up angle
and the pin nuts, and doing related investigative and corrective
actions if necessary. This new AD also adds airplanes to the
applicability of AD 2004-03-19. This AD was prompted by a determination
that the optional terminating modification must be required in order to
address the unsafe condition. We are issuing this AD to prevent fatigue
cracking in the transition and pick-up angles of the lower part of the
center fuselage, which could result in reduced structural integrity of
the wing-fuselage support and fuselage pressure vessel.
DATES: This AD becomes effective October 31, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 15,
2004 (69 FR 5922, February 9, 2004).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0291; or in person at the
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.
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 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 supersede AD 2004-03-19, Amendment 39-13463 (69 FR 5922,
February 9, 2004). AD 2004-03-19 applied to certain Airbus Model A320-
111, -211, and -231 series airplanes. The NPRM published in the Federal
Register on May 30, 2014 (79 FR 31057). The NPRM was prompted by a
determination that the optional terminating modification must be
[[Page 57754]]
required in order to address the unsafe condition. The NPRM proposed to
require repetitive inspections for cracking in the transition and pick-
up angles in the lower part of the center fuselage area, and corrective
action if necessary. The NPRM also proposed to require a terminating
modification for the repetitive inspection requirements. The NPRM also
proposed to add airplanes to the applicability. We are issuing this AD
to prevent fatigue cracking in the transition and pick-up angles of the
lower part of the center fuselage, which could result in reduced
structural integrity of the wing-fuselage support and fuselage pressure
vessel.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2013-0137, dated July 9, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A320-111, -211, and -231 series airplanes. The MCAI states:
During the A320 fatigue test campaign, it has been determined
that fatigue damage could appear on the transition and pick-up angle
between Frame (FR) 35 and FR36.
This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
To address this potential unsafe condition, DGAC [Direction
G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 2002-
183 [related to FAA AD 2004-03-19, Amendment 39-13463 (69 FR 5922,
February 9, 2004)], to require repetitive inspections of the center
fuselage pick-up angle between FR35 and FR36, below stringer 30,
left hand (LH) and right hand (RH) sides, and, depending on
findings, accomplishment of applicable corrective action(s).
Since that [DGAC] AD [2002-183] was issued, a modification was
developed, which has been published through Airbus Service Bulletin
(SB) A320-53-1027 for in-service application, introducing additional
washers below the riveting, which constitutes terminating action for
the repetitive inspections.
For the reasons described above, this [EASA] AD retains the
requirements of DGAC France AD 2002-183, which is superseded, and
requires modification of the transition and pick-up angle between
FR35 and FR36.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0291-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (79 FR 31057, May 30,
2014) or on the determination of the cost to the public.
``Contacting the Manufacturer'' Paragraph in this AD
Since late 2006, we have included a standard paragraph titled
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD
based on a foreign authority's AD.
The MCAI or referenced service information in an FAA AD often
directs the owner/operator to contact the manufacturer for corrective
actions, such as a repair. Briefly, the Airworthy Product paragraph
allowed owners/operators to use corrective actions provided by the
manufacturer if those actions were FAA-approved. In addition, the
paragraph stated that any actions approved by the State of Design
Authority (or its delegated agent) are considered to be FAA-approved.
In the NPRM (79 FR 11016, February 27, 2014), we proposed to
prevent the use of repairs that were not specifically developed to
correct the unsafe condition, by requiring that the repair approval
provided by the State of Design Authority or its delegated agent
specifically refer to this FAA AD. This change was intended to clarify
the method of compliance and to provide operators with better
visibility of repairs that are specifically developed and approved to
correct the unsafe condition. In addition, for certain new
requirements, we proposed to change the phrase ``its delegated agent''
to include a design approval holder (DAH) with State of Design
Authority design organization approval (DOA), as applicable, to refer
to a DAH authorized to approve required repairs for the proposed AD.
No comments were provided to the NPRM (79 FR 11016, February 27,
2014) about these proposed changes. However, a comment was provided for
an NPRM having Directorate Identifier 2012-NM-101-AD (78 FR 78285,
December 26, 2013). The commenter stated the following: ``The proposed
wording, being specific to repairs, eliminates the interpretation that
Airbus messages are acceptable for approving minor deviations
(corrective actions) needed during accomplishment of an AD mandated
Airbus service bulletin.''
This comment has made the FAA aware that some operators have
misunderstood or misinterpreted the Airworthy Product paragraph to
allow the owner/operator to use messages provided by the manufacturer
as approval of deviations during the accomplishment of an AD-mandated
action. The Airworthy Product paragraph does not approve messages or
other information provided by the manufacturer for deviations to the
requirements of the AD-mandated actions. The Airworthy Product
paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified unsafe condition and does not
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request
the approval for an alternative method of compliance to the AD-required
actions using the procedures found in 14 CFR 39.19.
To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed the paragraph and retitled
it ``Contacting the Manufacturer.'' This paragraph now clarifies that
for any requirement in this AD to obtain corrective actions from a
manufacturer, the actions must be accomplished using a method approved
by the FAA, the European Aviation Safety Agency (EASA), or Airbus's
EASA Design Organization Approval (DOA).
The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DOA, the approval must include the DOA-authorized
signature. The DOA signature indicates that the data and information
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or
other information.
This clarification does not remove flexibility previously afforded
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.
Other commenters to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) pointed out that in many cases
the foreign manufacturer's service bulletin and the foreign authority's
MCAI might
[[Page 57755]]
have been issued some time before the FAA AD. Therefore, the DOA might
have provided U.S. operators with an approved repair, developed with
full awareness of the unsafe condition, before the FAA AD is issued.
Under these circumstances, to comply with the FAA AD, the operator
would be required to go back to the manufacturer's DOA and obtain a new
approval document, adding time and expense to the compliance process
with no safety benefit.
Based on these comments, we removed the requirement that the DAH-
provided repair specifically refer to this AD. Before adopting such a
requirement, the FAA will coordinate with affected DAHs and verify they
are prepared to implement means to ensure that their repair approvals
consider the unsafe condition addressed in this AD. Any such
requirements will be adopted through the normal AD rulemaking process,
including notice-and-comment procedures, when appropriate.
We also have decided not to include a generic reference to either
the ``delegated agent'' or ``DAH with State of Design Authority design
organization approval,'' but instead we have provided the specific
delegation approval granted by EASA for the DAH.
Conclusion
We reviewed the relevant data 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
minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 31057, May 30, 2014) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 31057, May 30, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 482 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection [retained action from 9 work-hours x $85 $0 $765 per inspection $18,360 per
AD 2004-03-19, Amendment 39- per hour = $765 per cycle. inspection cycle
13463 (69 FR 5922, February 9, inspection cycle. (24 airplanes).
2004)].
Inspection for Model A320-212 9 work-hours x $85 $0 $765 per inspection $32,130 per
airplanes [new action]. per hour = $765 per cycle. inspection cycle
inspection cycle. (42 airplanes).
Terminating modification [new 28 work-hours x $85 $1,837 $4,217.............. $2,032,594.
action]. per hour = $2,380.
----------------------------------------------------------------------------------------------------------------
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 AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0291; 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 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 removing Airworthiness Directive (AD)
2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004), and
adding the following new AD:
2014-19-04 Airbus: Amendment 39-17972. Docket No. FAA-2014-0291;
Directorate Identifier 2013-NM-137-AD.
(a) Effective Date
This AD becomes effective October 31, 2014.
[[Page 57756]]
(b) Affected ADs
This AD replaces AD 2004-03-19, Amendment 39-13463 (69 FR 5922,
February 9, 2004).
(c) Applicability
This AD applies to Airbus Model A320-111, -211, -212, and -231
airplanes, certificated in any category, all manufacturer serial
numbers.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by the determination that the modification
must be accomplished in order to address the unsafe condition. We
are issuing this AD to prevent fatigue cracking in the transition
and pick-up angles of the lower part of the center fuselage, which
could result in reduced structural integrity of the wing-fuselage
support and fuselage pressure vessel.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Detailed and Rotating Probe Inspections
This paragraph restates the requirements of paragraph (b) of AD
2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004). For
Model A320-111, -211, and -231 airplanes on which the modification
specified in AD 98-12-18, Amendment 39-10573 (63 FR 31345, June 9,
1998), has not been done: Do the applicable inspections specified in
paragraphs (g)(1) and (g)(2) of this AD, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-53-1028,
Revision 01, dated February 12, 2002.
(1) For airplanes on which the inspections required by AD 98-12-
18, Amendment 39-10573 (63 FR 31345, June 9, 1998), have been done:
Within 12,000 flight cycles after accomplishment of the last
inspection required by AD 98-12-18, do a detailed inspection of the
transition angle and a rotating probe inspection of the pick-up
angle in the lower part of the center fuselage area for cracking.
(2) For airplanes on which the inspections required by AD 98-12-
18, Amendment 39-10573 (63 FR 31345, June 9, 1998), have not been
done: At the later of the times specified in paragraphs (g)(2)(i)
and (g)(2)(ii) of this AD, do a detailed inspection of the
transition angle and a rotating probe inspection of the pick-up
angle in the lower part of the center fuselage area for cracking.
(i) Before the accumulation of 10,400 total flight cycles, or
24,600 total flight hours, whichever is first.
(ii) Before the accumulation of 16,000 total flight cycles, or
within 3,500 flight cycles after March 15, 2004 (the effective date
of AD 2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004),
whichever is first.
(h) Retained Repetitive Inspections
This paragraph restates the requirements of paragraph (c) of AD
2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004). For
Model A320-111, -211, and -231 airplanes: Repeat the detailed and
rotating probe inspections specified in paragraphs (g)(1) and (g)(2)
of this AD at intervals not to exceed 10,400 flight cycles or 24,600
flight hours, whichever is first, until the modification specified
in paragraph (m) of this AD has been done.
(i) Retained Corrective Action for Paragraphs (g) and (h) of This AD
This paragraph restates the requirements of paragraph (d) of AD
2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004), with
specific delegation approval language. For Model A320-111, -211, and
-231 airplanes: If any cracking is found during any inspection
required by paragraph (g) or (h) of this AD, prior to further
flight, either repair the cracking per the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1028, Revision 01,
dated February 12, 2002; or do the modification specified in
paragraph (m) of this AD. Where Airbus Service Bulletin A320-53-
1028, Revision 01, dated February 12, 2002, specifies to contact the
manufacturer for repair instructions, prior to further flight,
repair the cracking in accordance with 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); or the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (or its delegated
agent). If the cracking is repaired, repeat the inspections as
required by paragraph (h) of this AD.
(j) New Detailed and Rotating Probe Inspections for Model A320-212
Airplanes
For Model A320-212 airplanes on which the modification specified
in Airbus Service Bulletin A320-53-1027 has not been done as of the
effective date of this AD: Do the applicable inspections specified
in paragraph (j)(1) or (j)(2) of this AD, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-53-1028,
Revision 01, dated February 12, 2002.
(1) For airplanes on which the inspections specified in Airbus
Service Bulletin A320-53-1028 have been done as of the effective
date of this AD: At the later of the times specified in paragraphs
(j)(1)(i) and (j)(1)(ii) of this AD, do a detailed inspection of the
transition angle and a rotating probe inspection of the pick-up
angle in the lower part of the center fuselage area for cracking.
(i) Within 10,400 flight cycles or 24,600 flight hours,
whichever occurs first after accomplishing the most recent
inspection specified in Airbus Service Bulletin A320-53-1028.
(ii) Within 90 days after the effective date of this AD.
(2) For airplanes on which the inspections specified in Airbus
Service Bulletin A320-53-1028 have not been done as of the effective
date of this AD: At the later of the times specified in paragraphs
(j)(2)(i) and (j)(2)(ii) of this AD, do a detailed inspection of the
transition angle and a rotating probe inspection of the pick-up
angle in the lower part of the center fuselage area for cracking.
(i) Before the accumulation of 10,400 total flight cycles, or
24,600 total flight hours, whichever occurs first.
(ii) Within 90 days after the effective date of this AD.
(k) New Repetitive Inspections for Model A320-212 Airplanes
For Model A320-212 airplanes: Repeat the detailed and rotating
probe inspections specified in paragraphs (j)(1) and (j)(2) of this
AD at intervals not to exceed 10,400 flight cycles or 24,600 flight
hours, whichever occurs first, until the modification specified in
paragraph (m) of this AD has been done.
(l) New Corrective Action for Model A320-212 Airplanes
For Model A320-212 airplanes: If any cracking is found during
any inspection required by paragraph (j) or (k) of this AD, before
further flight, do the actions specified in either paragraph (l)(1)
or (l)(2) of this AD.
(1) Repair the crack in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1028, Revision 01,
dated February 12, 2002, except where Airbus Service Bulletin A320-
53-1028, Revision 01, dated February 12, 2002, specifies to contact
the manufacturer, before further flight, repair 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). After
the cracking is repaired, repeat the inspections required by
paragraph (k) of this AD.
(2) Do the modification specified in paragraph (m) of this AD.
(m) New Terminating Modification for All Airplanes
For all airplanes: Before the accumulation of 40,000 flight
cycles since first flight, or within 1,500 flight cycles after the
effective date of this AD, whichever occurs later, but not exceeding
48,000 flight cycles since first flight, modify by doing rotating
probe inspections for cracking of certain fastener holes, replacing
transition angles if any cracking is found in the transition angles,
repairing if any pick-up angles cracking is found, and installing
washers between the transition pick-up angle and the pin nuts; in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-53-1027, Revision 03, dated February 12, 2002, except
where Airbus Service Bulletin A320-53-1027, Revision 03, dated
February 12, 2001, specifies to contact Airbus, before further
flight, repair 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). Accomplishment of this modification
terminates the repetitive inspections required by paragraphs (h) and
(k) of this AD.
(n) Terminating Modification
For airplanes on which Airbus Modification 21202 has been
embodied in production: No actions are required by this AD.
[[Page 57757]]
(o) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraph (j) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A320-53-
1028, dated March 1, 1994, which was incorporated by reference in AD
98-12-18, Amendment 39-10573 (63 FR 31345, June 9, 1998).
(2) This paragraph provides credit for the action specified in
paragraph (m) of this AD, if that action was performed before the
effective date of this AD using the service information specified in
paragraph (o)(2)(i), (o)(2)(ii), or (o)(2)(iii) of this AD, which is
not incorporated by reference in this AD.
(i) Airbus Service Bulletin A320-53-1027, dated March 1, 1994.
(ii) Airbus Service Bulletin A320-53-1027, Revision 1, dated
September 5, 1994.
(iii) Airbus Service Bulletin A320-53-1027, Revision 2, dated
June 8, 1995 (which was incorporated by reference in AD 98-12-18,
Amendment 39-10573 (63 FR 31345, June 9, 1998)).
(p) 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.
(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 in accordance with AD 2004-03-19,
Amendment 39-13463 (69 FR 5922, February 9, 2004), are approved as
AMOCs for the corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, 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 the European Aviation Safety Agency
(EASA); or Airbus's EASA Design Organization Approval (DOA). If
approved by the DOA, the approval must include the DOA-authorized
signature.
(q) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency Airworthiness Directive 2013-
0137, dated July 9, 2013, for related information. You may examine
the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0291-0002.
(2) Service information identified in this AD that is not
incorporated by reference in this AD is available at the addresses
specified in paragraphs (r)(4) and (r)(5) of this AD.
(r) 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 this AD specifies otherwise.
(3) The following service information was approved for IBR on
March 15, 2004 (69 FR 5922, February 9, 2004).
(i) Airbus Service Bulletin A320-53-1027, Revision 03, dated
February 12, 2002.
(ii) Airbus Service Bulletin A320-53-1028, Revision 01, dated
February 12, 2002.
(4) 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.
(5) 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.
(6) 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 September 12, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-22469 Filed 9-25-14; 8:45 am]
BILLING CODE 4910-13-P
