Airworthiness Directives; Airbus Airplanes, 26492-26496 [2015-10949]
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Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules
Flight Standards District Office, as
appropriate. If sending information directly
to the ACO, send it to ATTN: Program
Manager, Continuing Operational Safety,
FAA, New York ACO, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone:
516–228–7300; fax: 516–794–5531. 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) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, New York ACO, ANE–170,
FAA; or TCCA; or Bombardier, Inc.’s TCCA
DAO. If approved by the DAO, the approval
must include the DAO-authorized signature.
(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2014–32, dated
September 8, 2014, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2015–0929.
(2) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone: 514–855–5000; fax: 514–
855–7401; email thd.crj@
aero.bombardier.com; Internet https://
www.bombardier.com. You may view this
service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA, call
425–227–1221.
Issued in Renton, Washington, on April 13,
2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–10947 Filed 5–7–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–1275; Directorate
Identifier 2014–NM–070–AD]
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2004–14–
09, for certain Airbus Model A320–211,
–212, and –231 airplanes. AD 2004–14–
SUMMARY:
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09 currently requires repetitive
inspections for fatigue cracking of the
lower surface panel on the wing center
box, and repair if necessary; and
modification of the lower surface panel
on the wing center box, which
constitutes terminating action for the
repetitive inspections. Since we issued
AD 2004–14–09, we have determined
that, based on the average flight
duration, the average weight of fuel at
landing is higher than that defined for
the analysis of the fatigue-related tasks;
and that shot peening might have been
improperly done on the chromic acid
anodizing (CAA) protection, which
would adversely affect fatigue crack
protection. This proposed AD would
reduce the compliance times for the
repetitive inspections, and would
require a repair for certain airplanes. We
are proposing this AD to detect and
correct fatigue cracking of the lower
surface panel on the wing center box,
which could result in reduced structural
integrity of the airplane.
DATES: We must receive comments on
this proposed AD by June 22, 2015.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Airbus,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
1275; or in person at the Docket
Management Facility between 9 a.m.
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and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2015–1275; Directorate Identifier
2014–NM–070–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On June 29, 2004, we issued AD
2004–14–09, Amendment 39–13718 (69
FR 41398, July 9, 2004). AD 2004–14–
09 requires actions intended to address
an unsafe condition on the products
listed above. AD 2004–14–09
superseded AD 98–22–05, Amendment
39–10851 (63 FR 56542, October 22,
1998).
Since we issued AD 2004–14–09,
Amendment 39–13718 (69 FR 41398,
July 9, 2004), we have determined that,
based on the average flight duration, the
average weight of fuel at landing is
higher than that defined for the analysis
of the fatigue-related tasks; and that shot
peening might have been improperly
done on the CAA protection, which
would adversely affect fatigue crack
protection.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0065, dated March 14,
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asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition on certain Model
A320–211, –212, and –231 airplanes.
The MCAI states:
During center fuselage certification full
scale test, damage was found in the center
wing box (CWB) lower surface panel.
This condition, if not detected and
corrected, could affect the structural integrity
of the CWB.
To prevent such damage, Airbus developed
mod 22418 which consists in shot-peening of
the lower panel in the related area. Mod
22418 has been embodied in production from
aeroplane [manufacturer serial number]
(MSN) 0359. For unmodified in-service
aeroplanes, Airbus issued Service Bulletin
(SB) A320–57–1082 to introduce repetitive
High Frequency Eddy Current (HFEC)
inspections on the external face of the center
wing box lower panel between Frame (FR) 41
and FR42 to detect damage.
´ ´
DGAC [Direction Generale de l’Aviation
Civile] France issued AD 2002–342 [https://
ad.easa.europa.eu/blob/20023420tb_
superseded.pdf/AD_F-2002-342_1] to require
these inspections and, depending on
findings, applicable corrective action(s).
Airbus also issued SB A320–57–1043 as an
optional terminating action for the repetitive
inspections required by DGAC France AD
2002–342.
Since that [DGAC] AD was issued, the
results of a survey, carried out on the A320
fleet, highlighted some differences between
the mission parameters, mainly on the weight
of fuel at landing and on the average flight
duration, which are higher than those
defined for the analysis of the fatigue related
tasks.
These findings have led to an adjustment
of the A320 reference fatigue mission.
Consequently, the threshold and intervals of
these repetitive inspections have been
revised and a new threshold figure expressed
in flight hours (FH) has been established.
In addition, it has been identified that, on
aeroplanes that have been modified in
accordance with Airbus SB A320–57–1043
(Airbus mod 22418) at Revision 05 or an
earlier Revision, the shot peening may have
been improperly done on the Chromic Acid
Anodizing (CAA) protection, which has no
fatigue benefit effect. Therefore, the
inspections per Airbus SB A320–57–1082 are
required again on these aeroplanes.
Consequently, new shot-peening
procedures with proper CAA protection
removal instructions have been developed
and their embodiment through Airbus SB
A320–57–1043 Revision 06 cancels the
repetitive inspections per Airbus SB A320–
57–1082, as required by DGAC France AD
2002–342.
For the reasons described above, this new
[EASA] AD retains the requirements of DGAC
France AD 2002–342, which is superseded,
but requires these actions to be accomplished
within reduced thresholds and intervals. In
addition, the optional terminating action
provision (SB A320–57–1043) is amended by
including reference to the SB at Revision 06.
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The optional terminating action
described in Airbus Service Bulletin
A320–57–1043, Revision 06, dated
December 5, 2013, is accomplishing
shot peening in the radius of the milling
step between stiffeners 13 and 14 near
the fuel pump aperture.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
1275.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–57–1043, Revision 06, dated
December 5, 2013. This service bulletin
describes procedures for shot peening in
the radius of the milling step between
stiffeners 13 and 14 near the fuel pump
aperture.
Airbus has also issued Service
Bulletin A320–57–1082, Revision 04,
dated December 5, 2013. This service
bulletin describes procedures for
inspections for cracking of the lower
surface panel on the wing center box.
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI. This service information is
reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section of this NPRM.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD
affects 46 airplanes of U.S. registry.
The actions that are required by AD
2004–14–09, Amendment 39–13718 (69
FR 41398, July 9, 2004), and retained in
this proposed AD take about 25 workhours per product, at an average labor
rate of $85 per work-hour. Based on
these figures, the estimated cost of the
actions that were required by AD 2004–
14–09 is $2,125 per product.
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26493
The new requirements of this
proposed AD would add no additional
economic burden.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD. We have
no way of determining the number of
aircraft that might need these actions.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
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Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2004–14–09, Amendment 39–13718 (69
FR 41398, July 9, 2004), and adding the
following new AD:
■
Airbus: Docket No. FAA–2014–1275;
Directorate Identifier 2014–NM–070–AD.
(a) Comments Due Date
We must receive comments by June 22,
2015.
(b) Affected ADs
This AD replaces AD 2004–14–09,
Amendment 39–13718 (69 FR 41398, July 9,
2004).
(c) Applicability
This AD applies to Airbus Model A320–
211, –212, and –231 airplanes, certificated in
any category, all manufacturer serial
numbers, except those on which Airbus
Modification 22418 has been embodied in
production.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by a determination
that, based on the average flight duration, the
average weight of fuel at landing is higher
than that defined for the analysis of the
fatigue-related tasks; and that shot peening
might have been improperly done on the
chromic acid anodizing (CAA) protection,
which would adversely affect fatigue crack
protection. We are issuing this AD to detect
and correct fatigue cracking of the lower
surface panel on the wing center box (WCB),
which could result in reduced structural
integrity of the airplane.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Repetitive Inspections, With No
Changes
This paragraph restates the requirements of
paragraph (a) of AD 2004–14–09,
Amendment 39–13718 (69 FR 41398, July 9,
2004), with no changes. Except as provided
by paragraph (k) of this AD: Prior to the
accumulation of 20,000 total flight cycles, or
within 60 days after November 27, 1998 (the
effective date of AD 98–22–05, Amendment
39–10851 (63 FR 56542, October 22, 1998)),
whichever occurs later, perform a high
frequency eddy current (HFEC) inspection to
detect fatigue cracking of the lower surface
panel on the WCB, in accordance with
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Airbus Service Bulletin A320–57–1082,
Revision 01, dated December 10, 1997; or
Revision 03, dated April 30, 2002. Repeat the
HFEC inspection thereafter at intervals not to
exceed 7,500 flight cycles until the actions
required by paragraph (i) of this AD are
accomplished.
contact Airbus for an appropriate action:
Prior to further flight, repair using a method
approved by the Manager, International
Branch, ANM–116, FAA, Transport Airplane
´ ´
Directorate; or the Direction Generale de
l’Aviation Civile (DGAC) (or its delegated
agent).
(h) Retained Repair, With No Changes
This paragraph restates the requirements of
paragraph (b) of AD 2004–14–09,
Amendment 39–13718 (69 FR 41398, July 9,
2004), with no changes. Except as provided
by paragraph (j) of this AD, if any cracking
is detected during any inspection required by
paragraph (g) of this AD: Prior to further
flight, repair in accordance with Airbus
Service Bulletin A320–57–1082, Revision 01,
dated December 10, 1997; or Revision 03,
dated April 30, 2002. Accomplishment of the
repair constitutes terminating action for the
repetitive inspections required by paragraph
(g) of this AD for the repaired area only.
(k) Retained Provision for Certain Inspection
Exception, With No Changes
This paragraph restates the provision of
paragraph (e) of AD 2004–14–09,
Amendment 39–13718 (69 FR 41398, July 9,
2004), with no changes. The actions required
by paragraph (g) of this AD are not required
to be accomplished if the requirements of
paragraph (i) of this AD are accomplished at
the time specified in paragraph (g) of this AD.
(i) Retained Inspection/Modification/Repair,
With Terminating Action
This paragraph restates the requirements of
paragraph (c) of AD 2004–14–09,
Amendment 39–13718 (69 FR 41398, July 9,
2004), with terminating action provided.
Prior to the accumulation of 25,000 total
flight cycles, or within 60 days after
November 27, 1998 (the effective date of AD
98–22–05, Amendment 39–10851 (63 FR
56542, October 22, 1998)), whichever occurs
later: Perform an HFEC inspection to detect
fatigue cracking of the lower surface panel on
the WCB, in accordance with Airbus Service
Bulletin A320–57–1082, Revision 01, dated
December 10, 1997; or Revision 03, dated
April 30, 2002. Accomplishment of the initial
inspection required by paragraph (p) of this
AD constitutes terminating action for the
inspection requirements of this paragraph.
(1) If no cracking is detected: Prior to
further flight, modify the lower surface panel
on the WCB, in accordance with Airbus
Service Bulletin A320–57–1043, Revision 02,
dated May 14, 1997; or Revision 05, dated
April 30, 2002. Accomplishment of the
modification constitutes terminating action
for the requirements of paragraph (g) of this
AD.
(2) Except as provided by paragraph (j) of
this AD: If any cracking is detected, prior to
further flight, repair in accordance with
Airbus Service Bulletin A320–57–1082,
Revision 01, dated December 10, 1997, or
Revision 03, dated April 30, 2002; and
modify any uncracked area, in accordance
with Airbus Service Bulletin A320–57–1043,
Revision 02, dated May 14, 1997, or Revision
05, dated April 30, 2002. Accomplishment of
the repair of cracked area(s) and modification
of uncracked area(s) constitutes terminating
action for the requirements of paragraph (g)
of this AD.
(j) Retained Service Bulletin Exception, With
No Changes
This paragraph restates the requirements of
paragraph (d) of AD 2004–14–09,
Amendment 39–13718 (69 FR 41398, July 9,
2004), with no changes. If any cracking is
detected during any inspection required by
paragraph (h) or (i)(2) of this AD, and the
applicable service bulletin specifies to
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(l) Retained Initial Inspection, With
Terminating Action
This paragraph restates the requirements of
paragraph (f) of AD 2004–14–09, Amendment
39–13718 (69 FR 41398, July 9, 2004), with
terminating action provided. For airplanes on
which neither the inspection required by
paragraph (g) of this AD, nor the modification
required by paragraph (i)(1) of this AD has
been done before August 13, 2004 (the
effective date of AD 2004–14–09): Perform an
HFEC inspection to detect fatigue cracking of
the lower surface panel on the WCB, in
accordance with Airbus Service Bulletin
A320–57–1082, Revision 01, dated December
10, 1997; or Revision 03, dated April 30,
2002; at the later of the times specified in
paragraphs (l)(1) and (l)(2) of this AD.
Accomplishment of the inspection required
by this paragraph terminates the
requirements of paragraph (g) of this AD.
Accomplishment of the initial inspection
required by paragraph (p) of this AD
terminates the inspection requirements of
this paragraph.
(1) Prior to the accumulation of 13,200
total flight cycles or 39,700 total flight hours,
whichever is first.
(2) Prior to the accumulation of 20,000
total flight cycles, or within 3,500 flight
cycles after August 13, 2004 (the effective
date of AD 2004–14–09, Amendment 39–
13718 (69 FR 41398, July 9, 2004)),
whichever is later.
(m) Retained Repetitive Inspections, With
No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2004–14–09,
Amendment 39–13718 (69 FR 41398, July 9,
2004), with no changes. If no cracking is
detected during the inspection required by
paragraph (g) or (l) of this AD: Repeat the
inspection required by paragraph (l) of this
AD at the applicable time specified in
paragraph (m)(1) or (m)(2) of this AD.
Accomplishment of the modification
required by paragraph (i)(1) of this AD
terminates the requirements of this
paragraph.
(1) For airplanes on which the inspections
required by paragraph (g) of this AD have
been initiated before August 13, 2004 (the
effective date of AD 2004–14–09,
Amendment 39–13718 (69 FR 41398, July 9,
2004)): Do the next inspection within 5,700
flight cycles after accomplishment of the last
inspection, or within 1,800 flight cycles after
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August 13, 2004, whichever is later. Repeat
the inspection thereafter at intervals not to
exceed 5,700 flight cycles.
(2) For airplanes on which no inspection
required by paragraph (g) of this AD has been
done before August 13, 2004 (the effective
date of AD 2004–14–09, Amendment 39–
13718 (69 FR 41398, July 9, 2004)): Do the
next inspection within 5,700 flight cycles
after accomplishment of the inspection
required by paragraph (l) of this AD. Repeat
the inspection thereafter at intervals not to
exceed 5,700 flight cycles.
(n) Retained Repair/Modification, With No
Changes
This paragraph restates the requirements of
paragraph (h) of AD 2004–14–09,
Amendment 39–13718 (69 FR 41398, July 9,
2004), with no changes. If any cracking is
detected during any inspection required by
paragraph (l) or (m) of this AD, prior to
further flight, repair in accordance with
Airbus Service Bulletin A320–57–1082,
Revision 01, dated December 10, 1997, or
Revision 03, dated April 30, 2002; and
modify any uncracked area, in accordance
with Airbus Service Bulletin A320–57–1043,
Revision 02, dated May 14, 1997, or Revision
05, dated April 30, 2002. Where Airbus
Service Bulletin A320–57–1082 specifies to
contact Airbus for an appropriate repair
action: Prior to further flight, repair using a
method approved by the Manager,
International Branch, ANM–116, FAA,
Transport Airplane Directorate; or the DGAC
(or its delegated agent). Accomplishment of
the repair of cracked area(s) and modification
of uncracked area(s) constitutes terminating
action for the requirements of paragraphs (g)
through (n) of this AD.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(o) New Requirement of This AD: Repair of
Certain Airplanes
For airplanes on which the actions
described in Airbus Service Bulletin A320–
57–1043 have not been accomplished, and on
which a repair has been accomplished, as
described in Airbus Service Bulletin A320–
57–1082, dated October 31, 1996; Revision
01, dated December 10, 1997; Revision 02,
dated July 26, 1999; or Revision 03, dated
April 30, 2002: Within 30 days after the
effective date of this AD, repair using a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; the European
Aviation Safety Agency (EASA); or Airbus’s
EASA design organization approval (DOA).
(p) New Requirement of This AD: Repetitive
WCB Inspections
At the applicable time specified in
paragraphs (p)(1) and (p)(2) of this AD: Do an
HFEC inspection for cracking of the lower
surface panel on the WCB, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–57–1082,
Revision 04, dated December 5, 2013. Repeat
the inspection of the lower surface panel on
the WCB thereafter at intervals not to exceed
7,200 flight cycles or 14,400 flight hours,
whichever occurs first. Accomplishment of
the initial inspection required by this
paragraph terminates the inspections
required by paragraphs (g), (i), and (l) of this
AD.
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(1) For airplanes on which the actions
described in Airbus Service Bulletin A320–
57–1043 have not been done: At the later of
the times specified in paragraphs (p)(1)(i) and
(p)(1)(ii) of this AD.
(i) Before the accumulation of 20,700 flight
cycles or 41,400 flight hours, whichever
occurs first since first flight of the airplane.
(ii) Within 7,200 flight cycles or 14,400
flight hours, whichever occurs first after
doing the most recent inspection as specified
in Airbus Service Bulletin A320–57–1082,
dated October 31, 1996; Revision 01, dated
December 10, 1997; Revision 02, dated July
26, 1999; or Revision 03, dated April 30,
2002.
(2) For airplanes on which the actions
specified in Airbus Service Bulletin A320–
57–1043, dated February 16, 1993; Revision
01, dated June 14, 1996; Revision 02, dated
May 14, 1997; Revision 03, dated October 24,
1997; Revision 04, dated March 15, 1999; or
Revision 05, dated April 30, 2002; have been
done: At the latest of the times specified in
paragraphs (p)(2)(i), (p)(2)(ii), and (p)(2)(iii)
of this AD.
(i) Within 7,200 flight cycles or 14,400
flight hours, whichever occurs first since
doing the actions specified in Airbus Service
Bulletin A320–57–1043.
(ii) Within 3,750 flight cycles or 7,500
flight hours, whichever occurs first after July
31, 2012 (as described in Airbus Service
Bulletin A320–57–1082, Revision 04, dated
December 5, 2013).
(iii) Within 850 flight cycles or 1,700 flight
hours, whichever occurs first after the
effective date of this AD.
(q) New Requirement of This AD: Repair of
WCB
If any crack is found during any inspection
required by paragraph (p) of this AD: Before
further flight, repair using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; the EASA; or Airbus’s
EASA DOA.
(r) New Optional Terminating Action
Modification of an airplane, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–57–1043,
Revision 06, dated December 5, 2013,
constitutes terminating action for the actions
required by paragraph (p) of this AD.
(s) Credit for Previous Actions
This paragraph provides credit for
applicable actions required by paragraphs (g)
through (n) of this AD, if those actions were
performed before the effective date of this AD
using the applicable Airbus Service
Information provided in paragraphs (s)(1)
through (s)(8) of this AD.
(1) Airbus Service Bulletin A320–57–1043,
dated February 16, 1993, which is not
incorporated by reference in this AD.
(2) Airbus Service Bulletin A320–57–1043,
Revision 01, dated June 14, 1996, which is
not incorporated by reference in this AD.
(3) Airbus Service Bulletin A320–57–1043,
Revision 02, dated May 14, 1997, which was
incorporated by reference on November 27,
1998 (63 FR 56542, October 22, 1998).
PO 00000
Frm 00027
Fmt 4702
Sfmt 4702
26495
(4) Airbus Service Bulletin A320–57–1043,
Revision 03, dated October 24, 1997, which
is not incorporated by reference in this AD.
(5) Airbus Service Bulletin A320–57–1043,
Revision 04, dated May 15, 1999, which is
not incorporated by reference in this AD.
(6) Airbus Service Bulletin A320–57–1082,
Revision 01, dated December 10, 1997, which
was incorporated by reference on November
27, 1998 (63 FR 56542, October 22, 1998).
(7) Airbus Service Bulletin A320–57–1082,
Revision 02, dated July 26, 1999, which is
not incorporated by reference in this AD.
(8) Airbus Service Bulletin A320–57–1082,
Revision 03, dated April 30, 2002, which was
incorporated by reference on August 13, 2004
(69 FR 41398, July 9, 2004).
(t) 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. 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.
(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 EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(u) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0065, dated
March 14, 2014, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2014–1275.
(2) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
You may view this service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
E:\FR\FM\08MYP1.SGM
08MYP1
26496
Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules
Issued in Renton, Washington, on April 29,
2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–10949 Filed 5–7–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2014–0565; Airspace
Docket No. 14–ACE–7]
Proposed Revocation of Class D and E
Airspace; Independence, KS
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (SNPRM).
AGENCY:
This supplemental notice of
proposed rulemaking proposes to
remove Class D airspace and Class E
surface area airspace at Independence
Municipal Airport, Independence, KS.
In an NPRM published in the Federal
Register September 25, 2014, the FAA
proposed to remove Class D airspace at
Independence Municipal Airport,
Independence, KS. The FAA has
reassessed the proposal to include the
removal of the associated Class E
surface area airspace. The closure of the
airport’s air traffic control tower has
necessitated the need for this proposal.
DATES: Comments must be received on
or before June 22, 2015.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, 1200
New Jersey Avenue SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590–0001. You must
identify the docket number FAA–2014–
0565/Airspace Docket No. 14–ACE–7, at
the beginning of your comments. You
may also submit comments through the
Internet at https://www.regulations.gov.
You may review the public docket
containing the proposal, any comments
received, and any final disposition in
person in the Dockets Office between
9:00 a.m. and 5:00 p.m., Monday
through Friday, except Federal holidays.
The Docket Office (telephone 1–800–
647–5527) is on the ground floor of the
building at the above address.
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
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
16:19 May 07, 2015
Jkt 235001
(NARA). For information on the
availability of this proposed
incorporation by reference material at
NARA, call 202–741–6030, or go to
https://www.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: Raul
Garza, Jr., Central Service Center,
Operations Support Group, Federal
Aviation Administration, Southwest
Region, 2601 Meacham Blvd., Fort
Worth, TX 76137; telephone: 817–321–
7654.
SUPPLEMENTARY INFORMATION:
History
On September 25, 2014, the FAA
published a NPRM to remove Class D
airspace at Independence Municipal
Airport, Independence, KS, as the air
traffic control tower has closed (79 FR
57483). The comment period closed
November 10, 2014. No comments were
received. Subsequent to publication, the
FAA reassessed the proposal to include
the removal of the associated Class E
surface area airspace at Independence
Municipal Airport, Independence, KS.
Also, the title section is amended to
include Class E airspace. The FAA seeks
comments on this SNPRM.
Comments Invited
Interested parties are invited to
participate in this proposed rulemaking
by submitting such written data, views,
or arguments, as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
developing reasoned regulatory
decisions on the proposal. Comments
are specifically invited on the overall
regulatory, aeronautical, economic,
environmental, and energy-related
aspects of the proposal.
Communications should identify both
docket numbers and be submitted in
triplicate to the address listed above.
Commenters wishing the FAA to
acknowledge receipt of their comments
on this notice must submit with those
comments a self-addressed, stamped
postcard on which the following
statement is made: ‘‘Comments to
Docket No. FAA–2014–0565/Airspace
Docket No. 14–ACE–7.’’ The postcard
will be date/time stamped and returned
to the commenter.
PO 00000
Frm 00028
Fmt 4702
Sfmt 4702
Availability of SNPRMs
An electronic copy of this document
may be downloaded through the
Internet at https://www.regulations.gov.
Recently published rulemaking
documents can also be accessed through
the FAA’s Web page at https://
www.faa.gov/airports_airtraffic/air_
traffic/publications/airspace_
amendments/.
You may review the public docket
containing the proposal, any comments
received and any final disposition in
person in the Dockets Office (see
ADDRESSES section for address and
phone number) between 9:00 a.m. and
5:00 p.m., Monday through Friday,
except Federal holidays. An informal
docket may also be examined during
normal business hours at the office of
the Central Service Center, 2601
Meacham Blvd., Fort Worth, TX 76137.
Persons interested in being placed on
a mailing list for future NPRMs should
contact the FAA’s Office of Rulemaking
(202) 267–9677, to request a copy of
Advisory Circular No. 11–2A, Notice of
Proposed Rulemaking Distribution
System, which describes the application
procedure.
Availability and Summary of
Documents Proposed for Incorporation
by Reference
This document proposes to amend
FAA Order 7400.9Y, Airspace
Designations and Reporting Points,
dated August 6, 2014, and effective
September 15, 2014. FAA Order
7400.9Y is publicly available as listed in
the ADDRESSES section of this proposed
rule. FAA Order 7400.9Y lists Class A,
B, C, D, and E airspace areas, air traffic
service routes, and reporting points.
The Supplemental Proposal
This supplemental proposal proposes
to amend Title 14, Code of Federal
Regulations (14 CFR), Part 71 by
removing Class D airspace and the
associated Class E surface area airspace
at Independence Municipal Airport,
Independence, KS. The closing of the
airport’s air traffic control tower has
made this action necessary. Also, the
Title section is amended to read
‘‘Proposed Revocation of Class D and E
Airspace; Independence, KS’’.
Class D and E airspace areas are
published in Paragraph 5000 and 6002,
respectively, of FAA Order 7400.9Y,
dated August 6, 2014, and effective
September 15, 2014, which is
incorporated by reference in 14 CFR
71.1. The Class D and E airspace
designations listed in this document
will be published subsequently in the
Order.
E:\FR\FM\08MYP1.SGM
08MYP1
]]>Agencies
[Federal Register Volume 80, Number 89 (Friday, May 8, 2015)]
[Proposed Rules]
[Pages 26492-26496]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-10949]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-1275; Directorate Identifier 2014-NM-070-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2004-14-
09, for certain Airbus Model A320-211, -212, and -231 airplanes. AD
2004-14-09 currently requires repetitive inspections for fatigue
cracking of the lower surface panel on the wing center box, and repair
if necessary; and modification of the lower surface panel on the wing
center box, which constitutes terminating action for the repetitive
inspections. Since we issued AD 2004-14-09, we have determined that,
based on the average flight duration, the average weight of fuel at
landing is higher than that defined for the analysis of the fatigue-
related tasks; and that shot peening might have been improperly done on
the chromic acid anodizing (CAA) protection, which would adversely
affect fatigue crack protection. This proposed AD would reduce the
compliance times for the repetitive inspections, and would require a
repair for certain airplanes. We are proposing this AD to detect and
correct fatigue cracking of the lower surface panel on the wing center
box, which could result in reduced structural integrity of the
airplane.
DATES: We must receive comments on this proposed AD by June 22, 2015.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1275; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-1275;
Directorate Identifier 2014-NM-070-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On June 29, 2004, we issued AD 2004-14-09, Amendment 39-13718 (69
FR 41398, July 9, 2004). AD 2004-14-09 requires actions intended to
address an unsafe condition on the products listed above. AD 2004-14-09
superseded AD 98-22-05, Amendment 39-10851 (63 FR 56542, October 22,
1998).
Since we issued AD 2004-14-09, Amendment 39-13718 (69 FR 41398,
July 9, 2004), we have determined that, based on the average flight
duration, the average weight of fuel at landing is higher than that
defined for the analysis of the fatigue-related tasks; and that shot
peening might have been improperly done on the CAA protection, which
would adversely affect fatigue crack protection.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0065, dated March 14,
[[Page 26493]]
2014 (referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''), to correct an unsafe condition on
certain Model A320-211, -212, and -231 airplanes. The MCAI states:
During center fuselage certification full scale test, damage was
found in the center wing box (CWB) lower surface panel.
This condition, if not detected and corrected, could affect the
structural integrity of the CWB.
To prevent such damage, Airbus developed mod 22418 which
consists in shot-peening of the lower panel in the related area. Mod
22418 has been embodied in production from aeroplane [manufacturer
serial number] (MSN) 0359. For unmodified in-service aeroplanes,
Airbus issued Service Bulletin (SB) A320-57-1082 to introduce
repetitive High Frequency Eddy Current (HFEC) inspections on the
external face of the center wing box lower panel between Frame (FR)
41 and FR42 to detect damage.
DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France issued AD 2002-342 [https://ad.easa.europa.eu/blob/20023420tb_superseded.pdf/AD_F-2002-342_1] to require these
inspections and, depending on findings, applicable corrective
action(s). Airbus also issued SB A320-57-1043 as an optional
terminating action for the repetitive inspections required by DGAC
France AD 2002-342.
Since that [DGAC] AD was issued, the results of a survey,
carried out on the A320 fleet, highlighted some differences between
the mission parameters, mainly on the weight of fuel at landing and
on the average flight duration, which are higher than those defined
for the analysis of the fatigue related tasks.
These findings have led to an adjustment of the A320 reference
fatigue mission. Consequently, the threshold and intervals of these
repetitive inspections have been revised and a new threshold figure
expressed in flight hours (FH) has been established.
In addition, it has been identified that, on aeroplanes that
have been modified in accordance with Airbus SB A320-57-1043 (Airbus
mod 22418) at Revision 05 or an earlier Revision, the shot peening
may have been improperly done on the Chromic Acid Anodizing (CAA)
protection, which has no fatigue benefit effect. Therefore, the
inspections per Airbus SB A320-57-1082 are required again on these
aeroplanes.
Consequently, new shot-peening procedures with proper CAA
protection removal instructions have been developed and their
embodiment through Airbus SB A320-57-1043 Revision 06 cancels the
repetitive inspections per Airbus SB A320-57-1082, as required by
DGAC France AD 2002-342.
For the reasons described above, this new [EASA] AD retains the
requirements of DGAC France AD 2002-342, which is superseded, but
requires these actions to be accomplished within reduced thresholds
and intervals. In addition, the optional terminating action
provision (SB A320-57-1043) is amended by including reference to the
SB at Revision 06.
The optional terminating action described in Airbus Service Bulletin
A320-57-1043, Revision 06, dated December 5, 2013, is accomplishing
shot peening in the radius of the milling step between stiffeners 13
and 14 near the fuel pump aperture.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1275.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-57-1043, Revision 06, dated
December 5, 2013. This service bulletin describes procedures for shot
peening in the radius of the milling step between stiffeners 13 and 14
near the fuel pump aperture.
Airbus has also issued Service Bulletin A320-57-1082, Revision 04,
dated December 5, 2013. This service bulletin describes procedures for
inspections for cracking of the lower surface panel on the wing center
box.
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section of this NPRM.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD affects 46 airplanes of U.S.
registry.
The actions that are required by AD 2004-14-09, Amendment 39-13718
(69 FR 41398, July 9, 2004), and retained in this proposed AD take
about 25 work-hours per product, at an average labor rate of $85 per
work-hour. Based on these figures, the estimated cost of the actions
that were required by AD 2004-14-09 is $2,125 per product.
The new requirements of this proposed AD would add no additional
economic burden.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD. We have no way of determining the number of aircraft that might
need these actions.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator,
[[Page 26494]]
the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), and adding
the following new AD:
Airbus: Docket No. FAA-2014-1275; Directorate Identifier 2014-NM-
070-AD.
(a) Comments Due Date
We must receive comments by June 22, 2015.
(b) Affected ADs
This AD replaces AD 2004-14-09, Amendment 39-13718 (69 FR 41398,
July 9, 2004).
(c) Applicability
This AD applies to Airbus Model A320-211, -212, and -231
airplanes, certificated in any category, all manufacturer serial
numbers, except those on which Airbus Modification 22418 has been
embodied in production.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by a determination that, based on the
average flight duration, the average weight of fuel at landing is
higher than that defined for the analysis of the fatigue-related
tasks; and that shot peening might have been improperly done on the
chromic acid anodizing (CAA) protection, which would adversely
affect fatigue crack protection. We are issuing this AD to detect
and correct fatigue cracking of the lower surface panel on the wing
center box (WCB), which could result in reduced structural integrity
of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Repetitive Inspections, With No Changes
This paragraph restates the requirements of paragraph (a) of AD
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no
changes. Except as provided by paragraph (k) of this AD: Prior to
the accumulation of 20,000 total flight cycles, or within 60 days
after November 27, 1998 (the effective date of AD 98-22-05,
Amendment 39-10851 (63 FR 56542, October 22, 1998)), whichever
occurs later, perform a high frequency eddy current (HFEC)
inspection to detect fatigue cracking of the lower surface panel on
the WCB, in accordance with Airbus Service Bulletin A320-57-1082,
Revision 01, dated December 10, 1997; or Revision 03, dated April
30, 2002. Repeat the HFEC inspection thereafter at intervals not to
exceed 7,500 flight cycles until the actions required by paragraph
(i) of this AD are accomplished.
(h) Retained Repair, With No Changes
This paragraph restates the requirements of paragraph (b) of AD
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no
changes. Except as provided by paragraph (j) of this AD, if any
cracking is detected during any inspection required by paragraph (g)
of this AD: Prior to further flight, repair in accordance with
Airbus Service Bulletin A320-57-1082, Revision 01, dated December
10, 1997; or Revision 03, dated April 30, 2002. Accomplishment of
the repair constitutes terminating action for the repetitive
inspections required by paragraph (g) of this AD for the repaired
area only.
(i) Retained Inspection/Modification/Repair, With Terminating Action
This paragraph restates the requirements of paragraph (c) of AD
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with
terminating action provided. Prior to the accumulation of 25,000
total flight cycles, or within 60 days after November 27, 1998 (the
effective date of AD 98-22-05, Amendment 39-10851 (63 FR 56542,
October 22, 1998)), whichever occurs later: Perform an HFEC
inspection to detect fatigue cracking of the lower surface panel on
the WCB, in accordance with Airbus Service Bulletin A320-57-1082,
Revision 01, dated December 10, 1997; or Revision 03, dated April
30, 2002. Accomplishment of the initial inspection required by
paragraph (p) of this AD constitutes terminating action for the
inspection requirements of this paragraph.
(1) If no cracking is detected: Prior to further flight, modify
the lower surface panel on the WCB, in accordance with Airbus
Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997; or
Revision 05, dated April 30, 2002. Accomplishment of the
modification constitutes terminating action for the requirements of
paragraph (g) of this AD.
(2) Except as provided by paragraph (j) of this AD: If any
cracking is detected, prior to further flight, repair in accordance
with Airbus Service Bulletin A320-57-1082, Revision 01, dated
December 10, 1997, or Revision 03, dated April 30, 2002; and modify
any uncracked area, in accordance with Airbus Service Bulletin A320-
57-1043, Revision 02, dated May 14, 1997, or Revision 05, dated
April 30, 2002. Accomplishment of the repair of cracked area(s) and
modification of uncracked area(s) constitutes terminating action for
the requirements of paragraph (g) of this AD.
(j) Retained Service Bulletin Exception, With No Changes
This paragraph restates the requirements of paragraph (d) of AD
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no
changes. If any cracking is detected during any inspection required
by paragraph (h) or (i)(2) of this AD, and the applicable service
bulletin specifies to contact Airbus for an appropriate action:
Prior to further flight, repair using a method approved by the
Manager, International Branch, ANM-116, FAA, Transport Airplane
Directorate; or the Direction G[eacute]n[eacute]rale de l'Aviation
Civile (DGAC) (or its delegated agent).
(k) Retained Provision for Certain Inspection Exception, With No
Changes
This paragraph restates the provision of paragraph (e) of AD
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no
changes. The actions required by paragraph (g) of this AD are not
required to be accomplished if the requirements of paragraph (i) of
this AD are accomplished at the time specified in paragraph (g) of
this AD.
(l) Retained Initial Inspection, With Terminating Action
This paragraph restates the requirements of paragraph (f) of AD
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with
terminating action provided. For airplanes on which neither the
inspection required by paragraph (g) of this AD, nor the
modification required by paragraph (i)(1) of this AD has been done
before August 13, 2004 (the effective date of AD 2004-14-09):
Perform an HFEC inspection to detect fatigue cracking of the lower
surface panel on the WCB, in accordance with Airbus Service Bulletin
A320-57-1082, Revision 01, dated December 10, 1997; or Revision 03,
dated April 30, 2002; at the later of the times specified in
paragraphs (l)(1) and (l)(2) of this AD. Accomplishment of the
inspection required by this paragraph terminates the requirements of
paragraph (g) of this AD. Accomplishment of the initial inspection
required by paragraph (p) of this AD terminates the inspection
requirements of this paragraph.
(1) Prior to the accumulation of 13,200 total flight cycles or
39,700 total flight hours, whichever is first.
(2) Prior to the accumulation of 20,000 total flight cycles, or
within 3,500 flight cycles after August 13, 2004 (the effective date
of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004)),
whichever is later.
(m) Retained Repetitive Inspections, With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no
changes. If no cracking is detected during the inspection required
by paragraph (g) or (l) of this AD: Repeat the inspection required
by paragraph (l) of this AD at the applicable time specified in
paragraph (m)(1) or (m)(2) of this AD. Accomplishment of the
modification required by paragraph (i)(1) of this AD terminates the
requirements of this paragraph.
(1) For airplanes on which the inspections required by paragraph
(g) of this AD have been initiated before August 13, 2004 (the
effective date of AD 2004-14-09, Amendment 39-13718 (69 FR 41398,
July 9, 2004)): Do the next inspection within 5,700 flight cycles
after accomplishment of the last inspection, or within 1,800 flight
cycles after
[[Page 26495]]
August 13, 2004, whichever is later. Repeat the inspection
thereafter at intervals not to exceed 5,700 flight cycles.
(2) For airplanes on which no inspection required by paragraph
(g) of this AD has been done before August 13, 2004 (the effective
date of AD 2004-14-09, Amendment 39-13718 (69 FR 41398, July 9,
2004)): Do the next inspection within 5,700 flight cycles after
accomplishment of the inspection required by paragraph (l) of this
AD. Repeat the inspection thereafter at intervals not to exceed
5,700 flight cycles.
(n) Retained Repair/Modification, With No Changes
This paragraph restates the requirements of paragraph (h) of AD
2004-14-09, Amendment 39-13718 (69 FR 41398, July 9, 2004), with no
changes. If any cracking is detected during any inspection required
by paragraph (l) or (m) of this AD, prior to further flight, repair
in accordance with Airbus Service Bulletin A320-57-1082, Revision
01, dated December 10, 1997, or Revision 03, dated April 30, 2002;
and modify any uncracked area, in accordance with Airbus Service
Bulletin A320-57-1043, Revision 02, dated May 14, 1997, or Revision
05, dated April 30, 2002. Where Airbus Service Bulletin A320-57-1082
specifies to contact Airbus for an appropriate repair action: Prior
to further flight, repair using a method approved by the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate;
or the DGAC (or its delegated agent). Accomplishment of the repair
of cracked area(s) and modification of uncracked area(s) constitutes
terminating action for the requirements of paragraphs (g) through
(n) of this AD.
(o) New Requirement of This AD: Repair of Certain Airplanes
For airplanes on which the actions described in Airbus Service
Bulletin A320-57-1043 have not been accomplished, and on which a
repair has been accomplished, as described in Airbus Service
Bulletin A320-57-1082, dated October 31, 1996; Revision 01, dated
December 10, 1997; Revision 02, dated July 26, 1999; or Revision 03,
dated April 30, 2002: Within 30 days after the effective date of
this AD, repair using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
the European Aviation Safety Agency (EASA); or Airbus's EASA design
organization approval (DOA).
(p) New Requirement of This AD: Repetitive WCB Inspections
At the applicable time specified in paragraphs (p)(1) and (p)(2)
of this AD: Do an HFEC inspection for cracking of the lower surface
panel on the WCB, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A320-57-1082, Revision 04, dated December
5, 2013. Repeat the inspection of the lower surface panel on the WCB
thereafter at intervals not to exceed 7,200 flight cycles or 14,400
flight hours, whichever occurs first. Accomplishment of the initial
inspection required by this paragraph terminates the inspections
required by paragraphs (g), (i), and (l) of this AD.
(1) For airplanes on which the actions described in Airbus
Service Bulletin A320-57-1043 have not been done: At the later of
the times specified in paragraphs (p)(1)(i) and (p)(1)(ii) of this
AD.
(i) Before the accumulation of 20,700 flight cycles or 41,400
flight hours, whichever occurs first since first flight of the
airplane.
(ii) Within 7,200 flight cycles or 14,400 flight hours,
whichever occurs first after doing the most recent inspection as
specified in Airbus Service Bulletin A320-57-1082, dated October 31,
1996; Revision 01, dated December 10, 1997; Revision 02, dated July
26, 1999; or Revision 03, dated April 30, 2002.
(2) For airplanes on which the actions specified in Airbus
Service Bulletin A320-57-1043, dated February 16, 1993; Revision 01,
dated June 14, 1996; Revision 02, dated May 14, 1997; Revision 03,
dated October 24, 1997; Revision 04, dated March 15, 1999; or
Revision 05, dated April 30, 2002; have been done: At the latest of
the times specified in paragraphs (p)(2)(i), (p)(2)(ii), and
(p)(2)(iii) of this AD.
(i) Within 7,200 flight cycles or 14,400 flight hours, whichever
occurs first since doing the actions specified in Airbus Service
Bulletin A320-57-1043.
(ii) Within 3,750 flight cycles or 7,500 flight hours, whichever
occurs first after July 31, 2012 (as described in Airbus Service
Bulletin A320-57-1082, Revision 04, dated December 5, 2013).
(iii) Within 850 flight cycles or 1,700 flight hours, whichever
occurs first after the effective date of this AD.
(q) New Requirement of This AD: Repair of WCB
If any crack is found during any inspection required by
paragraph (p) of this AD: Before further flight, repair using a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; the EASA; or Airbus's EASA DOA.
(r) New Optional Terminating Action
Modification of an airplane, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-57-1043,
Revision 06, dated December 5, 2013, constitutes terminating action
for the actions required by paragraph (p) of this AD.
(s) Credit for Previous Actions
This paragraph provides credit for applicable actions required
by paragraphs (g) through (n) of this AD, if those actions were
performed before the effective date of this AD using the applicable
Airbus Service Information provided in paragraphs (s)(1) through
(s)(8) of this AD.
(1) Airbus Service Bulletin A320-57-1043, dated February 16,
1993, which is not incorporated by reference in this AD.
(2) Airbus Service Bulletin A320-57-1043, Revision 01, dated
June 14, 1996, which is not incorporated by reference in this AD.
(3) Airbus Service Bulletin A320-57-1043, Revision 02, dated May
14, 1997, which was incorporated by reference on November 27, 1998
(63 FR 56542, October 22, 1998).
(4) Airbus Service Bulletin A320-57-1043, Revision 03, dated
October 24, 1997, which is not incorporated by reference in this AD.
(5) Airbus Service Bulletin A320-57-1043, Revision 04, dated May
15, 1999, which is not incorporated by reference in this AD.
(6) Airbus Service Bulletin A320-57-1082, Revision 01, dated
December 10, 1997, which was incorporated by reference on November
27, 1998 (63 FR 56542, October 22, 1998).
(7) Airbus Service Bulletin A320-57-1082, Revision 02, dated
July 26, 1999, which is not incorporated by reference in this AD.
(8) Airbus Service Bulletin A320-57-1082, Revision 03, dated
April 30, 2002, which was incorporated by reference on August 13,
2004 (69 FR 41398, July 9, 2004).
(t) 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.
(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 EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(u) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0065, dated March 14, 2014,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2014-1275.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA,
call 425-227-1221.
[[Page 26496]]
Issued in Renton, Washington, on April 29, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-10949 Filed 5-7-15; 8:45 am]
BILLING CODE 4910-13-P
