Airworthiness Directives; Airbus Airplanes, 85837-85840 [2016-28335]
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85837
Rules and Regulations
Federal Register
Vol. 81, No. 229
Tuesday, November 29, 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–2016–5596; Directorate
Identifier 2015–NM–121–AD; Amendment
39–18677; AD 2016–20–11]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2014–12–
06 for certain Airbus Model A300 B4–
600, B4–600R, and F4–600R series
airplanes, and Model A300 C4–605R
Variant F airplanes (collectively called
Model A300–600 series airplanes); and
Airbus Model A310 series airplanes. AD
2014–12–06 required repetitive
ultrasonic or detailed inspections of the
external area of the aft cargo door sill
beam for cracking, and repair if
necessary, and provided an optional
one-time high frequency eddy current
(HFEC) inspection that would terminate
the repetitive inspections. This new AD
requires the previously optional
terminating HFEC inspection, and
requires that it be done repetitively.
This AD was prompted by findings of
multiple fatigue cracks in the aft cargo
door that indicated the need for
additional, repetitive, HFEC
inspections. We are issuing this AD to
address the unsafe condition on these
products.
jstallworth on DSK7TPTVN1PROD with RULES
SUMMARY:
This AD is effective January 3,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 3, 2017.
DATES:
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The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of July 2, 2014 (79 FR 34403,
June 17, 2014).
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAW, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone
+33 5 61 93 36 96; fax +33 5 61 93 44
51; email account.airworth-eas@
airbus.com; Internet http://
www.airbus.com. You may view this
referenced service information at the
FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA.
For information on the availability of
this material at the FAA, call 425–227–
1221. It is also available on the Internet
at http://www.regulations.gov by
searching for and locating Docket No.
FAA–2016–5596.
Examining the AD Docket
You may examine the AD docket on
the Internet at http://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
5596, 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 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: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–2125;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2014–12–06,
Amendment 39–17867 (79 FR 34403,
June 17, 2014) (‘‘AD 2014–12–06’’). AD
2014–12–06 applied to certain Airbus
Model A300 B4–600, B4–600R, and F4–
600R series airplanes, and Model A300
C4–605R Variant F airplanes
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(collectively called Model A300–600
series airplanes); and Airbus Model
A310 series airplanes. AD 2014–12–06
required repetitive ultrasonic or detailed
inspections of the external area of the aft
cargo door sill beam for cracking, and
repair if necessary. AD 2014–12–16 also
provided an optional one-time HFEC
inspection that would terminate the
repetitive inspections. The NPRM
published in the Federal Register on
April 27, 2016 (81 FR 24745). The
NPRM was prompted by findings of
multiple fatigue cracks in the aft cargo
door that indicated the need for
repetitive HFEC inspections. The NPRM
proposed to continue to require
repetitive ultrasonic or detailed
inspections of the external area of the aft
cargo door sill beam for cracking, and
repair if necessary. The NPRM also
proposed to require the previously
optional terminating HFEC inspection,
and to require that it be done
repetitively. We are issuing this AD to
detect and correct fatigue cracking of the
cargo door sill beam, lock fitting, and
torsion box plate. Failure of one or more
of these components could result in the
loss of the door locking function and,
subsequently, complete loss of the cargo
door in flight with the risk of rapid
decompression.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2015–0150, dated July 23,
2015 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A300 B4–600, B4–600R, and F4–
600R series airplanes, and Model A300
C4–605R Variant F airplanes
(collectively called Model A300–600
series airplanes); and Airbus Model
A310 series airplanes. The MCAI states:
During accomplishment of Maintenance
Review Board Report (MRBR) task 531625–
01–1 on an A300–600 aeroplane having
accumulated more than 25,000 flight cycles
(FC) since aeroplane first flight, multiple
fatigue cracks were found on the following
parts:
—Aft cargo door sill beam Part Number
(P/N) A53973085210.
—Lock fitting P/N A53978239002.
—Torsion box plate P/N A53973318206.
Prompted by these findings, a stress
analysis was performed during which it was
discovered that there is no dedicated
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Federal Register / Vol. 81, No. 229 / Tuesday, November 29, 2016 / Rules and Regulations
scheduled maintenance task to inspect the
affected area for fatigue damage.
This condition, if not detected and
corrected, could lead to failure of multiple
lock fittings, possibly resulting in loss of the
cargo door in flight and consequent explosive
decompression of the aeroplane.
To address this unsafe condition, Airbus
issued Alert Operators Transmission (AOT)
A53W005–14 providing instructions for
inspection of the affected area.
Consequently, EASA issued Emergency AD
2014–0097–E [which corresponded to FAA
AD 2014–12–06] to require repetitive
ultrasonic (US) inspections or detailed
inspections (DET) of the aft cargo door sill
beam external area, and/or a one-time High
Frequency Eddy Current (HFEC) inspection
of the aft cargo door sill beam internal
structure and, depending on findings,
accomplishment of corrective action(s).
Since that [EASA] AD was issued, the
results of further analysis have indicated that
repetitive HFEC inspections need to be
introduced.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2014–0097–E, which is superseded, and
requires repetitive HFEC inspections of the
concerned areas. The first HFEC inspection
terminates the repetitive US/DET
inspections.
You may examine the MCAI in the
AD docket on the Internet at http://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
5596.
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.
Support for the NPRM
The Air Line Pilots Association,
International stated that it supports the
NPRM.
Request To Rewrite Reporting
Requirements
One commenter, Mark Hilborn,
requested that we revise the structure of
paragraph (i) of the proposed AD for
clarity and to change the location where
the reports should be sent. He stated
that we could rewrite paragraph (i) of
the proposed AD to remove the
subparagraphs.
We partially agree with the request.
We have updated the contact
information for submitting the reports.
We do not find it necessary, however, to
change the remainder of the paragraph
since it is restated from AD 2014–12–06,
and the compliance times are correct.
Request To Clarify the Terminating
Actions
Mark Hilborn requested we revise
paragraph (m) of the proposed AD for
clarity and to add new subparagraphs to
aid in that.
We agree with the request and have
changed paragraph (m) of this AD
accordingly.
Additional Changes Made in This Final
Rule
We have revised this AD to require
the current version of the service
information identified for the
terminating action specified in this AD.
This service information was revised to
make a small tooling change; no
additional work is necessary for
airplanes on which the original version
of this service information was
accomplished. We have also added
credit for airplanes on which the
original version of this service
information was accomplished, and
made related changes accordingly.
Conclusion
We reviewed the available data,
including 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 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.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information, which describes
procedures for repetitive HFEC
inspections of the cargo door sill beam,
lock fitting, and torsion box plate. These
service bulletins are distinct since they
apply to different airplane models.
• Airbus Service Bulletin A300–53–
6179, dated December 12, 2014.
• Airbus Service Bulletin A310–53–
2139, dated December 12, 2014.
Airbus has also issued AOT
A53W005–14, Revision 01, dated April
29, 2014, which describes procedures
for doing an ultrasonic inspection or
detailed inspection of the aft cargo door
sill beam external area for cracking.
Additionally, Airbus has issued the
following service information, which
describes procedures for reinforcing the
aft cargo door sill beam are between FR
60 and FR 63. These service bulletins
are distinct since they apply to different
airplane models.
• Airbus Service Bulletin A310–53–
2141, Revision 01, dated July 2, 2015.
• Airbus Service Bulletin A300–53–
6181, Revision 01, dated July 2, 2015.
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 75
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per product
Inspection .......................
12 work-hours × $85 per hour = $1,020 per inspection cycle.
1 work-hour × $85 per hour = $85 per inspection
cycle.
N/A ............
$1,020 per inspection
cycle.
$85 ................................
jstallworth on DSK7TPTVN1PROD with RULES
Reporting .......................
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
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N/A ............
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
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Cost on U.S. operators
$76,500 per inspection
cycle.
$6,375.
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is mandatory. Comments
concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to the FAA at 800
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Independence Ave. SW., Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this 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.
jstallworth on DSK7TPTVN1PROD with RULES
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:
■
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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing AD 2014–12–06, Amendment
39–17867 (79 FR 34403, June 17, 2014),
and adding the following new AD:
■
2016–20–11 Airbus: Amendment 39–18677;
Docket No. FAA–2016–5596; Directorate
Identifier 2015–NM–121–AD.
(a) Effective Date
This AD is effective January 3, 2017.
(b) Affected ADs
This AD replaces AD 2014–12–06,
Amendment 39–17867 (79 FR 34403, June
17, 2014) (‘‘AD 2014–12–06’’).
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1), (c)(2), (c)(3), (c)(4), and
(c)(5) of this AD, certificated in any category,
all manufacturer serial numbers on which
Airbus Modification 05438 has been
embodied in production, except those on
which Airbus Modification 12046 has been
embodied in production.
(1) Airbus Model A300 B4–601, B4–603,
B4–620, and B4–622 airplanes.
(2) Airbus Model A300 B4–605R and B4–
622R airplanes.
(3) Airbus Model A300 F4–605R and F4–
622R airplanes.
(4) Airbus Model A300 C4–605R Variant F
airplanes.
(5) Airbus Model A310–203, –204, –221,
–222, –304, –322, –324, and –325 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of
fatigue cracks on the cargo door sill beam,
lock fitting, and torsion box plate. We are
issuing this AD to detect and correct fatigue
cracking of the cargo door sill beam, lock
fitting, and torsion box plate, which could
result in the loss of the door locking function
and subsequently, complete loss of the cargo
door in flight with the risk of rapid
decompression.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspection, With Revised
Service Information
This paragraph restates the requirements of
paragraph (g)(1) of AD 2014–12–06, with
revised service information. Within the
compliance time identified in paragraph
(g)(1), (g)(2), or (g)(3) of this AD, as
applicable: Do an ultrasonic inspection or
detailed inspection of the aft cargo door sill
beam external area for cracking, in
accordance with Airbus Alert Operators
Transmission (AOT) A53W005–14, dated
April 22, 2014; or Airbus AOT A53W005–14,
Revision 01, dated April 29, 2014. Repeat the
inspection thereafter at intervals not to
exceed 275 flight cycles. As of the effective
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85839
date of this AD, only Airbus AOT A53W005–
14, Revision 01, dated April 29, 2014, may
be used to comply with the requirements of
this paragraph.
(1) For airplanes that have accumulated
30,000 flight cycles or more since the
airplane’s first flight as of July 2, 2014 (the
effective date of AD 2014–12–06): Within 50
flight cycles after July 2, 2014.
(2) For airplanes that have accumulated
18,000 flight cycles or more, but fewer than
30,000 flight cycles since the airplane’s first
flight as of July 2, 2014 (the effective date of
AD 2014–12–06): Within 275 flight cycles
after July 2, 2014.
(3) For airplanes that have accumulated
fewer than 18,000 flight cycles since the
airplane’s first flight as of July 2, 2014 (the
effective date of AD 2014–12–06): Before
exceeding 18,275 flight cycles since the
airplane’s first flight.
(h) Retained Optional Terminating Action,
With Revised Service Information and
Specific Delegation Approval Language
This paragraph restates the provisions of
paragraph (h) of AD 2014–12–06, with
revised service information and specific
delegation approval language.
Accomplishment of a high frequency eddy
current (HFEC) inspection for cracking, in
accordance with Airbus AOT A53W005–14,
dated April 22, 2014; or Airbus AOT
A53W005–14, Revision 01, dated April 29,
2014; terminates the repetitive inspections
required by paragraph (g) of this AD for that
airplane. If any cracking is found during the
HFEC inspection, before further flight, repair
using a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
(i) Retained Reporting Requirement, With
Revised Contact Information
This paragraph restates the provisions of
paragraph (i) of AD 2014–12–06, with revised
contact information. Submit a report of the
findings (both positive and negative) of the
inspection required by paragraph (g) of this
AD to ‘‘Airbus Service Bulletin Reporting
Online Application’’ on Airbus World
(https://w3.airbus.com/), at the applicable
time specified in paragraph (i)(1) or (i)(2) of
this AD. The report must include the
inspection results, including no findings.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
(j) Definition of Airplane Groups
Paragraphs (k)(1), (k)(2), and (k)(3) of this
AD refer to airplane groups, as identified in
paragraphs (j)(1), (j)(2), and (j)(3) of this AD.
(1) Airplanes on which an HFEC
inspection was accomplished as specified in
Airbus AOT A53W005–14.
(2) Airplanes on which no HFEC
inspection was accomplished as specified in
Airbus AOT A53W005–14, and that have
accumulated more than 18,000 total flight
cycles as of the effective date of this AD.
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(3) Airplanes on which no HFEC
inspection was accomplished as specified in
Airbus AOT A53W005–14, that have
accumulated 18,000 total flight cycles or
fewer as of the effective date of this AD.
(k) New Repetitive HFEC Inspections and
Repair
At the applicable time specified in
paragraph (k)(1), (k)(2), or (k)(3) of this AD:
Do an HFEC inspection for fatigue cracking
of the cargo door sill beam, lock fitting, and
torsion box plate, in accordance with Airbus
Service Bulletin A300–53–6179, dated
December 12, 2014; or Airbus Service
Bulletin A310–53–2139, dated December 12,
2014; as applicable. Repeat the HFEC
inspection thereafter at intervals not to
exceed 4,600 flight cycles.
(1) For airplanes identified in paragraph
(j)(1) of this AD: Inspect within 4,600 flight
cycles after the most recent HFEC inspection
specified in Airbus AOT A53W005–14.
(2) For airplanes identified in paragraph
(j)(2) of this AD: Inspect within 2,000 flight
cycles after the effective date of this AD.
(3) For airplanes identified in paragraph
(j)(3) of this AD: Inspect before exceeding
13,000 total flight cycles since the airplane’s
first flight, or within 2,000 flight cycles after
the effective date of this AD, whichever
occurs later.
(l) Corrective Action
If any crack is found during any inspection
required by paragraph (g) or (k) of this AD:
Before further flight, repair using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or the EASA; or Airbus’s
EASA DOA.
jstallworth on DSK7TPTVN1PROD with RULES
(m) Terminating Action for Repetitive
Inspections
This paragraph identifies the requirements
to terminate repetitive inspections mandated
by this AD.
(1) For any airplane identified in
paragraphs (j)(2) and (j)(3) of this AD,
accomplishment of the initial inspection
required by paragraph (k) of this AD
terminates the repetitive inspections required
by paragraph (g) of this AD.
(2) For any airplane identified in
paragraphs (c)(1) through (c)(5) of this AD,
accomplishment of Airbus Service Bulletin
A310–53–2141, Revision 01, dated July 2,
2015; or Airbus Service Bulletin A300–53–
6181, Revision 01, dated July 2, 2015; as
applicable; terminates the repetitive
inspections required by paragraph (k) of this
AD.
(n) Credit for Previous Actions
This paragraph provides credit for actions
provided in paragraph (m)(2) of this AD, if
those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A300–53–6181, dated June 26, 2015;
or Airbus Service Bulletin A310–53–2141,
dated June 26, 2015; as applicable.
(o) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
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Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–2125; fax 425–227–1149.
Information may be emailed to: 9-ANM-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: As of the
effective date of this AD, 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) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(4) Required for Compliance (RC): Except
as required by paragraph (l) of this AD: 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.
(p) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
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Airworthiness Directive 2015–0150, dated
July 23, 2015, for related information. This
MCAI may be found in the AD docket on the
Internet at http://www.regulations.gov by
searching for and locating Docket No. FAA–
2016–5596.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (q)(5) and (q)(6) of this AD.
(q) 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.
(3) The following service information was
approved for IBR on January 3, 2017.
(i) Airbus Alert Operators Transmission
(AOT) A53W005–14, Revision 01, dated
April 29, 2014.
(ii) Airbus Service Bulletin A310–53–2141,
Revision 01, dated July 2, 2015.
(iii) Airbus Service Bulletin A300–53–
6179, dated December 12, 2014.
(iv) Airbus Service Bulletin A300–53–
6181, Revision 01, dated July 2, 2015.
(v) Airbus Service Bulletin A310–53–2139,
dated December 12, 2014.
(4) The following service information was
approved for IBR on July 2, 2014 (79 FR
34403, June 17, 2014).
(i) Airbus AOT A53W005–14, dated April
22, 2014.
(ii) Reserved.
(5) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet http://www.airbus.com.
You may view this service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(6) 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.
(7) 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: http://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
September 28, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–28335 Filed 11–28–16; 8:45 am]
BILLING CODE 4910–13–P
E:\FR\FM\29NOR1.SGM
29NOR1
Agencies
[Federal Register Volume 81, Number 229 (Tuesday, November 29, 2016)]
[Rules and Regulations]
[Pages 85837-85840]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-28335]
========================================================================
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. 229 / Tuesday, November 29, 2016 /
Rules and Regulations
[[Page 85837]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-5596; Directorate Identifier 2015-NM-121-AD;
Amendment 39-18677; AD 2016-20-11]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2014-12-06 for
certain Airbus Model A300 B4-600, B4-600R, and F4-600R series
airplanes, and Model A300 C4-605R Variant F airplanes (collectively
called Model A300-600 series airplanes); and Airbus Model A310 series
airplanes. AD 2014-12-06 required repetitive ultrasonic or detailed
inspections of the external area of the aft cargo door sill beam for
cracking, and repair if necessary, and provided an optional one-time
high frequency eddy current (HFEC) inspection that would terminate the
repetitive inspections. This new AD requires the previously optional
terminating HFEC inspection, and requires that it be done repetitively.
This AD was prompted by findings of multiple fatigue cracks in the aft
cargo door that indicated the need for additional, repetitive, HFEC
inspections. We are issuing this AD to address the unsafe condition on
these products.
DATES: This AD is effective January 3, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 3,
2017.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of July
2, 2014 (79 FR 34403, June 17, 2014).
ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet
http://www.airbus.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5596.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5596, 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 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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2014-12-06, Amendment 39-17867 (79 FR 34403,
June 17, 2014) (``AD 2014-12-06''). AD 2014-12-06 applied to certain
Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and
Model A300 C4-605R Variant F airplanes (collectively called Model A300-
600 series airplanes); and Airbus Model A310 series airplanes. AD 2014-
12-06 required repetitive ultrasonic or detailed inspections of the
external area of the aft cargo door sill beam for cracking, and repair
if necessary. AD 2014-12-16 also provided an optional one-time HFEC
inspection that would terminate the repetitive inspections. The NPRM
published in the Federal Register on April 27, 2016 (81 FR 24745). The
NPRM was prompted by findings of multiple fatigue cracks in the aft
cargo door that indicated the need for repetitive HFEC inspections. The
NPRM proposed to continue to require repetitive ultrasonic or detailed
inspections of the external area of the aft cargo door sill beam for
cracking, and repair if necessary. The NPRM also proposed to require
the previously optional terminating HFEC inspection, and to require
that it be done repetitively. We are issuing this AD to detect and
correct fatigue cracking of the cargo door sill beam, lock fitting, and
torsion box plate. Failure of one or more of these components could
result in the loss of the door locking function and, subsequently,
complete loss of the cargo door in flight with the risk of rapid
decompression.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2015-0150, dated July 23, 2015 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-
605R Variant F airplanes (collectively called Model A300-600 series
airplanes); and Airbus Model A310 series airplanes. The MCAI states:
During accomplishment of Maintenance Review Board Report (MRBR)
task 531625-01-1 on an A300-600 aeroplane having accumulated more
than 25,000 flight cycles (FC) since aeroplane first flight,
multiple fatigue cracks were found on the following parts:
--Aft cargo door sill beam Part Number (P/N) A53973085210.
--Lock fitting P/N A53978239002.
--Torsion box plate P/N A53973318206.
Prompted by these findings, a stress analysis was performed
during which it was discovered that there is no dedicated
[[Page 85838]]
scheduled maintenance task to inspect the affected area for fatigue
damage.
This condition, if not detected and corrected, could lead to
failure of multiple lock fittings, possibly resulting in loss of the
cargo door in flight and consequent explosive decompression of the
aeroplane.
To address this unsafe condition, Airbus issued Alert Operators
Transmission (AOT) A53W005-14 providing instructions for inspection
of the affected area.
Consequently, EASA issued Emergency AD 2014-0097-E [which
corresponded to FAA AD 2014-12-06] to require repetitive ultrasonic
(US) inspections or detailed inspections (DET) of the aft cargo door
sill beam external area, and/or a one-time High Frequency Eddy
Current (HFEC) inspection of the aft cargo door sill beam internal
structure and, depending on findings, accomplishment of corrective
action(s).
Since that [EASA] AD was issued, the results of further analysis
have indicated that repetitive HFEC inspections need to be
introduced.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2014-0097-E, which is superseded, and
requires repetitive HFEC inspections of the concerned areas. The
first HFEC inspection terminates the repetitive US/DET inspections.
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5596.
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.
Support for the NPRM
The Air Line Pilots Association, International stated that it
supports the NPRM.
Request To Rewrite Reporting Requirements
One commenter, Mark Hilborn, requested that we revise the structure
of paragraph (i) of the proposed AD for clarity and to change the
location where the reports should be sent. He stated that we could
rewrite paragraph (i) of the proposed AD to remove the subparagraphs.
We partially agree with the request. We have updated the contact
information for submitting the reports. We do not find it necessary,
however, to change the remainder of the paragraph since it is restated
from AD 2014-12-06, and the compliance times are correct.
Request To Clarify the Terminating Actions
Mark Hilborn requested we revise paragraph (m) of the proposed AD
for clarity and to add new subparagraphs to aid in that.
We agree with the request and have changed paragraph (m) of this AD
accordingly.
Additional Changes Made in This Final Rule
We have revised this AD to require the current version of the
service information identified for the terminating action specified in
this AD. This service information was revised to make a small tooling
change; no additional work is necessary for airplanes on which the
original version of this service information was accomplished. We have
also added credit for airplanes on which the original version of this
service information was accomplished, and made related changes
accordingly.
Conclusion
We reviewed the available data, including 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 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.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information, which
describes procedures for repetitive HFEC inspections of the cargo door
sill beam, lock fitting, and torsion box plate. These service bulletins
are distinct since they apply to different airplane models.
Airbus Service Bulletin A300-53-6179, dated December 12,
2014.
Airbus Service Bulletin A310-53-2139, dated December 12,
2014.
Airbus has also issued AOT A53W005-14, Revision 01, dated April 29,
2014, which describes procedures for doing an ultrasonic inspection or
detailed inspection of the aft cargo door sill beam external area for
cracking.
Additionally, Airbus has issued the following service information,
which describes procedures for reinforcing the aft cargo door sill beam
are between FR 60 and FR 63. These service bulletins are distinct since
they apply to different airplane models.
Airbus Service Bulletin A310-53-2141, Revision 01, dated
July 2, 2015.
Airbus Service Bulletin A300-53-6181, Revision 01, dated
July 2, 2015.
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 75 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection..................... 12 work-hours x $85 N/A.............. $1,020 per $76,500 per
per hour = $1,020 per inspection cycle. inspection
inspection cycle. cycle.
Reporting...................... 1 work-hour x $85 per N/A.............. $85.............. $6,375.
hour = $85 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800
[[Page 85839]]
Independence Ave. SW., Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this 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 removing AD 2014-12-06, Amendment 39-
17867 (79 FR 34403, June 17, 2014), and adding the following new AD:
2016-20-11 Airbus: Amendment 39-18677; Docket No. FAA-2016-5596;
Directorate Identifier 2015-NM-121-AD.
(a) Effective Date
This AD is effective January 3, 2017.
(b) Affected ADs
This AD replaces AD 2014-12-06, Amendment 39-17867 (79 FR 34403,
June 17, 2014) (``AD 2014-12-06'').
(c) Applicability
This AD applies to the airplanes identified in paragraphs
(c)(1), (c)(2), (c)(3), (c)(4), and (c)(5) of this AD, certificated
in any category, all manufacturer serial numbers on which Airbus
Modification 05438 has been embodied in production, except those on
which Airbus Modification 12046 has been embodied in production.
(1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622
airplanes.
(2) Airbus Model A300 B4-605R and B4-622R airplanes.
(3) Airbus Model A300 F4-605R and F4-622R airplanes.
(4) Airbus Model A300 C4-605R Variant F airplanes.
(5) Airbus Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of fatigue cracks on the cargo
door sill beam, lock fitting, and torsion box plate. We are issuing
this AD to detect and correct fatigue cracking of the cargo door
sill beam, lock fitting, and torsion box plate, which could result
in the loss of the door locking function and subsequently, complete
loss of the cargo door in flight with the risk of rapid
decompression.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection, With Revised Service Information
This paragraph restates the requirements of paragraph (g)(1) of
AD 2014-12-06, with revised service information. Within the
compliance time identified in paragraph (g)(1), (g)(2), or (g)(3) of
this AD, as applicable: Do an ultrasonic inspection or detailed
inspection of the aft cargo door sill beam external area for
cracking, in accordance with Airbus Alert Operators Transmission
(AOT) A53W005-14, dated April 22, 2014; or Airbus AOT A53W005-14,
Revision 01, dated April 29, 2014. Repeat the inspection thereafter
at intervals not to exceed 275 flight cycles. As of the effective
date of this AD, only Airbus AOT A53W005-14, Revision 01, dated
April 29, 2014, may be used to comply with the requirements of this
paragraph.
(1) For airplanes that have accumulated 30,000 flight cycles or
more since the airplane's first flight as of July 2, 2014 (the
effective date of AD 2014-12-06): Within 50 flight cycles after July
2, 2014.
(2) For airplanes that have accumulated 18,000 flight cycles or
more, but fewer than 30,000 flight cycles since the airplane's first
flight as of July 2, 2014 (the effective date of AD 2014-12-06):
Within 275 flight cycles after July 2, 2014.
(3) For airplanes that have accumulated fewer than 18,000 flight
cycles since the airplane's first flight as of July 2, 2014 (the
effective date of AD 2014-12-06): Before exceeding 18,275 flight
cycles since the airplane's first flight.
(h) Retained Optional Terminating Action, With Revised Service
Information and Specific Delegation Approval Language
This paragraph restates the provisions of paragraph (h) of AD
2014-12-06, with revised service information and specific delegation
approval language. Accomplishment of a high frequency eddy current
(HFEC) inspection for cracking, in accordance with Airbus AOT
A53W005-14, dated April 22, 2014; or Airbus AOT A53W005-14, Revision
01, dated April 29, 2014; terminates the repetitive inspections
required by paragraph (g) of this AD for that airplane. If any
cracking is found during the HFEC inspection, before further flight,
repair using a method approved by the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA); or Airbus's EASA Design Organization
Approval (DOA).
(i) Retained Reporting Requirement, With Revised Contact Information
This paragraph restates the provisions of paragraph (i) of AD
2014-12-06, with revised contact information. Submit a report of the
findings (both positive and negative) of the inspection required by
paragraph (g) of this AD to ``Airbus Service Bulletin Reporting
Online Application'' on Airbus World (https://w3.airbus.com/), at
the applicable time specified in paragraph (i)(1) or (i)(2) of this
AD. The report must include the inspection results, including no
findings.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
(j) Definition of Airplane Groups
Paragraphs (k)(1), (k)(2), and (k)(3) of this AD refer to
airplane groups, as identified in paragraphs (j)(1), (j)(2), and
(j)(3) of this AD.
(1) Airplanes on which an HFEC inspection was accomplished as
specified in Airbus AOT A53W005-14.
(2) Airplanes on which no HFEC inspection was accomplished as
specified in Airbus AOT A53W005-14, and that have accumulated more
than 18,000 total flight cycles as of the effective date of this AD.
[[Page 85840]]
(3) Airplanes on which no HFEC inspection was accomplished as
specified in Airbus AOT A53W005-14, that have accumulated 18,000
total flight cycles or fewer as of the effective date of this AD.
(k) New Repetitive HFEC Inspections and Repair
At the applicable time specified in paragraph (k)(1), (k)(2), or
(k)(3) of this AD: Do an HFEC inspection for fatigue cracking of the
cargo door sill beam, lock fitting, and torsion box plate, in
accordance with Airbus Service Bulletin A300-53-6179, dated December
12, 2014; or Airbus Service Bulletin A310-53-2139, dated December
12, 2014; as applicable. Repeat the HFEC inspection thereafter at
intervals not to exceed 4,600 flight cycles.
(1) For airplanes identified in paragraph (j)(1) of this AD:
Inspect within 4,600 flight cycles after the most recent HFEC
inspection specified in Airbus AOT A53W005-14.
(2) For airplanes identified in paragraph (j)(2) of this AD:
Inspect within 2,000 flight cycles after the effective date of this
AD.
(3) For airplanes identified in paragraph (j)(3) of this AD:
Inspect before exceeding 13,000 total flight cycles since the
airplane's first flight, or within 2,000 flight cycles after the
effective date of this AD, whichever occurs later.
(l) Corrective Action
If any crack is found during any inspection required by
paragraph (g) or (k) of this AD: Before further flight, repair using
a method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA
DOA.
(m) Terminating Action for Repetitive Inspections
This paragraph identifies the requirements to terminate
repetitive inspections mandated by this AD.
(1) For any airplane identified in paragraphs (j)(2) and (j)(3)
of this AD, accomplishment of the initial inspection required by
paragraph (k) of this AD terminates the repetitive inspections
required by paragraph (g) of this AD.
(2) For any airplane identified in paragraphs (c)(1) through
(c)(5) of this AD, accomplishment of Airbus Service Bulletin A310-
53-2141, Revision 01, dated July 2, 2015; or Airbus Service Bulletin
A300-53-6181, Revision 01, dated July 2, 2015; as applicable;
terminates the repetitive inspections required by paragraph (k) of
this AD.
(n) Credit for Previous Actions
This paragraph provides credit for actions provided in paragraph
(m)(2) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A300-53-
6181, dated June 26, 2015; or Airbus Service Bulletin A310-53-2141,
dated June 26, 2015; as applicable.
(o) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, 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) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(4) Required for Compliance (RC): Except as required by
paragraph (l) of this AD: 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.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2015-0150, dated July 23, 2015,
for related information. This MCAI may be found in the AD docket on
the Internet at http://www.regulations.gov by searching for and
locating Docket No. FAA-2016-5596.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (q)(5) and (q)(6) of this AD.
(q) 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.
(3) The following service information was approved for IBR on
January 3, 2017.
(i) Airbus Alert Operators Transmission (AOT) A53W005-14,
Revision 01, dated April 29, 2014.
(ii) Airbus Service Bulletin A310-53-2141, Revision 01, dated
July 2, 2015.
(iii) Airbus Service Bulletin A300-53-6179, dated December 12,
2014.
(iv) Airbus Service Bulletin A300-53-6181, Revision 01, dated
July 2, 2015.
(v) Airbus Service Bulletin A310-53-2139, dated December 12,
2014.
(4) The following service information was approved for IBR on
July 2, 2014 (79 FR 34403, June 17, 2014).
(i) Airbus AOT A53W005-14, dated April 22, 2014.
(ii) Reserved.
(5) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com;
Internet http://www.airbus.com. You may view this service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
(6) 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.
(7) 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on September 28, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-28335 Filed 11-28-16; 8:45 am]
BILLING CODE 4910-13-P