Airworthiness Directives; Airbus Airplanes, 14689-14693 [2016-05700]
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14689
Rules and Regulations
Federal Register
Vol. 81, No. 53
Friday, March 18, 2016
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2963; Directorate
Identifier 2015–NM–016–AD; Amendment
39–18434; AD 2016–06–03]
Examining the AD Docket
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting 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 AD was
prompted by reports of forward engine
mount attachment pins that were
manufactured from discrepant raw
material. This AD requires identification
and replacement of affected forward
engine mount attachment pins. 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.
DATES: This AD becomes effective April
22, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 22, 2016.
ADDRESSES: For Airbus service
information identified in this final rule,
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.
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SUMMARY:
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For Goodrich Aerostructures service
information identified in this final rule,
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. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
2963.
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 AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is Docket Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
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:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus Model A319–131,
–132, and –133 airplanes; Model A320–
232 and –233 airplanes; and Model
A321–131, –231, and –232 airplanes.
The NPRM published in the Federal
Register on July 30, 2015 (80 FR 45462)
(‘‘the NPRM’’).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
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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.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To Clarify Which Attachment
Pin Part Numbers May Be Installed
United Airlines (UAL) requested that
paragraph (h) of the proposed AD be rewritten to clarify which attachment pin
part numbers can be used as
replacement parts.
We partially agree with the
commenter’s request. We agree to
provide clarification but we do not agree
to revise paragraph (h) of this AD.
Paragraph (h) of this AD states to
replace with a serviceable part having a
part number other than part number
(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 other words, the replacement part
cannot have a combination of P/N 740–
2022–501 and any serial number that is
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included in figure 1 to paragraphs (h)
and (j) of this AD. We have not changed
this AD in this regard.
Request To Clarify Which Airplanes
Are Not Affected by the Requirements
Proposed in the NPRM
JetBlue requested clarification of the
intent of paragraph (i) of the proposed
AD. JetBlue asserted that the way this
paragraph is written it contradicts the
requirements in EASA AD 2015–0004,
dated January 13, 2015, and the intent
of the inspection in paragraph (h) of the
proposed AD.
We agree with the commenter’s
request to clarify the intent of paragraph
(i) of this AD. Airplanes with
manufacturer serial numbers not
identified in figure 2 to paragraph (i) of
this AD that have not had an engine
replaced after March 1, 2011, are not
required to do the actions mandated by
paragraphs (g) and (h) of this AD, which
corresponds to paragraph (2) of the
MCAI AD. In paragraph (i) of the
proposed AD we inadvertently specified
‘‘airplanes with manufacturer serial
numbers identified in figure 2 to
paragraph (i) of this AD.’’ We have
changed paragraph (i) of this AD to
specify ‘‘airplanes with manufacturer
serial numbers not identified in figure 2
to paragraph (i) of this AD.’’
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Request To Extend the Compliance
Time
UAL requested that the compliance
times in paragraph (g) of the proposed
AD be extended. UAL stated that this
would keep costs down and ‘‘make
engine removal the most likely time the
inspection would occur.’’ UAL also
asserted that the safety concern is
overstated based on information in the
Goodrich Aerostructures service
information. The ‘‘Background’’
paragraph of the Goodrich
Aerostructures service information
states that ‘‘a minor metallurgical
discontinuity’’ was found on some
forward engine mount crossbeam to
main beam attach pins (P/N 740–2022–
501). UAL stated that a minor
metallurgical issue should not drive a
significant safety concern.
We do not agree with the commenter’s
request to extend the compliance time.
Even a ‘‘minor metallurgical
discontinuity’’ can result in a safety
concern. Forward engine mount
attachment pins that were manufactured
from discrepant raw material can lead to
the failure of a forward engine mount
attachment pin; this condition could
result in possible loss of an engine inflight and consequent reduced
controllability of the airplane.
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After considering all of the available
information, we have determined that
the compliance time, as proposed,
represents an appropriate interval of
time in which the required actions can
be performed in a timely manner with
the affected fleet, while still maintaining
an adequate level of safety. In
developing an appropriate compliance
time, we considered the safety
implications, parts availability, and
normal maintenance schedules for
timely accomplishment of the
replacement. However, under the
provisions of paragraph (m)(1) of this
AD, we may approve requests for
adjustments to the compliance time if
data are submitted to substantiate that
such an adjustment would provide an
acceptable level of safety. We have not
changed this AD in this regard.
Request To Revise the Estimated Costs
of Compliance
UAL requested that the estimated
costs of compliance in the NPRM be
increased from $156,740 to $313,480.
UAL also requested that the costs for
opening and closing the reversers be
mentioned as costs that cannot be
calculated. Furthermore, UAL stated
that based on the proposed compliance
times in paragraph (g) of the proposed
AD and the size of the UAL fleet, the
proposed requirements would have to
be scheduled independently from its
maintenance schedule.
We agree with the commenter’s
request to increase the estimated costs
for compliance with the requirements of
this AD. We note that these are only
estimated costs and may vary based on
an airplane’s configuration. We also
acknowledge that the costs for opening
and closing the reversers are not known
and are not included in the ‘‘Costs of
Compliance’’ paragraph of this AD.
However, as specified in the service
information, the inspection takes
approximately 4 work-hours, with an
estimated cost of $313,480 for U.S.
operators. We have changed the ‘‘Costs
of Compliance’’ paragraph of this AD
accordingly.
Request To Refer to Current Service
Information
JetBlue Airways (JetBlue) requested
that the NPRM be revised to refer to
Airbus Service Bulletin A320–71–1064,
Revision 01, dated April 1, 2015; and
Goodrich Aerostructures Service
Bulletin V2500–NAC–71–0323,
Revision 01, dated January 28, 2015.
JetBlue noted that the service
information for both Airbus and
Goodrich Aerostructures had been
revised since the NPRM was published.
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We agree with the commenter’s
request and have revised the ‘‘Related
Service Information under 1 CFR part
51’’ section and paragraphs (g) and (h)
of this AD to refer to Airbus Service
Bulletin A320–71–1064, Revision 01,
dated April 1, 2015; and Goodrich
Aerostructures Service Bulletin V2500–
NAC–71–0323, Revision 01, dated
January 28, 2015. We have also added
new paragraph (l) to this AD to give
credit for actions done using Airbus
Service Bulletin A320–71–1064, dated
November 5, 2014; and Goodrich
Aerostructures Service Bulletin V2500–
NAC–71–0323, dated September 18,
2014. We redesignated subsequent
paragraphs accordingly.
Request To Allow Use of Airbus or
Goodrich Aerostructures Service
Information To Accomplish Required
Actions
JetBlue requested that paragraph (g) of
the proposed AD be revised to allow
operators to use either the Airbus
service information or the Goodrich
Aerostructures service information to do
the actions required by that paragraph.
JetBlue stated that if the engine is being
inspected at the shop, the actions in the
Airbus service information would not be
accomplished because the Airbus
service information addresses
inspections of the wing. JetBlue also
stated this revision would correspond
with the requirements in corresponding
EASA AD 2015–0004, dated January 13,
2015.
We do not agree with the commenter’s
request to allow operators to have the
option of doing the actions required by
paragraph (g) of this AD in accordance
with either the Accomplishment
Instructions of the Airbus service
information or the Goodrich
Aerostructures service information. The
Airbus service information includes
steps that are considered ‘‘required for
compliance’’ (RC) and those steps are
not included in the Goodrich
Aerostructures service information. In
addition, Goodrich Aerostructures
Service Bulletin V2500–NAC–71–0323,
Revision 01, dated January 28, 2015,
does not distinguish between ‘‘RC’’ and
non-‘‘RC’’ steps and refers to the Airbus
service bulletin for incorporation of
several steps. Therefore, regardless of
whether the AD requirements are
accomplished ‘‘on wing’’ or ‘‘in shop,’’
operators must use a combination of
Airbus and Goodrich Aerostructures
service information for accomplishing
the AD requirements. We have not
changed this AD regarding this issue.
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Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under
1 CFR Part 51
Airbus has issued Service Bulletin
A320–71–1064, Revision 01, dated April
1, 2015; and Goodrich Aerostructures
has issued Service Bulletin V2500–
NAC–71–0323, Revision 01, dated
January 28, 2015. 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.
Costs of Compliance
We estimate that this AD affects 922
airplanes of U.S. registry.
We also estimate that it will take
about 4 work-hours per product to
comply with the basic requirements of
this AD. The average labor rate is $85
per work-hour. Required parts will cost
about $0 per product. Based on these
figures, we estimate the cost of this AD
on U.S. operators to be $313,480, or
$340 per product.
In addition, we estimate that any
necessary follow-on actions will 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.
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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.
18:10 Mar 17, 2016
Jkt 238001
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
Authority for This Rulemaking
VerDate Sep<11>2014
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.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2016–06–03 Airbus: Amendment 39–18434.
Docket No. FAA–2015–2963; Directorate
Identifier 2015–NM–016–AD.
(a) Effective Date
This AD becomes effective April 22, 2016.
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14691
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes,
certificated in any category, identified in
paragraphs (c)(1), (c)(2), and (c)(3) of this AD,
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, Revision 01, dated April 1, 2015;
and Goodrich Aerostructures Service Bulletin
V2500–NAC–71–0323, Revision 01, dated
January 28, 2015. 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.
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(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, Revision 01, dated April 1, 2015;
and Goodrich Aerostructures Service Bulletin
V2500–NAC–71–0323, Revision 01, dated
January 28, 2015.
FIGURE 1 TO PARAGRAPHS (h) AND (j)
OF THIS AD—PART NUMBERS AND
SERIAL NUMBERS OF AFFECTED
FORWARD ENGINE MOUNTS AND ATTACHMENT PINS—Continued
Attachment Pin
(P/N 740–2022–501)
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
1467SC
1445SC
1462SC
1464SC
1466SC
1470SC
1459SC
1463SC
1475SC
1458SC
1477SC
1474SC
1478SC
1479SC
1472SC
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
13813001
13755001
13789001
13793001
13811001
13819001
13783001
13791001
13829001
13781001
13833001
13827001
13835001
13837001
13823001
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Forward Engine
Mount
(P/N 745–2010–503)
13665001
13655001
13689001
13669001
13683001
13697001
13701001
13699001
13693001
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
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18:10 Mar 17, 2016
Jkt 238001
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
Forward Engine
Mount
(P/N 745–2010–503)
Serial Numbers
1396SC
1391SC
1412SC
1402SC
1409SC
1416SC
1418SC
1417SC
1414SC
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
Airplane Manufacturer Serial Nos.
Serial Numbers
FIGURE 1 TO PARAGRAPHS (h) AND (j)
OF THIS AD—PART NUMBERS AND
SERIAL NUMBERS OF AFFECTED
FORWARD ENGINE MOUNTS AND ATTACHMENT PINS
Attachment Pin
(P/N 740–2022–501)
FIGURE 2 TO PARAGRAPH (i) OF THIS
AD—AIRPLANE MANUFACTURER SERIAL NOS.
(i) Exception to Paragraph (g) of This AD
For airplanes with manufacturer serial
numbers not 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.
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(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) Special Flight Permits
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.
(l) 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
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effective date of this AD using the service
information specified in paragraphs (l)(1) and
(l)(2) of this AD.
(1) Airbus Service Bulletin A320–71–1064,
dated November 5, 2014, which is not
incorporated by reference in this AD.
(2) Goodrich Aerostructures Service
Bulletin V2500–NAC–71–0323, dated
September 18, 2014, which is not
incorporated by reference in this AD.
asabaliauskas on DSK3SPTVN1PROD with RULES
(m) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to 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
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(n) 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) Airbus service information identified in
this AD that is not incorporated by reference
is available at the addresses specified in
paragraphs (o)(3) and (o)(5) of this AD.
VerDate Sep<11>2014
18:10 Mar 17, 2016
Jkt 238001
(3) Goodrich Aerostructures service
information identified in this AD that is not
incorporated by reference is available at the
addresses specified in paragraphs (o)(4) and
(o)(5) of this AD.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320–71–1064,
Revision 01, dated April 1, 2015.
(ii) Goodrich Aerostructures Service
Bulletin V2500–NAC–71–0323, Revision 01,
dated January 28, 2015.
(3) 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.
(4) 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.
(5) 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.
(6) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on March 7,
2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–05700 Filed 3–17–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2961; Directorate
Identifier 2014–NM–145–AD; Amendment
39–18430; AD 2016–05–12]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
14693
We are superseding
Airworthiness Directive (AD) 2012–15–
13, for certain The Boeing Company
Model 747–100B SUD, 747–300, 747–
400, and 747–400D series airplanes; and
Model 747–200B series airplanes having
a stretched upper deck. AD 2012–15–13
required inspections for cracking and
discrepancies of certain fasteners;
modification of the frame-to-tension-tie
joints; repetitive post-modification
inspections; related investigative and
corrective actions if necessary; and
repetitive inspections for cracking in the
tension tie channels, and repair if
necessary. For certain airplanes, AD
2012–15–13 also required an inspection
to determine if the angle is installed
correctly, and re-installation if
necessary; and an inspection at the
fastener locations where the tension tie
previously attached to the frame prior to
certain modifications, and repair if
necessary. This new AD adds a new
inspection for cracking in the tension tie
channels and post-modification
inspections of the modified tension ties
for cracking, and repair if necessary.
This AD was prompted by an evaluation
indicated that the upper deck is subject
to widespread fatigue damage (WFD).
We are issuing this AD to prevent
fatigue cracking of the tension ties,
shear webs, and frames of the upper
deck, which could result in rapid
decompression and reduced structural
integrity of the airplane.
DATES: This AD is effective April 22,
2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 22, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of September 12, 2012 (77 FR
47267, August 8, 2012).
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of November 28, 2007 (72 FR
65655, November 23, 2007).
ADDRESSES: For service information
identified in this final rule, contact
Boeing 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. It is also
available on the Internet at https://
SUMMARY:
E:\FR\FM\18MRR1.SGM
18MRR1
]]>Agencies
[Federal Register Volume 81, Number 53 (Friday, March 18, 2016)]
[Rules and Regulations]
[Pages 14689-14693]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-05700]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules
and Regulations
[[Page 14689]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-2963; Directorate Identifier 2015-NM-016-AD;
Amendment 39-18434; AD 2016-06-03]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A319-131, -132, and -133 airplanes; Model A320-232 and -
233 airplanes; and Model A321-131, -231, and -232 airplanes. This AD
was prompted by reports of forward engine mount attachment pins that
were manufactured from discrepant raw material. This AD requires
identification and replacement of affected forward engine mount
attachment pins. 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.
DATES: This AD becomes effective April 22, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 22,
2016.
ADDRESSES: For Airbus service information identified in this final
rule, 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
final rule, 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. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2963.
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 AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (telephone
800-647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: 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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all Airbus Model A319-131,
-132, and -133 airplanes; Model A320-232 and -233 airplanes; and Model
A321-131, -231, and -232 airplanes. The NPRM published in the Federal
Register on July 30, 2015 (80 FR 45462) (``the NPRM'').
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.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Request To Clarify Which Attachment Pin Part Numbers May Be Installed
United Airlines (UAL) requested that paragraph (h) of the proposed
AD be re-written to clarify which attachment pin part numbers can be
used as replacement parts.
We partially agree with the commenter's request. We agree to
provide clarification but we do not agree to revise paragraph (h) of
this AD. Paragraph (h) of this AD states to replace with a serviceable
part having a part number other than part number (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 other words, the replacement part
cannot have a combination of P/N 740-2022-501 and any serial number
that is
[[Page 14690]]
included in figure 1 to paragraphs (h) and (j) of this AD. We have not
changed this AD in this regard.
Request To Clarify Which Airplanes Are Not Affected by the Requirements
Proposed in the NPRM
JetBlue requested clarification of the intent of paragraph (i) of
the proposed AD. JetBlue asserted that the way this paragraph is
written it contradicts the requirements in EASA AD 2015-0004, dated
January 13, 2015, and the intent of the inspection in paragraph (h) of
the proposed AD.
We agree with the commenter's request to clarify the intent of
paragraph (i) of this AD. Airplanes with manufacturer serial numbers
not identified in figure 2 to paragraph (i) of this AD that have not
had an engine replaced after March 1, 2011, are not required to do the
actions mandated by paragraphs (g) and (h) of this AD, which
corresponds to paragraph (2) of the MCAI AD. In paragraph (i) of the
proposed AD we inadvertently specified ``airplanes with manufacturer
serial numbers identified in figure 2 to paragraph (i) of this AD.'' We
have changed paragraph (i) of this AD to specify ``airplanes with
manufacturer serial numbers not identified in figure 2 to paragraph (i)
of this AD.''
Request To Extend the Compliance Time
UAL requested that the compliance times in paragraph (g) of the
proposed AD be extended. UAL stated that this would keep costs down and
``make engine removal the most likely time the inspection would
occur.'' UAL also asserted that the safety concern is overstated based
on information in the Goodrich Aerostructures service information. The
``Background'' paragraph of the Goodrich Aerostructures service
information states that ``a minor metallurgical discontinuity'' was
found on some forward engine mount crossbeam to main beam attach pins
(P/N 740-2022-501). UAL stated that a minor metallurgical issue should
not drive a significant safety concern.
We do not agree with the commenter's request to extend the
compliance time. Even a ``minor metallurgical discontinuity'' can
result in a safety concern. Forward engine mount attachment pins that
were manufactured from discrepant raw material can lead to the failure
of a forward engine mount attachment pin; this condition could result
in possible loss of an engine in-flight and consequent reduced
controllability of the airplane.
After considering all of the available information, we have
determined that the compliance time, as proposed, represents an
appropriate interval of time in which the required actions can be
performed in a timely manner with the affected fleet, while still
maintaining an adequate level of safety. In developing an appropriate
compliance time, we considered the safety implications, parts
availability, and normal maintenance schedules for timely
accomplishment of the replacement. However, under the provisions of
paragraph (m)(1) of this AD, we may approve requests for adjustments to
the compliance time if data are submitted to substantiate that such an
adjustment would provide an acceptable level of safety. We have not
changed this AD in this regard.
Request To Revise the Estimated Costs of Compliance
UAL requested that the estimated costs of compliance in the NPRM be
increased from $156,740 to $313,480. UAL also requested that the costs
for opening and closing the reversers be mentioned as costs that cannot
be calculated. Furthermore, UAL stated that based on the proposed
compliance times in paragraph (g) of the proposed AD and the size of
the UAL fleet, the proposed requirements would have to be scheduled
independently from its maintenance schedule.
We agree with the commenter's request to increase the estimated
costs for compliance with the requirements of this AD. We note that
these are only estimated costs and may vary based on an airplane's
configuration. We also acknowledge that the costs for opening and
closing the reversers are not known and are not included in the ``Costs
of Compliance'' paragraph of this AD. However, as specified in the
service information, the inspection takes approximately 4 work-hours,
with an estimated cost of $313,480 for U.S. operators. We have changed
the ``Costs of Compliance'' paragraph of this AD accordingly.
Request To Refer to Current Service Information
JetBlue Airways (JetBlue) requested that the NPRM be revised to
refer to Airbus Service Bulletin A320-71-1064, Revision 01, dated April
1, 2015; and Goodrich Aerostructures Service Bulletin V2500-NAC-71-
0323, Revision 01, dated January 28, 2015. JetBlue noted that the
service information for both Airbus and Goodrich Aerostructures had
been revised since the NPRM was published.
We agree with the commenter's request and have revised the
``Related Service Information under 1 CFR part 51'' section and
paragraphs (g) and (h) of this AD to refer to Airbus Service Bulletin
A320-71-1064, Revision 01, dated April 1, 2015; and Goodrich
Aerostructures Service Bulletin V2500-NAC-71-0323, Revision 01, dated
January 28, 2015. We have also added new paragraph (l) to this AD to
give credit for actions done using Airbus Service Bulletin A320-71-
1064, dated November 5, 2014; and Goodrich Aerostructures Service
Bulletin V2500-NAC-71-0323, dated September 18, 2014. We redesignated
subsequent paragraphs accordingly.
Request To Allow Use of Airbus or Goodrich Aerostructures Service
Information To Accomplish Required Actions
JetBlue requested that paragraph (g) of the proposed AD be revised
to allow operators to use either the Airbus service information or the
Goodrich Aerostructures service information to do the actions required
by that paragraph. JetBlue stated that if the engine is being inspected
at the shop, the actions in the Airbus service information would not be
accomplished because the Airbus service information addresses
inspections of the wing. JetBlue also stated this revision would
correspond with the requirements in corresponding EASA AD 2015-0004,
dated January 13, 2015.
We do not agree with the commenter's request to allow operators to
have the option of doing the actions required by paragraph (g) of this
AD in accordance with either the Accomplishment Instructions of the
Airbus service information or the Goodrich Aerostructures service
information. The Airbus service information includes steps that are
considered ``required for compliance'' (RC) and those steps are not
included in the Goodrich Aerostructures service information. In
addition, Goodrich Aerostructures Service Bulletin V2500-NAC-71-0323,
Revision 01, dated January 28, 2015, does not distinguish between
``RC'' and non-``RC'' steps and refers to the Airbus service bulletin
for incorporation of several steps. Therefore, regardless of whether
the AD requirements are accomplished ``on wing'' or ``in shop,''
operators must use a combination of Airbus and Goodrich Aerostructures
service information for accomplishing the AD requirements. We have not
changed this AD regarding this issue.
[[Page 14691]]
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-71-1064, Revision 01, dated
April 1, 2015; and Goodrich Aerostructures has issued Service Bulletin
V2500-NAC-71-0323, Revision 01, dated January 28, 2015. 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.
Costs of Compliance
We estimate that this AD affects 922 airplanes of U.S. registry.
We also estimate that it will take about 4 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts will cost about $0 per
product. Based on these figures, we estimate the cost of this AD on
U.S. operators to be $313,480, or $340 per product.
In addition, we estimate that any necessary follow-on actions will
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 AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2016-06-03 Airbus: Amendment 39-18434. Docket No. FAA-2015-2963;
Directorate Identifier 2015-NM-016-AD.
(a) Effective Date
This AD becomes effective April 22, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of
this AD, 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, Revision 01,
dated April 1, 2015; and Goodrich Aerostructures Service Bulletin
V2500-NAC-71-0323, Revision 01, dated January 28, 2015. 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.
[[Page 14692]]
(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,
Revision 01, dated April 1, 2015; and Goodrich Aerostructures
Service Bulletin V2500-NAC-71-0323, Revision 01, dated January 28,
2015.
Figure 1 to Paragraphs (h) and (j) of This AD--Part Numbers and Serial
Numbers of Affected Forward Engine Mounts and Attachment Pins
------------------------------------------------------------------------
Serial Numbers
-------------------------------------------------------------------------
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
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------------------------------------------------------------------------
(i) Exception to Paragraph (g) of This AD
For airplanes with manufacturer serial numbers not 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 Nos.
------------------------------------------------------------------------
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) Special Flight Permits
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.
(l) 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
[[Page 14693]]
effective date of this AD using the service information specified in
paragraphs (l)(1) and (l)(2) of this AD.
(1) Airbus Service Bulletin A320-71-1064, dated November 5,
2014, which is not incorporated by reference in this AD.
(2) Goodrich Aerostructures Service Bulletin V2500-NAC-71-0323,
dated September 18, 2014, which is not incorporated by reference in
this AD.
(m) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to 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 an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(n) 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) Airbus service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (o)(3) and (o)(5) of this AD.
(3) Goodrich Aerostructures service information identified in
this AD that is not incorporated by reference is available at the
addresses specified in paragraphs (o)(4) and (o)(5) of this AD.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320-71-1064, Revision 01, dated
April 1, 2015.
(ii) Goodrich Aerostructures Service Bulletin V2500-NAC-71-0323,
Revision 01, dated January 28, 2015.
(3) 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.
(4) 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.
(5) 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.
(6) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on March 7, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-05700 Filed 3-17-16; 8:45 am]
BILLING CODE 4910-13-P
