Airworthiness Directives; Airbus Airplanes, 10255-10258 [2017-01776]
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10255
Rules and Regulations
Federal Register
Vol. 82, No. 27
Friday, February 10, 2017
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
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REGISTER issue of each week.
Examining the AD Docket
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–5040; Directorate
Identifier 2013–NM–192–AD; Amendment
39–18787; AD 2017–02–08]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A300 series airplanes;
and Model A300 B4–600, B4–600R, and
F4–600R series airplanes, and Model
A300 C4–605R Variant F airplanes
(collectively called Model A300–600
series airplanes). This AD was prompted
by a determination that certain
inspection thresholds and intervals
must be reduced. This AD requires
repetitive detailed inspections for
corrosion of the lower wing root joint,
and related investigative and corrective
actions if necessary. We are issuing this
AD to address the unsafe condition on
these products.
DATES: This AD is effective March 17,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 17, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAW, 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
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SUMMARY:
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referenced service information at the
FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA.
For information on the availability of
this material at the FAA, call 425–227–
1221. It is also available on the Internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2016–5040.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
5040; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is Docket Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone (425) 227–2125;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus Model A300
series airplanes; and Model A300 B4–
600, B4–600R, and F4–600R series
airplanes, and Model A300 C4–605R
Variant F airplanes (collectively called
Model A300–600 series airplanes). The
NPRM published in the Federal
Register on April 5, 2016 (81 FR 19509)
(‘‘the NPRM’’).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2013–0230,
dated September 24, 2013 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus Model A300 series
airplanes; and Model A300 B4–600, B4–
600R, and F4–600R series airplanes, and
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Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes). The MCAI
states:
Several cases of corrosion on the lower
wing root joint, located in the wing bottom
skin inboard and outboard of the external
lower surface splice, have been reported by
operators.
This condition, if not detected and
corrected, could affect the structural integrity
of the airframe.
Prompted by these findings, [Direction
´ ´
Generale de l’Aviation Civile] (DGAC) France
issued AD 1997–006–210 [which
corresponds to FAA AD 98–21–34,
Amendment 39–10842 (63 FR 55524, October
16, 1998)] to require repetitive inspections to
detect the presence of corrosion and prevent
crack propagation at the wing bottom skin,
inboard and outboard of the Rib 1 external
lower surface splice, between Frame (FR) 40
and FR47.
DGAC France * * * issued [an AD] to
expand the choice of applicable Service
Bulletins (SB). [The] DGAC France AD * * *
was issued to allow A300–600 operators to
use Revision 04 of Airbus SB A300–57–6047,
converting flight cycles/’’Fatigue rating’’ into
flight cycles (FC)/flight hours (FH).
Subsequently, Airbus modification 10599
was developed to improve the corrosion
behaviour of the area. This improvement
allowed refining the inspection programme
of the A300–600 aeroplane. For postmodification 10599 A300–600 aeroplanes,
the application of the Maintenance Review
Board Report (MRBR) inspection tasks was
deemed sufficient for maintaining an
adequate level of safety on these aeroplanes.
Consequently, EASA issued AD 2008–0208
(later revised), retaining the requirements of
[a] DGAC France AD * * *, which was
superseded, to require the use of Airbus SB
A300–57–6047 Revision 05 for the
inspections and to exclude post-modification
10599 A300–600 aeroplanes from the
Applicability.
Since EASA AD 2008–0208R1 was issued,
a fleet survey and updated Fatigue and
Damage Tolerance analyses have been
performed in order to substantiate the second
A300–600 Extended Service Goal (ESG2)
exercise. The results of these analyses
determined that the threshold and interval
must be reduced to allow timely detection of
these cracks and the accomplishment of an
applicable corrective action.
For the reasons described above, this
[EASA] AD takes over and retains the
requirements for A300 and A300–600
aeroplanes from EASA AD 2008–0208R1
(which has been revised, remaining
applicable only to A310 aeroplanes) and
requires accomplishment of the inspections
within the new thresholds and intervals.
Required actions include repetitive
detailed inspections for corrosion of the
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rib 1 external lower surface splice
between FR40 and FR47, repetitive
fatigue inspections for cracking of the
fasteners and on the surface of the
forward and aft lower surface panels if
necessary, and corrective actions
(including application of new protective
coating, removal of corrosion, and
measurement of the reworked depth) if
necessary.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
5040.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To Clarify the Applicability
United Parcel Service (UPS) requested
that we change the information in
paragraph (c), Applicability, of the
proposed AD. UPS explained that
paragraph (c) of the proposed AD
defines the airplane models applicable
to the proposed rule, then has an
exclusion later in paragraph (g) of the
proposed AD. UPS reasoned that we
should simplify by having related
information in the same location, and
suggested we combine paragraph (c) and
paragraph (g) of the proposed AD into
a single paragraph (c) of the proposed
AD.
For the reasons stated by the
commenter, we agree to include the
phrase, ‘‘except those on which Airbus
modification 10599 has been
incorporated,’’ in paragraph (c)(2) of this
AD. However, we disagree with moving
the statement, ‘‘As of the effective date
of this AD, the actions specified in AD
98–21–34, Amendment 39–10842 (63
FR 55524, October 16, 1998) (‘‘AD 98–
21–34’’) are no longer required’’ from
paragraph (g) of this AD to paragraph (c)
of this AD because the Applicability
should not include this type of
information; it is appropriately included
in other regulatory text such as
paragraph (g) of this AD.
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Request To Clarify the Headings of
Paragraphs (h) and (i) of the Proposed
AD
UPS requested that we revise the
headings of paragraphs (h) and (i) of the
proposed AD because the paragraph
titles do not reflect what is contained
within the respective paragraphs. UPS
explained that paragraph (h) of the
proposed AD does not contain any
corrective actions, and paragraph (i) of
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the proposed AD contains fatigue
inspection requirements.
For the reasons stated by the
commenter, we agree and have revised
the headings of both paragraphs (h) and
(i) of this AD.
Request for Grace Period
UPS stated that upon its review of the
fatigue inspection requirements, it
identified that there is not a transition/
grace period for airplanes on which
inspections are already being
accomplished, but for which the new
repetitive inspection intervals have
already been exceeded due to the
service bulletin interval reductions.
We agree with the commenter’s
statement. We had erroneously specified
Airbus Service Bulletin A300–57–6047,
Revision 06, dated October 17, 2011, in
the compliance time in paragraph
(i)(2)(ii)(B) of the proposed AD; the
correct reference is Airbus Service
Bulletin A300–57–6047, Revision 05,
dated May 27, 2008. We have changed
paragraph (i)(2)(ii)(B) of this AD to
include a grace period of 500 flight
cycles or 1,050 flight hours (whichever
occurs first), without exceeding the
compliance time specified in Airbus
Service Bulletin A300–57–6047,
Revision 05, dated May 27, 2008.
Request To Remove Paragraph (j) of the
Proposed AD
UPS requested that we delete
paragraph (j) of the proposed AD. UPS
explained that paragraphs (j)(1) and
(j)(2) of the proposed AD identify
differences between the service bulletin
requirements specified by the original
equipment manufacturer (OEM) and the
proposed AD. UPS stated that in its
review of paragraphs (j)(1) and (j)(2) of
the proposed AD, it does not recognize
a difference between contacting Airbus
for corrective action, and using a
method approved by the FAA for either
situation. UPS reasoned that, as the
discrepancy is located on primary
structure and allowable/approved
rework limits are exceeded, damage
tolerance analysis is required as part of
the repair definition process. UPS adds
that the existing OEM process, the
Repair Design Approval Sheet (RDAS),
contains instructions for continued
airworthiness and is approved by an
EASA-designated airworthiness
engineer. Based on the existing process
and procedures in place, UPS does not
believe that paragraph (j) of the
proposed AD is necessary.
We disagree with the request to delete
paragraph (j) of this AD. Paragraph (j)(1)
of this AD is required to address certain
inspection findings. The service
information specifies that Airbus be
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contacted for corrective action;
however, paragraph (j)(1) of this AD
requires that one of the specific
organizations identified must approve
those corrective actions. Likewise,
paragraph (j)(2) of this AD specifies the
appropriate organizations for
compliance time determinations.
Therefore, we have not changed this AD
in this regard.
Request To Define Average Flight Time
(AFT)
UPS requested that we revise
paragraph (k) of the proposed AD to
match paragraph (i) of AD 2016–07–20,
Amendment 39–18465 (81 FR 21255,
April 11, 2016). UPS reasoned that AD
2016–07–20 clearly defines when the
AFT value is calculated in subsequent
repetitive inspection interval
determinations. UPS explained that
recent FAA ADs have included using
AFT to determine repetitive inspection
intervals, but the definition of
calculating the AFT value has varied
among ADs, which further complicates
compliance across several mandatory
ADs.
For the reasons stated by the
commenter, we have added more
specific criteria for establishing the AFT
in paragraph (k) of this AD.
Request To Include Approval for
Previous Alternative Methods of
Compliance (AMOCs)
UPS requested that we revise
paragraph (m) of the proposed AD to
include approval for previous AMOCs.
UPS explained that other final rules
include approved AMOCs for prior or
superseded ADs. UPS explained further
that it received AMOC approval for AD
98–21–34 in which the intent is
embodied within the proposed AD (i.e.,
no additional action for an airplane with
modification 10599 embodied), and that
there may be other AMOC approvals
applicable to the previous AD.
We agree for the reasons stated by the
commenter. We added the previous
AMOC approval information in
paragraph (m)(1)(ii) of this final rule.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
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We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Related Service Information Under 1
CFR Part 51
We reviewed Airbus Service Bulletin
A300–57–0204, Revision 01, dated April
2, 1999; and Airbus Service Bulletin
A300–57–6047, Revision 06, dated
October 17, 2011. This service
information describes procedures for
repetitive detailed inspections for
corrosion of the rib 1 external lower
surface splice between FR40 and FR47,
repetitive fatigue inspections for
cracking of the fasteners and on the
surface of the forward and aft lower
surface panels if necessary, and
corrective actions (including application
of new protective coating, removal of
corrosion, and measurement of the
reworked depth) if necessary. These
documents are distinct since they apply
to different airplane models. 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.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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Costs of Compliance
We estimate that this AD affects 29
airplanes of U.S. registry. We also
estimate that it would take about 8
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate the
cost of this AD on U.S. operators to be
$19,720, or $680 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 8 work-hours, for a cost of $680
per product. 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
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–02–08 Airbus: Amendment 39–18787;
Docket No. FAA–2016–5040; Directorate
Identifier 2013–NM–192–AD.
(a) Effective Date
This AD is effective March 17, 2017.
(b) Affected ADs
This AD affects AD 98–21–34, Amendment
39–10842 (63 FR 55524, October 16, 1998)
(‘‘AD 98–21–34’’).
(c) Applicability
This AD applies to Airbus airplanes,
certificated in any category, identified in
paragraphs (c)(1) and (c)(2) of this AD.
(1) All Model A300 B2–1A, B2–1C, B2K–
3C, B2–203, B4–2C, B4–103, and B4–203
airplanes.
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(2) Model A300 B4–601, B4–603, B4–620,
B4–622, B4–605R, B4–622R, F4–605R, F4–
622R, and C4–605R Variant F airplanes,
except those on which Airbus modification
10599 has been incorporated.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by reports of
corrosion on the lower wing root joint
located in the wing bottom skin inboard and
outboard of the external lower surface splice,
and the determination that certain existing
inspection thresholds and intervals must be
reduced. We are issuing this AD to detect and
correct corrosion and cracking on the lower
wing root joint, which could reduce the
structural integrity of the airframe.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Airplanes Excluded From the
Requirements of AD 98–21–34 and This AD
For Model A300 B4–601, B4–603, B4–620,
B4–622, B4–605R, B4–622R, F4–605R, F4–
622R, and C4–605R Variant F airplanes, on
which Airbus modification 10599 has been
incorporated: As of the effective date of this
AD, the actions specified in AD 98–21–34 are
no longer required. No action is required by
this AD.
(h) Repetitive Inspections
Within 60 months since the airplane’s first
flight, or within 60 months since
accomplishment of the last inspection
specified in Airbus Service Bulletin A300–
57–0204 or A300–57–6047, whichever occurs
later: Do a detailed inspection for corrosion
of the rib 1 external lower surface splice
between frame (FR)40 and FR47, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–0204, Revision 01, dated April 2, 1999; or
Airbus Service Bulletin A300–57–6047,
Revision 06, dated October 17, 2011; as
applicable. Repeat the inspection thereafter
at intervals not to exceed 60 months.
Accomplishment of the initial inspection
required by this paragraph terminates the
requirements of AD 98–21–34 for Model
A300 and A300–600 series airplanes.
(i) Corrective Actions, Repetitive Fatigue
Inspections, and Repair
If any corrosion is found during any
inspection required by paragraph (h) of this
AD, do the actions specified in paragraph
(i)(1) and (i)(2) of this AD.
(1) Before further flight, do all applicable
corrective actions, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–0204, Revision 01,
dated April 2, 1999; or Airbus Service
Bulletin A300–57–6047, Revision 06, dated
October 17, 2011; as applicable; except as
required by paragraph (j)(1) of this AD.
(2) At the applicable time specified in
paragraph (i)(2)(i) or (i)(2)(ii) of this AD,
except as required by paragraph (j)(2) of this
AD: Do fatigue inspections to detect cracks of
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the fasteners and on the surface of the
forward and aft lower surface panels, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–0204, Revision 01, dated April 2, 1999; or
Airbus Service Bulletin A300–57–6047,
Revision 06, dated October 17, 2011; as
applicable. Repeat the fatigue inspections
thereafter at the applicable interval specified
in paragraph B.(5) of Airbus Service Bulletin
A300–57–0204, Revision 01, dated April 2,
1999; or Figure A–FBGAA, Sheet 01, of
Airbus Service Bulletin A300–57–6047,
Revision 06, dated October 17, 2011; as
applicable; except as required by paragraph
(j)(2) of this AD. If any cracking is found
during any fatigue inspection required by
this paragraph: 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).
(i) For Model A300 series airplanes: Do the
initial inspection at the applicable time
specified in paragraph B.(5) of Airbus Service
Bulletin A300–57–0204, Revision 01, dated
April 2, 1999.
(ii) For Model A300–600 series airplanes:
Do the initial inspection at the later of the
times specified in paragraphs (i)(2)(ii)(A) and
(i)(2)(ii)(B) of this AD.
(A) At the applicable time specified in
Figure A–FBGAA, Sheet 01, of Airbus
Service Bulletin A300–57–6047, Revision 06,
dated October 17, 2011.
(B) Within 500 flight cycles or 1,050 flight
hours after the effective date of this AD,
whichever occurs first, without exceeding the
compliance time specified in Airbus Service
Bulletin A300–57–6047, Revision 05, dated
May 27, 2008.
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(j) Exceptions to Service Bulletin
Specifications
(1) Where Airbus Service Bulletin A300–
57–0204, Revision 01, dated April 2, 1999; or
Airbus Service Bulletin A300–57–6047,
Revision 06, dated October 17, 2011;
specifies to contact Airbus for appropriate
corrective action, this AD requires repair
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.
(2) Where Airbus Service Bulletin A300–
57–6047, Revision 06, dated October 17,
2011, specifies to contact Airbus for the
appropriate threshold or repetitive interval,
this AD requires that the compliance time be
determined using a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA.
(k) Calculating Average Flight Time (AFT)
For the purposes of paragraph (i)(2) of this
AD, the AFT must be established as specified
in paragraphs (k)(1), (k)(2), and (k)(3) of this
AD.
(1) For the initial inspection, the AFT is
the total accumulated flight hours, counted
from take-off to touch-down, divided by the
total accumulated flight cycles at the
effective date of this AD.
(2) For the first repeated inspection
interval, the AFT is the total accumulated
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flight hours divided by the total accumulated
flight cycles at the time of the inspection
threshold.
(3) For all inspection intervals onward, the
AFT is the flight hours accumulated between
the two most recent inspections divided by
the flight cycles accumulated between the
two most recent inspections.
(l) Credit for Previous Actions
This paragraph provides credit for the
inspections and corrective actions required
by paragraphs (h) and (i) of this AD, if those
actions were performed before the effective
date of this AD using the applicable service
information specified in paragraphs (l)(1)
through (l)(3) of this AD.
(1) Airbus Service Bulletin A300–57–6047,
Revision 02, dated April 2, 1999.
(2) Airbus Service Bulletin A300–57–6047,
Revision 03, dated September 28, 1999.
(3) Airbus Service Bulletin A300–57–6047,
Revision 05, dated May 27, 2008.
(m) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227–2125; fax (425) 227–
1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
(i) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(ii) AMOCs approved previously for AD
98–21–34 are approved as AMOCs for the
corresponding provisions of paragraphs (h)
and (i) of this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2013–0230, dated September 24, 2013, 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–2016–5040.
(2) Service information identified in this
AD that is not incorporated by reference is
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available at the addresses specified in
paragraphs (o)(3) and (o)(4) of this AD.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A300–57–0204,
Revision 01, dated April 2, 1999.
(ii) Airbus Service Bulletin A300–57–6047,
Revision 06, dated October 17, 2011.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(4) You may view 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on January
18, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–01776 Filed 2–9–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–6670; Directorate
Identifier 2016–NM–006–AD; Amendment
39–18789; AD 2017–02–10]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2013–19–
04 for certain The Boeing Company
Model 737–600, –700, –700C, –800, and
–900 series airplanes. AD 2013–19–04
required repetitive inspections for
cracking of the skin around the fasteners
common to the ends of certain bulkhead
chords, and related investigative actions
and corrective actions if necessary; and
SUMMARY:
E:\FR\FM\10FER1.SGM
10FER1
Agencies
[Federal Register Volume 82, Number 27 (Friday, February 10, 2017)]
[Rules and Regulations]
[Pages 10255-10258]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-01776]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 82, No. 27 / Friday, February 10, 2017 /
Rules and Regulations
[[Page 10255]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-5040; Directorate Identifier 2013-NM-192-AD;
Amendment 39-18787; AD 2017-02-08]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A300 series airplanes; and Model A300 B4-600, B4-600R, and
F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes
(collectively called Model A300-600 series airplanes). This AD was
prompted by a determination that certain inspection thresholds and
intervals must be reduced. This AD requires repetitive detailed
inspections for corrosion of the lower wing root joint, and related
investigative and corrective actions if necessary. We are issuing this
AD to address the unsafe condition on these products.
DATES: This AD is effective March 17, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 17,
2017.
ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EAW, 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. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5040.
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-2016-
5040; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (telephone
800-647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-2125;
fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Airbus Model A300
series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series
airplanes, and Model A300 C4-605R Variant F airplanes (collectively
called Model A300-600 series airplanes). The NPRM published in the
Federal Register on April 5, 2016 (81 FR 19509) (``the NPRM'').
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2013-0230, dated September 24, 2013 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Airbus Model A300 series
airplanes; and Model A300 B4-600, B4-600R, and F4-600R series
airplanes, and Model A300 C4-605R Variant F airplanes (collectively
called Model A300-600 series airplanes). The MCAI states:
Several cases of corrosion on the lower wing root joint, located
in the wing bottom skin inboard and outboard of the external lower
surface splice, have been reported by operators.
This condition, if not detected and corrected, could affect the
structural integrity of the airframe.
Prompted by these findings, [Direction G[eacute]n[eacute]rale de
l'Aviation Civile] (DGAC) France issued AD 1997-006-210 [which
corresponds to FAA AD 98-21-34, Amendment 39-10842 (63 FR 55524,
October 16, 1998)] to require repetitive inspections to detect the
presence of corrosion and prevent crack propagation at the wing
bottom skin, inboard and outboard of the Rib 1 external lower
surface splice, between Frame (FR) 40 and FR47.
DGAC France * * * issued [an AD] to expand the choice of
applicable Service Bulletins (SB). [The] DGAC France AD * * * was
issued to allow A300-600 operators to use Revision 04 of Airbus SB
A300-57-6047, converting flight cycles/''Fatigue rating'' into
flight cycles (FC)/flight hours (FH).
Subsequently, Airbus modification 10599 was developed to improve
the corrosion behaviour of the area. This improvement allowed
refining the inspection programme of the A300-600 aeroplane. For
post-modification 10599 A300-600 aeroplanes, the application of the
Maintenance Review Board Report (MRBR) inspection tasks was deemed
sufficient for maintaining an adequate level of safety on these
aeroplanes.
Consequently, EASA issued AD 2008-0208 (later revised),
retaining the requirements of [a] DGAC France AD * * *, which was
superseded, to require the use of Airbus SB A300-57-6047 Revision 05
for the inspections and to exclude post-modification 10599 A300-600
aeroplanes from the Applicability.
Since EASA AD 2008-0208R1 was issued, a fleet survey and updated
Fatigue and Damage Tolerance analyses have been performed in order
to substantiate the second A300-600 Extended Service Goal (ESG2)
exercise. The results of these analyses determined that the
threshold and interval must be reduced to allow timely detection of
these cracks and the accomplishment of an applicable corrective
action.
For the reasons described above, this [EASA] AD takes over and
retains the requirements for A300 and A300-600 aeroplanes from EASA
AD 2008-0208R1 (which has been revised, remaining applicable only to
A310 aeroplanes) and requires accomplishment of the inspections
within the new thresholds and intervals.
Required actions include repetitive detailed inspections for
corrosion of the
[[Page 10256]]
rib 1 external lower surface splice between FR40 and FR47, repetitive
fatigue inspections for cracking of the fasteners and on the surface of
the forward and aft lower surface panels if necessary, and corrective
actions (including application of new protective coating, removal of
corrosion, and measurement of the reworked depth) if necessary.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5040.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Request To Clarify the Applicability
United Parcel Service (UPS) requested that we change the
information in paragraph (c), Applicability, of the proposed AD. UPS
explained that paragraph (c) of the proposed AD defines the airplane
models applicable to the proposed rule, then has an exclusion later in
paragraph (g) of the proposed AD. UPS reasoned that we should simplify
by having related information in the same location, and suggested we
combine paragraph (c) and paragraph (g) of the proposed AD into a
single paragraph (c) of the proposed AD.
For the reasons stated by the commenter, we agree to include the
phrase, ``except those on which Airbus modification 10599 has been
incorporated,'' in paragraph (c)(2) of this AD. However, we disagree
with moving the statement, ``As of the effective date of this AD, the
actions specified in AD 98-21-34, Amendment 39-10842 (63 FR 55524,
October 16, 1998) (``AD 98-21-34'') are no longer required'' from
paragraph (g) of this AD to paragraph (c) of this AD because the
Applicability should not include this type of information; it is
appropriately included in other regulatory text such as paragraph (g)
of this AD.
Request To Clarify the Headings of Paragraphs (h) and (i) of the
Proposed AD
UPS requested that we revise the headings of paragraphs (h) and (i)
of the proposed AD because the paragraph titles do not reflect what is
contained within the respective paragraphs. UPS explained that
paragraph (h) of the proposed AD does not contain any corrective
actions, and paragraph (i) of the proposed AD contains fatigue
inspection requirements.
For the reasons stated by the commenter, we agree and have revised
the headings of both paragraphs (h) and (i) of this AD.
Request for Grace Period
UPS stated that upon its review of the fatigue inspection
requirements, it identified that there is not a transition/grace period
for airplanes on which inspections are already being accomplished, but
for which the new repetitive inspection intervals have already been
exceeded due to the service bulletin interval reductions.
We agree with the commenter's statement. We had erroneously
specified Airbus Service Bulletin A300-57-6047, Revision 06, dated
October 17, 2011, in the compliance time in paragraph (i)(2)(ii)(B) of
the proposed AD; the correct reference is Airbus Service Bulletin A300-
57-6047, Revision 05, dated May 27, 2008. We have changed paragraph
(i)(2)(ii)(B) of this AD to include a grace period of 500 flight cycles
or 1,050 flight hours (whichever occurs first), without exceeding the
compliance time specified in Airbus Service Bulletin A300-57-6047,
Revision 05, dated May 27, 2008.
Request To Remove Paragraph (j) of the Proposed AD
UPS requested that we delete paragraph (j) of the proposed AD. UPS
explained that paragraphs (j)(1) and (j)(2) of the proposed AD identify
differences between the service bulletin requirements specified by the
original equipment manufacturer (OEM) and the proposed AD. UPS stated
that in its review of paragraphs (j)(1) and (j)(2) of the proposed AD,
it does not recognize a difference between contacting Airbus for
corrective action, and using a method approved by the FAA for either
situation. UPS reasoned that, as the discrepancy is located on primary
structure and allowable/approved rework limits are exceeded, damage
tolerance analysis is required as part of the repair definition
process. UPS adds that the existing OEM process, the Repair Design
Approval Sheet (RDAS), contains instructions for continued
airworthiness and is approved by an EASA-designated airworthiness
engineer. Based on the existing process and procedures in place, UPS
does not believe that paragraph (j) of the proposed AD is necessary.
We disagree with the request to delete paragraph (j) of this AD.
Paragraph (j)(1) of this AD is required to address certain inspection
findings. The service information specifies that Airbus be contacted
for corrective action; however, paragraph (j)(1) of this AD requires
that one of the specific organizations identified must approve those
corrective actions. Likewise, paragraph (j)(2) of this AD specifies the
appropriate organizations for compliance time determinations.
Therefore, we have not changed this AD in this regard.
Request To Define Average Flight Time (AFT)
UPS requested that we revise paragraph (k) of the proposed AD to
match paragraph (i) of AD 2016-07-20, Amendment 39-18465 (81 FR 21255,
April 11, 2016). UPS reasoned that AD 2016-07-20 clearly defines when
the AFT value is calculated in subsequent repetitive inspection
interval determinations. UPS explained that recent FAA ADs have
included using AFT to determine repetitive inspection intervals, but
the definition of calculating the AFT value has varied among ADs, which
further complicates compliance across several mandatory ADs.
For the reasons stated by the commenter, we have added more
specific criteria for establishing the AFT in paragraph (k) of this AD.
Request To Include Approval for Previous Alternative Methods of
Compliance (AMOCs)
UPS requested that we revise paragraph (m) of the proposed AD to
include approval for previous AMOCs. UPS explained that other final
rules include approved AMOCs for prior or superseded ADs. UPS explained
further that it received AMOC approval for AD 98-21-34 in which the
intent is embodied within the proposed AD (i.e., no additional action
for an airplane with modification 10599 embodied), and that there may
be other AMOC approvals applicable to the previous AD.
We agree for the reasons stated by the commenter. We added the
previous AMOC approval information in paragraph (m)(1)(ii) of this
final rule.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
[[Page 10257]]
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed Airbus Service Bulletin A300-57-0204, Revision 01,
dated April 2, 1999; and Airbus Service Bulletin A300-57-6047, Revision
06, dated October 17, 2011. This service information describes
procedures for repetitive detailed inspections for corrosion of the rib
1 external lower surface splice between FR40 and FR47, repetitive
fatigue inspections for cracking of the fasteners and on the surface of
the forward and aft lower surface panels if necessary, and corrective
actions (including application of new protective coating, removal of
corrosion, and measurement of the reworked depth) if necessary. These
documents are distinct since they apply to different airplane models.
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.
Costs of Compliance
We estimate that this AD affects 29 airplanes of U.S. registry. We
also estimate that it would take about 8 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD on U.S. operators to be $19,720, or $680 per product.
In addition, we estimate that any necessary follow-on actions would
take about 8 work-hours, for a cost of $680 per product. 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 AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2017-02-08 Airbus: Amendment 39-18787; Docket No. FAA-2016-5040;
Directorate Identifier 2013-NM-192-AD.
(a) Effective Date
This AD is effective March 17, 2017.
(b) Affected ADs
This AD affects AD 98-21-34, Amendment 39-10842 (63 FR 55524,
October 16, 1998) (``AD 98-21-34'').
(c) Applicability
This AD applies to Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) All Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103,
and B4-203 airplanes.
(2) Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R,
F4-605R, F4-622R, and C4-605R Variant F airplanes, except those on
which Airbus modification 10599 has been incorporated.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports of corrosion on the lower wing
root joint located in the wing bottom skin inboard and outboard of
the external lower surface splice, and the determination that
certain existing inspection thresholds and intervals must be
reduced. We are issuing this AD to detect and correct corrosion and
cracking on the lower wing root joint, which could reduce the
structural integrity of the airframe.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Airplanes Excluded From the Requirements of AD 98-21-34 and This AD
For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R,
F4-605R, F4-622R, and C4-605R Variant F airplanes, on which Airbus
modification 10599 has been incorporated: As of the effective date
of this AD, the actions specified in AD 98-21-34 are no longer
required. No action is required by this AD.
(h) Repetitive Inspections
Within 60 months since the airplane's first flight, or within 60
months since accomplishment of the last inspection specified in
Airbus Service Bulletin A300-57-0204 or A300-57-6047, whichever
occurs later: Do a detailed inspection for corrosion of the rib 1
external lower surface splice between frame (FR)40 and FR47, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus
Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011;
as applicable. Repeat the inspection thereafter at intervals not to
exceed 60 months. Accomplishment of the initial inspection required
by this paragraph terminates the requirements of AD 98-21-34 for
Model A300 and A300-600 series airplanes.
(i) Corrective Actions, Repetitive Fatigue Inspections, and Repair
If any corrosion is found during any inspection required by
paragraph (h) of this AD, do the actions specified in paragraph
(i)(1) and (i)(2) of this AD.
(1) Before further flight, do all applicable corrective actions,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus
Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011;
as applicable; except as required by paragraph (j)(1) of this AD.
(2) At the applicable time specified in paragraph (i)(2)(i) or
(i)(2)(ii) of this AD, except as required by paragraph (j)(2) of
this AD: Do fatigue inspections to detect cracks of
[[Page 10258]]
the fasteners and on the surface of the forward and aft lower
surface panels, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2,
1999; or Airbus Service Bulletin A300-57-6047, Revision 06, dated
October 17, 2011; as applicable. Repeat the fatigue inspections
thereafter at the applicable interval specified in paragraph B.(5)
of Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2,
1999; or Figure A-FBGAA, Sheet 01, of Airbus Service Bulletin A300-
57-6047, Revision 06, dated October 17, 2011; as applicable; except
as required by paragraph (j)(2) of this AD. If any cracking is found
during any fatigue inspection required by this paragraph: 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).
(i) For Model A300 series airplanes: Do the initial inspection
at the applicable time specified in paragraph B.(5) of Airbus
Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999.
(ii) For Model A300-600 series airplanes: Do the initial
inspection at the later of the times specified in paragraphs
(i)(2)(ii)(A) and (i)(2)(ii)(B) of this AD.
(A) At the applicable time specified in Figure A-FBGAA, Sheet
01, of Airbus Service Bulletin A300-57-6047, Revision 06, dated
October 17, 2011.
(B) Within 500 flight cycles or 1,050 flight hours after the
effective date of this AD, whichever occurs first, without exceeding
the compliance time specified in Airbus Service Bulletin A300-57-
6047, Revision 05, dated May 27, 2008.
(j) Exceptions to Service Bulletin Specifications
(1) Where Airbus Service Bulletin A300-57-0204, Revision 01,
dated April 2, 1999; or Airbus Service Bulletin A300-57-6047,
Revision 06, dated October 17, 2011; specifies to contact Airbus for
appropriate corrective action, this AD requires repair 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.
(2) Where Airbus Service Bulletin A300-57-6047, Revision 06,
dated October 17, 2011, specifies to contact Airbus for the
appropriate threshold or repetitive interval, this AD requires that
the compliance time be determined using a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or EASA; or Airbus's EASA DOA.
(k) Calculating Average Flight Time (AFT)
For the purposes of paragraph (i)(2) of this AD, the AFT must be
established as specified in paragraphs (k)(1), (k)(2), and (k)(3) of
this AD.
(1) For the initial inspection, the AFT is the total accumulated
flight hours, counted from take-off to touch-down, divided by the
total accumulated flight cycles at the effective date of this AD.
(2) For the first repeated inspection interval, the AFT is the
total accumulated flight hours divided by the total accumulated
flight cycles at the time of the inspection threshold.
(3) For all inspection intervals onward, the AFT is the flight
hours accumulated between the two most recent inspections divided by
the flight cycles accumulated between the two most recent
inspections.
(l) Credit for Previous Actions
This paragraph provides credit for the inspections and
corrective actions required by paragraphs (h) and (i) of this AD, if
those actions were performed before the effective date of this AD
using the applicable service information specified in paragraphs
(l)(1) through (l)(3) of this AD.
(1) Airbus Service Bulletin A300-57-6047, Revision 02, dated
April 2, 1999.
(2) Airbus Service Bulletin A300-57-6047, Revision 03, dated
September 28, 1999.
(3) Airbus Service Bulletin A300-57-6047, Revision 05, dated May
27, 2008.
(m) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone (425) 227-2125; fax (425) 227-1149. Information may
be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office. The AMOC approval letter must specifically
reference this AD.
(ii) AMOCs approved previously for AD 98-21-34 are approved as
AMOCs for the corresponding provisions of paragraphs (h) and (i) of
this AD.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA;
or Airbus's EASA DOA. If approved by the DOA, the approval must
include the DOA-authorized signature.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2013-0230, dated September 24, 2013, 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-2016-5040.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (o)(3) and (o)(4) of this AD.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A300-57-0204, Revision 01, dated
April 2, 1999.
(ii) Airbus Service Bulletin A300-57-6047, Revision 06, dated
October 17, 2011.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com;
Internet https://www.airbus.com.
(4) You may view 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on January 18, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-01776 Filed 2-9-17; 8:45 am]
BILLING CODE 4910-13-P