Airworthiness Directives; Airbus Airplanes, 45462-45465 [2015-18533]
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45462
Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules
(d) Subject
Air Transport Association (ATA) of
America Code 54, Nacelles/pylons.
(e) Unsafe Condition
This AD was prompted by a report of fuel
leaking onto the hot exhaust portion of the
engine as a result of an unintended leak path
from the leading edge through the pylons. We
are issuing this AD to prevent fuel leaking
from an unintended drain path from the
leading edge through the pylons and onto the
hot engine parts or brakes, which could lead
to a major ground fire.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Installation of Inboard and Outboard
Seal Dams
Within 60 months after the effective date
of this AD, install new seal dams in the
inboard and outboard corners of the aft pylon
frame on the left and right engines, including
a general visual inspection to detect damage
of the outboard blade seal, and do all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin B787–81205–
SB540004–00, Issue 001, dated October 24,
2014. Do all applicable corrective actions
before further flight.
Lhorne on DSK7TPTVN1PROD with PROPOSALS
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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 ACO, send it to the
attention of the person identified in
paragraph (i)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(i) Related Information
(1) For more information about this AD,
contact Sherry Vevea, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, Seattle
Aircraft Certification Office (ACO), 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6514; fax: 425–917–6590;
email: sherry.vevea@faa.gov.
(2) For Boeing service information
identified in this AD, contact Boeing
VerDate Sep<11>2014
13:52 Jul 29, 2015
Jkt 235001
Commercial Airplanes, Attention: Data &
Services Management, P.O. Box 3707, MC
2H–65, Seattle, WA 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; Internet https://
www.myboeingfleet.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 July 22,
2015.
Victor Wicklund,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–18561 Filed 7–29–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2963; Directorate
Identifier 2015–NM–016–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 A319–131, –132, and
–133 airplanes; Model A320–232 and
–233 airplanes; and Model A321–131,
–231, and –232 airplanes. This proposed
AD was prompted by reports of forward
engine mount attachment pins that were
manufactured from discrepant raw
material. This proposed AD would
require identification and replacement
of affected forward engine mount
attachment pins. We are proposing this
AD to prevent failure of a forward
engine mount attachment pin, possible
loss of an engine in-flight, and
consequent reduced controllability of
the airplane.
DATES: We must receive comments on
this proposed AD by September 14,
2015.
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:
PO 00000
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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 Airbus service information
identified in this proposed AD, contact
Airbus, Airworthiness Office—EIAS, 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. For
Goodrich Aerostructures service
information identified in this proposed
AD, contact UTC Aerospace Systems,
ATTN: Christopher Newth—V2500 A1/
A5 Project Engineer, Aftermarket—
Aerostructures; 850 Lagoon Drive, Chula
Vista, CA; telephone 619–498–7505;
email christopher.newth@utas.utc.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–2015–
2963; 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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
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–2015–2963; Directorate Identifier
2015–NM–016–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
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Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules
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 2015–0004, dated January 13,
2015 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A319–131, –132, and –133
airplanes; Model A320–232 and –233
airplanes; and Model A321–131, –231,
and –232 airplanes. The MCAI states:
A number of forward engine mount pins,
Part Number (P/N) 740–2022–501, intended
for IAE V2500 series engines, have been
reported as non-compliant with the current
certification requirements, due to a quality
issue during manufacturing of the raw
material. It was also determined that a batch
of 88 affected pins are installed on in-service
aeroplanes fitted with forward engine mount
P/N 745–2010–503 and the serial numbers (s/
n) of the affected pins and the [manufacturer
serial number] MSN of the related aeroplanes
have been identified.
This condition, if not corrected, could lead
to forward engine mount pin failure, possibly
resulting in in-flight loss of an engine and
consequent reduced control of the aeroplane.
For the reasons described above, this
[EASA] AD requires identification of the
affected forward engine mount pins and
removal from service [replacement] of those
pins.
Lhorne on DSK7TPTVN1PROD with PROPOSALS
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–2015–
2963.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–71–1064, dated November 5,
2014; and Goodrich Aerostructures has
issued Service Bulletin V2500–NAC–
71–0323, dated September 18, 2014. The
service information describes
procedures for an inspection to
determine the serial number of the
attachment pins for the forward engine
mount crossbeam to main beam for each
engine, and replacement of affected
pins. This service information is
reasonably available because the
VerDate Sep<11>2014
13:52 Jul 29, 2015
Jkt 235001
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section of this NPRM.
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.
Explanation of ‘‘RC’’ Procedures and
Tests in Service Information
The FAA worked in conjunction with
industry, under the Airworthiness
Directive Implementation Aviation
Rulemaking Committee (ARC), to
enhance the AD system. One
enhancement was a new process for
annotating which procedures and tests
in the service information are required
for compliance with an AD.
Differentiating these procedures and
tests from other tasks in the service
information is expected to improve an
owner’s/operator’s understanding of
crucial AD requirements and help
provide consistent judgment in AD
compliance. The procedures and tests
identified as RC (required for
compliance) in any service information
have a direct effect on detecting,
preventing, resolving, or eliminating an
identified unsafe condition.
As specified in a NOTE under the
Accomplishment Instructions of the
specified Airbus service information,
procedures and tests identified as RC
must be done to comply with the
proposed AD. However, procedures and
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 alternative method of compliance
(AMOC), provided the procedures and
tests identified as RC can be done and
the airplane can be put back in a
serviceable condition. Any substitutions
or changes to procedures or tests
identified as RC will require approval of
an AMOC.
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45463
Costs of Compliance
We estimate that this proposed AD
affects 922 airplanes of U.S. registry.
We also estimate that it would take
about 2 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Required
parts would cost about $0 per product.
Based on these figures, we estimate the
cost of this proposed AD on U.S.
operators to be $156,740, or $170 per
product.
In addition, we estimate that any
necessary follow-on actions would take
about 4 work-hours and require parts
costing $1,724, for a cost of $2,064 per
attachment pin replacement. We have
no way of determining the number of
aircraft that might need this action.
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,
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45464
Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2015–2963;
Directorate Identifier 2015–NM–016–AD.
(a) Comments Due Date
We must receive comments by September
14, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1), (c)(2), and
(c)(3) of this AD, certificated in any category,
all manufacturer serial numbers.
(1) Model A319–131, –132, and –133
airplanes.
(2) Model A320–232 and –233 airplanes.
(3) Model A321–131, –231, and –232
airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 71, Power Plant.
Lhorne on DSK7TPTVN1PROD with PROPOSALS
(e) Reason
This AD was prompted by reports of
forward engine mount attachment pins that
were manufactured from discrepant raw
material. We are issuing this AD to prevent
failure of a forward engine mount attachment
pin, possible loss of an engine in-flight, and
consequent reduced controllability of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
pin for that forward engine mount, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
71–1064, dated November 5, 2014; and
Goodrich Aerostructures Service Bulletin
V2500–NAC–71–0323, dated September 18,
2014. A review of airplane maintenance
records is acceptable in lieu of this
identification if the part number of the
forward engine mount, and the part number
and serial number of the attachment pin for
that forward engine mount can be
conclusively determined from that review. If
any part number of the forward engine
mount, or part number or serial number of
the attachment pins for the forward engine
mount, cannot be identified: At the earliest
of the times specified in paragraphs (g)(1)
through (g)(4) of this AD, contact 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), for identification
information.
(1) Within 24 months after the effective
date of this AD.
(2) At the next engine removal after the
effective date of this AD.
(3) Within 7,500 flight hours after the
effective date of this AD.
(4) Within 5,000 flight cycles after the
effective date of this AD.
18:03 Jul 29, 2015
Jkt 235001
Serial Nos.
Attachment Pin
(P/N 740–2022–501)
Forward Engine
Mount
(P/N 745–2010–503)
1415SC
1420SC
1421SC
1422SC
1436SC
1438SC
1452SC
1456SC
1397SC
1432SC
1405SC
1411SC
1389SC
1392SC
1382SC
1384SC
1407SC
1408SC
1395SC
1406SC
1383SC
1404SC
1393SC
1413SC
1386SC
1388SC
1390SC
1410SC
1423SC
1424SC
1403SC
1419SC
1385SC
1387SC
1431SC
1433SC
1425SC
1428SC
1429SC
1430SC
1427SC
1434SC
1442SC
1394SC
1441SC
1426SC
1437SC
1439SC
1443SC
1448SC
1435SC
1440SC
1454SC
1455SC
1451SC
1453SC
1444SC
1450SC
1461SC
1469SC
1480SC
1481SC
1446SC
1449SC
13695001
13705001
13707001
13709001
13737001
13741001
13769001
13777001
13667001
13729001
13675001
13687001
13651001
13657001
13637001
13641001
13679001
13681001
13663001
13677001
13639001
13673001
13659001
13691001
13645001
13649001
13653001
13685001
13711001
13713001
13671001
13703001
13643001
13647001
13727001
13731001
13715001
13721001
13723001
13725001
13719001
13733001
13749001
13661001
13747001
13717001
13739001
13743001
13751001
13761001
13735001
13745001
13773001
13775001
13767001
13771001
13753001
13765001
13787001
13817001
13839001
13841001
13757001
13763001
(h) Corrective Actions
If, during any identification required by
paragraph (g) of this AD, a forward engine
mount having part number (P/N) 745–2010–
503 is found, and the attachment pin has P/
N 740–2022–501 with any serial number that
is included in figure 1 to paragraphs (h) and
(j) of this AD: At the earliest of the times
specified in paragraphs (g)(1) through (g)(4)
of this AD, replace the affected attachment
pin with a serviceable part having a part
number other than P/N 740–2022–501, and
having a serial number that is not identified
in figure 1 to paragraphs (h) and (j) of this
AD, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
71–1064, dated November 5, 2014; and
Goodrich Aerostructures Service Bulletin
V2500–NAC–71–0323, dated September 18,
2014.
FIGURE 1 TO PARAGRAPHS (h) AND (j)
OF THIS AD—PART NUMBERS AND
SERIAL NUMBERS OF AFFECTED
FORWARD ENGINE MOUNTS AND ATTACHMENT PINS
Serial Nos.
Attachment Pin
(P/N 740–2022–501)
Forward Engine
Mount
(P/N 745–2010–503)
1396SC
1391SC
1412SC
1402SC
1409SC
1416SC
1418SC
1417SC
1414SC
13665001
13655001
13689001
13669001
13683001
13697001
13701001
13699001
13693001
(g) Identification of Part Numbers for
Forward Engine Mount and Attachment Pins
Except as provided by paragraph (i) of this
AD, at the earliest of the times specified in
paragraphs (g)(1) through (g)(4) of this AD:
For each engine, identify the part number of
the forward engine mount, and the part
number and serial number of the attachment
VerDate Sep<11>2014
FIGURE 1 TO PARAGRAPHS (h) AND (j)
OF THIS AD—PART NUMBERS AND
SERIAL NUMBERS OF AFFECTED
FORWARD ENGINE MOUNTS AND ATTACHMENT PINS—Continued
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Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules
FIGURE 1 TO PARAGRAPHS (h) AND (j)
OF THIS AD—PART NUMBERS AND
SERIAL NUMBERS OF AFFECTED
FORWARD ENGINE MOUNTS AND ATTACHMENT PINS—Continued
FIGURE 2 TO PARAGRAPH (i) OF THIS
AD—AIRPLANE MANUFACTURER SERIAL NUMBERS—Continued
Airplane manufacturer serial Nos.
4753
4754
4755
4757
4761
4762
4772
4773
4774
4775
4779
4782
4783
4784
4786
4788
4790
4791
4798
4804
4813
Serial No.
Attachment Pin
(P/N 740–2022–501)
Forward Engine
Mount
(P/N 745–2010–503)
1467SC
1445SC
1462SC
1464SC
1466SC
1470SC
1459SC
1463SC
1475SC
1458SC
1477SC
1474SC
1478SC
1479SC
1472SC
13813001
13755001
13789001
13793001
13811001
13819001
13783001
13791001
13829001
13781001
13833001
13827001
13835001
13837001
13823001
(i) Exception to Paragraph (g) of This AD
For airplanes with manufacturer serial
numbers identified in figure 2 to paragraph
(i) of this AD: If it can be conclusively
determined that an engine has not been
replaced after March 1, 2011 (the date of
manufacture of the first airplane with
affected engine mounts), the airplane is not
affected by the requirements of paragraphs (g)
and (h) of this AD.
FIGURE 2 TO PARAGRAPH (i) OF THIS
AD—AIRPLANE MANUFACTURER SERIAL NUMBERS
Lhorne on DSK7TPTVN1PROD with PROPOSALS
Airplane manufacturer serial Nos.
4593
4602
4620
4637
4638
4642
4643
4644
4660
4677
4690
4696
4700
4701
4703
4706
4707
4710
4716
4719
4725
4726
4731
4736
4737
4741
4746
4751
4752
VerDate Sep<11>2014
13:52 Jul 29, 2015
Jkt 235001
(k) 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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
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. The AMOC approval letter
must specifically reference this AD.
(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 Airbus’s EASA DOA. If
approved by 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
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Fmt 4702
Sfmt 4702
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
a serviceable condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(l) Special Flight Permits Prohibited
Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(j) Parts Installation Prohibition
As of the effective date of this AD, no
person may install on any airplane any
engine mount attachment pin having P/N
740–2022–501 with a serial number
identified in figure 1 to paragraphs (h) and
(j) of this AD.
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45465
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0004, dated
January 13, 2015, 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–2015–2963.
(2) For Airbus service information
identified in this AD, contact Airbus,
Airworthiness Office—EIAS, 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.
For Goodrich Aerostructures service
information identified in this AD, contact
UTC Aerospace Systems, ATTN: Christopher
Newth—V2500 A1/A5 Project Engineer,
Aftermarket—Aerostructures; 850 Lagoon
Drive, Chula Vista, CA; telephone 619–498–
7505; email christopher.newth@utas.utc.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 July 17,
2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–18533 Filed 7–29–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HEALTH AND
HUMAN SERVICES
Food and Drug Administration
21 CFR Part 101
[Docket No. FDA–2015–D–1839]
The Food and Drug Administration’s
Policy on Declaring Small Amounts of
Nutrients and Dietary Ingredients on
Nutrition Labels; Draft Guidance for
Industry; Availability
AGENCY:
Food and Drug Administration,
HHS.
E:\FR\FM\30JYP1.SGM
30JYP1
]]>Agencies
[Federal Register Volume 80, Number 146 (Thursday, July 30, 2015)]
[Proposed Rules]
[Pages 45462-45465]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-18533]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-2963; Directorate Identifier 2015-NM-016-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 A319-131, -132, and -133 airplanes; Model A320-232 and -
233 airplanes; and Model A321-131, -231, and -232 airplanes. This
proposed AD was prompted by reports of forward engine mount attachment
pins that were manufactured from discrepant raw material. This proposed
AD would require identification and replacement of affected forward
engine mount attachment pins. We are proposing this AD to prevent
failure of a forward engine mount attachment pin, possible loss of an
engine in-flight, and consequent reduced controllability of the
airplane.
DATES: We must receive comments on this proposed AD by September 14,
2015.
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 Airbus service information identified in this proposed AD,
contact Airbus, Airworthiness Office--EIAS, 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. For Goodrich Aerostructures service information
identified in this proposed AD, contact UTC Aerospace Systems, ATTN:
Christopher Newth--V2500 A1/A5 Project Engineer, Aftermarket--
Aerostructures; 850 Lagoon Drive, Chula Vista, CA; telephone 619-498-
7505; email christopher.newth@utas.utc.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-2015-
2963; 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: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
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-2015-2963;
Directorate Identifier 2015-NM-016-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
[[Page 45463]]
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 2015-0004, dated January 13, 2015 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A319-131, -132, and -133 airplanes; Model A320-232 and -233 airplanes;
and Model A321-131, -231, and -232 airplanes. The MCAI states:
A number of forward engine mount pins, Part Number (P/N) 740-
2022-501, intended for IAE V2500 series engines, have been reported
as non-compliant with the current certification requirements, due to
a quality issue during manufacturing of the raw material. It was
also determined that a batch of 88 affected pins are installed on
in-service aeroplanes fitted with forward engine mount P/N 745-2010-
503 and the serial numbers (s/n) of the affected pins and the
[manufacturer serial number] MSN of the related aeroplanes have been
identified.
This condition, if not corrected, could lead to forward engine
mount pin failure, possibly resulting in in-flight loss of an engine
and consequent reduced control of the aeroplane.
For the reasons described above, this [EASA] AD requires
identification of the affected forward engine mount pins and removal
from service [replacement] of those pins.
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-2015-
2963.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-71-1064, dated November 5,
2014; and Goodrich Aerostructures has issued Service Bulletin V2500-
NAC-71-0323, dated September 18, 2014. The service information
describes procedures for an inspection to determine the serial number
of the attachment pins for the forward engine mount crossbeam to main
beam for each engine, and replacement of affected pins. 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 of this NPRM.
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.
Explanation of ``RC'' Procedures and Tests in Service Information
The FAA worked in conjunction with industry, under the
Airworthiness Directive Implementation Aviation Rulemaking Committee
(ARC), to enhance the AD system. One enhancement was a new process for
annotating which procedures and tests in the service information are
required for compliance with an AD. Differentiating these procedures
and tests from other tasks in the service information is expected to
improve an owner's/operator's understanding of crucial AD requirements
and help provide consistent judgment in AD compliance. The procedures
and tests identified as RC (required for compliance) in any service
information have a direct effect on detecting, preventing, resolving,
or eliminating an identified unsafe condition.
As specified in a NOTE under the Accomplishment Instructions of the
specified Airbus service information, procedures and tests identified
as RC must be done to comply with the proposed AD. However, procedures
and 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 alternative method
of compliance (AMOC), provided the procedures and tests identified as
RC can be done and the airplane can be put back in a serviceable
condition. Any substitutions or changes to procedures or tests
identified as RC will require approval of an AMOC.
Costs of Compliance
We estimate that this proposed AD affects 922 airplanes of U.S.
registry.
We also estimate that it would take about 2 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $0 per
product. Based on these figures, we estimate the cost of this proposed
AD on U.S. operators to be $156,740, or $170 per product.
In addition, we estimate that any necessary follow-on actions would
take about 4 work-hours and require parts costing $1,724, for a cost of
$2,064 per attachment pin replacement. We have no way of determining
the number of aircraft that might need this action.
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,
[[Page 45464]]
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-2015-2963; Directorate Identifier 2015-NM-
016-AD.
(a) Comments Due Date
We must receive comments by September 14, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category,
all manufacturer serial numbers.
(1) Model A319-131, -132, and -133 airplanes.
(2) Model A320-232 and -233 airplanes.
(3) Model A321-131, -231, and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 71, Power Plant.
(e) Reason
This AD was prompted by reports of forward engine mount
attachment pins that were manufactured from discrepant raw material.
We are issuing this AD to prevent failure of a forward engine mount
attachment pin, possible loss of an engine in-flight, and consequent
reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Identification of Part Numbers for Forward Engine Mount and
Attachment Pins
Except as provided by paragraph (i) of this AD, at the earliest
of the times specified in paragraphs (g)(1) through (g)(4) of this
AD: For each engine, identify the part number of the forward engine
mount, and the part number and serial number of the attachment pin
for that forward engine mount, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-71-1064, dated November
5, 2014; and Goodrich Aerostructures Service Bulletin V2500-NAC-71-
0323, dated September 18, 2014. A review of airplane maintenance
records is acceptable in lieu of this identification if the part
number of the forward engine mount, and the part number and serial
number of the attachment pin for that forward engine mount can be
conclusively determined from that review. If any part number of the
forward engine mount, or part number or serial number of the
attachment pins for the forward engine mount, cannot be identified:
At the earliest of the times specified in paragraphs (g)(1) through
(g)(4) of this AD, contact 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), for identification information.
(1) Within 24 months after the effective date of this AD.
(2) At the next engine removal after the effective date of this
AD.
(3) Within 7,500 flight hours after the effective date of this
AD.
(4) Within 5,000 flight cycles after the effective date of this
AD.
(h) Corrective Actions
If, during any identification required by paragraph (g) of this
AD, a forward engine mount having part number (P/N) 745-2010-503 is
found, and the attachment pin has P/N 740-2022-501 with any serial
number that is included in figure 1 to paragraphs (h) and (j) of
this AD: At the earliest of the times specified in paragraphs (g)(1)
through (g)(4) of this AD, replace the affected attachment pin with
a serviceable part having a part number other than P/N 740-2022-501,
and having a serial number that is not identified in figure 1 to
paragraphs (h) and (j) of this AD, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-71-1064,
dated November 5, 2014; and Goodrich Aerostructures Service Bulletin
V2500-NAC-71-0323, dated September 18, 2014.
Figure 1 to Paragraphs (h) and (j) of This AD--Part Numbers and Serial
Numbers of Affected Forward Engine Mounts and Attachment Pins
------------------------------------------------------------------------
Serial Nos.
-------------------------------------------------------------------------
Forward Engine Mount (P/N 745-2010-
Attachment Pin (P/N 740-2022-501) 503)
------------------------------------------------------------------------
1396SC 13665001
1391SC 13655001
1412SC 13689001
1402SC 13669001
1409SC 13683001
1416SC 13697001
1418SC 13701001
1417SC 13699001
1414SC 13693001
1415SC 13695001
1420SC 13705001
1421SC 13707001
1422SC 13709001
1436SC 13737001
1438SC 13741001
1452SC 13769001
1456SC 13777001
1397SC 13667001
1432SC 13729001
1405SC 13675001
1411SC 13687001
1389SC 13651001
1392SC 13657001
1382SC 13637001
1384SC 13641001
1407SC 13679001
1408SC 13681001
1395SC 13663001
1406SC 13677001
1383SC 13639001
1404SC 13673001
1393SC 13659001
1413SC 13691001
1386SC 13645001
1388SC 13649001
1390SC 13653001
1410SC 13685001
1423SC 13711001
1424SC 13713001
1403SC 13671001
1419SC 13703001
1385SC 13643001
1387SC 13647001
1431SC 13727001
1433SC 13731001
1425SC 13715001
1428SC 13721001
1429SC 13723001
1430SC 13725001
1427SC 13719001
1434SC 13733001
1442SC 13749001
1394SC 13661001
1441SC 13747001
1426SC 13717001
1437SC 13739001
1439SC 13743001
1443SC 13751001
1448SC 13761001
1435SC 13735001
1440SC 13745001
1454SC 13773001
1455SC 13775001
1451SC 13767001
1453SC 13771001
1444SC 13753001
1450SC 13765001
1461SC 13787001
1469SC 13817001
1480SC 13839001
1481SC 13841001
1446SC 13757001
1449SC 13763001
[[Page 45465]]
1467SC 13813001
1445SC 13755001
1462SC 13789001
1464SC 13793001
1466SC 13811001
1470SC 13819001
1459SC 13783001
1463SC 13791001
1475SC 13829001
1458SC 13781001
1477SC 13833001
1474SC 13827001
1478SC 13835001
1479SC 13837001
1472SC 13823001
------------------------------------------------------------------------
(i) Exception to Paragraph (g) of This AD
For airplanes with manufacturer serial numbers identified in
figure 2 to paragraph (i) of this AD: If it can be conclusively
determined that an engine has not been replaced after March 1, 2011
(the date of manufacture of the first airplane with affected engine
mounts), the airplane is not affected by the requirements of
paragraphs (g) and (h) of this AD.
Figure 2 to Paragraph (i) of This AD--Airplane Manufacturer Serial
Numbers
------------------------------------------------------------------------
Airplane manufacturer serial Nos.
-------------------------------------------------------------------------
4593
4602
4620
4637
4638
4642
4643
4644
4660
4677
4690
4696
4700
4701
4703
4706
4707
4710
4716
4719
4725
4726
4731
4736
4737
4741
4746
4751
4752
4753
4754
4755
4757
4761
4762
4772
4773
4774
4775
4779
4782
4783
4784
4786
4788
4790
4791
4798
4804
4813
------------------------------------------------------------------------
(j) Parts Installation Prohibition
As of the effective date of this AD, no person may install on
any airplane any engine mount attachment pin having P/N 740-2022-501
with a serial number identified in figure 1 to paragraphs (h) and
(j) of this AD.
(k) 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: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; 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) 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 Airbus's EASA DOA. If approved by 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 a serviceable
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(l) Special Flight Permits Prohibited
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2015-0004, dated January 13,
2015, 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-2015-2963.
(2) For Airbus service information identified in this AD,
contact Airbus, Airworthiness Office--EIAS, 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. For Goodrich Aerostructures service
information identified in this AD, contact UTC Aerospace Systems,
ATTN: Christopher Newth--V2500 A1/A5 Project Engineer, Aftermarket--
Aerostructures; 850 Lagoon Drive, Chula Vista, CA; telephone 619-
498-7505; email christopher.newth@utas.utc.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 July 17, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-18533 Filed 7-29-15; 8:45 am]
BILLING CODE 4910-13-P
