Airworthiness Directives; Airbus Airplanes, 24903-24906 [2017-10979]
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Federal Register / Vol. 82, No. 103 / Wednesday, May 31, 2017 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0520; Directorate
Identifier 2016–NM–143–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus Model A300 series airplanes;
and Model A300 B4–600, B4–600R, and
F4–600R series airplanes, and Model
A300 C4–605R Variant F airplanes
(collectively called Model A300–600
series airplanes). This proposed AD was
prompted by reports of cracks initiating
at the upper radius of frame (FR) 47 and
a determination that the current
inspection procedure is not reliable in
detecting certain cracking of the forward
fitting of FR 47. This proposed AD
would require repetitive inspections to
detect cracking of the upper radius of
the forward fitting of FR 47, and related
investigative actions and corrective
actions if necessary. We are proposing
this AD to address the unsafe condition
on these products.
DATES: We must receive comments on
this proposed AD by July 17, 2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, 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
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SUMMARY:
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SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0520; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone: 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: 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:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2017–0520; Directorate Identifier
2016–NM–143–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2016–0150,
dated July 25, 2016 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
on all. The MCAI states:
During scheduled maintenance inspections
on the fuselage, cracks initiating at the upper
radius of frame (FR) 47 have been reported
on several aeroplanes. Similar damage was
also discovered on the A300 fatigue test
fuselage.
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24903
This condition, if not detected and
corrected, could reduce the structural
integrity of the fuselage.
Prompted by these findings, Airbus issued
Service Bulletin (SB) A300–53–0246, SB
A300–53–6029 and SB A300–53–9014 to
provide inspection instructions and,
consequently, DGAC France issued AD F–
2006–016 to require repetitive inspections
and corrective action.
Since that [French] AD was issued, further
investigation led to the conclusion that the
current ultrasonic inspection performed in
accordance with Airbus SB A300–53–0246
Revision 06, or SB A300–53–6029 Revision
08, or SB A300–53–9014 Revision 01, as
applicable, was not reliable to detect deep
crack going downward.
Consequently, to ensure the crack depth is
correctly measured whatever the crack
direction, Airbus developed a new
nondestructive testing method [eddy current]
for this special detailed inspection (SDI) and
revised the affected SBs accordingly.
For the reasons described above, this
[EASA] AD retains the requirements of DGAC
France AD F–2006–016, which is
superseded, but requires the accomplishment
of repetitive SDI to replace the previously
required ultrasonic inspections [and related
investigative actions and corrective actions if
necessary].
Related investigative actions include
an ultrasonic inspection for cracking on
the forward face of forward fitting and
a detailed inspection for cracking of the
aft fitting around the fasteners.
Corrective actions include crack repairs,
modification of the sealing fittings and
sealing shims. This proposed AD
requires reporting of the inspection
results to Airbus. 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–2017–0520.
Related Service Information Under 1
CFR Part 51
Airbus has issued Airbus Service
Bulletin A300–53–0246, Revision 08,
including Appendix 1, dated April 13,
2016 (for Model A300 series airplanes);
and Airbus Service Bulletin A300–53–
6029, Revision 12, including Appendix
1, dated April 13, 2016 (for Model
A300–600 series airplanes). The service
information describes procedures for
doing an SDI for cracking of the FR 47
forward fitting upper radius on the lefthand and right-hand sides of the
fuselage, and related investigative
actions and corrective actions. 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.
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Federal Register / Vol. 82, No. 103 / Wednesday, May 31, 2017 / Proposed Rules
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type designs.
This NPRM would not supersede AD
2007–26–14, Amendment 39–15316 (73
FR 2803, January 16, 2008). Rather, we
have determined that a stand-alone AD
would be more appropriate to address
the changes in the MCAI. This NPRM
would require repetitive inspections to
detect cracking of the upper radius of
the forward fitting of FR 47, and related
investigative actions and corrective
actions if necessary. Accomplishment of
the proposed actions would then
terminate all requirements of AD 2007–
26–14 for the inspected airplane.
Differences Between This Proposed AD
and the MCAI or Service Information
Although the MCAI and service
information allow further flight if cracks
are found during accomplishment of the
required action, this proposed AD
requires that any cracking be repaired
before further flight.
Costs of Compliance
We estimate that this proposed AD
affects 132 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Inspection .......
Reporting .......
19 work-hours × $85 per hour = $1,615 ....
1 work-hour × $85 per hour = $85 .............
We estimate the following costs to do
any necessary related investigative and
corrective actions that would be
Parts cost
$0
0
Cost per product
Cost on U.S. operators
$1,615 per inspection cycle .....
$85 per inspection cycle ..........
required based on the results of the
proposed inspection. We have no way of
$213,180 per inspection cycle.
$11,220 per inspection cycle.
determining the number of airplanes
that might need these repairs:
ON-CONDITION COSTS
Action
Labor cost
Related investigative and Corrective actions ...............
21 work-hours × $85 per hour = $1,785 ......................
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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 proposed AD is 2120–
0056. The paperwork cost associated
with this proposed 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 proposed
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,
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section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
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Parts cost
Cost per
product
$1,835
$3,620
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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Federal Register / Vol. 82, No. 103 / Wednesday, May 31, 2017 / Proposed Rules
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2017–0520;
Directorate Identifier 2016–NM–143–AD.
(a) Comments Due Date
We must receive comments by July 17,
2017.
(b) Affected ADs
This AD affects AD 2007–26–14,
Amendment 39–15316 (73 FR 2803, January
16, 2008) (‘‘AD 2007–26–14’’).
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(5)
of this AD, certificated in any category,
except airplanes that have been repaired as
specified in Airbus Service Bulletin A300–
53–0370 or Airbus Service Bulletin A300–
53–6144, as applicable.
(1) Model A300 B2–1A, B2–1C, B2K–3C,
B2–203, B4–2C, B4–103, and B4–203
airplanes.
(2) Model A300 B4–601, B4–603, B4–620,
and B4–622 airplanes.
(3) Model A300 B4–605R and B4–622R
airplanes.
(4) Model A300 F4–605R and F4–622R
airplanes.
(5) Model A300 C4–605R Variant F
airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracks
initiating at the upper radius of frame (FR)
47 and a determination that the current
inspection procedure is not reliable in
detecting certain cracking of the forward
fitting of FR 47. We are issuing this AD to
detect and correct fatigue cracking of the FR
47 forward fitting upper radius on the lefthand and right-hand sides of the fuselage,
which could propagate and result in reduced
structural integrity of the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections
Except as required by paragraph (h) of this
AD: Before exceeding 10,000 flight cycles
since first flight of the airplane or within 30
days after the effective date of this AD,
whichever is later, do a special detailed
inspection (SDI) for cracking of the FR 47
forward fitting upper radius on the left-hand
and right-hand sides of the fuselage, in
accordance with the Accomplishment
Instructions of the applicable Airbus service
information specified in paragraphs (g)(1)
and (g)(2) of this AD. Repeat the inspection
thereafter at intervals not to exceed 4,150
flight cycles, except as required by paragraph
(j) of this AD.
(1) Airbus Service Bulletin A300–53–0246,
Revision 08, including Appendix 1, dated
April 13, 2016.
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(2) Airbus Service Bulletin A300–53–6029,
Revision 12, including Appendix 1, dated
April 13, 2016.
(h) Initial Inspection for Airplanes
Previously Inspected
For airplanes previously inspected as
specified in the applicable Airbus service
information specified in paragraphs (h)(1)
through (h)(6) of this AD and on which no
cracking was found: Within 4,150 flight
cycles after the most recent inspection, do
the inspection for cracking of the FR 47
forward fitting upper radius required by
paragraph (g) of this AD.
(1) Airbus Service Bulletin A300–53–0246,
Revision 06, dated October 19, 2005.
(2) Airbus Service Bulletin A300–53–0246,
Revision 07, dated September 9, 2008.
(3) Airbus Service Bulletin A300–53–6029,
Revision 08, dated October 19, 2005.
(4) Airbus Service Bulletin A300–53–6029,
Revision 09, dated September 9, 2008.
(5) Airbus Service Bulletin A300–53–6029,
Revision 10, dated July 9, 2009.
(6) Airbus Service Bulletin A300–53–6029,
Revision 11, dated September 28, 2009.
(i) Inspections for Airplanes With Abnormal
Load Events
For airplanes on which any crack was
found during any inspection done as
specified in Airbus Service Bulletin A300–
53–0246 or Airbus Service Bulletin A300–
53–6029, as applicable, and on which any
abnormal load event, such as hard landing or
flight in excessive turbulence, occurred
within 3 months before the effective date of
this AD or occurs on or after the effective
date of this AD: Within 3 months after each
event, accomplish an SDI for cracking of the
FR 47 forward fitting upper radius, left-hand
and right-hand sides of the fuselage, in
accordance with the applicable
Accomplishment Instructions of the Airbus
service information specified in paragraphs
(g)(1) or (g)(2) of this AD. If, during this 3month period, another abnormal load event
occurs, and if no SDI has yet been
accomplished, before further flight after the
second event, obtain corrective action
instructions from 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), and
accomplish those instructions accordingly.
(j) Corrective Actions for Airplanes With
Cracks
If, during any SDI as required by paragraph
(g), (h), or (i) of this AD, any crack is found:
Before further flight, do the applicable
related investigative actions and corrective
actions, in accordance with the
Accomplishment Instructions of the
applicable Airbus service information
specified in paragraphs (g)(1) or (g)(2) of this
AD, and obtain additional corrective action
instructions from the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or Airbus’s EASA
DOA, and accomplish those instructions
accordingly before further flight.
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(k) Reporting
Submit a report of the findings (both
positive and negative) of each SDI inspection
required by paragraphs (g), (h), and (i) of this
AD to Airbus Service Bulletin Reporting
Online Application on Airbus World (https://
w3.airbus.com/), 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) Terminating Action for AD 2007–26–14
Accomplishing any inspection required by
paragraph (g) or (h) of this AD terminates all
requirements of AD 2007–26–14 for the
inspected airplane.
(m) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to 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. 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: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(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:
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Federal Register / Vol. 82, No. 103 / Wednesday, May 31, 2017 / Proposed Rules
Information Collection Clearance Officer,
AES–200.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0150, dated July 25, 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–2017–0520.
(2) For more information about this AD,
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.
(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.
You may view this service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on May 19,
2017.
Victor Wicklund,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–10979 Filed 5–30–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0516; Directorate
Identifier 2016–NM–125–AD]
RIN 2120–AA64
Airworthiness Directives; ATR—GIE
´
Avions de Transport Regional
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2015–23–
12, for all ATR—GIE Avions de
´
Transport Regional Model ATR42 and
ATR72 airplanes. AD 2015–23–12
currently requires identifying the serial
number and part number of the main
landing gear (MLG) rear hinge pins, and
replacing pins or the MLG if necessary.
Since we issued AD 2015–23–12, we
have received a new report of a certain
cracked MLG hinge pin on a Model
ATR42 airplane. We have determined
that certain additional MLG hinge pins
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SUMMARY:
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14:38 May 30, 2017
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must be replaced, and certain
compliance times must be reduced. This
proposed AD would require identifying
the serial number and part number of
the MLG rear hinge pins, and replacing
pins if necessary. We are proposing this
AD to address the unsafe condition on
these products.
DATES: We must receive comments on
this proposed AD by July 17, 2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact ATR—GIE Avions
´
´
de Transport Regional, 1, Allee Pierre
Nadot, 31712 Blagnac Cedex, France;
telephone +33 (0) 5 62 21 62 21; fax +33
(0) 5 62 21 67 18; email
continued.airworthiness@atr.fr; Internet
https://www.aerochain.com. You may
view this referenced service information
at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0516; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Shahram Daneshmandi, Aerospace
Engineer, International Branch, ANM–
116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue SW., Renton,
WA 98057–3356; telephone 425–227–
1112; fax 425–227–1149.
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SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2017–0516; Directorate Identifier
2016–NM–125–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On November 12, 2015, we issued AD
2015–23–12, Amendment 39–18329 (80
FR 73096, November 24, 2015) (‘‘AD
2015–23–12’’), for all ATR—GIE Avions
´
de Transport Regional Model ATR42
and ATR72 airplanes. AD 2015–23–12
was prompted by new occurrences of
certain cracked MLG rear hinge pins.
AD 2015–23–12 requires identifying the
serial number and part number of the
MLG rear hinge pins, and replacing pins
or the MLG if necessary. We issued AD
2015–23–12 to detect and correct
cracked rear hinge pins, which could
lead to MLG structural failure, possibly
resulting in collapse of the MLG and
consequent injury to the occupants of
the airplane.
Since we issued AD 2015–23–12, we
have received a new report of a cracked
MLG hinge pin having P/N D62055 on
a Model ATR42 airplane. We have
determined that certain additional MLG
hinge pins must be replaced, and certain
compliance times must be reduced.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2016–0135, dated July 8, 2016
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for all ATR—GIE Avions de
´
Transport Regional Model ATR42 and
ATR72 airplanes. The MCAI states:
Prompted by cases of rupture of main
landing gear (MLG) rear hinge pin part
number (P/N) D61000 encountered in service
´ ´
in 1994 and 1996, DGAC [Direction Generale
de l’Aviation Civile] France issued AD 96–
131–064 (B) for ATR42 aeroplanes and AD
96–096–029 (B) for ATR72 aeroplanes to
E:\FR\FM\31MYP1.SGM
31MYP1
Agencies
[Federal Register Volume 82, Number 103 (Wednesday, May 31, 2017)]
[Proposed Rules]
[Pages 24903-24906]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10979]
[[Page 24903]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0520; Directorate Identifier 2016-NM-143-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Airbus Model A300 series airplanes; and Model A300 B4-600, B4-
600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F
airplanes (collectively called Model A300-600 series airplanes). This
proposed AD was prompted by reports of cracks initiating at the upper
radius of frame (FR) 47 and a determination that the current inspection
procedure is not reliable in detecting certain cracking of the forward
fitting of FR 47. This proposed AD would require repetitive inspections
to detect cracking of the upper radius of the forward fitting of FR 47,
and related investigative actions and corrective actions if necessary.
We are proposing this AD to address the unsafe condition on these
products.
DATES: We must receive comments on this proposed AD by July 17, 2017.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, 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.
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-
0520; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: 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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0520;
Directorate Identifier 2016-NM-143-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2016-0150, dated July 25, 2016 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition on all. The MCAI states:
During scheduled maintenance inspections on the fuselage, cracks
initiating at the upper radius of frame (FR) 47 have been reported
on several aeroplanes. Similar damage was also discovered on the
A300 fatigue test fuselage.
This condition, if not detected and corrected, could reduce the
structural integrity of the fuselage.
Prompted by these findings, Airbus issued Service Bulletin (SB)
A300-53-0246, SB A300-53-6029 and SB A300-53-9014 to provide
inspection instructions and, consequently, DGAC France issued AD F-
2006-016 to require repetitive inspections and corrective action.
Since that [French] AD was issued, further investigation led to
the conclusion that the current ultrasonic inspection performed in
accordance with Airbus SB A300-53-0246 Revision 06, or SB A300-53-
6029 Revision 08, or SB A300-53-9014 Revision 01, as applicable, was
not reliable to detect deep crack going downward.
Consequently, to ensure the crack depth is correctly measured
whatever the crack direction, Airbus developed a new nondestructive
testing method [eddy current] for this special detailed inspection
(SDI) and revised the affected SBs accordingly.
For the reasons described above, this [EASA] AD retains the
requirements of DGAC France AD F-2006-016, which is superseded, but
requires the accomplishment of repetitive SDI to replace the
previously required ultrasonic inspections [and related
investigative actions and corrective actions if necessary].
Related investigative actions include an ultrasonic inspection for
cracking on the forward face of forward fitting and a detailed
inspection for cracking of the aft fitting around the fasteners.
Corrective actions include crack repairs, modification of the sealing
fittings and sealing shims. This proposed AD requires reporting of the
inspection results to Airbus. 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-2017-0520.
Related Service Information Under 1 CFR Part 51
Airbus has issued Airbus Service Bulletin A300-53-0246, Revision
08, including Appendix 1, dated April 13, 2016 (for Model A300 series
airplanes); and Airbus Service Bulletin A300-53-6029, Revision 12,
including Appendix 1, dated April 13, 2016 (for Model A300-600 series
airplanes). The service information describes procedures for doing an
SDI for cracking of the FR 47 forward fitting upper radius on the left-
hand and right-hand sides of the fuselage, and related investigative
actions and corrective actions. 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.
[[Page 24904]]
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type designs.
This NPRM would not supersede AD 2007-26-14, Amendment 39-15316 (73
FR 2803, January 16, 2008). Rather, we have determined that a stand-
alone AD would be more appropriate to address the changes in the MCAI.
This NPRM would require repetitive inspections to detect cracking of
the upper radius of the forward fitting of FR 47, and related
investigative actions and corrective actions if necessary.
Accomplishment of the proposed actions would then terminate all
requirements of AD 2007-26-14 for the inspected airplane.
Differences Between This Proposed AD and the MCAI or Service
Information
Although the MCAI and service information allow further flight if
cracks are found during accomplishment of the required action, this
proposed AD requires that any cracking be repaired before further
flight.
Costs of Compliance
We estimate that this proposed AD affects 132 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection........................ 19 work-hours x $85 $0 $1,615 per $213,180 per
per hour = $1,615. inspection cycle. inspection cycle.
Reporting......................... 1 work-hour x $85 0 $85 per inspection $11,220 per
per hour = $85. cycle. inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary related
investigative and corrective actions that would be required based on
the results of the proposed inspection. We have no way of determining
the number of airplanes that might need these repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Related investigative and Corrective actions.. 21 work-hours x $85 per hour = $1,835 $3,620
$1,785.
----------------------------------------------------------------------------------------------------------------
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 proposed AD
is 2120-0056. The paperwork cost associated with this proposed 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 proposed 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[[Page 24905]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2017-0520; Directorate Identifier 2016-NM-
143-AD.
(a) Comments Due Date
We must receive comments by July 17, 2017.
(b) Affected ADs
This AD affects AD 2007-26-14, Amendment 39-15316 (73 FR 2803,
January 16, 2008) (``AD 2007-26-14'').
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(5) of this AD, certificated in any category,
except airplanes that have been repaired as specified in Airbus
Service Bulletin A300-53-0370 or Airbus Service Bulletin A300-53-
6144, as applicable.
(1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and
B4-203 airplanes.
(2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(3) Model A300 B4-605R and B4-622R airplanes.
(4) Model A300 F4-605R and F4-622R airplanes.
(5) Model A300 C4-605R Variant F airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracks initiating at the
upper radius of frame (FR) 47 and a determination that the current
inspection procedure is not reliable in detecting certain cracking
of the forward fitting of FR 47. We are issuing this AD to detect
and correct fatigue cracking of the FR 47 forward fitting upper
radius on the left-hand and right-hand sides of the fuselage, which
could propagate and result in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections
Except as required by paragraph (h) of this AD: Before exceeding
10,000 flight cycles since first flight of the airplane or within 30
days after the effective date of this AD, whichever is later, do a
special detailed inspection (SDI) for cracking of the FR 47 forward
fitting upper radius on the left-hand and right-hand sides of the
fuselage, in accordance with the Accomplishment Instructions of the
applicable Airbus service information specified in paragraphs (g)(1)
and (g)(2) of this AD. Repeat the inspection thereafter at intervals
not to exceed 4,150 flight cycles, except as required by paragraph
(j) of this AD.
(1) Airbus Service Bulletin A300-53-0246, Revision 08, including
Appendix 1, dated April 13, 2016.
(2) Airbus Service Bulletin A300-53-6029, Revision 12, including
Appendix 1, dated April 13, 2016.
(h) Initial Inspection for Airplanes Previously Inspected
For airplanes previously inspected as specified in the
applicable Airbus service information specified in paragraphs (h)(1)
through (h)(6) of this AD and on which no cracking was found: Within
4,150 flight cycles after the most recent inspection, do the
inspection for cracking of the FR 47 forward fitting upper radius
required by paragraph (g) of this AD.
(1) Airbus Service Bulletin A300-53-0246, Revision 06, dated
October 19, 2005.
(2) Airbus Service Bulletin A300-53-0246, Revision 07, dated
September 9, 2008.
(3) Airbus Service Bulletin A300-53-6029, Revision 08, dated
October 19, 2005.
(4) Airbus Service Bulletin A300-53-6029, Revision 09, dated
September 9, 2008.
(5) Airbus Service Bulletin A300-53-6029, Revision 10, dated
July 9, 2009.
(6) Airbus Service Bulletin A300-53-6029, Revision 11, dated
September 28, 2009.
(i) Inspections for Airplanes With Abnormal Load Events
For airplanes on which any crack was found during any inspection
done as specified in Airbus Service Bulletin A300-53-0246 or Airbus
Service Bulletin A300-53-6029, as applicable, and on which any
abnormal load event, such as hard landing or flight in excessive
turbulence, occurred within 3 months before the effective date of
this AD or occurs on or after the effective date of this AD: Within
3 months after each event, accomplish an SDI for cracking of the FR
47 forward fitting upper radius, left-hand and right-hand sides of
the fuselage, in accordance with the applicable Accomplishment
Instructions of the Airbus service information specified in
paragraphs (g)(1) or (g)(2) of this AD. If, during this 3-month
period, another abnormal load event occurs, and if no SDI has yet
been accomplished, before further flight after the second event,
obtain corrective action instructions from 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), and accomplish those
instructions accordingly.
(j) Corrective Actions for Airplanes With Cracks
If, during any SDI as required by paragraph (g), (h), or (i) of
this AD, any crack is found: Before further flight, do the
applicable related investigative actions and corrective actions, in
accordance with the Accomplishment Instructions of the applicable
Airbus service information specified in paragraphs (g)(1) or (g)(2)
of this AD, and obtain additional corrective action instructions
from the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or EASA; or Airbus's EASA DOA, and accomplish
those instructions accordingly before further flight.
(k) Reporting
Submit a report of the findings (both positive and negative) of
each SDI inspection required by paragraphs (g), (h), and (i) of this
AD to Airbus Service Bulletin Reporting Online Application on Airbus
World (https://w3.airbus.com/), 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) Terminating Action for AD 2007-26-14
Accomplishing any inspection required by paragraph (g) or (h) of
this AD terminates all requirements of AD 2007-26-14 for the
inspected airplane.
(m) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to 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. 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: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA DOA. If approved by the DOA, the approval must include
the DOA-authorized signature.
(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:
[[Page 24906]]
Information Collection Clearance Officer, AES-200.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0150, dated July 25, 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-2017-0520.
(2) For more information about this AD, 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.
(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. You may view this service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on May 19, 2017.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-10979 Filed 5-30-17; 8:45 am]
BILLING CODE 4910-13-P