[Federal Register Volume 83, Number 161 (Monday, August 20, 2018)]
[Rules and Regulations]
[Pages 42017-42022]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-17752]
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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.
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Federal Register / Vol. 83, No. 161 / Monday, August 20, 2018 / Rules
and Regulations
[[Page 42017]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0277; Product Identifier 2017-NM-124-AD; Amendment
39-19364; AD 2018-17-10]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are superseding Airworthiness Directive (AD) 2017-15-17,
which applied to certain Airbus Model A300 B4-600R series airplanes,
Model A300 C4-605R Variant F airplanes, and Model A300 F4-600R series
airplanes. AD 2017-15-17 required an inspection of the lower area of a
certain frame (FR) radius for cracking, and corrective action if
necessary. This AD requires new repetitive inspections of the forward
fitting lower radius of a certain frame for cracking, and corrective
actions if necessary. This AD was prompted by a determination that
repetitive inspections and applicable corrective actions are necessary.
We are issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective September 24, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September 5,
2017 (82 FR 35644, August 1, 2017).
ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EAW, Rond-Point Emile
Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email [email protected];
internet http://www.airbus.com. You may view this referenced 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. It is also available on the
internet at http://www.regulations.gov by searching for and locating
Docket No. FAA-2018-0277.
Examining the AD Docket
You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0277; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations (phone: 800-647-
5527) is in the ADDRESSES section.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2017-15-17, Amendment 39-18977 (82 FR 35644,
August 1, 2017) (``AD 2017-15-17''). AD 2017-15-17 applied to certain
Airbus Model A300 B4-600R series airplanes, Model A300 C4-605R Variant
F airplanes, and Model A300 F4-600R series airplanes. The NPRM
published in the Federal Register on April 17, 2018 (83 FR 16787). The
NPRM was prompted by a determination that new repetitive inspections of
the lower area of a certain frame radius for cracking, and corrective
actions are necessary. The NPRM proposed to require an inspection of
the lower area of a certain frame radius for cracking, and corrective
action if necessary. The NPRM also proposed to add new repetitive
inspections of the lower area of a certain frame radius for cracking,
and corrective actions if necessary. We are issuing this AD to detect
and correct cracking in the forward fitting lower radius of a certain
frame. Such cracking could reduce the structural integrity of the
fuselage.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0158, dated August 25, 2017 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Airbus SAS Model A300 B4-600R
series airplanes, Model A300 C4-605R Variant F airplanes, and Model
A300 F4-600R series airplanes. The MCAI states:
Following a full stress analysis of the Frame (FR) 40 lower
area, supported by a Finite Element Model (FEM), of the post-mod
[modification] 10221 configuration, it was demonstrated that, for
the FR40 forward fitting lower radius, a crack could occur after a
certain number of flight cycles (FC).
This condition, if not detected and corrected, could reduce the
structural integrity of the fuselage.
To address this potential unsafe condition, Airbus established
that crack detection could be achieved through a special detailed
inspection (SDI) using a high frequency eddy current (HFEC) method,
and issued Alert Operators Transmission (AOT) A57W009-16 to provide
those inspection instructions.
Consequently, EASA issued AD 2016-0085 to require a one-time SDI
of the FR40 lower area and, depending on findings, accomplishment of
applicable corrective action(s). After that [EASA] AD was issued,
further cracks were detected, originating from the fastener hole,
and, based on these findings, it was determined that the inspection
area must be enlarged, and Airbus issued AOT A57W009-16 Revision
(Rev.) 01 accordingly. Consequently, EASA issued AD 2016-0179 [which
corresponds to FAA AD 2017-15-17], retaining the requirements of
EASA AD 2016-0085, which was superseded, to extend the area of
inspection, and to require an additional inspection for aeroplanes
that were previously inspected.
The one-time SDI for high cycle A300-600 aeroplanes was intended
to mitigate the highest risks within the fleet, pending development
of instructions for repetitive inspections.
Since EASA AD 2016-0179 was issued, Airbus published SB A300-57-
6120 * * * [for] the inspection programme for A300-600 * * * post-
mod 10221 * * * [airplanes]. The AOT one-time inspection is
superseded by these repetitive inspection SBs. These SBs include
alternative inspection methods and repair solutions in case of
findings together with the associated inspection programme.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2016-0179, which is superseded, * * * and
defines new inspections methods with
[[Page 42018]]
new compliance times, including repetitive inspections, depending on
the aeroplane inspection status.
You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0277.
Comments
We gave the public the opportunity to participate in developing
this final rule. We received no comments on the NPRM or on the
determination of the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting this final rule as proposed,
except for minor editorial changes. We have determined that these minor
changes:
Are consistent with the intent that was proposed in the
NPRM for addressing 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 SAS has issued Service Bulletin A300-57-6120, dated April
28, 2017. This service information describes procedures for repetitive
inspections of the forward fitting lower radius of FR 40 for cracking,
and corrective action. 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 94 airplanes of U.S. registry.
The actions required by AD 2017-15-17, and retained in this AD,
take about 4 work-hours per product, at an average labor rate of $85
per work-hour. Based on these figures, the estimated cost of the
actions that are required by AD 2017-15-17 is $340 per product.
We also estimate that it takes about 4 work-hours per product to
comply with the new requirements of this AD, including 1 work-hour per
product for reporting. 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 $39,950, or $425 per product.
We have received no definitive data that enables us to provide cost
estimates for the on-condition actions specified in this AD.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
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)
2017-15-17, Amendment 39-18977 (82 FR 35644, August 1, 2017), and
adding the following new AD:
2018-17-10 Airbus SAS: Amendment 39-19364; Docket No. FAA-2018-0277;
Product Identifier 2017-NM-124-AD.
(a) Effective Date
This AD is effective September 24, 2018.
(b) Affected ADs
This AD replaces AD 2017-15-17, Amendment 39-18977 (82 FR 35644,
August 1, 2017) (``AD 2017-15-17'').
(c) Applicability
This AD applies to Airbus SAS airplanes, certificated in any
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of
this AD, on which Airbus SAS Modification 10221 was embodied in
production.
(1) Airbus SAS Model A300 B4-605R and B4-622R airplanes.
(2) Airbus SAS Model A300 C4-605R Variant F airplanes.
(3) Airbus SAS Model A300 F4-605R and F4-622R airplanes.
[[Page 42019]]
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by the detection of cracking that
originated from the fastener holes in the forward fitting lower
radius of frame (FR) 40. We are issuing this AD to detect and
correct cracking in the forward fitting lower radius of FR 40. Such
cracking could reduce the structural integrity of the fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Definitions
(1) For the purpose of this AD, the average flight time (AFT)
can be established by dividing the flight hours (FHs) by the flight
cycles (FCs) counted:
(i) From first flight, for selecting the inspection threshold of
the non-repaired area.
(ii) From repair, for selecting the inspection threshold of the
repaired area.
(iii) From the last inspection, for selecting the inspection
interval.
(2) For the purpose of this AD, Group 1 airplanes are those
airplanes already inspected in accordance with paragraph 4.2.2 in
Alert Operators Transmission (AOT) A57W009-16, Revision 01, dated
July 13, 2016, before the effective date of this AD. Group 2
airplanes are those airplanes not inspected in accordance with
paragraph 4.2.2 in AOT A57W009-16, Revision 01, dated July 13, 2016,
as of the effective date of this AD.
(3) For the purpose of this AD, inspection method A is a high
frequency eddy current (HFEC) inspection of the radius and fastener
area. Inspection method B is a HFEC inspection of the radius and
fastener area and a rototest of the fastener hole. Both are defined
as a special detailed inspection (SDI) in this AD.
(h) Repetitive Inspections for Non-Repaired Areas
Within the compliance time values specified in table 1 to
paragraph (h) of this AD (Group 1 airplanes) or table 2 to paragraph
(h) of this AD (Group 2 airplanes), as applicable, and, thereafter,
at intervals not exceeding the values specified in table 3 to
paragraph (h) of this AD: Do a SDI for cracking of any non-repaired
radius, fastener areas, and fastener holes, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6120,
dated April 28, 2017; except where Airbus Service Bulletin A300-57-
6120, dated April 28, 2017, specifies contacting Airbus SAS for
appropriate action, before further flight, obtain instructions using
the procedures specified in paragraph (m)(2) of this AD and
accomplish those instructions.
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(i) Repetitive Inspections for Repaired Areas
Within the compliance time values specified in table 4 to
paragraph (i) of this AD, and, thereafter, at intervals not
exceeding those same values, do a SDI for cracking of the repaired
radius, fastener areas, and fastener holes, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6120,
dated April 28, 2017; except where Airbus Service Bulletin A300-57-
6120, dated April 28, 2017, specifies contacting Airbus SAS for
appropriate action, before further flight, obtain instructions using
the procedures specified in paragraph (m)(2) of this AD and
accomplish those instructions.
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(j) Corrective Action
If any crack is found during any inspection required by
paragraph (h) or (i) of this AD: Before further flight, repair in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-57-6120, dated April 28, 2017.
(k) Reporting
Submit a report of the findings (both positive and negative) of
each inspection required by paragraphs (h) and (i) of this AD to
Airbus SAS, in accordance with the instructions of Airbus Service
Bulletin A300-57-6120, dated April 28, 2017, at the applicable time
specified in paragraph (k)(1) or (k)(2) of this AD.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
(l) Paperwork Reduction Act Burden Statement
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty
for failure to comply with a collection of information subject to
the requirements of the Paperwork Reduction Act unless that
collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 1 hour per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
(m) Other FAA AD Provisions
(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 (n)(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
[[Page 42022]]
the Manager, International Section, Transport Standards Branch, FAA;
or the European Aviation Safety Agency (EASA); or Airbus SAS's EASA
Design Organization Approval (DOA). If approved by the DOA, the
approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraphs (h) and (i) 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.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2017-0158, dated August 25,
2017, for related information. This MCAI may be found in the AD
docket on the internet at http://www.regulations.gov by searching
for and locating Docket No. FAA-2018-0277.
(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
and fax 206-231-3225.
(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.
(3) The following service information was approved for IBR on
September 5, 2017 (82 FR 35644, August 1, 2017).
(i) Airbus Service Bulletin A300-57-6120, dated April 28, 2017.
(ii) Reserved.
(4) 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 http://www.airbus.com.
(5) 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.
(6) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on August 9, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-17752 Filed 8-17-18; 8:45 am]
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