Airworthiness Directives; Airbus Airplanes, 25249-25254 [2015-10177]
Download as PDF
<![CDATA[
Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Fokker Services B.V.: Docket No. FAA–
2015–0933; Directorate Identifier 2014–
NM–098–AD.
(a) Comments Due Date
We must receive comments by June 18,
2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Fokker Services B.V.
Model F.27 Mark 200, 300, 400, 500, 600, and
700 airplanes, certificated in any category, all
serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 28, Fuel.
(e) Reason
This AD was prompted by a design review,
which revealed that no controlled bonding
provisions are present on a number of critical
locations inside the fuel tank or connected to
the fuel tank wall; and no anti-spray cover is
installed on the fuel shut-off valve (FSOV) in
both wings. We are issuing this AD to
prevent an ignition source in the fuel tank
vapor space, which could result in a fuel tank
explosion and consequent loss of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Installation of Bonding Provisions and
Anti-Spray Cover
At the next scheduled opening of the fuel
tanks after the effective date of this AD, but
no later than 84 months after the effective
date of this AD: Install additional bonding
provisions at the applicable locations, and
install an anti-spray cover on the FSOV in
both wings, using a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA.
tkelley on DSK3SPTVN1PROD with PROPOSALS
(h) Revision of Maintenance or Inspection
Program
Within 30 days after installing the bonding
provisions and anti-spray cover specified in
paragraph (g) of this AD: Revise the airplane
maintenance or inspection program, as
applicable, by incorporating fuel
airworthiness limitation items and Critical
Design Configuration Control Limitations
(CDCCLs), using a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA.
(i) No Alternative Actions, Intervals, and/or
CDCCLs
After accomplishing the revision required
by paragraph (h) of this AD, no alternative
actions (e.g., inspections), intervals, or
CDCCLs may be used unless the actions,
intervals, or CDCCLs are approved as an
alternative method of compliance (AMOC) in
VerDate Sep<11>2014
17:53 May 01, 2015
Jkt 235001
accordance with the procedures specified in
paragraph (j) of this AD.
ACTION:
(j) 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:
Tom Rodriguez, Aerospace Engineer,
International Branch; ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1137; fax 425–227–1137.
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. 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, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Fokker Services B.V.’s EASA
Design Organization Approval (DOA). If
approved by the DOA, the approval must
include the DOA-authorized signature.
25249
SUMMARY:
(k) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0099, dated
April 30, 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–
2015–0933.
Issued in Renton, Washington, on April 17,
2015.
Victor Wicklund,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–10180 Filed 5–1–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0937; Directorate
Identifier 2014–NM–024–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
Notice of proposed rulemaking
(NPRM).
We propose to supersede
Airworthiness Directive (AD) 2011–24–
05, for certain Airbus Model A330–201,
–202, –203, –223, –243, –301, –302,
–303, –321, –322, –323, –341, –342, and
–343 airplanes; and Model A340–200
and –300 series airplanes. AD 2011–24–
05 currently requires repetitive
inspections for cracking of the hole(s) of
the horizontal flange of the keel beam,
and repair if necessary. Since we issued
AD 2011–24–05, a determination was
made that the rototest inspection and
applicable corrective actions of a certain
fastener hole were inadvertently omitted
from the requirements in that AD. This
proposed AD would change the
inspection compliance times, and, for
certain airplanes, would add a one-time
ultrasonic inspection for cracking at a
certain fastener hole. This proposed AD
would also provide optional terminating
action for the repetitive inspections. We
are proposing this AD to detect and
correct cracking of the fastener holes,
which could result in rupture of the keel
beam, and consequent reduced
structural integrity of the airplane.
DATES: We must receive comments on
this proposed AD by June 18, 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 SAS—
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@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://
E:\FR\FM\04MYP1.SGM
04MYP1
25250
Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
0937; 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:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1138;
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–2015–0937; Directorate Identifier
2014–NM–024–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.
tkelley on DSK3SPTVN1PROD with PROPOSALS
Discussion
On November 7, 2011, we issued AD
2011–24–05, Amendment 39–16869 (76
FR 73496, November 29, 2011), for
certain Airbus Model A330–201, –202,
–203, –223, –243, –301, –302, –303,
–321, –322, –323, –341, –342, and –343
airplanes; and Model A340–200 and
–300 series airplanes. AD 2011–24–05
requires actions intended to address the
unsafe condition on the products listed
above.
Since we issued AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011), the European
Aviation Safety Agency (EASA), which
is the Technical Agent for the Member
States of the European Union, has
issued EASA Airworthiness Directive
2014–0010R1, dated May 5, 2014
(referred to after this as the Mandatory
Continuing Airworthiness Information,
VerDate Sep<11>2014
17:53 May 01, 2015
Jkt 235001
or ‘‘the MCAI’’), to correct an unsafe
condition for certain Airbus Model
A330–201, –202, –203, –223, –243,
–301, –302, –303, –321, –322, –323,
–341, –342, and –343 airplanes; and
Model A340–200 and –300 series
airplanes. The MCAI states:
During A330 and A340 aeroplanes fatigue
tests, cracks were detected on the RH [righthand] and LH [left-hand] sides between the
crossing area of the keel beam fitting and the
front spar of the Centre Wing Box (CWB).
This condition, if not detected and
corrected, could lead to keel beam rupture
which would affect the area structural
integrity of the area.
Prompted by this potential unsafe
condition, EASA issued AD 2006–0315
[https://ad.easa.europa.eu/blob/easa_ad_
2006_0315.pdf/AD_2006-0315] (later revised
to R1) to require repetitive special detailed
inspections (SDI) [rotating probe inspection
for cracking] on the horizontal flange of the
keel beam in the area of first fastener hole aft
of Frame (FR) 40 in order to maintain the
structural integrity of the aeroplane.
After that [EASA] AD was issued, EASA
issued AD 2010–0024 [which corresponds to
FAA AD 2011–24–05, Amendment 39–16869
(76 FR 73496, November 29, 2011)], retaining
the inspection requirements of EASA AD
2006–0315R1 [https://ad.easa.europa.eu/blob/
easa_ad_2006_0315R1.pdf/AD_20060315R1], which was superseded, extending
the applicability to aeroplanes with Airbus
Mod 49202 embodied, and reducing the
inspection thresholds and intervals.
Since that [EASA] AD [2010–0024] was
issued, a new fatigue and damage tolerance
evaluation has been conducted by Airbus,
which concluded that due to the aeroplane
utilization, the current inspection threshold
and intervals have to be modified.
In addition, it was determined that the
rototest inspection of fastener hole Nr 6,
necessary to ensure that no crack was left
unrepaired at the time of fastener hold cold
working, was inadvertently not included in
Revisions 01 and 02 of both Airbus Service
Bulletin (SB) A330–57–3098 and A340–57–
4106.
Prompted by these findings, EASA issued
AD 2014–0010 [https://ad.easa.europa.eu/
blob/easa_ad_2014-0010.pdf/AD_2014-0010],
retaining the requirements of EASA AD
2010–0024, which was superseded, and
redefined the inspection thresholds and
intervals [by reducing certain compliance
times], and added a one-time ultrasonic
inspection of fastener hold Nr 6 in the
junction keel beam fitting at FR40 on both LH
and RH side[s].
Following issuance of EASA AD 2014–
0010, it was identified that there was a need
for clarifications [of affected airplanes]
* * *.
The compliance times vary depending
on airplane utilization and
configuration. The earliest compliance
time for the initial rotating probe
inspections is the later of (1) before
10,400 total flight cycles or 67,800 total
flight hours, whichever occurs first; and
(2) within 24 months or 14,590 flight
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
cycles or 43,790 flight hours, whichever
occurs first. The latest compliance time
for the initial inspections is the later of
(1) before 20,800 total flight cycles or
67,900 total flight hours, whichever
occurs first; and (2) within 24 months or
21,180 flight cycles or 63,560 flight
hours, whichever occurs first. The
compliance times for the repetitive
intervals range between 7,800 flight
cycles or 50,900 flight hours and 10,700
flight cycles or 35,200 flight hours. The
compliance times for the one-time
ultrasonic inspection are the latest of (1)
21,000 flight cycles or 60,600 flight
hours and within 2,400 flight cycles or
24 months; or the latest of (2) 22,100
flight cycles and 64,400 flight hours, or
within 1,300 flight cycles or 24 months.
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–
0937.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information.
• Airbus Service Bulletin A330–57–
3081, Revision 05, including Appendix
01, dated November 13, 2012.
• Airbus Service Bulletin A330–57–
3090, dated June 15, 2011.
• Airbus Service Bulletin A330–57–
3098, dated August 30, 2007.
• Airbus Service Bulletin A330–57–
3098, Revision 02, June 15, 2011.
• Airbus Service Bulletin A330–57–
3098, Revision 03, including Appendix
01, dated September 24, 2014.
• Airbus Service Bulletin A330–57–
3117, including Appendix 01, dated
January 25, 2013.
• Airbus Service Bulletin A340–57–
4089, Revision 05, including Appendix
01, dated November 13, 2012.
• Airbus Service Bulletin A340–57–
4098, Revision 01, dated June 15, 2011.
• Airbus Service Bulletin A340–57–
4106, dated August 30, 2007.
• Airbus Service Bulletin A340–57–
4106, Revision 02, including Appendix
01, dated August 30, 2007.
• Airbus Service Bulletin A340–57–
4106, Revision 03, including Appendix
01, dated September 24, 2012.
• Airbus Service Bulletin A340–57–
4126, including Appendix 01, dated
January 25, 2013.
This service information describes
procedures for inspections for cracking
of the hole(s) of the horizontal flange of
the keel beam, and contacting the
manufacturer for repair instructions.
Additionally, this service information
describes procedures for a one-time
ultrasonic inspection for cracking at
fastener hole ‘‘Nr 6,’’ and provides
E:\FR\FM\04MYP1.SGM
04MYP1
Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules
optional terminating action for the
repetitive inspections.
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.
Explanation of Compliance Time
The compliance time for the
modification specified in this proposed
AD for addressing widespread fatigue
damage (WFD) was established to
ensure that discrepant structure is
modified before WFD develops in
airplanes. Standard inspection
techniques cannot be relied on to detect
WFD before it becomes a hazard to
flight. We will not grant any extensions
of the compliance time to complete any
AD-mandated service bulletin related to
WFD without extensive new data that
would substantiate and clearly warrant
such an extension.
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.
tkelley on DSK3SPTVN1PROD with PROPOSALS
Costs of Compliance
We estimate that this proposed AD
affects 35 airplanes of U.S. registry.
The actions that are required by AD
2011–24–05, Amendment 39–16869 (76
FR 73496, November 29, 2011), and
retained in this proposed AD take about
41 work-hours per product, at an
average labor rate of $85 per work hour.
Required parts cost about $191 per
product. Based on these figures, the
estimated cost of the actions that are
required by AD 2011–24–05 is $3,676
per product.
We also estimate that it would take
about 23 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
this proposed AD on U.S. operators to
be $68,425, or $1,955 per product.
VerDate Sep<11>2014
17:53 May 01, 2015
Jkt 235001
We have received no definitive data
that would enable us to provide a cost
estimate for the on-condition actions
specified in this proposed AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this 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.
25251
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)
2011–24–05, Amendment 39–16869 (76
FR 73496, November 29, 2011), and
adding the following new AD:
■
Airbus: Docket No. FAA–2015–0937;
Directorate Identifier 2014–NM–024–AD.
(a) Comments Due Date
We must receive comments by June 18,
2015.
(b) Affected ADs
This AD replaces AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011).
(c) Applicability
(1) This AD applies to the airplanes
identified in paragraphs (c)(1)(i) and (c)(1)(ii)
of this AD, certificated in any category,
except as provided by paragraph (c)(2) of this
AD.
(i) Airbus Model A330–201, –202, –203,
–223, –243, –301, –302, –303, –321, –322,
–323, –341, –342, and –343 airplanes, all
serial numbers, except those on which
Airbus modification 55306 or 55792 has been
embodied in production.
(ii) Airbus Model A340–211, –212, –213,
–311, –312, and –313 airplanes, all serial
numbers, except those on which Airbus
modification 55306 or 55792 has been
embodied in production.
(2) This AD does not apply to Airbus
Model A340–211, –212, –213, –311, –312,
and –313 airplanes on which the repair
specified in Airbus Repair Drawing
R57115053, R57115051, or R57115047
(installation of titanium doubler on both
sides) has been accomplished. AD 2007–12–
08, Amendment 39–15086 (72 FR 31171,
June 6, 2007), applies to these airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
The Proposed Amendment
(e) Reason
This AD was prompted by reports of cracks
on the keel beam fitting and the front spar
of the center wing box. This AD was also
prompted by a determination that the rototest
inspection and applicable corrective actions
of fastener hole Nr 6 were inadvertently
omitted from the requirements in AD 2011–
24–05, Amendment 39–16869 (76 FR 73496,
November 29, 2011). We are issuing this AD
to detect and correct cracking of the fastener
holes, which could result in rupture of the
keel beam, and consequent reduced
structural integrity of the airplane.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
PO 00000
Frm 00015
Fmt 4702
Sfmt 4702
E:\FR\FM\04MYP1.SGM
04MYP1
tkelley on DSK3SPTVN1PROD with PROPOSALS
25252
Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules
(g) Retained Non-Destructive Test (NDT)
Inspection
This paragraph restates the requirements of
paragraph (n) of AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011), with new service
information and revised credit for certain
actions. At the applicable time in paragraph
(g)(1) or (g)(2) of this AD, do an NDT
inspection of the hole(s) of the horizontal
flange of the keel beam located on frame (FR)
40 datum on the right-hand (RH) and/or lefthand (LH) side of the fuselage, in accordance
with the Accomplishment Instructions of the
applicable service information specified in
paragraph (g)(3), (g)(4), (g)(5), or (g)(6) of this
AD. Accomplishing an inspection required
by paragraph (j) of this AD terminates the
inspections required by this paragraph.
(1) For airplanes on which an inspection
required by paragraph (h) of AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011), has not been done as of
January 3, 2012 (the effective date of AD
2011–24–05): At the applicable time
specified in paragraph (g)(1)(i) or (g)(1)(ii) of
this AD.
(i) For all airplanes except those identified
in paragraph (g)(1)(ii) of this AD: Within the
‘‘Mandatory Threshold’’ (flight cycles or
flight hours) specified in table 1 of paragraph
1.E.(2) of the Accomplishment Instructions of
Airbus Service Bulletin A330–57–3081,
including Appendix 01, Revision 04, dated
May 31, 2011; or Airbus Service Bulletin
A340–57–4089, including Appendix 01,
Revision 04, dated May 31, 2011; as
applicable; or within 3 months after January
3, 2012 (the effective date AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011)); whichever occurs later.
The compliance times for configurations 02
through 06 specified in the ‘‘Mandatory
Threshold’’ column in table 1 of paragraph
1.E., ‘‘Compliance,’’ are total flight cycles and
total flight hours.
(ii) For Model A330–201, –202, –203, –223,
–243, –301, –321, –322, –323, –341, –342,
and –343 airplanes, except those on which
Airbus modification 49202 has been
embodied in production, or Airbus Service
Bulletin A330–57–3090 has been embodied
in service, and Model A340–200 and –300
series airplanes, except those on which
Airbus modification 49202 has been
embodied in production or Airbus Service
Bulletin A340–57–4098 has been embodied
in service, and except Model A340–211,
–212, –213, –311, –312, and –313 airplanes
on which the repair specified in Airbus
Repair Drawing R57115053, R57115051, or
R57115047 has been accomplished: At the
earlier of the times specified in paragraphs
(g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD.
(A) Within the ‘‘Mandatory Threshold’’
(flight cycles or flight hours) specified in
table 1 of paragraph 1.E.(2) of Airbus Service
Bulletin A340–57–4089, including Appendix
01, Revision 02, dated January 24, 2006; or
Airbus Service Bulletin A330–57–3081,
including Appendix 01, Revision 02, dated
January 24, 2006; depending on the
configuration of the aircraft model; or within
3 months after September 13, 2007,
whichever occurs later. The compliance
times for Model A330 post-mod. 41652 and
VerDate Sep<11>2014
17:53 May 01, 2015
Jkt 235001
pre-mod. 44360, post-mod. 44360, and premod. 49202 (specified in Airbus Service
Bulletin A330–57–3081, including Appendix
01, Revision 02, dated January 24, 2006); and
Model A340 post-mod. 41652, post-mod.
43500 and pre-mod. 44360, post-mod. 44360
and pre-mod. 49202, and weight variant 027
(specified in Airbus Service Bulletin A340–
57–4089, including Appendix 01, Revision
02, dated January 24, 2006); specified in the
‘‘Mandatory Threshold’’ column in table 1 of
paragraph 1.E., ‘‘Compliance,’’ are total flight
cycles and total flight hours.
(B) Within the ‘‘Mandatory Threshold’’
(flight cycles or flight hours) specified in
table 1 of paragraph 1.E.(2) of the
Accomplishment Instructions of Airbus
Service Bulletin A330–57–3081, including
Appendix 01, Revision 04, dated May 31,
2011; or Airbus Service Bulletin A340–57–
4089, including Appendix 01, Revision 04,
dated May 31, 2011; as applicable; or within
3 months after January 3, 2012 (the effective
date of AD 2011–24–05, Amendment 39–
16869 (76 FR 73496, November 29, 2011));
whichever occurs later. The compliance
times for configurations 02 through 06
specified in the ‘‘Mandatory Threshold’’
column in table 1 of paragraph 1.E.,
‘‘Compliance,’’ are total flight cycles and
total flight hours.
(2) For airplanes on which an inspection
required by paragraph (h) of AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011), has been done as of
January 3, 2012 (the effective date of AD
2011–24–05): At the earlier of the times
specified in paragraphs (g)(2)(i) and (g)(2)(ii)
of this AD.
(i) Within the ‘‘Mandatory Intervals’’ given
in table 1 of paragraph 1.E.(2) of Airbus
Service Bulletin A340–57–4089, including
Appendix 01, Revision 02, dated January 24,
2006; or Airbus Service Bulletin A330–57–
3081, including Appendix 01, Revision 02,
dated January 24, 2006; as applicable.
(ii) Within the applicable ‘‘Mandatory
Interval’’ specified in table 1 of Paragraph
1.E.(2). of Airbus Service Bulletin A330–57–
3081, including Appendix 01, Revision 04,
dated May 31, 2011,; or Airbus Service
Bulletin A340–57–4089, including Appendix
01, Revision 04, dated May 31, 2011; as
applicable; or within 3 months after January
3, 2012 (the effective date of AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011)); whichever occurs later.
(3) Airbus Service Bulletin A330–57–3081,
including Appendix 01, Revision 04, dated
May 31, 2011.
(4) Airbus Service Bulletin A330–57–3081,
including Appendix 01, Revision 05, dated
November 13, 2012.
(5) Airbus Service Bulletin A340–57–4089,
including Appendix 01, Revision 04, dated
May 31, 2011.
(6) Airbus Service Bulletin A340–57–4089,
Revision 05, including Appendix 01, dated
November 13, 2012.
(h) Retained Repetitive Inspections
This paragraph restates the requirements of
paragraph (p) of AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011). If no cracking is found
during any inspection required by paragraph
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
(g) of this AD, do the actions required by
paragraphs (h)(1) and (h)(2) of this AD.
(1) Before further flight: Install a new or
oversized fastener, as applicable; seal the
fastener; and do all other applicable actions;
in accordance with the Accomplishment
Instructions of the applicable service
information specified in paragraph (g)(3),
(g)(4), (g)(5), or (g)(6) of this AD.
(2) Repeat the inspection required by
paragraph (g) of this AD thereafter at
intervals not to exceed the ‘‘Mandatory
Intervals’’ specified in Paragraph 1.E.(2). of
Airbus Service Bulletin A330–57–3081,
including Appendix 01, Revision 04, dated
May 31, 2011; or Airbus Service Bulletin
A340–57–4089, including Appendix 01,
Revision 04, dated May 31, 2014; as
applicable.
(i) Retained Corrective Action and Optional
Modification
(1) This paragraph restates the
requirements of paragraph (o) of AD 2011–
24–05, Amendment 39–16869 (76 FR 73496,
November 29, 2011), with revised method of
compliance language. If any cracking is
found during any inspection required by
paragraph (g) of this AD, 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).
(2) This paragraph restates the
requirements of paragraph (r) of AD 2011–
24–05, Amendment 39–16869 (76 FR 73496,
November 29, 2011), with new service
information and revised method of
compliance language. Modifying the fastener
installation in the junction keel beam fitting
at FR 40, as specified in paragraph (i)(2)(i),
(i)(2)(ii), (i)(2)(iii), or (i)(2)(iv) of this AD, as
applicable, terminates the requirements of
paragraphs (g) and (h) of this AD; except, for
airplanes on which a crack was detected at
hole 5 before oversizing of the keel beam, in
accordance with step 3.B.(1)(b)3 of the
Accomplishment Instructions of Airbus
Service Bulletin A330–57–3098, dated
August 30, 2007; or Airbus Service Bulletin
A340–57–4106, dated August 30, 2007; or in
accordance with step 3.C.(2)(c) of the
Accomplishment Instructions of Airbus
Service Bulletin A330–57–3098, Revision 03,
including Appendix 01, dated September 24,
2012, or Airbus Service Bulletin A340–57–
4106, Revision 03, including Appendix 01,
dated September 24, 2012; before further
flight, repair using a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA. In case of any
crack finding during any modification
specified in this paragraph: Where the
service information specifies to contact
Airbus, before further flight, repair using a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA DOA.
(i) Modification in accordance with Airbus
Service Bulletin A330–57–3098, dated
August 30, 2007, before January 3, 2012 (the
effective date of AD 2011–24–05,
E:\FR\FM\04MYP1.SGM
04MYP1
Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules
tkelley on DSK3SPTVN1PROD with PROPOSALS
Amendment 39–16869 (76 FR 73496,
November 29, 2011)).
(ii) Modification in accordance with Airbus
Service Bulletin A330–57–3098, Revision 03,
including Appendix 01, dated September 24,
2012, before the effective date of this AD.
(iii) Modification in accordance with
Airbus Service Bulletin A340–57–4106,
dated August 30, 2007, before January 3,
2012 (the effective date of AD 2011–24–05,
Amendment 39–16869 (76 FR 73496,
November 29, 2011)).
(iv) Modification in accordance with
Airbus Service Bulletin A340–57–4106,
Revision 03, including Appendix 01, dated
September 24, 2012, before the effective date
of this AD.
(j) New Repetitive Rotating Probe
Inspections
At the applicable times specified in
paragraphs (j)(1) and (j)(2) of this AD: Do a
rotating probe inspection for cracking of the
fastener hole(s) of the horizontal flange of the
keel beam located on FR 40 datum on the RH
and LH side of the fuselage, as applicable to
airplane type and depending on airplane
configuration and utilization, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A330–57–3081,
Revision 05, including Appendix 01, dated
November 13, 2012; or Airbus Service
Bulletin A340–57–4089, Revision 05,
including Appendix 01, dated November 13,
2012; as applicable. Repeat the inspection
thereafter at intervals not to exceed the
‘‘Mandatory Intervals’’ specified in Paragraph
1.E.(2)., of the Accomplishment Timescale of
Airbus Service Bulletin A330–57–3081,
Revision 05, including Appendix 01, dated
November 13, 2012; or Airbus Service
Bulletin A340–57–4089, Revision 05,
including Appendix 01, dated November 13,
2012; as applicable. Accomplishing an
inspection required by this paragraph
terminates the inspections required by
paragraph (g) of this AD.
(1) For airplanes on which the inspection
required by paragraph (g) of this AD has not
been done as of the effective date of this AD:
Do the inspection before exceeding the
applicable compliance times specified in the
‘‘mandatory threshold’’ column of the tables
in paragraph 1.E.(2)., of the Accomplishment
Timescale of Airbus Service Bulletin A330–
57–3081, Revision 05, including Appendix
01, dated November 13, 2012; or Airbus
Service Bulletin A340–57–4089, Revision 05,
including Appendix 01, dated November 13,
2012; as applicable; or within 12 months
after the effective date of this AD; whichever
occurs later.
(2) For airplanes on which the inspection
required by paragraph (g) of this AD has been
done as of the effective date of this AD: Do
the inspection within the applicable
compliance times specified in the
‘‘mandatory interval’’ column of the tables in
paragraph 1.E.(2)., of the Accomplishment
Timescale of Airbus Service Bulletin A330–
57–3081, Revision 05, including Appendix
01, dated November 13, 2012; or Airbus
Service Bulletin A340–57–4089, Revision 05,
including Appendix 01, dated November 13,
2012; as applicable; or within 12 months
after the effective date of this AD; whichever
occurs later.
VerDate Sep<11>2014
17:53 May 01, 2015
Jkt 235001
(k) Credit for Previous Actions
(1) This paragraph provides credit for the
initial rotating probe inspection that is part
of the inspections required by paragraphs (g)
and (j)(1) of this AD, if those actions were
performed before the effective date of this AD
using the service information specified in
paragraph (k)(1)(i) or (k)(1)(ii) of this AD.
(i) Airbus Technical Disposition
F57D03012810, Issue B, dated August 18,
2003.
(ii) Airbus Technical Disposition 582.0651/
2002, Issue A, dated October 17, 2002.
(2) This paragraph restates the credit for
the actions specified in paragraph (k) of AD
2011–24–05, Amendment 39–16869 (76 FR
73496, November 29, 2011), if those actions
were performed before January 3, 2012 (the
effective date of AD 2011–24–05), using the
service information specified in paragraphs
(k)(2)(i) through (k)(2)(viii) of this AD.
(i) Airbus Service Bulletin A330–57–3081,
dated October 30, 2003.
(ii) Airbus Service Bulletin A330–57–3081,
Revision 01, dated May 18, 2004.
(iii) Airbus Service Bulletin A330–57–
3081, Revision 02, including Appendix 01,
dated January 24, 2006.
(iv) Airbus Mandatory Service Bulletin
A330–57–3081, Revision 03, dated July 31,
2009.
(v) Airbus Service Bulletin A340–57–4089,
dated October 30, 2003.
(vi) Airbus Service Bulletin A340–57–
4089, Revision 01, dated March 2, 2004.
(vii) Airbus Service Bulletin A340–57–
4089, Revision 02, including Appendix 01,
dated January 24, 2006.
(viii) Airbus Mandatory Service Bulletin
A340–57–4089, Revision 03, dated July 31,
2009.
(l) New One-Time Ultrasonic Inspection
For airplanes in Configuration 2, as defined
in the applicable service information
identified in paragraph (l)(3), (l)(4), (l)(5), or
(l)(6) of this AD, on which the modification
has been done as of the effective date of this
AD in accordance with the Accomplishment
Instructions of the applicable service
information identified in paragraph (l)(3),
(l)(4), (l)(5), or (l)(6) of this AD; as applicable
to airplane type; and on which fastener hole
‘‘Nr 5’’ has been bushed before embodiment
of Airbus Service Bulletin A330–57–3098, or
Airbus Service Bulletin A340–57–4106, as
applicable; or on which a crack has been
found on fastener hole ‘‘Nr 5’’ during
embodiment of Airbus Service Bulletin
A330–57–3098, or Airbus Service Bulletin
A340–57–4106, as applicable: At the
applicable time specified in paragraph (l)(1)
or (l)(2) of this AD, do a one-time ultrasonic
inspection for cracking at fastener hole ‘‘Nr
6’’ in the junction keel beam fitting at FR 40
LH and RH sides, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–57–3117, including
Appendix 01, dated January 25, 2013; or
Airbus Service Bulletin A340–57–4126,
including Appendix 01, dated January 25,
2013; as applicable.
(1) For Model A330–201, –202, –203, –223,
–243, –301, –321, –322, –323, –341, –342,
and –343 airplanes: At the later of the times
specified in paragraphs (l)(1)(i) and (l)(1)(ii)
of this AD.
PO 00000
Frm 00017
Fmt 4702
Sfmt 4702
25253
(i) At the applicable time specified in
paragraph 1.E.(2)., of the Accomplishment
Timescale of Airbus Service Bulletin A330–
57–3117, including Appendix 01, dated
January 25, 2013.
(ii) Within 2,400 flight cycles or 24 months
after the effective date of this AD, whichever
occurs first.
(2) For Model A340–211, –212, –213, –311,
–312, and –313 airplanes: At the later of the
times specified in paragraphs (l)(2)(i) and
(l)(2)(ii) of this AD.
(i) At the applicable time specified in
paragraph 1.E.(2)., of the Accomplishment
Timescale of Airbus Service Bulletin A340–
57–4126, including Appendix 01, dated
January 25, 2013.
(ii) Within 1,300 flight cycles or 24 months
after the effective date of this AD, whichever
occurs first.
(3) Airbus Service Bulletin A330–57–3098,
Revision 01, dated July 31, 2009.
(4) Airbus Service Bulletin A330–57–3098,
Revision 02, dated June 15, 2011.
(5) Airbus Service Bulletin A340–57–4106,
Revision 01, dated July 31, 2009.
(6) Airbus Service Bulletin A340–57–4106,
Revision 02, dated June 15, 2011.
(m) Corrective Actions
(1) If no cracking is found during any
inspection required by paragraph (j) of this
AD, before further flight: Install new or
oversized fastener, as applicable; seal the
fastener; and do all other applicable
corrective actions; in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–57–3081, Revision 05,
including Appendix 01, dated November 13,
2012; or Airbus Service Bulletin A340–57–
4089, Revision 05, including Appendix 01,
dated November 13, 2012; as applicable.
Thereafter, repeat the inspection required by
paragraph (j) of this AD at intervals not to
exceed the ‘‘Mandatory Intervals’’ specified
in Paragraph 1.E.(2)., of the Accomplishment
Timescale of Airbus Service Bulletin A330–
57–3081, Revision 05, including Appendix
01, dated November 13, 2012; or Airbus
Service Bulletin A340–57–4089, Revision 05,
including Appendix 01, dated November 13,
2012; as applicable.
(2) If any crack is found during any
inspection required by paragraph (j) or (l) of
this AD; before further flight, repair using a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
(n) Airplanes Excluded From Certain
Requirements
(1) For airplanes on which a rototest was
done at fastener hole Nr 6 before cold
working of the fastener hole during
accomplishment of the actions specified in
the applicable service information identified
in paragraph (n)(1)(i), (n)(1)(ii), (n)(1)(iii), or
(n)(1)(iv) of this AD: The ultrasonic
inspection specified in paragraph (l) of this
AD is not required.
(i) Airbus Service Bulletin A330–57–3098,
Revision 01, dated July 31, 2009.
(ii) Airbus Service Bulletin A330–57–3098,
Revision 02, dated June 15, 2011.
E:\FR\FM\04MYP1.SGM
04MYP1
25254
Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules
(iii) Airbus Service Bulletin A340–57–
4106, Revision 01, dated June 31, 2009.
(iv) Airbus Service Bulletin A340–57–
4106, Revision 02, dated June 15, 2011.
(2) For airplanes that have been modified
as of the effective date of this AD in
accordance with the Accomplishment
Instructions of the applicable service
information identified in paragraph (n)(1)(i),
(n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD:
No action is required by this paragraph,
except as otherwise required by paragraph (l)
of this AD and, provided that if any crack
was found during any modification specified
in this paragraph and the service information
specified to contact Airbus, repair was done
before further flight using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
tkelley on DSK3SPTVN1PROD with PROPOSALS
(o) Optional Terminating Actions
(1) Modification of an airplane in
accordance with the Accomplishment
Instructions of the applicable service
information identified in paragraph (o)(1)(i),
(o)(1)(ii), (o)(1)(iii), (o)(1)(iv), (o)(1)(v), or
(o)(1)(vi) of this AD; as applicable to airplane
type and depending on airplane
configuration; terminates the requirements of
this AD, provided that in case of any crack
finding during any modification specified in
this paragraph, and the service information
specifies to contact Airbus, repair is done
before further flight, using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or Airbus’s EASA
DOA. If approved by the DOA, the approval
must include the DOA-authorized signature
(i) Airbus Service Bulletin A330–57–3090,
dated March 27, 2006.
(ii) Airbus Service Bulletin A330–57–3090,
Revision 01, dated June 15, 2011.
(iii) Airbus Service Bulletin A330–57–
3098, Revision 03, including Appendix 01,
dated September 24, 2012.
(iv) Airbus Service Bulletin A340–57–
4098, dated March 27, 2006.
(v) Airbus Service Bulletin A340–57–4098,
Revision 01, dated June 15, 2011.
(vi) Airbus Service Bulletin A340–57–
4106, Revision 03, including Appendix 01,
dated September 24, 2012.
(2) Accomplishment of the ultrasonic
inspection required by paragraph (l) of this
AD and all applicable corrective actions
required by paragraph (m) of this AD
terminates the requirements of this AD for
those airplanes.
(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
VerDate Sep<11>2014
17:53 May 01, 2015
Jkt 235001
to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1138; 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. The AMOC approval letter
must specifically reference this AD.
(2) AMOCs approved previously for AD
2011–24–05, Amendment 39–16869 (76 FR
73496, November 29, 2011), are approved as
AMOCs for the corresponding provisions of
this AD.
(3) 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
EASA; or Airbus’s EASA 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) EASA
Airworthiness Directive 2014–0010R1, dated
May 5, 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–
2015–0937.
(2) For service information identified in
this AD, contact Airbus SAS—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You may
view this service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
Issued in Renton, Washington, on April 13,
2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–10177 Filed 5–1–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0934; Directorate
Identifier 2014–NM–030–AD]
RIN 2120–AA64
Airworthiness Directives; Dassault
Aviation Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
PO 00000
Frm 00018
Fmt 4702
Sfmt 4702
Notice of proposed rulemaking
(NPRM).
ACTION:
We propose to adopt a new
airworthiness directive (AD) for all
Dassault Aviation Model FAN JET
FALCON, FAN JET FALCON SERIES C,
D, E, F, and G airplanes; Model
MYSTERE–FALCON 200 airplanes; and
Model MYSTERE–FALCON 20–C5, 20–
D5, 20–E5, and 20–F5 airplanes. This
proposed AD was prompted by reports
of defective fire extinguisher tubes. It
was determined the defects were caused
by corrosion. This proposed AD would
require repetitive general visual
inspections of the fire extinguisher
tubes for cracking and corrosion, and
replacement of any cracked tube with a
serviceable tube, if necessary. We are
proposing this AD to detect and correct
cracking and corrosion in the fire
extinguisher tubes, which could impact
the capability to extinguish an engine
fire, and possibly result in damage to
the airplane and injury to the
passengers.
DATES: We must receive comments on
this proposed AD by June 18, 2015.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: 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.
SUMMARY:
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–
0934; 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: Tom
Rodriguez, Aerospace Engineer,
E:\FR\FM\04MYP1.SGM
04MYP1
]]>Agencies
[Federal Register Volume 80, Number 85 (Monday, May 4, 2015)]
[Proposed Rules]
[Pages 25249-25254]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-10177]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0937; Directorate Identifier 2014-NM-024-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2011-24-
05, for certain Airbus Model A330-201, -202, -203, -223, -243, -301, -
302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model
A340-200 and -300 series airplanes. AD 2011-24-05 currently requires
repetitive inspections for cracking of the hole(s) of the horizontal
flange of the keel beam, and repair if necessary. Since we issued AD
2011-24-05, a determination was made that the rototest inspection and
applicable corrective actions of a certain fastener hole were
inadvertently omitted from the requirements in that AD. This proposed
AD would change the inspection compliance times, and, for certain
airplanes, would add a one-time ultrasonic inspection for cracking at a
certain fastener hole. This proposed AD would also provide optional
terminating action for the repetitive inspections. We are proposing
this AD to detect and correct cracking of the fastener holes, which
could result in rupture of the keel beam, and consequent reduced
structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by June 18, 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 SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 45 80; email airworthiness.A330-A340@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://
[[Page 25250]]
www.regulations.gov by searching for and locating Docket No. FAA-2015-
0937; 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: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138;
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-2015-0937;
Directorate Identifier 2014-NM-024-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 November 7, 2011, we issued AD 2011-24-05, Amendment 39-16869
(76 FR 73496, November 29, 2011), for certain Airbus Model A330-201, -
202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342,
and -343 airplanes; and Model A340-200 and -300 series airplanes. AD
2011-24-05 requires actions intended to address the unsafe condition on
the products listed above.
Since we issued AD 2011-24-05, Amendment 39-16869 (76 FR 73496,
November 29, 2011), the European Aviation Safety Agency (EASA), which
is the Technical Agent for the Member States of the European Union, has
issued EASA Airworthiness Directive 2014-0010R1, dated May 5, 2014
(referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''), to correct an unsafe condition for
certain Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-
200 and -300 series airplanes. The MCAI states:
During A330 and A340 aeroplanes fatigue tests, cracks were
detected on the RH [right-hand] and LH [left-hand] sides between the
crossing area of the keel beam fitting and the front spar of the
Centre Wing Box (CWB).
This condition, if not detected and corrected, could lead to
keel beam rupture which would affect the area structural integrity
of the area.
Prompted by this potential unsafe condition, EASA issued AD
2006-0315 [https://ad.easa.europa.eu/blob/easa_ad_2006_0315.pdf/AD_2006-0315] (later revised to R1) to require repetitive special
detailed inspections (SDI) [rotating probe inspection for cracking]
on the horizontal flange of the keel beam in the area of first
fastener hole aft of Frame (FR) 40 in order to maintain the
structural integrity of the aeroplane.
After that [EASA] AD was issued, EASA issued AD 2010-0024 [which
corresponds to FAA AD 2011-24-05, Amendment 39-16869 (76 FR 73496,
November 29, 2011)], retaining the inspection requirements of EASA
AD 2006-0315R1 [https://ad.easa.europa.eu/blob/easa_ad_2006_0315R1.pdf/AD_2006-0315R1], which was superseded,
extending the applicability to aeroplanes with Airbus Mod 49202
embodied, and reducing the inspection thresholds and intervals.
Since that [EASA] AD [2010-0024] was issued, a new fatigue and
damage tolerance evaluation has been conducted by Airbus, which
concluded that due to the aeroplane utilization, the current
inspection threshold and intervals have to be modified.
In addition, it was determined that the rototest inspection of
fastener hole Nr 6, necessary to ensure that no crack was left
unrepaired at the time of fastener hold cold working, was
inadvertently not included in Revisions 01 and 02 of both Airbus
Service Bulletin (SB) A330-57-3098 and A340-57-4106.
Prompted by these findings, EASA issued AD 2014-0010 [https://ad.easa.europa.eu/blob/easa_ad_2014-0010.pdf/AD_2014-0010],
retaining the requirements of EASA AD 2010-0024, which was
superseded, and redefined the inspection thresholds and intervals
[by reducing certain compliance times], and added a one-time
ultrasonic inspection of fastener hold Nr 6 in the junction keel
beam fitting at FR40 on both LH and RH side[s].
Following issuance of EASA AD 2014-0010, it was identified that
there was a need for clarifications [of affected airplanes] * * *.
The compliance times vary depending on airplane utilization and
configuration. The earliest compliance time for the initial rotating
probe inspections is the later of (1) before 10,400 total flight cycles
or 67,800 total flight hours, whichever occurs first; and (2) within 24
months or 14,590 flight cycles or 43,790 flight hours, whichever occurs
first. The latest compliance time for the initial inspections is the
later of (1) before 20,800 total flight cycles or 67,900 total flight
hours, whichever occurs first; and (2) within 24 months or 21,180
flight cycles or 63,560 flight hours, whichever occurs first. The
compliance times for the repetitive intervals range between 7,800
flight cycles or 50,900 flight hours and 10,700 flight cycles or 35,200
flight hours. The compliance times for the one-time ultrasonic
inspection are the latest of (1) 21,000 flight cycles or 60,600 flight
hours and within 2,400 flight cycles or 24 months; or the latest of (2)
22,100 flight cycles and 64,400 flight hours, or within 1,300 flight
cycles or 24 months.
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-
0937.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information.
Airbus Service Bulletin A330-57-3081, Revision 05,
including Appendix 01, dated November 13, 2012.
Airbus Service Bulletin A330-57-3090, dated June 15, 2011.
Airbus Service Bulletin A330-57-3098, dated August 30,
2007.
Airbus Service Bulletin A330-57-3098, Revision 02, June
15, 2011.
Airbus Service Bulletin A330-57-3098, Revision 03,
including Appendix 01, dated September 24, 2014.
Airbus Service Bulletin A330-57-3117, including Appendix
01, dated January 25, 2013.
Airbus Service Bulletin A340-57-4089, Revision 05,
including Appendix 01, dated November 13, 2012.
Airbus Service Bulletin A340-57-4098, Revision 01, dated
June 15, 2011.
Airbus Service Bulletin A340-57-4106, dated August 30,
2007.
Airbus Service Bulletin A340-57-4106, Revision 02,
including Appendix 01, dated August 30, 2007.
Airbus Service Bulletin A340-57-4106, Revision 03,
including Appendix 01, dated September 24, 2012.
Airbus Service Bulletin A340-57-4126, including Appendix
01, dated January 25, 2013.
This service information describes procedures for inspections for
cracking of the hole(s) of the horizontal flange of the keel beam, and
contacting the manufacturer for repair instructions. Additionally, this
service information describes procedures for a one-time ultrasonic
inspection for cracking at fastener hole ``Nr 6,'' and provides
[[Page 25251]]
optional terminating action for the repetitive inspections.
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.
Explanation of Compliance Time
The compliance time for the modification specified in this proposed
AD for addressing widespread fatigue damage (WFD) was established to
ensure that discrepant structure is modified before WFD develops in
airplanes. Standard inspection techniques cannot be relied on to detect
WFD before it becomes a hazard to flight. We will not grant any
extensions of the compliance time to complete any AD-mandated service
bulletin related to WFD without extensive new data that would
substantiate and clearly warrant such an extension.
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 35 airplanes of U.S.
registry.
The actions that are required by AD 2011-24-05, Amendment 39-16869
(76 FR 73496, November 29, 2011), and retained in this proposed AD take
about 41 work-hours per product, at an average labor rate of $85 per
work hour. Required parts cost about $191 per product. Based on these
figures, the estimated cost of the actions that are required by AD
2011-24-05 is $3,676 per product.
We also estimate that it would take about 23 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $68,425, or $1,955
per product.
We have received no definitive data that would enable us to provide
a cost estimate for the on-condition actions specified in this proposed
AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), and
adding the following new AD:
Airbus: Docket No. FAA-2015-0937; Directorate Identifier 2014-NM-
024-AD.
(a) Comments Due Date
We must receive comments by June 18, 2015.
(b) Affected ADs
This AD replaces AD 2011-24-05, Amendment 39-16869 (76 FR 73496,
November 29, 2011).
(c) Applicability
(1) This AD applies to the airplanes identified in paragraphs
(c)(1)(i) and (c)(1)(ii) of this AD, certificated in any category,
except as provided by paragraph (c)(2) of this AD.
(i) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes, all serial
numbers, except those on which Airbus modification 55306 or 55792
has been embodied in production.
(ii) Airbus Model A340-211, -212, -213, -311, -312, and -313
airplanes, all serial numbers, except those on which Airbus
modification 55306 or 55792 has been embodied in production.
(2) This AD does not apply to Airbus Model A340-211, -212, -213,
-311, -312, and -313 airplanes on which the repair specified in
Airbus Repair Drawing R57115053, R57115051, or R57115047
(installation of titanium doubler on both sides) has been
accomplished. AD 2007-12-08, Amendment 39-15086 (72 FR 31171, June
6, 2007), applies to these airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports of cracks on the keel beam
fitting and the front spar of the center wing box. This AD was also
prompted by a determination that the rototest inspection and
applicable corrective actions of fastener hole Nr 6 were
inadvertently omitted from the requirements in AD 2011-24-05,
Amendment 39-16869 (76 FR 73496, November 29, 2011). We are issuing
this AD to detect and correct cracking of the fastener holes, which
could result in rupture of the keel beam, and consequent reduced
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
[[Page 25252]]
(g) Retained Non-Destructive Test (NDT) Inspection
This paragraph restates the requirements of paragraph (n) of AD
2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011),
with new service information and revised credit for certain actions.
At the applicable time in paragraph (g)(1) or (g)(2) of this AD, do
an NDT inspection of the hole(s) of the horizontal flange of the
keel beam located on frame (FR) 40 datum on the right-hand (RH) and/
or left-hand (LH) side of the fuselage, in accordance with the
Accomplishment Instructions of the applicable service information
specified in paragraph (g)(3), (g)(4), (g)(5), or (g)(6) of this AD.
Accomplishing an inspection required by paragraph (j) of this AD
terminates the inspections required by this paragraph.
(1) For airplanes on which an inspection required by paragraph
(h) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29,
2011), has not been done as of January 3, 2012 (the effective date
of AD 2011-24-05): At the applicable time specified in paragraph
(g)(1)(i) or (g)(1)(ii) of this AD.
(i) For all airplanes except those identified in paragraph
(g)(1)(ii) of this AD: Within the ``Mandatory Threshold'' (flight
cycles or flight hours) specified in table 1 of paragraph 1.E.(2) of
the Accomplishment Instructions of Airbus Service Bulletin A330-57-
3081, including Appendix 01, Revision 04, dated May 31, 2011; or
Airbus Service Bulletin A340-57-4089, including Appendix 01,
Revision 04, dated May 31, 2011; as applicable; or within 3 months
after January 3, 2012 (the effective date AD 2011-24-05, Amendment
39-16869 (76 FR 73496, November 29, 2011)); whichever occurs later.
The compliance times for configurations 02 through 06 specified in
the ``Mandatory Threshold'' column in table 1 of paragraph 1.E.,
``Compliance,'' are total flight cycles and total flight hours.
(ii) For Model A330-201, -202, -203, -223, -243, -301, -321, -
322, -323, -341, -342, and -343 airplanes, except those on which
Airbus modification 49202 has been embodied in production, or Airbus
Service Bulletin A330-57-3090 has been embodied in service, and
Model A340-200 and -300 series airplanes, except those on which
Airbus modification 49202 has been embodied in production or Airbus
Service Bulletin A340-57-4098 has been embodied in service, and
except Model A340-211, -212, -213, -311, -312, and -313 airplanes on
which the repair specified in Airbus Repair Drawing R57115053,
R57115051, or R57115047 has been accomplished: At the earlier of the
times specified in paragraphs (g)(1)(ii)(A) and (g)(1)(ii)(B) of
this AD.
(A) Within the ``Mandatory Threshold'' (flight cycles or flight
hours) specified in table 1 of paragraph 1.E.(2) of Airbus Service
Bulletin A340-57-4089, including Appendix 01, Revision 02, dated
January 24, 2006; or Airbus Service Bulletin A330-57-3081, including
Appendix 01, Revision 02, dated January 24, 2006; depending on the
configuration of the aircraft model; or within 3 months after
September 13, 2007, whichever occurs later. The compliance times for
Model A330 post-mod. 41652 and pre-mod. 44360, post-mod. 44360, and
pre-mod. 49202 (specified in Airbus Service Bulletin A330-57-3081,
including Appendix 01, Revision 02, dated January 24, 2006); and
Model A340 post-mod. 41652, post-mod. 43500 and pre-mod. 44360,
post-mod. 44360 and pre-mod. 49202, and weight variant 027
(specified in Airbus Service Bulletin A340-57-4089, including
Appendix 01, Revision 02, dated January 24, 2006); specified in the
``Mandatory Threshold'' column in table 1 of paragraph 1.E.,
``Compliance,'' are total flight cycles and total flight hours.
(B) Within the ``Mandatory Threshold'' (flight cycles or flight
hours) specified in table 1 of paragraph 1.E.(2) of the
Accomplishment Instructions of Airbus Service Bulletin A330-57-3081,
including Appendix 01, Revision 04, dated May 31, 2011; or Airbus
Service Bulletin A340-57-4089, including Appendix 01, Revision 04,
dated May 31, 2011; as applicable; or within 3 months after January
3, 2012 (the effective date of AD 2011-24-05, Amendment 39-16869 (76
FR 73496, November 29, 2011)); whichever occurs later. The
compliance times for configurations 02 through 06 specified in the
``Mandatory Threshold'' column in table 1 of paragraph 1.E.,
``Compliance,'' are total flight cycles and total flight hours.
(2) For airplanes on which an inspection required by paragraph
(h) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29,
2011), has been done as of January 3, 2012 (the effective date of AD
2011-24-05): At the earlier of the times specified in paragraphs
(g)(2)(i) and (g)(2)(ii) of this AD.
(i) Within the ``Mandatory Intervals'' given in table 1 of
paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, including
Appendix 01, Revision 02, dated January 24, 2006; or Airbus Service
Bulletin A330-57-3081, including Appendix 01, Revision 02, dated
January 24, 2006; as applicable.
(ii) Within the applicable ``Mandatory Interval'' specified in
table 1 of Paragraph 1.E.(2). of Airbus Service Bulletin A330-57-
3081, including Appendix 01, Revision 04, dated May 31, 2011,; or
Airbus Service Bulletin A340-57-4089, including Appendix 01,
Revision 04, dated May 31, 2011; as applicable; or within 3 months
after January 3, 2012 (the effective date of AD 2011-24-05,
Amendment 39-16869 (76 FR 73496, November 29, 2011)); whichever
occurs later.
(3) Airbus Service Bulletin A330-57-3081, including Appendix 01,
Revision 04, dated May 31, 2011.
(4) Airbus Service Bulletin A330-57-3081, including Appendix 01,
Revision 05, dated November 13, 2012.
(5) Airbus Service Bulletin A340-57-4089, including Appendix 01,
Revision 04, dated May 31, 2011.
(6) Airbus Service Bulletin A340-57-4089, Revision 05, including
Appendix 01, dated November 13, 2012.
(h) Retained Repetitive Inspections
This paragraph restates the requirements of paragraph (p) of AD
2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011). If
no cracking is found during any inspection required by paragraph (g)
of this AD, do the actions required by paragraphs (h)(1) and (h)(2)
of this AD.
(1) Before further flight: Install a new or oversized fastener,
as applicable; seal the fastener; and do all other applicable
actions; in accordance with the Accomplishment Instructions of the
applicable service information specified in paragraph (g)(3),
(g)(4), (g)(5), or (g)(6) of this AD.
(2) Repeat the inspection required by paragraph (g) of this AD
thereafter at intervals not to exceed the ``Mandatory Intervals''
specified in Paragraph 1.E.(2). of Airbus Service Bulletin A330-57-
3081, including Appendix 01, Revision 04, dated May 31, 2011; or
Airbus Service Bulletin A340-57-4089, including Appendix 01,
Revision 04, dated May 31, 2014; as applicable.
(i) Retained Corrective Action and Optional Modification
(1) This paragraph restates the requirements of paragraph (o) of
AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011),
with revised method of compliance language. If any cracking is found
during any inspection required by paragraph (g) of this AD, 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).
(2) This paragraph restates the requirements of paragraph (r) of
AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011),
with new service information and revised method of compliance
language. Modifying the fastener installation in the junction keel
beam fitting at FR 40, as specified in paragraph (i)(2)(i),
(i)(2)(ii), (i)(2)(iii), or (i)(2)(iv) of this AD, as applicable,
terminates the requirements of paragraphs (g) and (h) of this AD;
except, for airplanes on which a crack was detected at hole 5 before
oversizing of the keel beam, in accordance with step 3.B.(1)(b)3 of
the Accomplishment Instructions of Airbus Service Bulletin A330-57-
3098, dated August 30, 2007; or Airbus Service Bulletin A340-57-
4106, dated August 30, 2007; or in accordance with step 3.C.(2)(c)
of the Accomplishment Instructions of Airbus Service Bulletin A330-
57-3098, Revision 03, including Appendix 01, dated September 24,
2012, or Airbus Service Bulletin A340-57-4106, Revision 03,
including Appendix 01, dated September 24, 2012; before further
flight, repair using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA DOA. In case of any crack finding during any
modification specified in this paragraph: Where the service
information specifies to contact Airbus, before further flight,
repair using a method approved by the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's
EASA DOA.
(i) Modification in accordance with Airbus Service Bulletin
A330-57-3098, dated August 30, 2007, before January 3, 2012 (the
effective date of AD 2011-24-05,
[[Page 25253]]
Amendment 39-16869 (76 FR 73496, November 29, 2011)).
(ii) Modification in accordance with Airbus Service Bulletin
A330-57-3098, Revision 03, including Appendix 01, dated September
24, 2012, before the effective date of this AD.
(iii) Modification in accordance with Airbus Service Bulletin
A340-57-4106, dated August 30, 2007, before January 3, 2012 (the
effective date of AD 2011-24-05, Amendment 39-16869 (76 FR 73496,
November 29, 2011)).
(iv) Modification in accordance with Airbus Service Bulletin
A340-57-4106, Revision 03, including Appendix 01, dated September
24, 2012, before the effective date of this AD.
(j) New Repetitive Rotating Probe Inspections
At the applicable times specified in paragraphs (j)(1) and
(j)(2) of this AD: Do a rotating probe inspection for cracking of
the fastener hole(s) of the horizontal flange of the keel beam
located on FR 40 datum on the RH and LH side of the fuselage, as
applicable to airplane type and depending on airplane configuration
and utilization, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A330-57-3081, Revision 05, including
Appendix 01, dated November 13, 2012; or Airbus Service Bulletin
A340-57-4089, Revision 05, including Appendix 01, dated November 13,
2012; as applicable. Repeat the inspection thereafter at intervals
not to exceed the ``Mandatory Intervals'' specified in Paragraph
1.E.(2)., of the Accomplishment Timescale of Airbus Service Bulletin
A330-57-3081, Revision 05, including Appendix 01, dated November 13,
2012; or Airbus Service Bulletin A340-57-4089, Revision 05,
including Appendix 01, dated November 13, 2012; as applicable.
Accomplishing an inspection required by this paragraph terminates
the inspections required by paragraph (g) of this AD.
(1) For airplanes on which the inspection required by paragraph
(g) of this AD has not been done as of the effective date of this
AD: Do the inspection before exceeding the applicable compliance
times specified in the ``mandatory threshold'' column of the tables
in paragraph 1.E.(2)., of the Accomplishment Timescale of Airbus
Service Bulletin A330-57-3081, Revision 05, including Appendix 01,
dated November 13, 2012; or Airbus Service Bulletin A340-57-4089,
Revision 05, including Appendix 01, dated November 13, 2012; as
applicable; or within 12 months after the effective date of this AD;
whichever occurs later.
(2) For airplanes on which the inspection required by paragraph
(g) of this AD has been done as of the effective date of this AD: Do
the inspection within the applicable compliance times specified in
the ``mandatory interval'' column of the tables in paragraph
1.E.(2)., of the Accomplishment Timescale of Airbus Service Bulletin
A330-57-3081, Revision 05, including Appendix 01, dated November 13,
2012; or Airbus Service Bulletin A340-57-4089, Revision 05,
including Appendix 01, dated November 13, 2012; as applicable; or
within 12 months after the effective date of this AD; whichever
occurs later.
(k) Credit for Previous Actions
(1) This paragraph provides credit for the initial rotating
probe inspection that is part of the inspections required by
paragraphs (g) and (j)(1) of this AD, if those actions were
performed before the effective date of this AD using the service
information specified in paragraph (k)(1)(i) or (k)(1)(ii) of this
AD.
(i) Airbus Technical Disposition F57D03012810, Issue B, dated
August 18, 2003.
(ii) Airbus Technical Disposition 582.0651/2002, Issue A, dated
October 17, 2002.
(2) This paragraph restates the credit for the actions specified
in paragraph (k) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496,
November 29, 2011), if those actions were performed before January
3, 2012 (the effective date of AD 2011-24-05), using the service
information specified in paragraphs (k)(2)(i) through (k)(2)(viii)
of this AD.
(i) Airbus Service Bulletin A330-57-3081, dated October 30,
2003.
(ii) Airbus Service Bulletin A330-57-3081, Revision 01, dated
May 18, 2004.
(iii) Airbus Service Bulletin A330-57-3081, Revision 02,
including Appendix 01, dated January 24, 2006.
(iv) Airbus Mandatory Service Bulletin A330-57-3081, Revision
03, dated July 31, 2009.
(v) Airbus Service Bulletin A340-57-4089, dated October 30,
2003.
(vi) Airbus Service Bulletin A340-57-4089, Revision 01, dated
March 2, 2004.
(vii) Airbus Service Bulletin A340-57-4089, Revision 02,
including Appendix 01, dated January 24, 2006.
(viii) Airbus Mandatory Service Bulletin A340-57-4089, Revision
03, dated July 31, 2009.
(l) New One-Time Ultrasonic Inspection
For airplanes in Configuration 2, as defined in the applicable
service information identified in paragraph (l)(3), (l)(4), (l)(5),
or (l)(6) of this AD, on which the modification has been done as of
the effective date of this AD in accordance with the Accomplishment
Instructions of the applicable service information identified in
paragraph (l)(3), (l)(4), (l)(5), or (l)(6) of this AD; as
applicable to airplane type; and on which fastener hole ``Nr 5'' has
been bushed before embodiment of Airbus Service Bulletin A330-57-
3098, or Airbus Service Bulletin A340-57-4106, as applicable; or on
which a crack has been found on fastener hole ``Nr 5'' during
embodiment of Airbus Service Bulletin A330-57-3098, or Airbus
Service Bulletin A340-57-4106, as applicable: At the applicable time
specified in paragraph (l)(1) or (l)(2) of this AD, do a one-time
ultrasonic inspection for cracking at fastener hole ``Nr 6'' in the
junction keel beam fitting at FR 40 LH and RH sides, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A330-57-3117, including Appendix 01, dated January 25, 2013; or
Airbus Service Bulletin A340-57-4126, including Appendix 01, dated
January 25, 2013; as applicable.
(1) For Model A330-201, -202, -203, -223, -243, -301, -321, -
322, -323, -341, -342, and -343 airplanes: At the later of the times
specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD.
(i) At the applicable time specified in paragraph 1.E.(2)., of
the Accomplishment Timescale of Airbus Service Bulletin A330-57-
3117, including Appendix 01, dated January 25, 2013.
(ii) Within 2,400 flight cycles or 24 months after the effective
date of this AD, whichever occurs first.
(2) For Model A340-211, -212, -213, -311, -312, and -313
airplanes: At the later of the times specified in paragraphs
(l)(2)(i) and (l)(2)(ii) of this AD.
(i) At the applicable time specified in paragraph 1.E.(2)., of
the Accomplishment Timescale of Airbus Service Bulletin A340-57-
4126, including Appendix 01, dated January 25, 2013.
(ii) Within 1,300 flight cycles or 24 months after the effective
date of this AD, whichever occurs first.
(3) Airbus Service Bulletin A330-57-3098, Revision 01, dated
July 31, 2009.
(4) Airbus Service Bulletin A330-57-3098, Revision 02, dated
June 15, 2011.
(5) Airbus Service Bulletin A340-57-4106, Revision 01, dated
July 31, 2009.
(6) Airbus Service Bulletin A340-57-4106, Revision 02, dated
June 15, 2011.
(m) Corrective Actions
(1) If no cracking is found during any inspection required by
paragraph (j) of this AD, before further flight: Install new or
oversized fastener, as applicable; seal the fastener; and do all
other applicable corrective actions; in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-57-3081,
Revision 05, including Appendix 01, dated November 13, 2012; or
Airbus Service Bulletin A340-57-4089, Revision 05, including
Appendix 01, dated November 13, 2012; as applicable. Thereafter,
repeat the inspection required by paragraph (j) of this AD at
intervals not to exceed the ``Mandatory Intervals'' specified in
Paragraph 1.E.(2)., of the Accomplishment Timescale of Airbus
Service Bulletin A330-57-3081, Revision 05, including Appendix 01,
dated November 13, 2012; or Airbus Service Bulletin A340-57-4089,
Revision 05, including Appendix 01, dated November 13, 2012; as
applicable.
(2) If any crack is found during any inspection required by
paragraph (j) or (l) of this AD; before further flight, repair using
a method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
If approved by the DOA, the approval must include the DOA-authorized
signature.
(n) Airplanes Excluded From Certain Requirements
(1) For airplanes on which a rototest was done at fastener hole
Nr 6 before cold working of the fastener hole during accomplishment
of the actions specified in the applicable service information
identified in paragraph (n)(1)(i), (n)(1)(ii), (n)(1)(iii), or
(n)(1)(iv) of this AD: The ultrasonic inspection specified in
paragraph (l) of this AD is not required.
(i) Airbus Service Bulletin A330-57-3098, Revision 01, dated
July 31, 2009.
(ii) Airbus Service Bulletin A330-57-3098, Revision 02, dated
June 15, 2011.
[[Page 25254]]
(iii) Airbus Service Bulletin A340-57-4106, Revision 01, dated
June 31, 2009.
(iv) Airbus Service Bulletin A340-57-4106, Revision 02, dated
June 15, 2011.
(2) For airplanes that have been modified as of the effective
date of this AD in accordance with the Accomplishment Instructions
of the applicable service information identified in paragraph
(n)(1)(i), (n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD: No
action is required by this paragraph, except as otherwise required
by paragraph (l) of this AD and, provided that if any crack was
found during any modification specified in this paragraph and the
service information specified to contact Airbus, repair was done
before further flight using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval
must include the DOA-authorized signature.
(o) Optional Terminating Actions
(1) Modification of an airplane in accordance with the
Accomplishment Instructions of the applicable service information
identified in paragraph (o)(1)(i), (o)(1)(ii), (o)(1)(iii),
(o)(1)(iv), (o)(1)(v), or (o)(1)(vi) of this AD; as applicable to
airplane type and depending on airplane configuration; terminates
the requirements of this AD, provided that in case of any crack
finding during any modification specified in this paragraph, and the
service information specifies to contact Airbus, repair is done
before further flight, using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval
must include the DOA-authorized signature
(i) Airbus Service Bulletin A330-57-3090, dated March 27, 2006.
(ii) Airbus Service Bulletin A330-57-3090, Revision 01, dated
June 15, 2011.
(iii) Airbus Service Bulletin A330-57-3098, Revision 03,
including Appendix 01, dated September 24, 2012.
(iv) Airbus Service Bulletin A340-57-4098, dated March 27, 2006.
(v) Airbus Service Bulletin A340-57-4098, Revision 01, dated
June 15, 2011.
(vi) Airbus Service Bulletin A340-57-4106, Revision 03,
including Appendix 01, dated September 24, 2012.
(2) Accomplishment of the ultrasonic inspection required by
paragraph (l) of this AD and all applicable corrective actions
required by paragraph (m) of this AD terminates the requirements of
this AD for those airplanes.
(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: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) AMOCs approved previously for AD 2011-24-05, Amendment 39-
16869 (76 FR 73496, November 29, 2011), are approved as AMOCs for
the corresponding provisions of this AD.
(3) 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 EASA; or Airbus's EASA 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) EASA Airworthiness Directive 2014-0010R1, dated May 5, 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-2015-0937.
(2) For service information identified in this AD, contact
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You may view this service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on April 13, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-10177 Filed 5-1-15; 8:45 am]
BILLING CODE 4910-13-P
