Airworthiness Directives; Airbus Airplanes, 28020-28023 [2017-12614]
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28020
Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules
For the Nuclear Regulatory Commission.
Annette L. Vietti-Cook,
Secretary of the Commission.
[FR Doc. 2017–12792 Filed 6–19–17; 8:45 am]
BILLING CODE 7590–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0561; Directorate
Identifier 2016–NM–141–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2001–16–
01, which applies to certain Airbus
Model A330–301, –321, –322, –341, and
–342 airplanes, and certain Model A340
series airplanes; and AD 2014–17–06,
which applies to all Airbus Model
A330–200 series airplanes, Model
A330–200 Freighter series airplanes,
and Model A330–300 series airplanes.
AD 2001–16–01 requires inspections for
cracking of the aft cargo compartment
door, and corrective action if necessary.
AD 2014–17–06 requires revising the
maintenance or inspection program, as
applicable, to incorporate structural
inspection requirements. Since we
issued AD 2001–16–01 and AD 2014–
17–06, we have determined that more
restrictive maintenance instructions and
airworthiness limitations are necessary.
This proposed AD would require
revising the maintenance or inspection
program, as applicable, to incorporate
new or revised airworthiness limitation
requirements; and remove airplanes
from the applicability. We are proposing
this AD to address the unsafe condition
on these products.
DATES: We must receive comments on
this proposed AD by August 4, 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.
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SUMMARY:
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• 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–2017–
0561; 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–2017–0561; Directorate Identifier
2016–NM–141–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.
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Discussion
On July 26, 2001, we issued AD 2001–
16–01, Amendment 39–12369 (66 FR
40874, August 6, 2001) (‘‘AD 2001–16–
01’’), for certain Airbus Model A330–
301, –321, –322, –341, and –342
airplanes, and certain Model A340
series airplanes. AD 2001–16–01 was
prompted by reports of cracking in
several structural parts of the aft cargo
compartment door. AD 2001–16–01
requires repetitive inspections to detect
cracking of the aft cargo compartment
door, and corrective action if necessary;
and also provides optional terminating
action for the repetitive inspections. We
issued AD 2001–16–01 to detect and
correct cracking of the aft cargo
compartment door, which could result
in reduced structural integrity of the
airplane.
On August 15, 2014, we issued AD
2014–17–06, Amendment 39–17959 (79
FR 52181, September 3, 2014) (‘‘AD
2014–17–06’’), for all Airbus Model
A330–200 series airplanes, Model
A330–200 Freighter series airplanes,
and Model A330–300 series airplanes.
AD 2014–17–06 superseded AD 2011–
17–08, Amendment 39–16772 (76 FR
53303, August 26, 2011). AD 2014–17–
06 was prompted by a revision of
certain airworthiness limitations items
documents, which specifies more
restrictive instructions and/or
airworthiness limitations. AD 2014–17–
06 requires a revision to the
maintenance or inspection program, as
applicable, to incorporate new or
revised structural inspection
requirements. We issued AD 2014–17–
06 to detect and correct fatigue cracking,
damage, and corrosion in certain
structure, which could result in reduced
structural integrity of the airplane.
Since we issued AD 2001–16–01 and
AD 2014–17–06, we have determined
that more restrictive maintenance
instructions and airworthiness
limitations are necessary, and that
Model A340 series airplanes should be
removed from the applicability as there
are currently no Model A340 series
airplanes on the U.S. register.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2016–0152, dated July 27,
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 Freighter, –200, and
–300 series airplanes; and Model A340–
200, –300, –500, and –600 series
airplanes. The MCAI states:
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Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules
The airworthiness limitations are currently
defined and published in the Airbus A330
and A340 Airworthiness Limitations Section
(ALS) documents.
The airworthiness limitations applicable to
the Damage Tolerant Airworthiness
Limitation Items (DT ALI), which are
approved by EASA, are specified in Airbus
A330 and A340 ALS Part 2. Failure to
comply with these instructions could result
in an unsafe condition [fatigue cracking,
damage, and corrosion in a certain structure,
which could result in reduced structural
integrity of the airplane].
EASA issued AD 2012–0211 (for A330
aeroplanes) [which corresponds to FAA AD
2014–17–06] and AD 2013–0127 (for A340
aeroplanes) [which corresponds to FAA AD
2001–16–01] to require the actions as
specified in Airbus A330 and A340 ALS Part
2 at original issue and Revision 01,
respectively.
Since those [EASA] ADs were issued,
Airbus issued Revision 01 and Revision 02,
respectively, of Airbus A330 and A340 ALS
Part 2, to introduce more restrictive
maintenance requirements and/or
airworthiness limitations.
For the reason described above, this
[EASA] AD retains the requirements of EASA
AD 2012–0211 and AD 2013–0127, which are
superseded, and requires accomplishment of
the actions specified in Airbus A330 ALS
Part 2 Revision 01 including Variation 1.1
and Variation 1.2, or A340 ALS Part 2
Revision 02 including Variation 2.1 and
Variation 2.2, as applicable (hereafter
collectively referred to as ‘the applicable
ALS’ in this [EASA] AD).
In addition, this [EASA] AD also
supersedes DGAC France AD 2001–126(B),
whose requirements applicable to A330
aeroplanes have been transferred into Airbus
A330 ALS Part 2, and supersedes DGAC
´ ´
[Direction Generale de l’Aviation Civile ]
France AD 2001–124(B), EASA AD 2012–
0031 and AD 2012–0167, whose
requirements applicable to A340 aeroplanes
have been transferred into Airbus A340 ALS
Part 2 [EASA ADs 2001–124(B) and 2001–
126(B) correspond with FAA AD 2001–16–
01].
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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–2017–
0561.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information, which describes
airworthiness limitation requirements
for damage-tolerant airworthiness
limitation items. These documents are
distinct since they provide different
limitation requirements.
• Airbus A330 ALS Part 2, DT-ALI,
Revision 01, issue 02, dated November
30, 2015.
• Airbus 330 ALS Part 2, DT-ALI,
Variation 1.1, dated December 15, 2015.
• Airbus 330 ALS Part 2, DT-ALI,
Variation 1.2, dated May 27, 2016.
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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 the same
type design.
This proposed AD requires revisions
to certain operator maintenance
documents to include new actions (e.g.,
inspections). Compliance with these
actions is required by 14 CFR 91.403(c).
For airplanes that have been previously
modified, altered, or repaired in the
areas addressed by this proposed AD,
the operator may not be able to
accomplish the actions described in the
revisions. In this situation, to comply
with 14 CFR 91.403(c), the operator
must request approval for an AMOC
according to paragraph (l)(1) of this
proposed AD. The request should
include a description of changes to the
required actions that will ensure the
continued damage tolerance of the
affected structure.
Differences Between This Proposed AD
and the MCAI
This proposed AD does not include
the Model A340 airplanes that are
specified in the MCAI. We have added
that MCAI to the required airworthiness
actions list (RAAL) for the Model A340
airplanes.
The MCAI specifies that if there are
findings from the ALS inspection tasks,
corrective actions must be accomplished
in accordance with Airbus maintenance
documentation. However, this proposed
AD does not include that requirement.
Operators of U.S.-registered airplanes
are required by general airworthiness
and operational regulations to perform
maintenance using methods that are
acceptable to the FAA. We consider
those methods to be adequate to address
any corrective actions necessitated by
the findings of ALS inspections required
by this proposed AD.
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Airworthiness Limitations Based on
Type Design
The FAA recently became aware of an
issue related to the applicability of ADs
that require incorporation of an ALS
revision into an operator’s maintenance
or inspection program.
Typically, when these types of ADs
are issued by civil aviation authorities
of other countries, they apply to all
airplanes covered under an identified
type certificate (TC). The corresponding
FAA AD typically retains applicability
to all of those airplanes.
In addition, U.S. operators must
operate their airplanes in an airworthy
condition, in accordance with 14 CFR
91.7(a). Included in this obligation is the
requirement to perform any
maintenance or inspections specified in
the ALS, and in accordance with the
ALS as specified in 14 CFR 43.16 and
91.403(c), unless an alternative has been
approved by the FAA.
When a TC is issued for a type design,
the specific ALS, including revisions, is
a part of that type design, as specified
in 14 CFR 21.31(c).
The sum effect of these operational
and maintenance requirements is an
obligation to comply with the ALS
defined in the type design referenced in
the manufacturer’s conformity
statement. This obligation may
introduce a conflict with an AD that
requires a specific ALS revision if new
airplanes are delivered with a later
revision as part of their type design.
To address this conflict, the FAA has
approved alternative methods of
compliance (AMOCs) that allow
operators to incorporate the most recent
ALS revision into their maintenance/
inspection programs, in lieu of the ALS
revision required by the AD. This
eliminates the conflict and enables the
operator to comply with both the AD
and the type design.
However, compliance with AMOCs is
normally optional, and we recently
became aware that some operators
choose to retain the AD-mandated ALS
revision in their fleet-wide
maintenance/inspection programs,
including those for new airplanes
delivered with later ALS revisions, to
help standardize the maintenance of the
fleet. To ensure that operators comply
with the applicable ALS revision for
newly delivered airplanes containing a
later revision than that specified in an
AD, we plan to limit the applicability of
ADs that mandate ALS revisions to
those airplanes that are subject to an
earlier revision of the ALS, either as part
of the type design or as mandated by an
earlier AD.
For purposes of this NPRM, in order
to ensure that affected airplanes are
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Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules
maintained in accordance with
mandatory instructions and
airworthiness limitations, this NPRM
includes the limitations specified in
Airbus 330 ALS Part 2, DT-ALI,
Variation 1.1, dated December 15, 2015;
and Airbus 330 ALS Part 2, DT-ALI,
Variation 1.2, dated May 27, 2016. This
NPRM, therefore, applies to Model
A330–200, –200 Freighter, and –300
series airplanes with an original
certificate of airworthiness or original
export certificate of airworthiness that
was issued on or before May 27, 2016,
the date of approval of Airbus 330 ALS
Part 2, DT-ALI, Variation 1.2. Operators
of airplanes with an original certificate
of airworthiness or original export
certificate of airworthiness issued after
that date must comply with the
airworthiness limitations specified as
part of the approved type design and
referenced on the type certificate data
sheet.
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Costs of Compliance
We estimate that this proposed AD
affects 101 airplanes of U.S. registry.
The actions required by AD 2014–17–
06, and retained in this proposed AD,
take about 1 work-hour per product, at
an average labor rate of $85 per workhour. Required parts cost about $0 per
product. Based on these figures, the
estimated cost of the actions that are
required by AD 2014–17–06 is $85 per
product.
We also estimate that it would take
about 1 work-hour per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Required
parts would cost about $0 per product.
Based on these figures, we estimate the
cost of this proposed AD on U.S.
operators to be $8,585, or $85 per
product.
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
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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
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:
a. Removing Airworthiness Directives
(AD) 2001–16–01, Amendment 39–
12369 (66 FR 40874, August 6, 2001);
and AD 2014–17–06, Amendment 39–
17959 (79 FR 52181, September 3,
2014); and
■ b. Adding the following new AD:
■
■
Airbus: Docket No. FAA–2017–0561;
Directorate Identifier 2016–NM–141–AD.
(a) Comments Due Date
We must receive comments by August 4,
2017.
(b) Affected ADs
This AD replaces AD 2001–16–01,
Amendment 39–12369 (66 FR 40874, August
6, 2001) (‘‘AD 2001–16–01’’); and AD 2014–
17–06, Amendment 39–17959 (79 FR 52181,
September 3, 2014) (‘‘AD 2014–17–06’’).
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(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1), (c)(2), and
(c)(3) of this AD, certificated in any category,
with an original certificate of airworthiness
or original export certificate of airworthiness
issued on or before May 27, 2016.
(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.
(d) Subject
Air Transport Association (ATA) of
America Code 05, Periodic inspections.
(e) Reason
This AD was prompted by a determination
that more restrictive maintenance
instructions and airworthiness limitations are
necessary. We are issuing this AD to detect
and correct fatigue cracking, damage, and
corrosion in a certain structure, which could
result in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Requirement: Maintenance or
Inspection Program Revision, With a New
Terminating Action
This paragraph restates the requirements of
paragraph (i) of AD 2014–17–06, with a new
terminating action. Accomplishing the
revision required by paragraph (j) of this AD
terminates the requirements of this
paragraph.
(1) Within 3 months after October 8, 2014
(the effective date of AD 2014–17–06): Revise
the maintenance or inspection program, as
applicable, by incorporating Airbus
Document AI/SE–M4/95A.0089/97, ‘‘A330
Airworthiness Limitation Items,’’ Issue 19,
dated March 23, 2012; ‘‘Variation to Issue 19
of ALI Document (referenced in ALS Part 2)
Damage Tolerant Airworthiness Limitation
Items (DT ALI),’’ variation reference
0GVLG120018/C0S, dated October 24, 2012;
and ‘‘Variation to Issue 19 of ALI Document
(referenced in ALS Part 2) Damage Tolerant
Airworthiness Limitation Items (DT ALI),’’
variation reference 0GVLG130002/C01, dated
March 26, 2013.
(2) Comply with all applicable instructions
and airworthiness limitations included in
Airbus Document AI/SE M4/95A.0089/97,
‘‘A330 Airworthiness Limitation Items,’’
Issue 19, dated March 23, 2012; ‘‘Variation to
Issue 19 of ALI Document (referenced in ALS
Part 2) Damage Tolerant Airworthiness
Limitation Items (DT ALI),’’ variation
reference 0GVLG120018/C0S, dated October
24, 2012; and ‘‘Variation to Issue 19 of ALI
Document (referenced in ALS Part 2) Damage
Tolerant Airworthiness Limitation Items (DT
ALI),’’ variation reference 0GVLG130002/
C01, dated March 26, 2013. The initial
compliance times for the actions specified in
Airbus Document AI/SE–M4/95A.0089/97,
‘‘A330 Airworthiness Limitation Items,’’
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Issue 19, dated March 23, 2012; ‘‘Variation to
Issue 19 of ALI Document (referenced in ALS
Part 2) Damage Tolerant Airworthiness
Limitation Items (DT ALI),’’ variation
reference 0GVLG120018/C0S, dated October
24, 2012; and ‘‘Variation to Issue 19 of ALI
Document (referenced in ALS Part 2) Damage
Tolerant Airworthiness Limitation Items (DT
ALI),’’ 0GVLG130002/C01, dated March 26,
2013; are at the times specified in Airbus
Document AI/SE–M4/95A.0089/97, ‘‘A330
Airworthiness Limitation Items,’’ Issue 19,
dated March 23, 2012; ‘‘Variation to Issue 19
of ALI Document (referenced in ALS Part 2)
Damage Tolerant Airworthiness Limitation
Items (DT ALI),’’ variation ref.
0GVLG120018/C0S, dated October 24, 2012;
and ‘‘Variation to Issue 19 of ALI Document
(referenced in ALS Part 2) Damage Tolerant
Airworthiness Limitation Items (DT ALI),’’
variation ref. 0GVLG130002/C01, dated
March 26, 2013; or within 3 months after
October 8, 2014 (the effective date of AD
2014–17–06), whichever occurs later.
later. Accomplishing the revision specified in
this paragraph terminates the requirements of
paragraph (g) of this AD and the provision
specified in paragraph (h) of this AD.
(1) Airbus A330 Airworthiness Limitations
Section (ALS) Part 2, Damage Tolerant
Airworthiness Limitation Items (DT-ALI),
Revision 01, issue 02, dated November 30,
2015.
(2) Airbus 330 ALS Part 2, DT-ALI,
Variation 1.1, dated December 15, 2015.
(3) Airbus 330 ALS Part 2, DT-ALI,
Variation 1.2, dated May 27, 2016.
(h) Retained Provision: Optional
Compliance, With a New Terminating
Action
This paragraph restates the provision in
paragraph (j) of AD 2014–17–06, with a new
terminating action. Compliance with tasks
533021–02–01, 533021–02–02, and 533021–
02–03, specified in ‘‘Variation to Issue 19 of
ALI Document (referenced in ALS Part 2)
Damage Tolerant Airworthiness Limitation
Items (DT ALI),’’ variation ref.
0GVLG120022/C0S, dated December 21,
2012, may be used as a method of
compliance to tasks 533021–01–01, 533021–
01–02, 533021–01–03 specified in Section
2.2.1 and 2.2.2 of Section 2, ‘‘Airworthiness
Limitations,’’ of Airbus Document AI/SE M4/
95A.0089/97, ‘‘A330 Airworthiness
Limitation Items,’’ Issue 19, dated March 23,
2012. Accomplishing the revision required
by paragraph (j) of this AD terminates the
provision specified in this paragraph.
(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 the
attention of the person identified in
paragraph (m)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@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.
(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 European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
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(i) Retained Requirement: No Alternative
Intervals or Limits, With a New Exception
This paragraph restates the requirements of
paragraph (k) of AD 2014–17–06, with a new
exception. Except as provided by paragraph
(h) of this AD and as required by paragraph
(j) of this AD, after the maintenance or
inspection program, as applicable, has been
revised as required by paragraph (g) of this
AD, no alternative actions (e.g., inspections)
or intervals may be used unless the actions
or intervals are approved as an alternative
method of compliance (AMOC) under the
provisions of paragraph (l)(1) of this AD.
(j) New Requirement: Maintenance or
Inspection Program Revision
Within 3 months after the effective date of
this AD: Revise the maintenance or
inspection program, as applicable, by
incorporating the service information
specified in paragraphs (j)(1), (j)(2), and (j)(3)
of this AD. The initial compliance times for
the actions specified in the service
information referenced in paragraphs (j)(1),
(j)(2), and (j)(3) of this AD are the times
specified in the applicable service
information, or within 3 months after the
effective date of this AD, whichever occurs
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(k) New Requirement: No Alternative
Actions or Intervals
After the maintenance or inspection
program, as applicable, has been revised, as
required by paragraph (j) of this AD, no
alternative actions (e.g., inspections) or
intervals may be used unless the actions or
intervals are approved as an AMOC in
accordance with the procedures specified in
paragraph (l)(1) of this AD.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0152, dated
July 27, 2016, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2017–0561.
(2) For more information about this AD,
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.
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
28023
(3) 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 June 9,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–12614 Filed 6–19–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0559; Directorate
Identifier 2017–NM–013–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all The
Boeing Company Model 747–100, 747–
100B, 747–100B SUD, 747–200B, 747–
200C, 747–200F, 747–300, 747–400,
747–400D, 747–400F, 747SR, and 747SP
airplanes. This proposed AD was
prompted by a report of damage found
at the lower trailing edge panels of the
left wing and a broken fuse pin of the
landing gear beam end fitting. This
proposed AD would require repetitive
replacement or inspection of certain
fuse pins, and applicable on-condition
actions. We are proposing this AD to
address the unsafe condition on these
products.
SUMMARY:
We must receive comments on
this proposed AD by August 4, 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
DATES:
E:\FR\FM\20JNP1.SGM
20JNP1
Agencies
[Federal Register Volume 82, Number 117 (Tuesday, June 20, 2017)]
[Proposed Rules]
[Pages 28020-28023]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-12614]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0561; Directorate Identifier 2016-NM-141-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2001-16-
01, which applies to certain Airbus Model A330-301, -321, -322, -341,
and -342 airplanes, and certain Model A340 series airplanes; and AD
2014-17-06, which applies to all Airbus Model A330-200 series
airplanes, Model A330-200 Freighter series airplanes, and Model A330-
300 series airplanes. AD 2001-16-01 requires inspections for cracking
of the aft cargo compartment door, and corrective action if necessary.
AD 2014-17-06 requires revising the maintenance or inspection program,
as applicable, to incorporate structural inspection requirements. Since
we issued AD 2001-16-01 and AD 2014-17-06, we have determined that more
restrictive maintenance instructions and airworthiness limitations are
necessary. This proposed AD would require revising the maintenance or
inspection program, as applicable, to incorporate new or revised
airworthiness limitation requirements; and remove airplanes from the
applicability. We are proposing this AD to address the unsafe condition
on these products.
DATES: We must receive comments on this proposed AD by August 4, 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-2017-
0561; 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-2017-0561;
Directorate Identifier 2016-NM-141-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
On July 26, 2001, we issued AD 2001-16-01, Amendment 39-12369 (66
FR 40874, August 6, 2001) (``AD 2001-16-01''), for certain Airbus Model
A330-301, -321, -322, -341, and -342 airplanes, and certain Model A340
series airplanes. AD 2001-16-01 was prompted by reports of cracking in
several structural parts of the aft cargo compartment door. AD 2001-16-
01 requires repetitive inspections to detect cracking of the aft cargo
compartment door, and corrective action if necessary; and also provides
optional terminating action for the repetitive inspections. We issued
AD 2001-16-01 to detect and correct cracking of the aft cargo
compartment door, which could result in reduced structural integrity of
the airplane.
On August 15, 2014, we issued AD 2014-17-06, Amendment 39-17959 (79
FR 52181, September 3, 2014) (``AD 2014-17-06''), for all Airbus Model
A330-200 series airplanes, Model A330-200 Freighter series airplanes,
and Model A330-300 series airplanes. AD 2014-17-06 superseded AD 2011-
17-08, Amendment 39-16772 (76 FR 53303, August 26, 2011). AD 2014-17-06
was prompted by a revision of certain airworthiness limitations items
documents, which specifies more restrictive instructions and/or
airworthiness limitations. AD 2014-17-06 requires a revision to the
maintenance or inspection program, as applicable, to incorporate new or
revised structural inspection requirements. We issued AD 2014-17-06 to
detect and correct fatigue cracking, damage, and corrosion in certain
structure, which could result in reduced structural integrity of the
airplane.
Since we issued AD 2001-16-01 and AD 2014-17-06, we have determined
that more restrictive maintenance instructions and airworthiness
limitations are necessary, and that Model A340 series airplanes should
be removed from the applicability as there are currently no Model A340
series airplanes on the U.S. register.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2016-0152, dated July 27, 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 Freighter, -200, and -300 series airplanes; and Model A340-
200, -300, -500, and -600 series airplanes. The MCAI states:
[[Page 28021]]
The airworthiness limitations are currently defined and
published in the Airbus A330 and A340 Airworthiness Limitations
Section (ALS) documents.
The airworthiness limitations applicable to the Damage Tolerant
Airworthiness Limitation Items (DT ALI), which are approved by EASA,
are specified in Airbus A330 and A340 ALS Part 2. Failure to comply
with these instructions could result in an unsafe condition [fatigue
cracking, damage, and corrosion in a certain structure, which could
result in reduced structural integrity of the airplane].
EASA issued AD 2012-0211 (for A330 aeroplanes) [which
corresponds to FAA AD 2014-17-06] and AD 2013-0127 (for A340
aeroplanes) [which corresponds to FAA AD 2001-16-01] to require the
actions as specified in Airbus A330 and A340 ALS Part 2 at original
issue and Revision 01, respectively.
Since those [EASA] ADs were issued, Airbus issued Revision 01
and Revision 02, respectively, of Airbus A330 and A340 ALS Part 2,
to introduce more restrictive maintenance requirements and/or
airworthiness limitations.
For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2012-0211 and AD 2013-0127, which are
superseded, and requires accomplishment of the actions specified in
Airbus A330 ALS Part 2 Revision 01 including Variation 1.1 and
Variation 1.2, or A340 ALS Part 2 Revision 02 including Variation
2.1 and Variation 2.2, as applicable (hereafter collectively
referred to as `the applicable ALS' in this [EASA] AD).
In addition, this [EASA] AD also supersedes DGAC France AD 2001-
126(B), whose requirements applicable to A330 aeroplanes have been
transferred into Airbus A330 ALS Part 2, and supersedes DGAC
[Direction G[eacute]n[eacute]rale de l'Aviation Civile ] France AD
2001-124(B), EASA AD 2012-0031 and AD 2012-0167, whose requirements
applicable to A340 aeroplanes have been transferred into Airbus A340
ALS Part 2 [EASA ADs 2001-124(B) and 2001-126(B) correspond with FAA
AD 2001-16-01].
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-2017-
0561.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information, which
describes airworthiness limitation requirements for damage-tolerant
airworthiness limitation items. These documents are distinct since they
provide different limitation requirements.
Airbus A330 ALS Part 2, DT-ALI, Revision 01, issue 02,
dated November 30, 2015.
Airbus 330 ALS Part 2, DT-ALI, Variation 1.1, dated
December 15, 2015.
Airbus 330 ALS Part 2, DT-ALI, Variation 1.2, dated May
27, 2016.
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 the same
type design.
This proposed AD requires revisions to certain operator maintenance
documents to include new actions (e.g., inspections). Compliance with
these actions is required by 14 CFR 91.403(c). For airplanes that have
been previously modified, altered, or repaired in the areas addressed
by this proposed AD, the operator may not be able to accomplish the
actions described in the revisions. In this situation, to comply with
14 CFR 91.403(c), the operator must request approval for an AMOC
according to paragraph (l)(1) of this proposed AD. The request should
include a description of changes to the required actions that will
ensure the continued damage tolerance of the affected structure.
Differences Between This Proposed AD and the MCAI
This proposed AD does not include the Model A340 airplanes that are
specified in the MCAI. We have added that MCAI to the required
airworthiness actions list (RAAL) for the Model A340 airplanes.
The MCAI specifies that if there are findings from the ALS
inspection tasks, corrective actions must be accomplished in accordance
with Airbus maintenance documentation. However, this proposed AD does
not include that requirement. Operators of U.S.-registered airplanes
are required by general airworthiness and operational regulations to
perform maintenance using methods that are acceptable to the FAA. We
consider those methods to be adequate to address any corrective actions
necessitated by the findings of ALS inspections required by this
proposed AD.
Airworthiness Limitations Based on Type Design
The FAA recently became aware of an issue related to the
applicability of ADs that require incorporation of an ALS revision into
an operator's maintenance or inspection program.
Typically, when these types of ADs are issued by civil aviation
authorities of other countries, they apply to all airplanes covered
under an identified type certificate (TC). The corresponding FAA AD
typically retains applicability to all of those airplanes.
In addition, U.S. operators must operate their airplanes in an
airworthy condition, in accordance with 14 CFR 91.7(a). Included in
this obligation is the requirement to perform any maintenance or
inspections specified in the ALS, and in accordance with the ALS as
specified in 14 CFR 43.16 and 91.403(c), unless an alternative has been
approved by the FAA.
When a TC is issued for a type design, the specific ALS, including
revisions, is a part of that type design, as specified in 14 CFR
21.31(c).
The sum effect of these operational and maintenance requirements is
an obligation to comply with the ALS defined in the type design
referenced in the manufacturer's conformity statement. This obligation
may introduce a conflict with an AD that requires a specific ALS
revision if new airplanes are delivered with a later revision as part
of their type design.
To address this conflict, the FAA has approved alternative methods
of compliance (AMOCs) that allow operators to incorporate the most
recent ALS revision into their maintenance/inspection programs, in lieu
of the ALS revision required by the AD. This eliminates the conflict
and enables the operator to comply with both the AD and the type
design.
However, compliance with AMOCs is normally optional, and we
recently became aware that some operators choose to retain the AD-
mandated ALS revision in their fleet-wide maintenance/inspection
programs, including those for new airplanes delivered with later ALS
revisions, to help standardize the maintenance of the fleet. To ensure
that operators comply with the applicable ALS revision for newly
delivered airplanes containing a later revision than that specified in
an AD, we plan to limit the applicability of ADs that mandate ALS
revisions to those airplanes that are subject to an earlier revision of
the ALS, either as part of the type design or as mandated by an earlier
AD.
For purposes of this NPRM, in order to ensure that affected
airplanes are
[[Page 28022]]
maintained in accordance with mandatory instructions and airworthiness
limitations, this NPRM includes the limitations specified in Airbus 330
ALS Part 2, DT-ALI, Variation 1.1, dated December 15, 2015; and Airbus
330 ALS Part 2, DT-ALI, Variation 1.2, dated May 27, 2016. This NPRM,
therefore, applies to Model A330-200, -200 Freighter, and -300 series
airplanes with an original certificate of airworthiness or original
export certificate of airworthiness that was issued on or before May
27, 2016, the date of approval of Airbus 330 ALS Part 2, DT-ALI,
Variation 1.2. Operators of airplanes with an original certificate of
airworthiness or original export certificate of airworthiness issued
after that date must comply with the airworthiness limitations
specified as part of the approved type design and referenced on the
type certificate data sheet.
Costs of Compliance
We estimate that this proposed AD affects 101 airplanes of U.S.
registry.
The actions required by AD 2014-17-06, and retained in this
proposed AD, take about 1 work-hour per product, at an average labor
rate of $85 per work-hour. Required parts cost about $0 per product.
Based on these figures, the estimated cost of the actions that are
required by AD 2014-17-06 is $85 per product.
We also estimate that it would take about 1 work-hour per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $0 per
product. Based on these figures, we estimate the cost of this proposed
AD on U.S. operators to be $8,585, or $85 per product.
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:
0
a. Removing Airworthiness Directives (AD) 2001-16-01, Amendment 39-
12369 (66 FR 40874, August 6, 2001); and AD 2014-17-06, Amendment 39-
17959 (79 FR 52181, September 3, 2014); and
0
b. Adding the following new AD:
Airbus: Docket No. FAA-2017-0561; Directorate Identifier 2016-NM-
141-AD.
(a) Comments Due Date
We must receive comments by August 4, 2017.
(b) Affected ADs
This AD replaces AD 2001-16-01, Amendment 39-12369 (66 FR 40874,
August 6, 2001) (``AD 2001-16-01''); and AD 2014-17-06, Amendment
39-17959 (79 FR 52181, September 3, 2014) (``AD 2014-17-06'').
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category,
with an original certificate of airworthiness or original export
certificate of airworthiness issued on or before May 27, 2016.
(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.
(d) Subject
Air Transport Association (ATA) of America Code 05, Periodic
inspections.
(e) Reason
This AD was prompted by a determination that more restrictive
maintenance instructions and airworthiness limitations are
necessary. We are issuing this AD to detect and correct fatigue
cracking, damage, and corrosion in a certain structure, which could
result in reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Requirement: Maintenance or Inspection Program Revision,
With a New Terminating Action
This paragraph restates the requirements of paragraph (i) of AD
2014-17-06, with a new terminating action. Accomplishing the
revision required by paragraph (j) of this AD terminates the
requirements of this paragraph.
(1) Within 3 months after October 8, 2014 (the effective date of
AD 2014-17-06): Revise the maintenance or inspection program, as
applicable, by incorporating Airbus Document AI/SE-M4/95A.0089/97,
``A330 Airworthiness Limitation Items,'' Issue 19, dated March 23,
2012; ``Variation to Issue 19 of ALI Document (referenced in ALS
Part 2) Damage Tolerant Airworthiness Limitation Items (DT ALI),''
variation reference 0GVLG120018/C0S, dated October 24, 2012; and
``Variation to Issue 19 of ALI Document (referenced in ALS Part 2)
Damage Tolerant Airworthiness Limitation Items (DT ALI),'' variation
reference 0GVLG130002/C01, dated March 26, 2013.
(2) Comply with all applicable instructions and airworthiness
limitations included in Airbus Document AI/SE M4/95A.0089/97, ``A330
Airworthiness Limitation Items,'' Issue 19, dated March 23, 2012;
``Variation to Issue 19 of ALI Document (referenced in ALS Part 2)
Damage Tolerant Airworthiness Limitation Items (DT ALI),'' variation
reference 0GVLG120018/C0S, dated October 24, 2012; and ``Variation
to Issue 19 of ALI Document (referenced in ALS Part 2) Damage
Tolerant Airworthiness Limitation Items (DT ALI),'' variation
reference 0GVLG130002/C01, dated March 26, 2013. The initial
compliance times for the actions specified in Airbus Document AI/SE-
M4/95A.0089/97, ``A330 Airworthiness Limitation Items,''
[[Page 28023]]
Issue 19, dated March 23, 2012; ``Variation to Issue 19 of ALI
Document (referenced in ALS Part 2) Damage Tolerant Airworthiness
Limitation Items (DT ALI),'' variation reference 0GVLG120018/C0S,
dated October 24, 2012; and ``Variation to Issue 19 of ALI Document
(referenced in ALS Part 2) Damage Tolerant Airworthiness Limitation
Items (DT ALI),'' 0GVLG130002/C01, dated March 26, 2013; are at the
times specified in Airbus Document AI/SE-M4/95A.0089/97, ``A330
Airworthiness Limitation Items,'' Issue 19, dated March 23, 2012;
``Variation to Issue 19 of ALI Document (referenced in ALS Part 2)
Damage Tolerant Airworthiness Limitation Items (DT ALI),'' variation
ref. 0GVLG120018/C0S, dated October 24, 2012; and ``Variation to
Issue 19 of ALI Document (referenced in ALS Part 2) Damage Tolerant
Airworthiness Limitation Items (DT ALI),'' variation ref.
0GVLG130002/C01, dated March 26, 2013; or within 3 months after
October 8, 2014 (the effective date of AD 2014-17-06), whichever
occurs later.
(h) Retained Provision: Optional Compliance, With a New Terminating
Action
This paragraph restates the provision in paragraph (j) of AD
2014-17-06, with a new terminating action. Compliance with tasks
533021-02-01, 533021-02-02, and 533021-02-03, specified in
``Variation to Issue 19 of ALI Document (referenced in ALS Part 2)
Damage Tolerant Airworthiness Limitation Items (DT ALI),'' variation
ref. 0GVLG120022/C0S, dated December 21, 2012, may be used as a
method of compliance to tasks 533021-01-01, 533021-01-02, 533021-01-
03 specified in Section 2.2.1 and 2.2.2 of Section 2,
``Airworthiness Limitations,'' of Airbus Document AI/SE M4/95A.0089/
97, ``A330 Airworthiness Limitation Items,'' Issue 19, dated March
23, 2012. Accomplishing the revision required by paragraph (j) of
this AD terminates the provision specified in this paragraph.
(i) Retained Requirement: No Alternative Intervals or Limits, With a
New Exception
This paragraph restates the requirements of paragraph (k) of AD
2014-17-06, with a new exception. Except as provided by paragraph
(h) of this AD and as required by paragraph (j) of this AD, after
the maintenance or inspection program, as applicable, has been
revised as required by paragraph (g) of this AD, no alternative
actions (e.g., inspections) or intervals may be used unless the
actions or intervals are approved as an alternative method of
compliance (AMOC) under the provisions of paragraph (l)(1) of this
AD.
(j) New Requirement: Maintenance or Inspection Program Revision
Within 3 months after the effective date of this AD: Revise the
maintenance or inspection program, as applicable, by incorporating
the service information specified in paragraphs (j)(1), (j)(2), and
(j)(3) of this AD. The initial compliance times for the actions
specified in the service information referenced in paragraphs
(j)(1), (j)(2), and (j)(3) of this AD are the times specified in the
applicable service information, or within 3 months after the
effective date of this AD, whichever occurs later. Accomplishing the
revision specified in this paragraph terminates the requirements of
paragraph (g) of this AD and the provision specified in paragraph
(h) of this AD.
(1) Airbus A330 Airworthiness Limitations Section (ALS) Part 2,
Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision
01, issue 02, dated November 30, 2015.
(2) Airbus 330 ALS Part 2, DT-ALI, Variation 1.1, dated December
15, 2015.
(3) Airbus 330 ALS Part 2, DT-ALI, Variation 1.2, dated May 27,
2016.
(k) New Requirement: No Alternative Actions or Intervals
After the maintenance or inspection program, as applicable, has
been revised, as required by paragraph (j) of this AD, no
alternative actions (e.g., inspections) or intervals may be used
unless the actions or intervals are approved as an AMOC in
accordance with the procedures specified in paragraph (l)(1) 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 the attention of
the person identified in paragraph (m)(2) of this AD. 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.
(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 European Aviation Safety Agency
(EASA); or Airbus's EASA Design Organization Approval (DOA). If
approved by the DOA, the approval must include the DOA-authorized
signature.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2016-0152, dated July 27, 2016,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2017-0561.
(2) For more information about this AD, 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.
(3) 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 June 9, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-12614 Filed 6-19-17; 8:45 am]
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