Airworthiness Directives; Airbus Airplanes, 23166-23169 [2017-10140]
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Federal Register / Vol. 82, No. 97 / Monday, May 22, 2017 / Proposed Rules
TABLE 3 TO PARAGRAPH (h) OF THIS AD—COMPLIANCE TIMES FOR INSPECTIONS
Repetitive inspection
intervals
Airplane model
Initial inspection
FALCON 2000 airplanes .....................
Prior to exceeding 2,000 flight cycles since the airplane’s first flight, or
within 1,000 flight cycles after the effective date of this AD, whichever
occurs later.
Prior to exceeding 1,000 flight cycles since the airplane’s first flight, or
within 500 flight cycles after the effective date of this AD, whichever occurs later.
FALCON 2000EX airplanes ................
(i) Corrective Action
If any discrepancy is found during any
inspection required by paragraph (h) of this
AD: Before further flight, replace the affected
anti-ice piccolo tube with a new or
serviceable part, and replace or re-identify
the affected wing outboard slat as applicable,
in accordance with the Accomplishment
Instructions of Dassault Service Bulletin
F2000–431, Revision 1, dated June 6, 2016;
or Service Bulletin F2000EX–391, Revision 1,
dated June 6, 2016; as applicable.
(j) Optional Terminating Action
Modification of an airplane by installing a
new or serviceable anti-ice piccolo tube, and
replacing or re-identifying the affected wing
outboard slat, terminates the repetitive
inspections required by paragraph (h) of this
AD, if done in accordance with the
Accomplishment Instructions of Dassault
Service Bulletin F2000–431, Revision 1,
dated June 6, 2016; or Service Bulletin
F2000EX–391, Revision 1, dated June 6,
2016; as applicable.
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(k) Parts Installation Prohibition
As of the time specified in paragraph (k)(1)
or (k)(2) of this AD, as applicable, no person
may install on any airplane an affected antiice piccolo tube or an affected outboard slat.
(1) For an airplane that, on the effective
date of this AD, has an affected anti-ice
piccolo tube or an affected outboard slat
installed: Before further flight after
modification of that airplane as required by
paragraph (i) of this AD.
(2) For an airplane that, on the effective
date of this AD, does not have an affected
anti-ice piccolo tube or an affected outboard
slat installed: As of the effective date of this
AD.
(l) Later-Approved Parts
Installation on an airplane of an anti-ice
piccolo tube having a part number approved
after the effective date of this AD is
acceptable for compliance with the
requirements of paragraph (i) or paragraph (j)
of this AD, as applicable, provided the
conditions in paragraphs (l)(1) and (l)(2) of
this AD are met.
(1) The anti-ice piccolo tube part number
must be approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA); or Dassault
Aviation’s EASA Design Organization
Approval (DOA).
(2) The installation of the anti-ice piccolo
tube must be accomplished in accordance
with a method approved by the Manager,
International Branch, ANM–116, Transport
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Airplane Directorate, FAA; or the EASA; or
Dassault Aviation’s EASA DOA.
(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-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Dassault Aviation’s EASA
DOA. If approved by the DOA, the approval
must include the DOA-authorized signature.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0149, 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–2017–0475.
(2) For more information about this AD,
contact Tom Rodriguez, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1137; fax 425–227–1149.
(3) For service information identified in
this AD, contact Dassault Falcon Jet
Corporation, Teterboro Airport, P.O. Box
2000, South Hackensack, NJ 07606;
telephone 201–440–6700; Internet https://
www.dassaultfalcon.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.
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2,000 flight cycles.
1,000 flight cycles.
Issued in Renton, Washington, on May 11,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–10135 Filed 5–19–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0480; Directorate
Identifier 2016–NM–204–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 B4–600, B4–600R,
and F4–600R series airplanes, and
Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes); and Model
A310 series airplanes. This proposed
AD was prompted by cracking in the
door sill area of the aft cargo door. This
proposed AD would require repetitive
inspections of the aft cargo door lower
torsion box area, 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 6, 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
SUMMARY:
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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–
0480; 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–2017–0480; Directorate Identifier
2016–NM–204–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 Airworthiness
Directive 2016–0241, dated December 6,
2016 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
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); and Model A310 series
airplanes. The MCAI states:
Cracks were found on in-service aeroplane
post mod 5438 in the door sill area, from
frame (FR) 60 to FR63, including the sill
beam flag, lock fitting, door sill web and
torsion door panel. Two previous cases with
less crack extent were also reported.
This condition, if not detected and
corrected, could lead to reduced structural
integrity of the aeroplane.
To address this unsafe condition, Airbus
published Inspection Service Bulletin (SB)
A310–53–2139 and SB A300–53–6179 to
provide inspection instructions for the
affected areas. Airbus published also Airbus
SB A310–53–2141 and SB A300–53–6181 to
provide modification instructions.
Further analysis showed that aeroplanes
pre-mod 5438, for which one or several lock
fittings have been replaced by post mod
10319 lock fittings, could also be affected.
Airbus published SB A310–53–2143 and SB
23167
A300–53–6185 to provide inspection
instructions.
For the reason described above, this
[EASA] AD requires repetitive Special
Detailed Inspections (SDI) of the aft cargo
door lower torsion box area and, depending
on findings, accomplishment of applicable
corrective action(s).
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–
0480.
Related Service Information Under 1
CFR Part 51
We reviewed Airbus Service Bulletin
A300–53–6185, dated February 11,
2016; and Service Bulletin A310–53–
2143, dated February 11, 2016; which
describe, among other actions, repetitive
inspections of the aft cargo door sill area
for cracking. These documents are
distinct since they apply to different
airplane models. This service
information is reasonably available
because the interested parties have
access to it through their normal course
of business or by the means identified
in the ADDRESSES section.
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 these same
type designs.
Costs of Compliance
We estimate that this proposed AD
affects 18 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Labor cost
Inspection ...............................
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Action
12 work-hours × $85 per hour
= $1,020 per inspection
cycle.
We have received no definitive data
that would enable us to provide a cost
estimate for the on-condition corrective
actions specified in this proposed AD.
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Parts cost
Cost per product
$0
Cost on U.S. operators
$1,020 per inspection cycle ...
$18,360 per inspection cycle.
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:
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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:
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Federal Register / Vol. 82, No. 97 / Monday, May 22, 2017 / Proposed Rules
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
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
(2) Model A300 B4–605R and B4–622R
airplanes.
(3) Model A300 F4–605R and F4–622R
airplanes.
(4) Model A300 C4–605R Variant F
airplanes.
(5) Model A310–203, –204, –221, –222,
–304, –322, –324, and –325 airplanes.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2017–0480;
Directorate Identifier 2016–NM–204–AD.
(a) Comments Due Date
We must receive comments by July 6, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1), (c)(2), (c)(3),
(c)(4), and (c)(5) of this AD; certificated in
any category; except those on which Airbus
Modification 5438 was embodied in
production.
(1) Model A300 B4–601, B4–603, B4–620,
and B4–622 airplanes.
This AD was prompted by cracking in the
door sill area of the aft cargo door. We are
issuing this AD to detect and correct cracking
of the door sill area of the aft cargo; such
cracking could adversely affect the structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections
Within the applicable compliance time
specified in table 1 to paragraph (g) of this
AD: Do a high frequency eddy current
(HFEC) inspection for cracking of the door
sill area (including the sill beam flag, lock
fitting, door sill web, and torsion door panel)
of the aft cargo door lower torsion box area,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
53–6185, dated February 11, 2016; or Service
Bulletin A310–53–2143, dated February 11,
2016; as applicable. Repeat the HFEC
inspection thereafter at intervals not to
exceed 15,100 flight cycles.
TABLE 1 TO PARAGRAPH (g) OF THIS AD—INITIAL INSPECTION
Airplane configuration
Compliance time
Repaired (date known), post-Airbus Modification 10319 lock fittings installed using Airbus Structural Repair Manual (SRM) Task 51–72–00.
Repaired (no record, date unknown), post-Airbus Modification 10319
lock fittings installed using Airbus SRM Task 51–72–00.
Non-repaired airplane, or airplane repaired with pre-Airbus Modification
10319 lock fittings using Airbus SRM Task 51–72–00.
Before exceeding 25,800 flight cycles since the lock fitting replacement.
Before exceeding 25,800 flight cycles from November 1, 1996.
No inspection required.
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(h) Corrective Action
(i) Terminating Action
If any crack is found during any inspection
required by paragraph (g) of this AD: Before
further flight, repair in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–53–6185, dated
February 11, 2016; or Service Bulletin A310–
53–2143, dated February 11, 2016; as
applicable; except, where Airbus Service
Bulletin A300–53–6185, dated February 11,
2016; or Service Bulletin A310–53–2143,
dated February 11, 2016; specifies to contact
Airbus for appropriate action, and specifies
that action as ‘‘RC’’ (Required for
Compliance), before further flight,
accomplish corrective actions in accordance
with the procedures specified in paragraph
(j)(2) of this AD.
Repair of an airplane as required by
paragraph (h) of this AD constitutes
terminating action for the repetitive
inspections required by paragraph (g) of this
AD for that airplane.
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(j) 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
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to the manager of the International Branch,
send it to the attention of the person
identified in paragraph (k)(2) of this AD.
Information may be emailed to: 9-ANM-116AMOC-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
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
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the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
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(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0241, dated December 6, 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–2017–0480.
(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
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23169
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 12,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–10140 Filed 5–19–17; 8:45 am]
BILLING CODE 4910–13–P
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Agencies
[Federal Register Volume 82, Number 97 (Monday, May 22, 2017)]
[Proposed Rules]
[Pages 23166-23169]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10140]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0480; Directorate Identifier 2016-NM-204-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 B4-600, B4-600R, and F4-600R series
airplanes, and Model A300 C4-605R Variant F airplanes (collectively
called Model A300-600 series airplanes); and Model A310 series
airplanes. This proposed AD was prompted by cracking in the door sill
area of the aft cargo door. This proposed AD would require repetitive
inspections of the aft cargo door lower torsion box area, 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 6, 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
[[Page 23167]]
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-
0480; 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-2017-0480;
Directorate Identifier 2016-NM-204-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
Airworthiness Directive 2016-0241, dated December 6, 2016 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus 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); and Model A310 series airplanes. The MCAI states:
Cracks were found on in-service aeroplane post mod 5438 in the
door sill area, from frame (FR) 60 to FR63, including the sill beam
flag, lock fitting, door sill web and torsion door panel. Two
previous cases with less crack extent were also reported.
This condition, if not detected and corrected, could lead to
reduced structural integrity of the aeroplane.
To address this unsafe condition, Airbus published Inspection
Service Bulletin (SB) A310-53-2139 and SB A300-53-6179 to provide
inspection instructions for the affected areas. Airbus published
also Airbus SB A310-53-2141 and SB A300-53-6181 to provide
modification instructions.
Further analysis showed that aeroplanes pre-mod 5438, for which
one or several lock fittings have been replaced by post mod 10319
lock fittings, could also be affected. Airbus published SB A310-53-
2143 and SB A300-53-6185 to provide inspection instructions.
For the reason described above, this [EASA] AD requires
repetitive Special Detailed Inspections (SDI) of the aft cargo door
lower torsion box area and, depending on findings, accomplishment of
applicable corrective action(s).
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-
0480.
Related Service Information Under 1 CFR Part 51
We reviewed Airbus Service Bulletin A300-53-6185, dated February
11, 2016; and Service Bulletin A310-53-2143, dated February 11, 2016;
which describe, among other actions, repetitive inspections of the aft
cargo door sill area for cracking. These documents are distinct since
they apply to different airplane models. This service information is
reasonably available because the interested parties have access to it
through their normal course of business or by the means identified in
the ADDRESSES section.
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 these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 18 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....................... 12 work-hours x $85 $0 $1,020 per $18,360 per
per hour = $1,020 inspection cycle. inspection cycle.
per inspection
cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
a cost estimate for the on-condition corrective actions specified in
this proposed AD.
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:
[[Page 23168]]
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.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2017-0480; Directorate Identifier 2016-NM-
204-AD.
(a) Comments Due Date
We must receive comments by July 6, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1), (c)(2), (c)(3), (c)(4), and (c)(5) of this AD; certificated
in any category; except those on which Airbus Modification 5438 was
embodied in production.
(1) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(2) Model A300 B4-605R and B4-622R airplanes.
(3) Model A300 F4-605R and F4-622R airplanes.
(4) Model A300 C4-605R Variant F airplanes.
(5) Model A310-203, -204, -221, -222, -304, -322, -324, and -325
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by cracking in the door sill area of the
aft cargo door. We are issuing this AD to detect and correct
cracking of the door sill area of the aft cargo; such cracking could
adversely affect the structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections
Within the applicable compliance time specified in table 1 to
paragraph (g) of this AD: Do a high frequency eddy current (HFEC)
inspection for cracking of the door sill area (including the sill
beam flag, lock fitting, door sill web, and torsion door panel) of
the aft cargo door lower torsion box area, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-53-6185,
dated February 11, 2016; or Service Bulletin A310-53-2143, dated
February 11, 2016; as applicable. Repeat the HFEC inspection
thereafter at intervals not to exceed 15,100 flight cycles.
Table 1 to Paragraph (g) of This AD--Initial Inspection
------------------------------------------------------------------------
Airplane configuration Compliance time
------------------------------------------------------------------------
Repaired (date known), post-Airbus Before exceeding 25,800 flight
Modification 10319 lock fittings cycles since the lock fitting
installed using Airbus Structural replacement.
Repair Manual (SRM) Task 51-72-00.
Repaired (no record, date unknown), Before exceeding 25,800 flight
post-Airbus Modification 10319 lock cycles from November 1, 1996.
fittings installed using Airbus SRM
Task 51-72-00.
Non-repaired airplane, or airplane No inspection required.
repaired with pre-Airbus Modification
10319 lock fittings using Airbus SRM
Task 51-72-00.
------------------------------------------------------------------------
(h) Corrective Action
If any crack is found during any inspection required by
paragraph (g) of this AD: Before further flight, repair in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-53-6185, dated February 11, 2016; or Service Bulletin
A310-53-2143, dated February 11, 2016; as applicable; except, where
Airbus Service Bulletin A300-53-6185, dated February 11, 2016; or
Service Bulletin A310-53-2143, dated February 11, 2016; specifies to
contact Airbus for appropriate action, and specifies that action as
``RC'' (Required for Compliance), before further flight, accomplish
corrective actions in accordance with the procedures specified in
paragraph (j)(2) of this AD.
(i) Terminating Action
Repair of an airplane as required by paragraph (h) of this AD
constitutes terminating action for the repetitive inspections
required by paragraph (g) of this AD for that airplane.
(j) 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 manager of the International Branch, send it to the
attention of the person identified in paragraph (k)(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 the
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). If approved by
[[Page 23169]]
the DOA, the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0241, dated December 6, 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-2017-0480.
(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 12, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-10140 Filed 5-19-17; 8:45 am]
BILLING CODE 4910-13-P