Airworthiness Directives; Airbus Airplanes, 95538-95541 [2016-30611]
Download as PDF
95538
Federal Register / Vol. 81, No. 249 / Wednesday, December 28, 2016 / Proposed Rules
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.
(b) Affected ADs
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
(e) Unsafe Condition
This AD was prompted by wire harness
chafing on the electro-mechanical actuators
(EMAs) for certain spoilers due to
insufficient separation with adjacent
structure. We are issuing this AD to prevent
chafing that would cause wire damage that
could result in a potential source of ignition
in the flammable leakage zone and a
consequent fire or explosion.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
sradovich on DSK3GMQ082PROD with PROPOSALS
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2016–9516; Directorate Identifier 2016–
NM–053–AD.
(a) Comments Due Date
We must receive comments by February
13, 2017.
VerDate Sep<11>2014
18:33 Dec 27, 2016
Jkt 241001
None.
(c) Applicability
This AD applies to The Boeing Company
Model 787–8 and 787–9 airplanes,
certificated in any category, as identified in
Boeing Service Bulletin B787–81205–
SB270030–00, Issue 001, dated October 22,
2015.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight controls.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) EMA Replacement
Within 40 months after the effective date
of this AD, replace the EMAs with new
EMAs, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin B787–81205–SB270030–00,
Issue 001, dated October 22, 2015.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (i)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) For service information that contains
steps that are labeled as Required for
Compliance (RC), the provisions of
paragraphs (h)(4)(i) and (h)(4)(ii) of this AD
apply.
PO 00000
Frm 00043
Fmt 4702
Sfmt 4702
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or sub-step is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
sub-step. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled 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 RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(i) Related Information
(1) For more information about this AD,
contact Sean Schauer, Aerospace Engineer,
Systems and Equipment Branch, ANM–130S,
FAA, Seattle ACO, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–917–
6479; fax: 425–917–6590; email:
sean.schauer@faa.com.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet https://
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
Issued in Renton, Washington, on
December 9, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–30419 Filed 12–27–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9517; Directorate
Identifier 2016–NM–100–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Airbus Model A330–200, A330–200
Freighter, A330–300, A340–500, and
A340–600 series airplanes; and A340–
313 airplanes. This proposed AD was
prompted by the discovery of Tartaric
Sulfuric Anodizing (TSA)/Chromic Acid
SUMMARY:
E:\FR\FM\28DEP1.SGM
28DEP1
Federal Register / Vol. 81, No. 249 / Wednesday, December 28, 2016 / Proposed Rules
sradovich on DSK3GMQ082PROD with PROPOSALS
Anodizing (CAA) surface treatment in
certain bulk cargo door frame holes of
certain airplanes. This proposed AD
would require inspection of the fuselage
bulk cargo door frames at specific
locations, and corrective action if
necessary. We are proposing this AD to
address the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by February 13, 2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Airbus SAS,
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
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–2016–
9517; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1138;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
VerDate Sep<11>2014
18:33 Dec 27, 2016
Jkt 241001
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–9517; Directorate Identifier
2016–NM–100–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2016–0102, dated June 1,
2016; corrected June 7, 2016 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’); to correct an unsafe condition
for all Airbus Model A330–200, A330–
200 Freighter, A330–300, A340–500,
and A340–600 series airplanes; and
A340–313 airplanes. The MCAI states:
In the frame of the certification of the A330
Extended Service Goal exercise, it has been
identified that Tartaric Sulfuric Anodising
(TSA)/Chromic Acid Anodising (CAA)
surface treatment is present in some frame
holes, from aeroplane MSN 0400 and later
MSN, following production process
modification. On bulk cargo door frames (FR)
67 and FR 69 Right Hand Side, the door
fitting attachment holes have this TSA/CAA
treatment, which leads to a detrimental effect
on fatigue behaviour. This condition, if not
detected and corrected, could lead to critical
cracks in the primary structure, possibly
resulting in in-flight loss of a bulk cargo door,
consequent decompression and potential
damage to the aeroplane that could reduce
the control of the aeroplane.
To address this potential unsafe condition,
Airbus issued Alert Operators Transmission
(AOT) A53L012–16 to provide instructions to
inspect the fuselage bulk cargo door frames
at specific locations.
For the reasons described above, this
[EASA] AD requires repetitive nondestructive test (rototest and high-frequency
eddy-current (HFEC)) inspection or visual
detailed (DET) inspections [to detect
cracking] of the affected areas, and,
depending on findings, accomplishment of a
repair.
This [EASA] AD is considered an interim
measure, and further [EASA] AD action may
follow.
PO 00000
Frm 00044
Fmt 4702
Sfmt 4702
95539
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–2016–
9517.
Related Service Information Under 1
CFR Part 51
We reviewed Airbus Alert Operators
Transmission (AOT), AOT A53L012–16,
Revision 00, including Appendices 1
through 6, dated May 30, 2016:
• Appendix 1. Technical disposition
TD_K48_S3_01755_2016, Issue B, dated
May 12, 2016.
• Appendix 2. Technical disposition
TD_K48_S3_01754_2016, Issue B, dated
May 12, 2016.
• Appendix 3. Technical disposition
TD_K48_S3_01772_2016, Issue A, dated
May 12, 2016.
• Appendix 4. Technical disposition
TD_K48_S3_01773_2016, Issue A, dated
May 12, 2016.
• Appendix 5. AOT A53L012–16,
Revision 00, undated, titled Appendix
4: AOT reporting sheet 1; and AOT
A53L012–16, Revision 00, undated,
titled Appendix 4: AOT reporting sheet
2. (Appendix 5 of this document is
incorrectly identified as ‘‘Appendix
4.’’).
• Appendix 6. Non-destructive
Testing Manual Procedure 53–40–18,
‘‘Bulk Cargo Compartment Door Cut-Out
Lateral Frames at Bulk Door-Fittings
FR67 at STGR 37 and at STGR 42 and
FR 69 at STRG 38 and at STGR 45,’’
advanced copy approved for use, dated
May 18, 2016.
The service information describes
procedures for inspections of the
fuselage bulk cargo frames at the door
support and latch fittings location;
repair instructions; and reporting
instructions. This service information is
reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
E:\FR\FM\28DEP1.SGM
28DEP1
95540
Federal Register / Vol. 81, No. 249 / Wednesday, December 28, 2016 / Proposed Rules
Costs of Compliance
We estimate the following costs to
comply with this proposed AD:
We estimate that this proposed AD
affects 96 airplanes of U.S. registry.
ESTIMATED COSTS
Action
Labor cost
Inspection ...........
2 work-hours × $85 per hour =
$170 per inspection cycle.
1 work-hour × $85 per hour = $85
Reporting ............
Parts cost
We estimate the following costs to do
any necessary replacements that would
Cost per product
Cost on U.S. operators
$0
$170 per inspection cycle .............
$16,320 per inspection cycle.
0
$85 ................................................
$8,160.
be required based on the results of the
proposed inspection. We have no way of
determining the number of airplanes
that might need this replacement:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per
product
Optional door frame replacement .................................
200 work-hours × $85 per hour = $17,000 ..................
$68,000
$85,000
sradovich on DSK3GMQ082PROD with PROPOSALS
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 proposed AD is 2120–
0056. The paperwork cost associated
with this proposed 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 proposed
AD is 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.
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
VerDate Sep<11>2014
18:33 Dec 27, 2016
Jkt 241001
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
■
Regulatory Findings
■
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PO 00000
Frm 00045
Fmt 4702
Sfmt 4702
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Airbus: Docket No. FAA–2016–9517;
Directorate Identifier 2016–NM–100–AD.
(a) Comments Due Date
We must receive comments by February
13, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the following Airbus
airplanes, certificated in any category,
manufacturer serial numbers (MSNs) 0400
and higher.
(1) Airbus Model A330–201, –202, –203,
–223, and –243 airplanes.
(2) Airbus Model A330–223F and –243F
airplanes.
(3) Airbus Model A330–301, –302, –303,
–321, –322, –323, –341, –342, and –343
airplanes.
(4) Airbus Model A340–313 airplanes.
(5) Airbus Model A340–541 airplanes.
(6) Airbus Model A340–642 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by the discovery of
Tartaric Sulfuric Anodizing (TSA)/Chromic
Acid Anodizing (CAA) surface treatment in
certain bulk cargo door frame holes of
airplanes with MSNs 0400 and higher. We
are issuing this AD to detect and correct
fatigue cracks in the bulk cargo door frames,
E:\FR\FM\28DEP1.SGM
28DEP1
Federal Register / Vol. 81, No. 249 / Wednesday, December 28, 2016 / Proposed Rules
caused by TSA/CAA surface treatment in
certain bulk cargo door frame holes. Cracks
in the bulk cargo door frames can cause the
in-flight loss of a bulk cargo door, damage to
the airplane and subsequent reduced control
of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Initial Inspection
At the applicable compliance time
specified in table 1 to paragraph (g) of this
AD, do the actions specified in paragraph
(g)(1) or (g)(2) of this AD, in accordance with
the instructions of Airbus Alert Operators
Transmission (AOT), AOT A53L012–16,
Revision 00, dated May 30, 2016.
(1) Accomplish a rototest inspection to
detect cracking of the holes for the bulk cargo
door support fittings at fuselage frame (FR)
67 and FR 69, and a high-frequency eddycurrent (HFEC) inspection of the holes for the
door latch fitting at FR 69.
(2) Accomplish a detailed visual inspection
to detect cracking in the bulk cargo door
support fittings at FR 67 and FR 69 and the
holes for the door latch fitting at FR 69.
TABLE 1 TO PARAGRAPH (g) OF THIS
AD—INITIAL INSPECTION
Total flight cycles
accumulated since
airplane first flight, on
the effective date of
this AD
12,500 total flight cycles or more.
Fewer than 12,500
total flight cycles.
Compliance time
Within 200 flight cycles or 2 months,
whichever occurs
first, after the effective date of this AD.
Within 200 flight cycles or 2 months,
whichever occurs
first, after exceeding 12,500 flight cycles.
(h) Repetitive Inspections
At intervals not to exceed the values
specified in table 2 to paragraph (h) of this
AD, as applicable, depending on the
previously selected inspection method,
repeat the inspection(s) specified in either
paragraph (g)(1) or (g)(2) of this AD.
TABLE 2 TO PARAGRAPH (h) OF THIS
AD—REPETITIVE INSPECTIONS
sradovich on DSK3GMQ082PROD with PROPOSALS
Inspection method
Detailed visual inspection.
Rototest and HFEC
inspections.
Inspection interval
150 flight cycles.
2,900 flight cycles.
(i) Repair
If, during any inspection required by
paragraph (g) or (h) of this AD, any crack is
detected, before further flight, repair using a
method approved by the Manager,
VerDate Sep<11>2014
18:33 Dec 27, 2016
Jkt 241001
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
(j) Terminating Action
Accomplishment of a repair on an airplane,
as required by paragraph (i) of this AD, does
not constitute terminating action for the
inspections required by this AD for that
airplane, unless otherwise specified in repair
instructions approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA DOA.
(k) Reporting
After the initial inspection specified in
paragraph (g) of this AD, and after each
repetitive inspection specified in paragraph
(h) of this AD, at the applicable times
specified in paragraph (k)(1) and (k)(2) of this
AD: Report inspection findings, both positive
and negative, to Airbus in accordance with
the instructions of Airbus AOT A53L012–16,
Revision 00, dated May 30, 2016.
(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.
(l) 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:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1138; fax 425–227–1149.
Information may be emailed to: 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
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
PO 00000
Frm 00046
Fmt 4702
Sfmt 4702
95541
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.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0102, dated June 1, 2016; corrected
June 7, 2016, for related information. You
may examine the MCAI on the Internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2016–9517.
(2) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You may
view this service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
Issued in Renton, Washington, on
December 2, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–30611 Filed 12–27–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF THE TREASURY
Internal Revenue Service
26 CFR Part 1
[REG–114734–16]
RIN 1545–BN51
United States Property Held by
Controlled Foreign Corporations
Through Partnerships With Special
Allocations; Correction
Internal Revenue Service (IRS),
Treasury.
ACTION: Correction to a notice of
proposed rulemaking.
AGENCY:
This document contains
corrections to a notice of proposed
rulemaking (REG–114734–16) that was
published in the Federal Register on
Thursday, November 3, 2016 (81 FR
76542). The proposed regulations
provide rules regarding the
SUMMARY:
E:\FR\FM\28DEP1.SGM
28DEP1
Agencies
[Federal Register Volume 81, Number 249 (Wednesday, December 28, 2016)]
[Proposed Rules]
[Pages 95538-95541]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-30611]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9517; Directorate Identifier 2016-NM-100-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Airbus Model A330-200, A330-200 Freighter, A330-300, A340-500, and
A340-600 series airplanes; and A340-313 airplanes. This proposed AD was
prompted by the discovery of Tartaric Sulfuric Anodizing (TSA)/Chromic
Acid
[[Page 95539]]
Anodizing (CAA) surface treatment in certain bulk cargo door frame
holes of certain airplanes. This proposed AD would require inspection
of the fuselage bulk cargo door frames at specific locations, and
corrective action if necessary. We are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on this proposed AD by February 13,
2017.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Airbus
SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45
80; email airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.
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-2016-
9517; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-9517;
Directorate Identifier 2016-NM-100-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2016-0102, dated June 1, 2016; corrected June
7, 2016 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''); to correct an unsafe
condition for all Airbus Model A330-200, A330-200 Freighter, A330-300,
A340-500, and A340-600 series airplanes; and A340-313 airplanes. The
MCAI states:
In the frame of the certification of the A330 Extended Service
Goal exercise, it has been identified that Tartaric Sulfuric
Anodising (TSA)/Chromic Acid Anodising (CAA) surface treatment is
present in some frame holes, from aeroplane MSN 0400 and later MSN,
following production process modification. On bulk cargo door frames
(FR) 67 and FR 69 Right Hand Side, the door fitting attachment holes
have this TSA/CAA treatment, which leads to a detrimental effect on
fatigue behaviour. This condition, if not detected and corrected,
could lead to critical cracks in the primary structure, possibly
resulting in in-flight loss of a bulk cargo door, consequent
decompression and potential damage to the aeroplane that could
reduce the control of the aeroplane.
To address this potential unsafe condition, Airbus issued Alert
Operators Transmission (AOT) A53L012-16 to provide instructions to
inspect the fuselage bulk cargo door frames at specific locations.
For the reasons described above, this [EASA] AD requires
repetitive non-destructive test (rototest and high-frequency eddy-
current (HFEC)) inspection or visual detailed (DET) inspections [to
detect cracking] of the affected areas, and, depending on findings,
accomplishment of a repair.
This [EASA] AD is considered an interim measure, and further
[EASA] AD action may follow.
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-2016-
9517.
Related Service Information Under 1 CFR Part 51
We reviewed Airbus Alert Operators Transmission (AOT), AOT A53L012-
16, Revision 00, including Appendices 1 through 6, dated May 30, 2016:
Appendix 1. Technical disposition TD_K48_S3_01755_2016,
Issue B, dated May 12, 2016.
Appendix 2. Technical disposition TD_K48_S3_01754_2016,
Issue B, dated May 12, 2016.
Appendix 3. Technical disposition TD_K48_S3_01772_2016,
Issue A, dated May 12, 2016.
Appendix 4. Technical disposition TD_K48_S3_01773_2016,
Issue A, dated May 12, 2016.
Appendix 5. AOT A53L012-16, Revision 00, undated, titled
Appendix 4: AOT reporting sheet 1; and AOT A53L012-16, Revision 00,
undated, titled Appendix 4: AOT reporting sheet 2. (Appendix 5 of this
document is incorrectly identified as ``Appendix 4.'').
Appendix 6. Non-destructive Testing Manual Procedure 53-
40-18, ``Bulk Cargo Compartment Door Cut-Out Lateral Frames at Bulk
Door-Fittings FR67 at STGR 37 and at STGR 42 and FR 69 at STRG 38 and
at STGR 45,'' advanced copy approved for use, dated May 18, 2016.
The service information describes procedures for inspections of the
fuselage bulk cargo frames at the door support and latch fittings
location; repair instructions; and reporting instructions. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
[[Page 95540]]
Costs of Compliance
We estimate that this proposed AD affects 96 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection....................... 2 work-hours x $85 $0 $170 per inspection $16,320 per
per hour = $170 cycle. inspection cycle.
per inspection
cycle.
Reporting........................ 1 work-hour x $85 0 $85................ $8,160.
per hour = $85.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed inspection.
We have no way of determining the number of airplanes that might need
this replacement:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Optional door frame replacement.............. 200 work-hours x $85 per hour = $68,000 $85,000
$17,000.
----------------------------------------------------------------------------------------------------------------
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 proposed AD
is 2120-0056. The paperwork cost associated with this proposed 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 proposed AD is 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.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2016-9517; Directorate Identifier 2016-NM-
100-AD.
(a) Comments Due Date
We must receive comments by February 13, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the following Airbus airplanes, certificated
in any category, manufacturer serial numbers (MSNs) 0400 and higher.
(1) Airbus Model A330-201, -202, -203, -223, and -243 airplanes.
(2) Airbus Model A330-223F and -243F airplanes.
(3) Airbus Model A330-301, -302, -303, -321, -322, -323, -341, -
342, and -343 airplanes.
(4) Airbus Model A340-313 airplanes.
(5) Airbus Model A340-541 airplanes.
(6) Airbus Model A340-642 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by the discovery of Tartaric Sulfuric
Anodizing (TSA)/Chromic Acid Anodizing (CAA) surface treatment in
certain bulk cargo door frame holes of airplanes with MSNs 0400 and
higher. We are issuing this AD to detect and correct fatigue cracks
in the bulk cargo door frames,
[[Page 95541]]
caused by TSA/CAA surface treatment in certain bulk cargo door frame
holes. Cracks in the bulk cargo door frames can cause the in-flight
loss of a bulk cargo door, damage to the airplane and subsequent
reduced control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Initial Inspection
At the applicable compliance time specified in table 1 to
paragraph (g) of this AD, do the actions specified in paragraph
(g)(1) or (g)(2) of this AD, in accordance with the instructions of
Airbus Alert Operators Transmission (AOT), AOT A53L012-16, Revision
00, dated May 30, 2016.
(1) Accomplish a rototest inspection to detect cracking of the
holes for the bulk cargo door support fittings at fuselage frame
(FR) 67 and FR 69, and a high-frequency eddy-current (HFEC)
inspection of the holes for the door latch fitting at FR 69.
(2) Accomplish a detailed visual inspection to detect cracking
in the bulk cargo door support fittings at FR 67 and FR 69 and the
holes for the door latch fitting at FR 69.
Table 1 to Paragraph (g) of This AD--Initial Inspection
------------------------------------------------------------------------
Total flight cycles accumulated since
airplane first flight, on the effective Compliance time
date of this AD
------------------------------------------------------------------------
12,500 total flight cycles or more........ Within 200 flight cycles or
2 months, whichever occurs
first, after the effective
date of this AD.
Fewer than 12,500 total flight cycles..... Within 200 flight cycles or
2 months, whichever occurs
first, after exceeding
12,500 flight cycles.
------------------------------------------------------------------------
(h) Repetitive Inspections
At intervals not to exceed the values specified in table 2 to
paragraph (h) of this AD, as applicable, depending on the previously
selected inspection method, repeat the inspection(s) specified in
either paragraph (g)(1) or (g)(2) of this AD.
Table 2 to Paragraph (h) of This AD--Repetitive Inspections
------------------------------------------------------------------------
Inspection method Inspection interval
------------------------------------------------------------------------
Detailed visual inspection................ 150 flight cycles.
Rototest and HFEC inspections............. 2,900 flight cycles.
------------------------------------------------------------------------
(i) Repair
If, during any inspection required by paragraph (g) or (h) of
this AD, any crack is detected, 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).
(j) Terminating Action
Accomplishment of a repair on an airplane, as required by
paragraph (i) of this AD, does not constitute terminating action for
the inspections required by this AD for that airplane, unless
otherwise specified in repair instructions approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA; or Airbus's EASA DOA.
(k) Reporting
After the initial inspection specified in paragraph (g) of this
AD, and after each repetitive inspection specified in paragraph (h)
of this AD, at the applicable times specified in paragraph (k)(1)
and (k)(2) of this AD: Report inspection findings, both positive and
negative, to Airbus in accordance with the instructions of Airbus
AOT A53L012-16, Revision 00, dated May 30, 2016.
(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.
(l) 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: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information
may be emailed to: 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 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.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0102, dated June 1, 2016; corrected June 7,
2016, for related information. You may examine the MCAI on the
Internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2016-9517.
(2) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You may view this service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on December 2, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-30611 Filed 12-27-16; 8:45 am]
BILLING CODE 4910-13-P