Airworthiness Directives; Airbus Airplanes, 11399-11404 [2018-05018]
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Federal Register / Vol. 83, No. 51 / Thursday, March 15, 2018 / Rules and Regulations
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by
the design approval holder indicating that
the side panel-to-frame attachments and
frames of the aft cargo compartment are
subject to widespread fatigue damage. We are
issuing this AD to prevent fatigue cracking at
the attachment points of the side panel-toframe attachments of the aft cargo
compartment, which could result in reduced
structural integrity of the body frames, and
consequent rapid decompression of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) One-Time General Visual Inspection and
Corrective Actions
Except as required by paragraph (h) of this
AD: At the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 757–53A0012,
Revision 1, dated January 25, 2017, do all
applicable actions identified as ‘‘RC’’
(required for compliance) in, and in
accordance with, the Accomplishment
Instructions of Boeing Alert Service Bulletin
757–53A0012, Revision 1, dated January 25,
2017.
(h) Exceptions to Service Information
Specifications
(1) For purposes of determining
compliance with the requirements of this AD:
Where Boeing Alert Service Bulletin 757–
53A0012, Revision 1, dated January 25, 2017,
uses the phrase ‘‘the Revision 1 date of this
service bulletin,’’ this AD requires using ‘‘the
effective date of this AD.’’
(2) Where Boeing Alert Service Bulletin
757–53A0012, Revision 1, dated January 25,
2017, specifies contacting Boeing, and
specifies that action as RC: This AD requires
repair using a method approved in
accordance with the procedures specified in
paragraph (j) of this AD.
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(i) Terminating Action for Inspections
Accomplishment of a modification in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
757–53A0012, Revision 1, dated January 25,
2017, terminates the inspections required by
paragraph (g) of this AD at the modified
location only.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles ACO Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your
principal inspector or local Flight Standards
District Office, as appropriate. If sending
information directly to the manager of the
certification office, send it to the attention of
the person identified in paragraph (k) of this
AD. Information may be emailed to: 9-ANMLAACO-AMOC-Requests@faa.gov.
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(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO Branch, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (h)(2)
of this AD: For service information that
contains steps that are labeled as RC, the
provisions of paragraphs (j)(4)(i) and (j)(4)(ii)
of this AD apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(k) Related Information
For more information about this AD,
contact Peter Jarzomb, Aerospace Engineer,
Airframe Section, Los Angeles ACO Branch,
FAA, 3960 Paramount Boulevard, Lakewood,
CA 90712–4137; phone: 562–627–5234; fax:
562–627–5210; email: peter.jarzomb@faa.gov.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 757–
53A0012, Revision 1, dated January 25, 2017.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
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11399
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 March 2,
2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–05015 Filed 3–14–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0695; Product
Identifier 2016–NM–173–AD; Amendment
39–19223; AD 2018–06–03]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2009–18–
16, which applied to certain Airbus
Model A310–203, –204, –221, –222,
–304, –322, –324, and –325 airplanes.
AD 2009–18–16 required an inspection
for cracking of certain fastener holes on
certain frames, and related investigative
and corrective actions if necessary; and
modification of certain fastener holes.
This new AD reduces the compliance
times. This AD was prompted by the
identification of a structural
modification that falls within the scope
of the work related to the extension of
the service life of the affected airplanes
and widespread fatigue damage
evaluations. We are issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
This AD is effective April 19,
2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 19, 2018.
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.airwortheas@airbus.com; internet: https://
www.airbus.com. You may view this
referenced service information at the
FAA, Transport Standards Branch, 2200
DATES:
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Federal Register / Vol. 83, No. 51 / Thursday, March 15, 2018 / Rules and Regulations
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–
0695.
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–2017–
0695; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (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 Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone 206–231–3225.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2009–18–16,
Amendment 39–16012 (74 FR 46342,
September 9, 2009) (‘‘AD 2009–18–16’’).
AD 2009–18–16 applied to certain
Airbus Model A310–203, –204, –221,
–222, –304, –322, –324, and –325
airplanes. The NPRM published in the
Federal Register on July 14, 2017 (82 FR
32503). We are issuing this AD to
prevent fatigue cracking of the frame
foot run-outs, which could lead to
rupture of the frame foot and cracking
in adjacent frames and skin, and which
could result in reduced structural
integrity of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2016–0197,
dated October 5, 2016 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), for all Airbus Model A310–
203, –204, –221, –222, –304, –322, –324,
and –325 airplanes. EASA AD 2016–
0197 supersedes EASA AD 2008–0212,
dated December 4, 2008. EASA AD
2008–0212 was the MCAI referred to in
FAA AD 2009–18–16. The new MCAI
states:
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Within the scope of work related to the
extension of the service life of A310 design
and widespread fatigue damage evaluations,
´ ´
DGAC [Direction Generale de l’Aviation
Civile] France issued AD F–2005–078 (EASA
approval 2005–3957) [which corresponds to
FAA AD 2006–02–06, Amendment 39–14458
(71 FR 3214, January 20, 2006)] to require a
structural modification, as defined in Airbus
Service Bulletin (SB) A310–53–2124 (Airbus
modification 13023), to increase the service
life of junctions of center box upper frame
bases to upper fuselage arches.
The threshold timescales for
accomplishment of the tasks as defined in SB
A310–53–2124 were refined and reduced.
Consequently, EASA issued AD 2007–0238
to require compliance with Revision 01 of SB
A310–53–2124 at the reduced compliance
times, superseding (the requirements of)
DGAC France AD F–2005–078. Subsequently,
Airbus identified reference material that was
erroneously introduced into Airbus SB
A310–53–2124 Revision 01. As a result, the
SB instructions could not be accomplished
properly. Operators that tried to apply SB
A310–53–2124 at Revision 01 had to contact
Airbus; see also Airbus SBIT [service bulletin
information telex] ref. 914.0135/08, dated 03
March 2008.
Consequently, [EASA] AD 2007–0238 was
revised to exclude reference to Airbus SB
A310–53–2124 Revision 01 and to require
accomplishment of the task(s) as described in
the original SB A310–53–2124 instead,
although retaining the reduced compliance
times introduced by [EASA] AD 2007–0238
at original issue.
EASA AD 2008–0212, superseding [EASA]
AD 2007–0238R1, was published to refer to
Airbus SB A310 53–2124 Revision 02, the
corrected version that was used to meet the
requirements of this [EASA] AD.
Since [EASA] AD 2008–0212 was issued,
new investigations in the frame of the
Widespread Fatigue Damage campaign
induced thresholds reduction, and Airbus
issued SB A310–53–2124 Revision 03.
For the reason described above, this
[EASA] AD retains the requirements of EASA
AD 2008–0212, which is superseded, and
requires accomplishment of modification(s)
within reduced compliance time, as
published in Airbus SB A310–53–2124
Revision 03.
Required actions include a high
frequency eddy current (HFEC) rotating
probe inspection for cracking of certain
fastener holes on certain frames, and
related investigative and corrective
actions if necessary; and modification of
certain fastener holes. Related
investigative actions include an
additional HFEC rotating probe
inspection for cracking of fastener holes
and a check to determine the edge
distance of certain holes. Corrective
actions include ream out of cracks and
repair.
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–2017–
0695.
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Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the NPRM and the FAA’s
response to that comment.
Request To Revise the Costs of
Compliance
FedEx stated that repairs would cost
an additional $10,000 per airplane. The
commenter noted that 66% of its past
accomplishments required additional
efforts to incorporate the modification
with supplementary repair activities.
The commenter suggested that the
average cost of compliance would
approach $30,000 per airplane. We infer
that the commenter is requesting a
revision to the costs of compliance in
the NPRM. We agree with commenter’s
request to revise the costs of compliance
in this final rule. We have revised the
Costs of Compliance section in this final
rule accordingly.
Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting this AD
with the change 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.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A310–53–2124, Revision 03, dated
December 22, 2014. This service
information describes procedures for a
rotating probe inspection for cracking
between frame (FR) 43 through FR 46 on
the center box, and the cold expansion
(modification) of the most fatigue
sensitive fastener holes. 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 8
airplanes of U.S. registry.
We estimate that it will take about 41
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $85 per work-hour.
Required parts will cost about $20,180
per product. Based on these figures, we
estimate the cost of this AD on U.S.
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operators to be $189,320, or $23,665 per
product.
Although we have received no
definitive data that will enable us to
provide cost estimates for the oncondition actions (i.e., additional
inspection and modification for certain
airplanes) specified in this AD, we have
determined that the total repair costs
could be up to $10,000 per product. We
have no way of determining the number
of aircraft that might need these repairs.
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.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes to the Director of the System
Oversight Division.
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Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
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responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2009–18–16, Amendment 39–16012 (74
FR 46342, September 9, 2009), and
adding the following new AD:
■
2018–06–03 Airbus: Amendment 39–19223;
Docket No. FAA–2017–0695; Product
Identifier 2016–NM–173–AD.
(a) Effective Date
This AD is effective April 19, 2018.
(b) Affected ADs
This AD replaces AD 2009–18–16,
Amendment 39–16012 (74 FR 46342,
September 9, 2009) (‘‘AD 2009–18–16’’).
(c) Applicability
This AD applies to Airbus Model A310–
203, –204, –221, –222, –304, –322, –324 and
–325 airplanes; certificated in any category;
all serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
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11401
(e) Reason
This AD was prompted by an evaluation by
the design approval holder indicating that
the junctions of center box upper frame bases
to the upper fuselage arches are subject to
widespread fatigue damage and that the
compliance threshold for the modification in
AD 2009–18–16 should be reduced. We are
issuing this AD to prevent fatigue cracking of
the frame foot run-outs, which could lead to
rupture of the frame foot and cracking in
adjacent frames and skin, and which could
result in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspections and Modification of Fastener
Holes
Except for airplanes modified before the
effective date of this AD using the
Accomplishment Instructions of Airbus
Service Bulletin A310–53–2124: At the times
specified in paragraph (g)(1) of this AD but
no later than the times specified in paragraph
(g)(2) of this AD, do a high frequency eddy
current (HFEC) rotating probe inspection for
cracking of fastener holes H1 through H29 on
frames 43 through 46, and do all applicable
related investigative and corrective actions,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A310–
53–2124, Revision 03, dated December 22,
2014, except as required by paragraph (h) of
this AD. If no cracking is found and the edge
distance of the fastener hole is equal to or
greater than the distance specified in the
Accomplishment Instructions of Airbus
Service Bulletin A310–53–2124, Revision 03,
dated December 22, 2014, before further
flight, do the modification (cold expansion)
of the affected fastener holes, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A310–53–2124,
Revision 03, dated December 22, 2014. Do all
applicable related investigative and
corrective actions before further flight.
(1) Inspect at the applicable time specified
in table 1 to paragraph (g)(1) of this AD, or
within 24 months after the effective date of
this AD, whichever occurs later. To establish
the average flight time (AFT), take the
accumulated flight time (counted from the
take-off up to the landing) and divide by the
number of accumulated flight cycles. This
gives the AFT per flight cycle. Although the
thresholds for Model A310–304, –322, –324,
and –325 airplanes are optimized to airplane
utilization, an operator can choose to use the
thresholds for the other AFT.
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(2) Inspect at the later of the times
specified in paragraphs (g)(2)(i) and (g)(2)(ii)
of this AD.
(i) At the applicable time indicated in table
2 to paragraph (g)(2)(i) of this AD. Airbus
Model A310–304, –322, –324, and –325
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airplanes with an AFT equal to or less than
3.16 flight hours are short range airplanes.
Airbus Model A310–304, –322, –324, and
–325 airplanes with an AFT exceeding 3.16
flight hours are long range airplanes. For this
paragraph, to establish the average flight
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time, take the accumulated flight time
(counted from the take-off up to the landing)
and divide by the number of accumulated
flight cycles. This gives the AFT per flight
cycle.
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(h) Service Information Exception
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Where Airbus Service Bulletin A310–53–
2124, Revision 03, dated December 22, 2014,
specifies to contact Airbus for appropriate
action, and specifies that action as ‘‘RC’’
(required for compliance): Before further
flight, accomplish corrective actions in
accordance with the procedures specified in
paragraph (l)(2) of this AD.
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(i) Airplanes Modified per Revision 01 of the
Service Information
For airplanes modified before the effective
date of this AD using Airbus Service Bulletin
A310–53–2124, Revision 01, dated May 3,
2007: Unless already accomplished, before
further flight, do applicable corrective
actions using a method approved by the
Manager, International Section, Transport
Standards Branch, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must
include the DOA-authorized signature.
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(j) Additional Inspection and Modification
Except as provided by paragraphs (j)(1) and
(j)(2) of this AD, as applicable: At the
applicable thresholds specified in table 3 to
the introductory text of paragraph (j) of this
AD, contact the Manager, International
Section, Transport Standards Branch, FAA;
or EASA; or Airbus’s EASA DOA for
additional inspection and modification
instructions. Accomplish those instructions
within the compliance times approved by the
Manager, International Section, Transport
Standards Branch, FAA; or EASA; or
Airbus’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
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(ii) Within 500 flight cycles or 800 flight
hours after October 14, 2009 (the effective
date of AD 2009–18–16), whichever occurs
first.
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(1) For Model A310–203, –204, –221, and
–222 airplanes: No additional inspection is
required if the inspection and modification
specified in Airbus Service Bulletin A310–
53–2124 was done after the accumulation of
29,500 flight cycles and 70,900 flight hours
since the first flight of the airplane.
(2) For Model A310–304, -322, –324, and
–325 airplanes: No additional inspection is
required if the inspection and modification
specified in Airbus Service Bulletin A310–
53–2124 was done after the accumulation of
22,600 flight cycles and 69,400 flight hours
since the first flight of the airplane.
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(k) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using the
Accomplishment Instructions of Airbus
Service Bulletin A310–53–2124, dated April
4, 2005; or Airbus Service Bulletin A310–53–
2124, Revision 02, dated May 22, 2008.
(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, 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 Section, send it
to the attention of the person identified in
paragraph (m)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
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the Manager, International Section, Transport
Standards Branch, FAA; or EASA; or
Airbus’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): Except
as provided by paragraph (h) of this AD: If
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0197, dated October 5, 2016, 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–2017–0695.
(2) For more information about this AD,
contact Dan Rodina, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone: 206–231–
3225.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
(n) 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 A310–53–2124,
Revision 03, dated December 22, 2014.
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
(ii) Reserved.
(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 Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(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 March 2,
2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–05018 Filed 3–14–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0626; Product
Identifier 2016–NM–210–AD; Amendment
39–19226; AD 2018–06–06]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
E:\FR\FM\15MRR1.SGM
15MRR1
ER15MR18.004</GPH>
11404
]]>Agencies
[Federal Register Volume 83, Number 51 (Thursday, March 15, 2018)]
[Rules and Regulations]
[Pages 11399-11404]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-05018]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0695; Product Identifier 2016-NM-173-AD; Amendment
39-19223; AD 2018-06-03]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2009-18-16,
which applied to certain Airbus Model A310-203, -204, -221, -222, -304,
-322, -324, and -325 airplanes. AD 2009-18-16 required an inspection
for cracking of certain fastener holes on certain frames, and related
investigative and corrective actions if necessary; and modification of
certain fastener holes. This new AD reduces the compliance times. This
AD was prompted by the identification of a structural modification that
falls within the scope of the work related to the extension of the
service life of the affected airplanes and widespread fatigue damage
evaluations. We are issuing this AD to address the unsafe condition on
these products.
DATES: This AD is effective April 19, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 19,
2018.
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: [email protected];
internet: https://www.airbus.com. You may view this referenced service
information at the FAA, Transport Standards Branch, 2200
[[Page 11400]]
South 216th St., Des Moines, WA. For information on the availability of
this material at the FAA, call 206-231-3195. It is also available on
the internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2017-0695.
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-2017-
0695; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (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 Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone 206-231-3225.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2009-18-16, Amendment 39-16012 (74 FR 46342,
September 9, 2009) (``AD 2009-18-16''). AD 2009-18-16 applied to
certain Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and
-325 airplanes. The NPRM published in the Federal Register on July 14,
2017 (82 FR 32503). We are issuing this AD to prevent fatigue cracking
of the frame foot run-outs, which could lead to rupture of the frame
foot and cracking in adjacent frames and skin, and which could result
in reduced structural integrity of the airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2016-0197, dated October 5, 2016 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), for
all Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325
airplanes. EASA AD 2016-0197 supersedes EASA AD 2008-0212, dated
December 4, 2008. EASA AD 2008-0212 was the MCAI referred to in FAA AD
2009-18-16. The new MCAI states:
Within the scope of work related to the extension of the service
life of A310 design and widespread fatigue damage evaluations, DGAC
[Direction G[eacute]n[eacute]rale de l'Aviation Civile] France
issued AD F-2005-078 (EASA approval 2005-3957) [which corresponds to
FAA AD 2006-02-06, Amendment 39-14458 (71 FR 3214, January 20,
2006)] to require a structural modification, as defined in Airbus
Service Bulletin (SB) A310-53-2124 (Airbus modification 13023), to
increase the service life of junctions of center box upper frame
bases to upper fuselage arches.
The threshold timescales for accomplishment of the tasks as
defined in SB A310-53-2124 were refined and reduced. Consequently,
EASA issued AD 2007-0238 to require compliance with Revision 01 of
SB A310-53-2124 at the reduced compliance times, superseding (the
requirements of) DGAC France AD F-2005-078. Subsequently, Airbus
identified reference material that was erroneously introduced into
Airbus SB A310-53-2124 Revision 01. As a result, the SB instructions
could not be accomplished properly. Operators that tried to apply SB
A310-53-2124 at Revision 01 had to contact Airbus; see also Airbus
SBIT [service bulletin information telex] ref. 914.0135/08, dated 03
March 2008.
Consequently, [EASA] AD 2007-0238 was revised to exclude
reference to Airbus SB A310-53-2124 Revision 01 and to require
accomplishment of the task(s) as described in the original SB A310-
53-2124 instead, although retaining the reduced compliance times
introduced by [EASA] AD 2007-0238 at original issue.
EASA AD 2008-0212, superseding [EASA] AD 2007-0238R1, was
published to refer to Airbus SB A310 53-2124 Revision 02, the
corrected version that was used to meet the requirements of this
[EASA] AD.
Since [EASA] AD 2008-0212 was issued, new investigations in the
frame of the Widespread Fatigue Damage campaign induced thresholds
reduction, and Airbus issued SB A310-53-2124 Revision 03.
For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2008-0212, which is superseded, and requires
accomplishment of modification(s) within reduced compliance time, as
published in Airbus SB A310-53-2124 Revision 03.
Required actions include a high frequency eddy current (HFEC)
rotating probe inspection for cracking of certain fastener holes on
certain frames, and related investigative and corrective actions if
necessary; and modification of certain fastener holes. Related
investigative actions include an additional HFEC rotating probe
inspection for cracking of fastener holes and a check to determine the
edge distance of certain holes. Corrective actions include ream out of
cracks and repair.
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-2017-
0695.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the NPRM and
the FAA's response to that comment.
Request To Revise the Costs of Compliance
FedEx stated that repairs would cost an additional $10,000 per
airplane. The commenter noted that 66% of its past accomplishments
required additional efforts to incorporate the modification with
supplementary repair activities. The commenter suggested that the
average cost of compliance would approach $30,000 per airplane. We
infer that the commenter is requesting a revision to the costs of
compliance in the NPRM. We agree with commenter's request to revise the
costs of compliance in this final rule. We have revised the Costs of
Compliance section in this final rule accordingly.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting
this AD with the change 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.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A310-53-2124, Revision 03, dated
December 22, 2014. This service information describes procedures for a
rotating probe inspection for cracking between frame (FR) 43 through FR
46 on the center box, and the cold expansion (modification) of the most
fatigue sensitive fastener holes. 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 8 airplanes of U.S. registry.
We estimate that it will take about 41 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Required parts will cost about $20,180 per
product. Based on these figures, we estimate the cost of this AD on
U.S.
[[Page 11401]]
operators to be $189,320, or $23,665 per product.
Although we have received no definitive data that will enable us to
provide cost estimates for the on-condition actions (i.e., additional
inspection and modification for certain airplanes) specified in this
AD, we have determined that the total repair costs could be up to
$10,000 per product. We have no way of determining the number of
aircraft that might need these repairs.
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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.
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 removing Airworthiness Directive (AD)
2009-18-16, Amendment 39-16012 (74 FR 46342, September 9, 2009), and
adding the following new AD:
2018-06-03 Airbus: Amendment 39-19223; Docket No. FAA-2017-0695;
Product Identifier 2016-NM-173-AD.
(a) Effective Date
This AD is effective April 19, 2018.
(b) Affected ADs
This AD replaces AD 2009-18-16, Amendment 39-16012 (74 FR 46342,
September 9, 2009) (``AD 2009-18-16'').
(c) Applicability
This AD applies to Airbus Model A310-203, -204, -221, -222, -
304, -322, -324 and -325 airplanes; certificated in any category;
all serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by an evaluation by the design approval
holder indicating that the junctions of center box upper frame bases
to the upper fuselage arches are subject to widespread fatigue
damage and that the compliance threshold for the modification in AD
2009-18-16 should be reduced. We are issuing this AD to prevent
fatigue cracking of the frame foot run-outs, which could lead to
rupture of the frame foot and cracking in adjacent frames and skin,
and which could result in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections and Modification of Fastener Holes
Except for airplanes modified before the effective date of this
AD using the Accomplishment Instructions of Airbus Service Bulletin
A310-53-2124: At the times specified in paragraph (g)(1) of this AD
but no later than the times specified in paragraph (g)(2) of this
AD, do a high frequency eddy current (HFEC) rotating probe
inspection for cracking of fastener holes H1 through H29 on frames
43 through 46, and do all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A310-53-2124, Revision 03,
dated December 22, 2014, except as required by paragraph (h) of this
AD. If no cracking is found and the edge distance of the fastener
hole is equal to or greater than the distance specified in the
Accomplishment Instructions of Airbus Service Bulletin A310-53-2124,
Revision 03, dated December 22, 2014, before further flight, do the
modification (cold expansion) of the affected fastener holes, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-53-2124, Revision 03, dated December 22, 2014. Do all
applicable related investigative and corrective actions before
further flight.
(1) Inspect at the applicable time specified in table 1 to
paragraph (g)(1) of this AD, or within 24 months after the effective
date of this AD, whichever occurs later. To establish the average
flight time (AFT), take the accumulated flight time (counted from
the take-off up to the landing) and divide by the number of
accumulated flight cycles. This gives the AFT per flight cycle.
Although the thresholds for Model A310-304, -322, -324, and -325
airplanes are optimized to airplane utilization, an operator can
choose to use the thresholds for the other AFT.
[[Page 11402]]
[GRAPHIC] [TIFF OMITTED] TR15MR18.002
(2) Inspect at the later of the times specified in paragraphs
(g)(2)(i) and (g)(2)(ii) of this AD.
(i) At the applicable time indicated in table 2 to paragraph
(g)(2)(i) of this AD. Airbus Model A310-304, -322, -324, and -325
airplanes with an AFT equal to or less than 3.16 flight hours are
short range airplanes. Airbus Model A310-304, -322, -324, and -325
airplanes with an AFT exceeding 3.16 flight hours are long range
airplanes. For this paragraph, to establish the average flight time,
take the accumulated flight time (counted from the take-off up to
the landing) and divide by the number of accumulated flight cycles.
This gives the AFT per flight cycle.
[[Page 11403]]
[GRAPHIC] [TIFF OMITTED] TR15MR18.003
(ii) Within 500 flight cycles or 800 flight hours after October
14, 2009 (the effective date of AD 2009-18-16), whichever occurs
first.
(h) Service Information Exception
Where Airbus Service Bulletin A310-53-2124, Revision 03, dated
December 22, 2014, specifies to contact Airbus for appropriate
action, and specifies that action as ``RC'' (required for
compliance): Before further flight, accomplish corrective actions in
accordance with the procedures specified in paragraph (l)(2) of this
AD.
(i) Airplanes Modified per Revision 01 of the Service Information
For airplanes modified before the effective date of this AD
using Airbus Service Bulletin A310-53-2124, Revision 01, dated May
3, 2007: Unless already accomplished, before further flight, do
applicable corrective actions using a method approved by the
Manager, International Section, Transport Standards Branch, FAA; or
the European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(j) Additional Inspection and Modification
Except as provided by paragraphs (j)(1) and (j)(2) of this AD,
as applicable: At the applicable thresholds specified in table 3 to
the introductory text of paragraph (j) of this AD, contact the
Manager, International Section, Transport Standards Branch, FAA; or
EASA; or Airbus's EASA DOA for additional inspection and
modification instructions. Accomplish those instructions within the
compliance times approved by the Manager, International Section,
Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
[[Page 11404]]
[GRAPHIC] [TIFF OMITTED] TR15MR18.004
(1) For Model A310-203, -204, -221, and -222 airplanes: No
additional inspection is required if the inspection and modification
specified in Airbus Service Bulletin A310-53-2124 was done after the
accumulation of 29,500 flight cycles and 70,900 flight hours since
the first flight of the airplane.
(2) For Model A310-304, -322, -324, and -325 airplanes: No
additional inspection is required if the inspection and modification
specified in Airbus Service Bulletin A310-53-2124 was done after the
accumulation of 22,600 flight cycles and 69,400 flight hours since
the first flight of the airplane.
(k) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using the Accomplishment Instructions of
Airbus Service Bulletin A310-53-2124, dated April 4, 2005; or Airbus
Service Bulletin A310-53-2124, Revision 02, dated May 22, 2008.
(l) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, 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 Section, send it to the attention of
the person identified in paragraph (m)(2) of this AD. Information
may be emailed to: [email protected]. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Section, Transport Standards
Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA,
the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as provided by
paragraph (h) of this AD: If any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0197, dated October 5, 2016, 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-2017-0695.
(2) For more information about this AD, contact Dan Rodina,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone:
206-231-3225.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
(n) 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 A310-53-2124, Revision 03, dated
December 22, 2014.
(ii) Reserved.
(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: [email protected];
internet: https://www.airbus.com.
(4) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
(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 March 2, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-05018 Filed 3-14-18; 8:45 am]
BILLING CODE 4910-13-P
