Airworthiness Directives; Airbus Airplanes, 19296-19299 [2014-07801]
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19296
Federal Register / Vol. 79, No. 67 / Tuesday, April 8, 2014 / Proposed Rules
dated December 21, 2012), may be used as a
method of compliance to tasks 533021–01–
01, 533021–01–02, 533021–01–03 specified
in Section 2.2.1 and 2.2.2 of Airbus
Document AI/SE M4/95A.0089/97, ‘‘A330
Airworthiness Limitation Items,’’ Issue 19,
dated March 23, 2012.
(h) Retained Requirement: No Alternative
Intervals or Limits
This paragraph restates the requirements of
paragraph (i) of AD 2011–17–08, Amendment
39–16772 (76 FR 53303, August 26, 2011).
Except as provided by paragraphs (i) and
(k)(1) of this AD, after accomplishing the
actions specified in paragraph (g) of this AD,
no alternatives to the maintenance tasks,
intervals, or limitations specified in
paragraph (g) of this AD may be used.
rmajette on DSK2TPTVN1PROD with PROPOSALS
Airworthiness Limitation Items,’’ Issue 17,
dated May 28, 2010, comply with all
applicable maintenance requirements and
associated airworthiness limitations included
in Airbus Document AI/SE–M4/95A.0089/97,
‘‘A330 Airworthiness Limitation Items,’’
Issue 17, dated May 28, 2010.
(k) New Requirement: No Alternative
Intervals or Limits
Except as provided by paragraph (j) of this
AD, after the maintenance or inspection
program has been revised as required by
paragraph (i) of this AD, no alternative
actions (e.g., inspections) or intervals may be
used unless the actions or intervals are
approved as an alternative method of
compliance (AMOC) in accordance with the
procedures specified in paragraph (l)(1) of
this AD.
(i) New Maintenance or Inspection Program
Revision
(1) Within 3 months after the effective date
of this AD: Revise the maintenance or
inspection program, as applicable, by
incorporating Airbus Document AI/SE–M4/
95A.0089/97, ‘‘A330 Airworthiness
Limitation Items,’’ Issue 19, dated March 23,
2012; and Variations to Airbus Document AI/
SE M4/95A.0089/97, ‘‘A330 Airworthiness
Limitation Items,’’ Issue 19, dated March 23,
2012 (variations reference 0GVLG120018/
C0S, dated October 24, 2012; and
0GVLG130002/C01, dated March 26, 2013).
(2) Comply with all applicable instructions
and airworthiness limitations included in
Airbus Document AI/SE M4/95A.0089/97,
‘‘A330 Airworthiness Limitation Items,’’
Issue 19, dated March 23, 2012; and
Variations to Airbus Document AI/SE M4/
95A.0089/97, ‘‘A330 Airworthiness
Limitation Items,’’ Issue 19, dated March 23,
2012 (variations reference 0GVLG120018/
C0S, dated October 24, 2012; and
0GVLG130002/C01, dated March 26, 2013).
The initial compliance times for the actions
specified Airbus Document AI/SE–M4/
95A.0089/97, ‘‘A330 Airworthiness
Limitation Items,’’ Issue 19, dated March 23,
2012; and Variations to Airbus Document AI/
SE M4/95A.0089/97, ‘‘A330 Airworthiness
Limitation Items,’’ Issue 19, dated March 23,
2012 (variations reference 0GVLG120018/
C0S, dated October 24, 2012; and
0GVLG130002/C01, dated March 26, 2013);
are at the times specified in Airbus
Document AI/SE–M4/95A.0089/97, ‘‘A330
Airworthiness Limitation Items,’’ Issue 19,
dated March 23, 2012; and Variations to
Airbus Document AI/SE M4/95A.0089/97,
‘‘A330 Airworthiness Limitation Items,’’
Issue 19, dated March 23, 2012 (variations
reference 0GVLG120018/C0S, dated October
24, 2012; and 0GVLG130002/C01, dated
March 26, 2013); or within 3 months after the
effective date of this AD, whichever occurs
later. Accomplishing the revision in this
paragraph ends the requirements in
paragraph (g) of this AD.
(j) New Optional Compliance
Compliance with the tasks 533021–02–01,
533021–02–02, 533021–02–03 specified in
Variation to Airbus Document AI/SE M4/
95A.0089/97, ‘‘A330 Airworthiness
Limitation Items,’’ Issue 19, dated March 23,
2012 (variation reference 0GVLG120022/C0S,
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(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227–1138; fax (425) 227–
1149. Information may be emailed to: 9ANM-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. The AMOC
approval letter must specifically reference
this AD. AMOCs approved previously for AD
2011–17–08, Amendment 39–16772 (76 FR
53303, August 26, 2011), are approved as
AMOCs for the corresponding provisions of
paragraph (g) of this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or its delegated agent, or the DAH with a
State of Design Authority’s design
organization approval, as applicable). You
are required to assure the product is
airworthy before it is returned to service.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency Airworthiness
Directive 2012–0211, dated October 12, 2012,
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 it in Docket No. FAA–2014–
0190.
(2) For service information identified in
this AD, contact Airbus SAS—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@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.
Issued in Renton, Washington, on March
28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–07799 Filed 4–7–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0189; Directorate
Identifier 2013–NM–181–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 all
Airbus Model A300 series airplanes,
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 a report of chafing found
on the overflow sensor harness of the
surge tank, and subsequent contact
between the electrical wiring and fuel
tank structure. This proposed AD would
require a one-time inspection for
chafing of the overflow sensor harness
and structural damage of the outer tank,
and repair if necessary. This proposed
AD would also require modification of
the sensor harness. We are proposing
this AD to prevent chafing of the
harness and subsequent contact between
the electrical wiring and fuel tank
structure, which could result in
electrical arcing and a fuel tank
explosion and consequent loss of the
airplane.
SUMMARY:
We must receive comments on
this proposed AD by May 23, 2014.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
DATES:
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• 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 proposed 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 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.
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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–2014–
0189; 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–2014–0189; Directorate Identifier
2013–NM–181–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.
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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
Community, has issued EASA
Airworthiness Directive 2013–0193,
dated August 23, 2013 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus Model A300 series
airplanes, 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). The MCAI
states:
During a scheduled maintenance check on
an A300 aeroplane, chafing was found on the
surge tank overflow sensor harness. The
harness was found to contact the Magnetic
Fuel Level Indicator (MFLI) canister.
Prompted by these findings, DGAC
´ ´
[Direction Generale de l’Aviation Civile]
France issued https://ad.easa.europa.eu/blob/
easa_ad_1999_404_293.pdf/AD_1999-404293 to require modification of the harness
routing in accordance with the instructions
of Airbus SB [service bulletin] A300–28–
0058 or SB A300–28–6020, as applicable to
aeroplane model.
Since that [DGAC] AD was issued,
maintenance work on modified A300–600
aeroplanes revealed some chafing of the
harness, creating a potential contact between
the electrical wire and fuel tank structure.
Investigations have shown that although
measures were taken to prevent contact of the
harness with the MFLI (through modification
04489),the installation can be subject to
human error. As the MFLI is integral to the
access panel in this location, any potential
contact with the harness (as a result of
incorrect installation) is hidden.
This condition, if not detected and
corrected, could lead to electrical arcing,
possibly resulting in a fuel tank explosion
and loss of the aeroplane. To address this
potential unsafe condition, Airbus issued SB
A300–28–0091 for A300 aeroplanes, SB
A300–28–6109 for A300–600 aeroplanes, and
A300–28–9022 for A300–600ST aeroplanes.
For the reasons described above, this
[EASA] AD requires a one-time inspection of
the harness and, depending on findings,
corrective actions, as well as replacement of
angle brackets by error-proof harness
brackets.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating it in Docket No. FAA–
2014–0189.
PO 00000
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Fmt 4702
Sfmt 4702
19297
Relevant Service Information
Airbus has issued Mandatory Service
Bulletins A300–28–0091, dated March
5, 2013; and A300–28–6109, Revision
01, dated December 20, 2013. The
actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
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 design.
Repair Approvals
In many FAA transport ADs, when
the service information specifies to
contact the manufacturer for further
instructions if certain discrepancies are
found, we typically include in the AD
a requirement to accomplish the action
using a method approved by either the
FAA or the State of Design Authority (or
its delegated agent).
We have recently been notified that
certain laws in other countries do not
allow such delegation of authority, but
some countries do recognize design
approval organizations. In addition, we
have become aware that some U.S.
operators have used repair instructions
that were previously approved by a
State of Design Authority or a Design
Approval Holder (DAH) as a method of
compliance with this provision in FAA
ADs. Frequently, in these cases, the
previously approved repair instructions
come from the airplane structural repair
manual or the DAH repair approval
statements that were not specifically
developed to address the unsafe
condition corrected by the AD. Using
repair instructions that were not
specifically approved for a particular
AD creates the potential for doing
repairs that were not developed to
address the unsafe condition identified
by the MCAI AD, the FAA AD, or the
applicable service information, which
could result in the unsafe condition not
being fully corrected.
To prevent the use of repairs that
were not specifically developed to
correct the unsafe condition, certain
requirements of this proposed AD
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Federal Register / Vol. 79, No. 67 / Tuesday, April 8, 2014 / Proposed Rules
specify that the repair approval
specifically refer to the FAA AD. This
change is intended to clarify the method
of compliance and to provide operators
with better visibility of repairs that are
specifically developed and approved to
correct the unsafe condition. In
addition, we use the phrase ‘‘its
delegated agent, or the DAH with State
of Design Authority design organization
approval, as applicable’’ in this
proposed AD to refer to a DAH
authorized to approve certain required
repairs for this proposed AD.
Costs of Compliance
We estimate that this proposed AD
affects 123 airplanes of U.S. registry.
We also estimate that it would take
about 3 work-hours per product to
comply with the inspection required by
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
this inspection proposed by this AD on
U.S. operators to be $31,365, or $255 per
product.
We estimate that it would take about
12 work-hours per product to comply
with the modification requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Required
parts would cost about $500 per
product. Based on these figures, we
estimate the cost of this modification
proposed by this AD on U.S. operators
to be $186,960, or $1,520 per product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition repairs
specified in this proposed AD.
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
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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Authority for This Rulemaking
§ 39.13
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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[Amended]
2. Amend § 39.13 by adding the
following new airworthiness directive
(AD):
Airbus: Docket No. FAA–2014–0189;
Directorate Identifier 2013–NM–181–AD.
(a) Comments Due Date
We must receive comments by May 23,
2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes
specified in paragraphs (c)(1), (c)(2), (c)(3),
(c)(4), and (c)(5) of this AD; certificated in
any category; all manufacturer serial
numbers.
(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.
PO 00000
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Fmt 4702
Sfmt 4702
(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 28, Fuel.
(e) Reason
This AD was prompted by a report of
chafing found on the overflow sensor harness
of the surge tank, and subsequent contact
between the electrical wiring and fuel tank
structure. We are issuing this AD to prevent
chafing of the harness and subsequent
contact between the electrical wiring and fuel
tank structure, which could result in
electrical arcing and a fuel tank explosion
and consequent loss of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) One-Time Inspection and Repair
Within 30 months after the effective date
of this AD: Perform a one-time visual
inspection for chafing of the outer tank
sensor harness between ribs 26 and 27, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A300–28–0091, dated March 5, 2013
(for Model A300 series airplanes); or Airbus
Mandatory Service Bulletin A300–28–6109,
Revision 01, dated December 20, 2013 (for
Model A300–600 series airplanes).
(1) If any previous repairs are identified, or
if braid and wire insulation is found
damaged with the conductor exposed during
the inspection required by paragraph (g) of
this AD: Before further flight, repair using a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA (or its
delegated agent, or the Design Approval
Holder with a State of Design Authority’s
design organization approval, as applicable).
For a repair method to be approved, the
repair approval must specifically refer to this
AD.
(2) If the braid and wire insulation is found
damaged without the conductor exposed
during the inspection required by paragraph
(g) of this AD: Before further flight, repair, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A300–28–0091, dated March 5, 2013
(for Model A300 series airplanes); or Airbus
Mandatory Service Bulletin A300–28–6109,
Revision 01, dated December 20, 2013 (for
Model A300–600 series airplanes).
(h) Modification
(1) For airplanes on which no damage was
found during the inspection required by
paragraph (g) of this AD: Before further flight,
install modified and error-proof angle
brackets to stringer 15 between ribs 26 and
27 of the outer tank sensor harness, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A300–28–0091, dated March 5, 2013
(for Model A300 series airplanes); or Airbus
Mandatory Service Bulletin A300–28–6109,
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Revision 01, dated December 20, 2013 (for
Model A300–600 series airplanes).
(2) For airplanes on which any damage was
found during the inspection required by
paragraph (g) of this AD, and the applicable
repair required by paragraph (g)(1) or (g)(2)
of this AD has been done: Before further
flight, install modified and error-proof angle
brackets to stringer 15 between ribs 26 and
27 of the outer tank sensor harness, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A300–28–0091, dated March 5, 2013
(for Model A300 series airplanes); or Airbus
Mandatory Service Bulletin A300–28–6109,
Revision 01, dated December 20, 2013 (for
Model A300–600 series airplanes).
(i) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g) and (h) of this AD,
if those actions were performed before the
effective date of this AD using Airbus
Mandatory Service Bulletin A300–28–6109,
dated March 5, 2013, which is not
incorporated by reference in this AD.
(2) 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 March
28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–07801 Filed 4–7–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
rmajette on DSK2TPTVN1PROD with PROPOSALS
(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 International Branch, send it to ATTN:
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. Information may be emailed to: 9ANM-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. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer, use these actions if they are
FAA-approved. Corrective actions are
considered FAA-approved if they were
approved by the State of Design Authority (or
its delegated agent, or the DAH with a State
of Design Authority’s design organization
approval, as applicable). You are required to
ensure the product is airworthy before it is
returned to service.
14 CFR Part 39
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0193, dated
August 23, 2013, 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 it in Docket No.
FAA–2014–0189.
DATES:
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[Docket No. FAA–2014–0188; Directorate
Identifier 2013–NM–157–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model DHC–8–400
series airplanes. This proposed AD was
prompted by reports of two in-service
incidents where one side of the main
landing gear (MLG) did not achieve
down-lock. This proposed AD would
require a detailed inspection of the apex
joints of the stabilizer brace lock link in
the MLG for clearance; rectifying and
repairing the clearance gap, if necessary;
and lubricating the apex joints of the
stabilizer brace lock link in the MLG.
We are proposing this AD to detect and
correct insufficiently greased stabilizer
brace lock linkage of the MLG and overtorqued lock linkage attachment bolts,
which could lead to the failure to
extend and down-lock the MLG, and
could affect the safe landing of the
airplane.
SUMMARY:
We must receive comments on
this proposed AD by May 23, 2014.
ADDRESSES: You may send comments 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.
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
19299
• 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 proposed AD, contact Bombardier,
Inc., Q-Series Technical Help Desk, 123
Garratt Boulevard, Toronto, Ontario
M3K 1Y5, Canada; telephone 416–375–
4000; fax 416–375–4539; email
thd.qseries@aero.bombardier.com;
Internet https://www.bombardier.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.
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–2014–
0188; 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:
Luke Walker, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone (516) 228–7363;
fax (516) 794–5531.
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–2014–0188; Directorate Identifier
2013–NM–157–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.
E:\FR\FM\08APP1.SGM
08APP1
]]>Agencies
[Federal Register Volume 79, Number 67 (Tuesday, April 8, 2014)]
[Proposed Rules]
[Pages 19296-19299]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-07801]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0189; Directorate Identifier 2013-NM-181-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 all
Airbus Model A300 series airplanes, 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 a report of chafing found on the overflow sensor
harness of the surge tank, and subsequent contact between the
electrical wiring and fuel tank structure. This proposed AD would
require a one-time inspection for chafing of the overflow sensor
harness and structural damage of the outer tank, and repair if
necessary. This proposed AD would also require modification of the
sensor harness. We are proposing this AD to prevent chafing of the
harness and subsequent contact between the electrical wiring and fuel
tank structure, which could result in electrical arcing and a fuel tank
explosion and consequent loss of the airplane.
DATES: We must receive comments on this proposed AD by May 23, 2014.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
[[Page 19297]]
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 proposed 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 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-2014-
0189; 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-2014-0189;
Directorate Identifier 2013-NM-181-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 Community, has issued EASA
Airworthiness Directive 2013-0193, dated August 23, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model A300
series airplanes, 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). The MCAI states:
During a scheduled maintenance check on an A300 aeroplane,
chafing was found on the surge tank overflow sensor harness. The
harness was found to contact the Magnetic Fuel Level Indicator
(MFLI) canister.
Prompted by these findings, DGAC [Direction
G[eacute]n[eacute]rale de l'Aviation Civile] France issued https://ad.easa.europa.eu/blob/easa_ad_1999_404_293.pdf/AD_1999-404-293
to require modification of the harness routing in accordance with
the instructions of Airbus SB [service bulletin] A300-28-0058 or SB
A300-28-6020, as applicable to aeroplane model.
Since that [DGAC] AD was issued, maintenance work on modified
A300-600 aeroplanes revealed some chafing of the harness, creating a
potential contact between the electrical wire and fuel tank
structure. Investigations have shown that although measures were
taken to prevent contact of the harness with the MFLI (through
modification 04489),the installation can be subject to human error.
As the MFLI is integral to the access panel in this location, any
potential contact with the harness (as a result of incorrect
installation) is hidden.
This condition, if not detected and corrected, could lead to
electrical arcing, possibly resulting in a fuel tank explosion and
loss of the aeroplane. To address this potential unsafe condition,
Airbus issued SB A300-28-0091 for A300 aeroplanes, SB A300-28-6109
for A300-600 aeroplanes, and A300-28-9022 for A300-600ST aeroplanes.
For the reasons described above, this [EASA] AD requires a one-
time inspection of the harness and, depending on findings,
corrective actions, as well as replacement of angle brackets by
error-proof harness brackets.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating it in Docket No.
FAA-2014-0189.
Relevant Service Information
Airbus has issued Mandatory Service Bulletins A300-28-0091, dated
March 5, 2013; and A300-28-6109, Revision 01, dated December 20, 2013.
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
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 design.
Repair Approvals
In many FAA transport ADs, when the service information specifies
to contact the manufacturer for further instructions if certain
discrepancies are found, we typically include in the AD a requirement
to accomplish the action using a method approved by either the FAA or
the State of Design Authority (or its delegated agent).
We have recently been notified that certain laws in other countries
do not allow such delegation of authority, but some countries do
recognize design approval organizations. In addition, we have become
aware that some U.S. operators have used repair instructions that were
previously approved by a State of Design Authority or a Design Approval
Holder (DAH) as a method of compliance with this provision in FAA ADs.
Frequently, in these cases, the previously approved repair instructions
come from the airplane structural repair manual or the DAH repair
approval statements that were not specifically developed to address the
unsafe condition corrected by the AD. Using repair instructions that
were not specifically approved for a particular AD creates the
potential for doing repairs that were not developed to address the
unsafe condition identified by the MCAI AD, the FAA AD, or the
applicable service information, which could result in the unsafe
condition not being fully corrected.
To prevent the use of repairs that were not specifically developed
to correct the unsafe condition, certain requirements of this proposed
AD
[[Page 19298]]
specify that the repair approval specifically refer to the FAA AD. This
change is intended to clarify the method of compliance and to provide
operators with better visibility of repairs that are specifically
developed and approved to correct the unsafe condition. In addition, we
use the phrase ``its delegated agent, or the DAH with State of Design
Authority design organization approval, as applicable'' in this
proposed AD to refer to a DAH authorized to approve certain required
repairs for this proposed AD.
Costs of Compliance
We estimate that this proposed AD affects 123 airplanes of U.S.
registry.
We also estimate that it would take about 3 work-hours per product
to comply with the inspection required by this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this inspection proposed by this AD on U.S. operators to be
$31,365, or $255 per product.
We estimate that it would take about 12 work-hours per product to
comply with the modification requirements of this proposed AD. The
average labor rate is $85 per work-hour. Required parts would cost
about $500 per product. Based on these figures, we estimate the cost of
this modification proposed by this AD on U.S. operators to be $186,960,
or $1,520 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition repairs 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: 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. Amend Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2014-0189; Directorate Identifier 2013-NM-
181-AD.
(a) Comments Due Date
We must receive comments by May 23, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes specified in paragraphs
(c)(1), (c)(2), (c)(3), (c)(4), and (c)(5) of this AD; certificated
in any category; all manufacturer serial numbers.
(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 28, Fuel.
(e) Reason
This AD was prompted by a report of chafing found on the
overflow sensor harness of the surge tank, and subsequent contact
between the electrical wiring and fuel tank structure. We are
issuing this AD to prevent chafing of the harness and subsequent
contact between the electrical wiring and fuel tank structure, which
could result in electrical arcing and a fuel tank explosion and
consequent loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) One-Time Inspection and Repair
Within 30 months after the effective date of this AD: Perform a
one-time visual inspection for chafing of the outer tank sensor
harness between ribs 26 and 27, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-28-0091, dated March 5, 2013 (for Model A300 series airplanes);
or Airbus Mandatory Service Bulletin A300-28-6109, Revision 01,
dated December 20, 2013 (for Model A300-600 series airplanes).
(1) If any previous repairs are identified, or if braid and wire
insulation is found damaged with the conductor exposed during the
inspection required by paragraph (g) of this AD: Before further
flight, repair using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or
its delegated agent, or the Design Approval Holder with a State of
Design Authority's design organization approval, as applicable). For
a repair method to be approved, the repair approval must
specifically refer to this AD.
(2) If the braid and wire insulation is found damaged without
the conductor exposed during the inspection required by paragraph
(g) of this AD: Before further flight, repair, in accordance with
the Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-28-0091, dated March 5, 2013 (for Model A300 series airplanes);
or Airbus Mandatory Service Bulletin A300-28-6109, Revision 01,
dated December 20, 2013 (for Model A300-600 series airplanes).
(h) Modification
(1) For airplanes on which no damage was found during the
inspection required by paragraph (g) of this AD: Before further
flight, install modified and error-proof angle brackets to stringer
15 between ribs 26 and 27 of the outer tank sensor harness, in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A300-28-0091, dated March 5, 2013 (for Model A300
series airplanes); or Airbus Mandatory Service Bulletin A300-28-
6109,
[[Page 19299]]
Revision 01, dated December 20, 2013 (for Model A300-600 series
airplanes).
(2) For airplanes on which any damage was found during the
inspection required by paragraph (g) of this AD, and the applicable
repair required by paragraph (g)(1) or (g)(2) of this AD has been
done: Before further flight, install modified and error-proof angle
brackets to stringer 15 between ribs 26 and 27 of the outer tank
sensor harness, in accordance with the Accomplishment Instructions
of Airbus Mandatory Service Bulletin A300-28-0091, dated March 5,
2013 (for Model A300 series airplanes); or Airbus Mandatory Service
Bulletin A300-28-6109, Revision 01, dated December 20, 2013 (for
Model A300-600 series airplanes).
(i) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using Airbus Mandatory Service
Bulletin A300-28-6109, dated March 5, 2013, which is not
incorporated by reference in this AD.
(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 International Branch, send it to ATTN: 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. 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. The
AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer, use these actions if they
are FAA-approved. Corrective actions are considered FAA-approved if
they were approved by the State of Design Authority (or its
delegated agent, or the DAH with a State of Design Authority's
design organization approval, as applicable). You are required to
ensure the product is airworthy before it is returned to service.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0193, dated August 23,
2013, 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 it in Docket No. FAA-2014-0189.
(2) 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 March 28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-07801 Filed 4-7-14; 8:45 am]
BILLING CODE 4910-13-P
