Airworthiness Directives; Airbus Airplanes, 35644-35647 [2017-15808]
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35644
Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations
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, Seattle
ACO, 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) For service information that contains
steps that are labeled as Required for
Compliance (RC), the provisions of
paragraphs (i)(4)(i) and (i)(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. 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.
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(j) Related Information
(1) For more information about this AD,
contact Kelly McGuckin, Aerospace
Engineer, Systems and Equipment Branch,
ANM–130S, FAA, Seattle ACO, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6490; fax: 425–917–6590;
email: kelly.mcguckin@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.
(k) 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 B787–
81205–SB290031–00, Issue 001, dated March
25, 2016.
(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;
telephone 562–797–1717; Internet https://
www.myboeingfleet.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.
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17:30 Jul 31, 2017
Jkt 241001
Issued in Renton, Washington, on July 14,
2017.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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–
9055; 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:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A300 B4–600R series
airplanes, Model A300 C4–605R Variant
F airplanes, and Model A300 F4–600R
series airplanes. This AD was prompted
by the results of a full stress analysis of
the lower area of a certain frame that
revealed that a crack could occur in this
area after a certain number of flight
cycles. This AD requires an inspection
of the lower area of a certain frame
radius for cracking, and corrective
action if necessary. We are issuing this
AD to address the unsafe condition on
these products.
DATES: This AD is effective September 5,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 5, 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–2016–9055.
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD
that would apply to certain Airbus
Model A300 B4–600R series airplanes,
Model A300 C4–605R Variant F
airplanes, and Model A300 F4–600R
series airplanes. The SNPRM published
in the Federal Register on March 2,
2017 (82 FR 12314) (‘‘the SNPRM’’). We
preceded the SNPRM with a notice of
proposed rulemaking (NPRM) that
published in the Federal Register on
September 8, 2016 (81 FR 62026) (‘‘the
NPRM’’). 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 was prompted by the results of
a full stress analysis of the lower area of
a certain frame that revealed a crack
could occur in the forward fitting lower
radius of a certain frame after a certain
number of flight cycles. The SNPRM
proposed to require extending the area
to be inspected for cracking and adding
an inspection for previously inspected
airplanes. 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 2016–0179,
dated September 12, 2016 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
[FR Doc. 2017–15486 Filed 7–31–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9055; Directorate
Identifier 2016–NM–071–AD; Amendment
39–18977; AD 2017–15–17]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
AGENCY:
SUMMARY:
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MCAI’’), which superseded EASA AD
2016–0085, dated April 28, 2016. EASA
AD 2016–0085 was the MCAI referred to
in the NPRM.
The MCAI was issued to correct an
unsafe condition for certain Airbus
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
10221 configuration, it was demonstrated
that, for the FR40 forward fitting lower
radius, a crack could occur after a certain
amount 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).
Since that [EASA] AD was issued, further
cracks were detected, originating from the
fastener hole, and, based on these findings,
it was determined that inspection area must
be enlarged, and Airbus AOT A57W009–16
Revision (Rev.) 01 was issued accordingly.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2016–0085, which is superseded, extends
the area of inspection, and requires an
additional inspection for aeroplanes
previously inspected.
The one-time SDI for high cycle aeroplanes
is intended to mitigate the highest risks
within the fleet. Airbus is currently
developing instructions for repetitive
inspections that are likely to be the subject
of further [EASA] AD action.
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–
9055.
Comments
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We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the SNPRM and the FAA’s
response to each comment.
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Jkt 241001
Requests To Refer to New Service
Information
FedEx and United Parcel Service
(UPS) requested that the SNPRM be
revised to refer to a service bulletin that
Airbus plans to release to replace Airbus
Alert Operators Transmission (AOT)
A57W009–16, Rev 01, including
Appendices 1 and 2, dated July 13, 2016
(‘‘AOT A57W009–16, Rev 01’’). AOT
A57W009–16, Rev 01, was identified as
the service information to be used to
accomplish the actions specified in the
SNPRM. UPS noted that the service
bulletin would include information
based on in-service reports from
operators who had accomplished the
inspection identified in AOT
A57W009–16, Rev 01, and based on the
results of a full stress analysis of the
frame (FR) 40 lower area. Based on this
information Airbus changed the initial
inspection compliance time from what
was specified in AOT A57W009–16,
Rev 01, and established repetitive
inspection intervals. FedEx and UPS
both mentioned that to reduce the
number of alternative method of
compliance (AMOC) requests, the
SNPRM should be revised to include the
service bulletin. UPS also noted that
including the service information would
benefit the FAA because the FAA could
avoid future rulemaking regarding this
issue.
We partially agree with the
commenters’ requests. After the SNPRM
was published, Airbus issued Service
Bulletin A300–57–6120, dated April 28,
2017. However, instead of removing the
reference to AOT A57W009–16, Rev 01,
in this AD, we have added paragraph (j)
to this AD to allow operators to do the
required actions in accordance with the
Accomplishment Instructions of Service
Bulletin A300–57–6120, dated April 28,
2017. We have redesignated the
subsequent paragraphs accordingly.
Request To Revise Reporting Method
FedEx requested that paragraph (j) of
the proposed AD (in the SNPRM) be
revised to provide flexibility regarding
the method of reporting inspection
results to Airbus. FedEx stated that to
utilize the Airbus online reporting
system would require substantial
updates to its information technology
systems and personnel training;
therefore, it is not prepared to utilize the
online reporting system at this time.
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35645
FedEx suggested that the older method
of reporting be allowed until it has the
computer and personnel resources in
place to utilize online reporting.
We agree with the commenter’s
request. We have determined that
operators may use either the online or
older reporting method. We have
revised paragraph (k) of this AD
(paragraph (j) of the proposed AD (in the
SNPRM)) to allow operators to report
inspection findings using the online
reporting system or submit the results to
Airbus in accordance with the
instructions of Airbus Service Bulletin
A300–57–6120, dated April 28, 2017.
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 SNPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM.
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 AOT A57W009–
16, Rev 01, including Appendices 1 and
2, dated July 13, 2016. This service
information describes procedures for a
one-time inspection of the forward
fitting lower radius of FR 40 for
cracking, and corrective action.
We have also reviewed Airbus 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.
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Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Inspection ................................
Report .....................................
3 work-hours × $85 per hour = $255 .....................................
1 work-hour × $85 per hour = $85 .........................................
We have received no definitive data
that would enable 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.
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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.
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Cost per
product
Parts cost
$0
0
Cost on U.S.
operators
$255
85
$23,970
7,990
Regulatory Findings
(c) Applicability
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.
This AD applies to Airbus airplanes,
certificated in any category, identified in
paragraphs (c)(1), (c)(2), and (c)(3) of this AD,
on which Airbus Modification 10221 was
embodied in production.
(1) Airbus Model A300 B4–605R and B4–
622R airplanes.
(2) Airbus Model A300 C4–605R Variant F
airplanes.
(3) Airbus Model A300 F4–605R and F4–
622R airplanes.
List of Subjects in 14 CFR Part 39
Comply with this AD within the
compliance times specified, unless already
done.
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):
■
2017–15–17 Airbus: Amendment 39–18977;
Docket No. FAA–2016–9055; Directorate
Identifier 2016–NM–071–AD.
(a) Effective Date
This AD is effective September 5, 2017.
(b) Affected ADs
None.
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(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
(g) Inspection
At the later of the compliance times
specified in paragraphs (g)(1) and (g)(2) of
this AD, do a high frequency eddy current
(HFEC) inspection of the lower area of the FR
40 radius for cracking, in accordance with
paragraph 4.2.2 in Airbus Alert Operators
Transmission (AOT) A57W009–16, Rev 01,
including Appendices 1 and 2, dated July 13,
2016.
(1) Prior to exceeding 19,000 total flight
cycles or 41,000 total flight hours since the
airplane’s first flight, whichever occurs first.
(2) Within 300 flight cycles or 630 flight
hours after the effective date of this AD,
whichever occurs first.
(h) Additional Inspection for Previously
Inspected Airplanes
For airplanes on which the HFEC
inspection required by paragraph (g) of this
AD was accomplished before the effective
date of this AD using the procedures in
Airbus AOT A57W009–16, Rev 00, including
Appendices 1 and 2, dated February 25,
2016: Within 300 flight cycles or 630 flight
hours after the effective date of this AD,
whichever occurs first, do a one-time
additional HFEC inspection of the lower area
of the FR 40 radius for cracking, in
accordance with paragraph 4.2.2 in Airbus
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Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations
AOT A57W009–16, Rev 01, including
Appendices 1 and 2, dated July 13, 2016.
(i) Corrective Action
If any crack is found during the inspection
required by paragraph (g) or (h) of this AD:
Before further flight, do the applicable
corrective actions in accordance with the
procedures in Airbus AOT A57W009–16, Rev
01, including Appendices 1 and 2, dated July
13, 2016. Where AOT A57W009–16, Rev 01,
including Appendices 1 and 2, dated July 13,
2016, specifies to contact Airbus for
appropriate action, accomplish the corrective
actions in accordance with the procedures
specified in paragraph (m)(2) of this AD.
(j) Optional Service Information for
Accomplishing Required Actions
Accomplishment of the actions required by
paragraphs (g), (h), and (i) of this AD, in
accordance with, and at the compliance
times specified in, the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–6120, dated April 28, 2017, is acceptable
for compliance with the requirements of
those paragraphs.
(k) Reporting Requirement
Submit a report of all findings (both
positive and negative) from the inspection
required by paragraph (g) of this AD to
Airbus Customer Services through
TechRequest on Airbus World (https://
w3.airbus.com/) by selecting Engineering
Domain and ATA 57–10; or submit the
results to Airbus in accordance with the
procedures in Airbus Service Bulletin A300–
57–6120, dated April 28, 2017.
(1) For airplanes on which the inspection
specified in paragraph (g) of this AD is
accomplished on or after the effective date of
this AD: Submit the report within 30 days
after performing the inspection.
(2) For airplanes on which the inspection
specified in paragraph (g) of this AD is
accomplished before the effective date of this
AD: Submit the report within 30 days after
the effective date of this AD.
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(l) Credit for Previous Actions
This paragraph provides credit for the
action required by paragraph (g) of this AD,
if that action was done before the effective
date of this AD using Airbus AOT A57W009–
16, Rev 00, including Appendices 1 and 2,
dated February 25, 2016, provided the
inspection required by paragraph (h) of this
AD is accomplished.
(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, 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 the
attention of the person identified in
paragraph (n)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov.
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(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 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.
(3) Reporting Requirements: 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 5 minutes 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.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0179, dated September 12, 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–2016–9055.
(2) For more information about this AD,
contact Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA, 1601
Lind Avenue SW., Renton, WA 98057–3356;
telephone 425–227–2125; fax 425–227–1149.
(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 Alert Operators Transmission
A57W009–16, Rev 01, including Appendices
1 and 2, dated July 13, 2016.
(ii) Airbus Service Bulletin A300–57–6120,
dated April 28, 2017.
(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
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35647
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 July 19,
2017.
Victor Wicklund,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–15808 Filed 7–31–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0142; Product
Identifier 2016–SW–013–AD; Amendment
39–18979; AD 2017–16–02]
RIN 2120–AA64
Airworthiness Directives; Agusta
S.p.A. Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Agusta
S.p.A. Model A109S helicopters. This
AD requires adding limitations to the
rotorcraft flight manual (RFM). This AD
was prompted by a report of a cabin
liner detaching from the helicopter and
hitting the main rotor (M/R) blades
during flight. The actions of this AD are
intended to prevent an unsafe condition
on these products.
DATES: This AD is effective September 5,
2017.
ADDRESSES: For service information
identified in this final rule, contact
AgustaWestland, Product Support
Engineering, Via del Gregge, 100, 21015
Lonate Pozzolo (VA) Italy, ATTN:
Maurizio D’Angelo; telephone 39–0331–
664757; fax 39 0331–664680; or at
https://www.agustawestland.com/
technical-bulletins. You may review the
referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0142; or in person at the Docket
Operations Office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
E:\FR\FM\01AUR1.SGM
01AUR1
Agencies
[Federal Register Volume 82, Number 146 (Tuesday, August 1, 2017)]
[Rules and Regulations]
[Pages 35644-35647]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-15808]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9055; Directorate Identifier 2016-NM-071-AD;
Amendment 39-18977; AD 2017-15-17]
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 B4-600R series airplanes, Model A300 C4-605R Variant
F airplanes, and Model A300 F4-600R series airplanes. This AD was
prompted by the results of a full stress analysis of the lower area of
a certain frame that revealed that a crack could occur in this area
after a certain number of flight cycles. This AD requires an inspection
of the lower area of a certain frame radius for cracking, and
corrective action if necessary. We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective September 5, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 5,
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-
9055.
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-
9055; 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 supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD that would apply to certain Airbus
Model A300 B4-600R series airplanes, Model A300 C4-605R Variant F
airplanes, and Model A300 F4-600R series airplanes. The SNPRM published
in the Federal Register on March 2, 2017 (82 FR 12314) (``the SNPRM'').
We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that
published in the Federal Register on September 8, 2016 (81 FR 62026)
(``the NPRM''). 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 was prompted by the results of a full stress
analysis of the lower area of a certain frame that revealed a crack
could occur in the forward fitting lower radius of a certain frame
after a certain number of flight cycles. The SNPRM proposed to require
extending the area to be inspected for cracking and adding an
inspection for previously inspected airplanes. 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
2016-0179, dated September 12, 2016 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the
[[Page 35645]]
MCAI''), which superseded EASA AD 2016-0085, dated April 28, 2016. EASA
AD 2016-0085 was the MCAI referred to in the NPRM.
The MCAI was issued to correct an unsafe condition for certain
Airbus 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
10221 configuration, it was demonstrated that, for the FR40 forward
fitting lower radius, a crack could occur after a certain amount 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).
Since that [EASA] AD was issued, further cracks were detected,
originating from the fastener hole, and, based on these findings, it
was determined that inspection area must be enlarged, and Airbus AOT
A57W009-16 Revision (Rev.) 01 was issued accordingly.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2016-0085, which is superseded, extends the
area of inspection, and requires an additional inspection for
aeroplanes previously inspected.
The one-time SDI for high cycle aeroplanes is intended to
mitigate the highest risks within the fleet. Airbus is currently
developing instructions for repetitive inspections that are likely
to be the subject of further [EASA] AD action.
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-
9055.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the SNPRM and
the FAA's response to each comment.
Requests To Refer to New Service Information
FedEx and United Parcel Service (UPS) requested that the SNPRM be
revised to refer to a service bulletin that Airbus plans to release to
replace Airbus Alert Operators Transmission (AOT) A57W009-16, Rev 01,
including Appendices 1 and 2, dated July 13, 2016 (``AOT A57W009-16,
Rev 01''). AOT A57W009-16, Rev 01, was identified as the service
information to be used to accomplish the actions specified in the
SNPRM. UPS noted that the service bulletin would include information
based on in-service reports from operators who had accomplished the
inspection identified in AOT A57W009-16, Rev 01, and based on the
results of a full stress analysis of the frame (FR) 40 lower area.
Based on this information Airbus changed the initial inspection
compliance time from what was specified in AOT A57W009-16, Rev 01, and
established repetitive inspection intervals. FedEx and UPS both
mentioned that to reduce the number of alternative method of compliance
(AMOC) requests, the SNPRM should be revised to include the service
bulletin. UPS also noted that including the service information would
benefit the FAA because the FAA could avoid future rulemaking regarding
this issue.
We partially agree with the commenters' requests. After the SNPRM
was published, Airbus issued Service Bulletin A300-57-6120, dated April
28, 2017. However, instead of removing the reference to AOT A57W009-16,
Rev 01, in this AD, we have added paragraph (j) to this AD to allow
operators to do the required actions in accordance with the
Accomplishment Instructions of Service Bulletin A300-57-6120, dated
April 28, 2017. We have redesignated the subsequent paragraphs
accordingly.
Request To Revise Reporting Method
FedEx requested that paragraph (j) of the proposed AD (in the
SNPRM) be revised to provide flexibility regarding the method of
reporting inspection results to Airbus. FedEx stated that to utilize
the Airbus online reporting system would require substantial updates to
its information technology systems and personnel training; therefore,
it is not prepared to utilize the online reporting system at this time.
FedEx suggested that the older method of reporting be allowed until it
has the computer and personnel resources in place to utilize online
reporting.
We agree with the commenter's request. We have determined that
operators may use either the online or older reporting method. We have
revised paragraph (k) of this AD (paragraph (j) of the proposed AD (in
the SNPRM)) to allow operators to report inspection findings using the
online reporting system or submit the results to Airbus in accordance
with the instructions of Airbus Service Bulletin A300-57-6120, dated
April 28, 2017.
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
SNPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM.
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 AOT A57W009-16, Rev 01, including Appendices 1
and 2, dated July 13, 2016. This service information describes
procedures for a one-time inspection of the forward fitting lower
radius of FR 40 for cracking, and corrective action.
We have also reviewed Airbus 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.
[[Page 35646]]
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspection......................... 3 work-hours x $85 per hour $0 $255 $23,970
= $255.
Report............................. 1 work-hour x $85 per hour 0 85 7,990
= $85.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable 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.
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):
2017-15-17 Airbus: Amendment 39-18977; Docket No. FAA-2016-9055;
Directorate Identifier 2016-NM-071-AD.
(a) Effective Date
This AD is effective September 5, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of
this AD, on which Airbus Modification 10221 was embodied in
production.
(1) Airbus Model A300 B4-605R and B4-622R airplanes.
(2) Airbus Model A300 C4-605R Variant F airplanes.
(3) Airbus Model A300 F4-605R and F4-622R airplanes.
(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) Inspection
At the later of the compliance times specified in paragraphs
(g)(1) and (g)(2) of this AD, do a high frequency eddy current
(HFEC) inspection of the lower area of the FR 40 radius for
cracking, in accordance with paragraph 4.2.2 in Airbus Alert
Operators Transmission (AOT) A57W009-16, Rev 01, including
Appendices 1 and 2, dated July 13, 2016.
(1) Prior to exceeding 19,000 total flight cycles or 41,000
total flight hours since the airplane's first flight, whichever
occurs first.
(2) Within 300 flight cycles or 630 flight hours after the
effective date of this AD, whichever occurs first.
(h) Additional Inspection for Previously Inspected Airplanes
For airplanes on which the HFEC inspection required by paragraph
(g) of this AD was accomplished before the effective date of this AD
using the procedures in Airbus AOT A57W009-16, Rev 00, including
Appendices 1 and 2, dated February 25, 2016: Within 300 flight
cycles or 630 flight hours after the effective date of this AD,
whichever occurs first, do a one-time additional HFEC inspection of
the lower area of the FR 40 radius for cracking, in accordance with
paragraph 4.2.2 in Airbus
[[Page 35647]]
AOT A57W009-16, Rev 01, including Appendices 1 and 2, dated July 13,
2016.
(i) Corrective Action
If any crack is found during the inspection required by
paragraph (g) or (h) of this AD: Before further flight, do the
applicable corrective actions in accordance with the procedures in
Airbus AOT A57W009-16, Rev 01, including Appendices 1 and 2, dated
July 13, 2016. Where AOT A57W009-16, Rev 01, including Appendices 1
and 2, dated July 13, 2016, specifies to contact Airbus for
appropriate action, accomplish the corrective actions in accordance
with the procedures specified in paragraph (m)(2) of this AD.
(j) Optional Service Information for Accomplishing Required Actions
Accomplishment of the actions required by paragraphs (g), (h),
and (i) of this AD, in accordance with, and at the compliance times
specified in, the Accomplishment Instructions of Airbus Service
Bulletin A300-57-6120, dated April 28, 2017, is acceptable for
compliance with the requirements of those paragraphs.
(k) Reporting Requirement
Submit a report of all findings (both positive and negative)
from the inspection required by paragraph (g) of this AD to Airbus
Customer Services through TechRequest on Airbus World (https://w3.airbus.com/) by selecting Engineering Domain and ATA 57-10; or
submit the results to Airbus in accordance with the procedures in
Airbus Service Bulletin A300-57-6120, dated April 28, 2017.
(1) For airplanes on which the inspection specified in paragraph
(g) of this AD is accomplished on or after the effective date of
this AD: Submit the report within 30 days after performing the
inspection.
(2) For airplanes on which the inspection specified in paragraph
(g) of this AD is accomplished before the effective date of this AD:
Submit the report within 30 days after the effective date of this
AD.
(l) Credit for Previous Actions
This paragraph provides credit for the action required by
paragraph (g) of this AD, if that action was done before the
effective date of this AD using Airbus AOT A57W009-16, Rev 00,
including Appendices 1 and 2, dated February 25, 2016, provided the
inspection required by paragraph (h) of this AD is accomplished.
(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, 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 the attention of the person identified in
paragraph (n)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
(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
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.
(3) Reporting Requirements: 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 5
minutes 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.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0179, dated September 12, 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-2016-9055.
(2) For more information about this AD, contact Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, FAA, 1601 Lind
Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-
227-1149.
(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 Alert Operators Transmission A57W009-16, Rev 01,
including Appendices 1 and 2, dated July 13, 2016.
(ii) Airbus Service Bulletin A300-57-6120, dated April 28, 2017.
(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 July 19, 2017.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-15808 Filed 7-31-17; 8:45 am]
BILLING CODE 4910-13-P