[Federal Register Volume 83, Number 38 (Monday, February 26, 2018)]
[Proposed Rules]
[Pages 8201-8207]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-03599]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0113; Product Identifier 2017-NM-060-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2016-12-
09, for certain Airbus Model A330-200, -200 Freighter, and -300 series
airplanes; and Model A340-200 and -300 series airplanes. AD 2016-12-09
requires removing fasteners, doing a rototest inspection of fastener
holes, installing new fasteners, oversizing the holes and doing
rototest inspections for cracks if necessary, and repairing any
cracking that was found. Since we issued AD 2016-12-09, an evaluation
by the design approval holder (DAH) indicates that certain fastener
holes are subject to widespread fatigue damage (WFD). This proposed AD
would add airplanes to the effectivity, add repetitive inspections of
the fastener holes at frame (FR) 40, and, for certain airplanes,
require a modification, which terminates the inspections. We are
proposing this AD to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by April 12, 2018.
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 http://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: [email protected]; internet: http://www.airbus.com. You may view this referenced service information at the
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA.
For information on the availability of this material at the FAA, call
206-231-3195.
Examining the AD Docket
You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0113; 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 Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax: 206-231-3229.
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-2018-0113;
Product Identifier 2017-NM-060-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 http://www.regulations.gov, including any personal information you provide. We
[[Page 8202]]
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
Fatigue damage can occur locally, in small areas or structural
design details, or globally, in widespread areas. Multiple-site damage
is widespread damage that occurs in a large structural element such as
a single rivet line of a lap splice joining two large skin panels.
Widespread damage can also occur in multiple elements such as adjacent
frames or stringers. Multiple-site damage and multiple-element damage
cracks are typically too small initially to be reliably detected with
normal inspection methods. Without intervention, these cracks will
grow, and eventually compromise the structural integrity of the
airplane. This condition is known as WFD. It is associated with general
degradation of large areas of structure with similar structural details
and stress levels. As an airplane ages, WFD will likely occur, and will
certainly occur if the airplane is operated long enough without any
intervention.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. The WFD rule requires certain actions to
prevent structural failure due to WFD throughout the operational life
of certain existing transport category airplanes and all of these
airplanes that will be certificated in the future. For existing and
future airplanes subject to the WFD rule, the rule requires that DAHs
establish a limit of validity (LOV) of the engineering data that
support the structural maintenance program. Operators affected by the
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV
is approved.
The WFD rule does not require identifying and developing
maintenance actions if the DAHs can show that such actions are not
necessary to prevent WFD before the airplane reaches the LOV. Many
LOVs, however, do depend on accomplishment of future maintenance
actions. As stated in the WFD rule, any maintenance actions necessary
to reach the LOV will be mandated by airworthiness directives through
separate rulemaking actions.
In the context of WFD, this action is necessary to enable DAHs to
propose LOVs that allow operators the longest operational lives for
their airplanes, and still ensure that WFD will not occur. This
approach allows for an implementation strategy that provides
flexibility to DAHs in determining the timing of service information
development (with FAA approval), while providing operators with
certainty regarding the LOV applicable to their airplanes.
We issued AD 2016-12-09, Amendment 39-18558 (81 FR 38573, June 14,
2016) (``AD 2016-12-09''), for certain Airbus Model A330-200, -200
Freighter, and -300 series airplanes, and Model A340-200 and -300
series airplanes. AD 2016-12-09 was prompted by reports that cracks
were found on an adjacent hole of certain frames of the center wing box
(CWB). AD 2016-12-09 requires removing fasteners, doing a rototest
inspection of fastener holes, installing new fasteners, oversizing the
holes and doing rototest inspections for cracks if necessary, and
repairing any cracking that was found. We issued AD 2016-12-09 to
detect and correct cracking on certain holes of the CWB, which could
affect the structural integrity of the airplane.
Actions Since AD 2016-12-09 Was Issued
Since we issued AD 2016-12-09, an evaluation by the DAH indicates
that the fastener holes at FR40 of the inside and outside CWB (above
and below bottom skin) are subject to WFD.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0069, dated April 25, 2017 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Airbus Model A330-200, -200
Freighter, and -300 series airplanes, and Model A340-200 and -300
series airplanes. The MCAI states:
During accomplishment of A330 Airworthiness Limitation Item
(ALI) task 57-11-04 on the rear fitting of the Frame (FR) 40 between
stringers (STR) 38 and STR39 on both LH [left-hand] and RH [right-
hand] sides of the fuselage, cracks were found on an adjacent hole.
After reaming at second oversize of the subject hole, the crack was
still present. As a result of a sampling inspection program,
additional crack findings were reported on this adjacent hole on
other A330 and A340 aeroplanes.
This condition, if not detected and corrected, could affect the
structural integrity of the centre fuselage of the aeroplane.
Prompted by these findings, EASA issued AD 2014-0149 [which
corresponds to FAA AD 2016-12-09] to require removal of the
fasteners and repetitive Special Detailed Inspection (SDI) of
fastener holes at FR40 vertical web above or below Centre Wing Box
(CWB) lower panel reference on both LH and RH sides of the fuselage,
and, depending on findings, accomplishment of the applicable
corrective actions. That [EASA] AD excluded certain aeroplanes from
the Applicability, on which Airbus modification (mod) 55792 or mod
55306 had been embodied in production.
Since EASA AD 2014-0149 was issued, prompted by complementary
fatigue analyses correlated with in-service findings, Airbus
published Service Bulletin (SB) A330-57-3115 Revision 01 and SB
A340-57-4124 Revision 02, which introduced revised thresholds and
intervals for the repetitive inspections of the inside CWB (above
bottom skin), and an alleviation of the number of holes to be
inspected, for post-mod 44360 and pre-mod 55306 configuration
aeroplanes.
In addition, for aeroplanes in post-mod 44360, post-mod 55306
and pre-mod 205225 configuration, Airbus developed mod 206051,
introducing reinforcement of the structural integrity of the inside
CWB (above bottom skin) area, and published associated Airbus SB
A330-57-3129 and SB A340-57-4136, as applicable, which avoids the
need for required repetitive inspections for the inside of the CWB.
Finally, Airbus published SB A330-57-3116 Revision 01 and SB
A330-57-4125 Revision 01, as applicable, to expand their Effectivity
to include aeroplanes in post-mod 44360 and post-mod 49202
configuration for inspections of the outside CWB (below bottom
skin), and introduced revised thresholds and intervals for the
repetitive inspections of the outside CWB, and to provide an
alleviation of the number of holes to be inspected. The repetitive
inspection program for aeroplanes in pre-mod 44360 configuration
remains unchanged.
For the reasons described above, this [EASA] AD partially
retains the requirements of EASA AD 2014-0149, which is superseded,
and requires new repetitive inspections of the fastener holes at
FR40 of the inside and the outside CWB (above and below bottom
skin), and the implementation of the modification of the inside CWB,
as terminating action of the repetitive SDI.
Required actions also include oversizing certain holes, installing
new fasteners, and repairing any cracking that is found.
The compliance times for the inspections range depending on
airplane operation and utilization. The earliest initial flight-cycle
compliance time is 13,500 flight cycles. The earliest initial flight-
hour compliance time is 57,000 flight hours. The latest initial flight-
cycle compliance time is 30,900 flight cycles. The latest initial
flight-hour compliance time is 162,000 flight hours. The earliest
repetitive flight-cycle compliance time is 5,950 flight cycles. The
earliest repetitive flight-hour compliance time is 24,300 flight hours.
The latest repetitive flight-cycle compliance time is 7,400 flight
cycles. The latest repetitive flight-hour compliance time is 40,400
flight hours. You may examine the MCAI in the AD docket on the internet
at http://www.regulations.gov by searching for and locating Docket No.
FAA-2018-0113.
[[Page 8203]]
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information. This service
information describes procedures for removing the fasteners and doing a
repetitive rototest inspection of fastener holes at FR40 vertical web
on both sides, checking for the existence of a repair done as specified
by a repair design approval sheet (RDAS), installing new fasteners in
transition fit, oversizing the holes, and repairing any crack found.
This service information is distinct because it applies to different
airplane models and configurations.
Airbus Service Bulletin A330-57-3114, Revision 01, dated
January 13, 2017.
Airbus Service Bulletin A330-57-3115, Revision 01,
including Appendices 01 and 02, dated November 23, 2016.
Airbus Service Bulletin A330-57-3116, Revision 01,
including Appendices 01 and 02, dated November 23, 2016.
Airbus Service Bulletin A340-57-4123, Revision 01, dated
January 13, 2017.
Airbus Service Bulletin A340-57-4124, Revision 02,
including Appendices 01 and 02, dated November 23, 2016.
Airbus Service Bulletin A340-57-4125, Revision 01,
including Appendices 01 and 02, dated November 23, 2016.
Airbus has also issued the following service information. This
service information describes procedures for modification of certain
fastener holes. The modification includes a rotating probe inspection
for cracking, related investigative actions (checks of the hole
diameter), and corrective actions (repair). This service information is
distinct because it applies to different airplane models and
configurations.
Airbus Service Bulletin A330-57-3129, dated October 5,
2016.
Airbus Service Bulletin A330-57-3130, dated November 23,
2016.
Airbus Service Bulletin A330-57-3131, dated November 23,
2016.
Airbus Service Bulletin A330-57-3132, including Appendices
01 and 02, dated November 23, 2016.
Airbus Service Bulletin A340-57-4136, dated October 5,
2016.
Airbus Service Bulletin A340-57-4137, dated November 23,
2016.
Airbus Service Bulletin A340-57-4138, dated November 23,
2016.
Airbus Service Bulletin A340-57-4139, including Appendices
01 and 02, dated November 23, 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 these
same type designs.
Explanation of a Certain Compliance Time
The compliance time for the replacement specified in this proposed
AD for addressing WFD was established to ensure that discrepant
structure is replaced before WFD develops in airplanes. Standard
inspection techniques cannot be relied on to detect WFD before it
becomes a hazard to flight. We will not grant any extensions of the
compliance time to complete any AD-mandated service bulletin related to
WFD without extensive new data that would substantiate and clearly
warrant such an extension.
Costs of Compliance
We estimate that this proposed AD affects 99 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
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Inspection (retained actions 78 work-hours x $85 $0.................. $6,630 per $232,050 per
from AD 2016-12-09) (35 per hour = $6,630 per inspection inspection
airplanes). inspection cycle. cycle. cycle.
Inspection (new proposed Up to 257 work-hours x $0.................. Up to $21,845 Up to $2,162,655
action) (99 airplanes). $85 per hour = per inspection per inspection
$21,845 per cycle. cycle.
inspection cycle.
Modification (new proposed Up to 136 work-hours x Up to $1,070........ Up to $12,630... Up to
action) (Up to 99 airplanes). $85 per hour = $1,250,370.
$11,560.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary on-condition
actions that would be required based on the results of the proposed
inspection. We have no way of determining the number of aircraft that
might need these actions:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
---------------------------------------------------------------------------------------------------------------
Oversize, installation, and Up to 105 work-hours Up to $21,560............ Up to $30,485............
inspection. x $85 per hour =
$8,925.
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We have received no definitive data that would enable us to provide
cost estimates for the on-condition repairs specified in this proposed
AD.
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
[[Page 8204]]
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.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes to the Director of the System Oversight
Division.
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 removing Airworthiness Directive (AD)
2016-12-09, Amendment 39-18558 (81 FR 38573, June 14, 2016), and adding
the following new AD:
Airbus: Docket No. FAA-2018-0113; Product Identifier 2017-NM-060-AD.
(a) Comments Due Date
We must receive comments by April 12, 2018.
(b) Affected ADs
This AD replaces AD 2016-12-09, Amendment 39-18558 (81 FR 38573,
June 14, 2016) (``AD 2016-12-09'').
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(5) of this AD, certificated in any category, all
manufacturer serial numbers, except those on which Airbus Repair
Instructions R57115092 have been embodied in service on both right-
hand (RH) and left-hand (LH) sides.
(1) Model A330-201, -202, -203, -223, and -243 airplanes.
(2) Model A330-223F and -243F airplanes.
(3) Model A330-301, -302, -303, -321, -322, -323, -341, -342,
and -343 airplanes.
(4) Model A340-211, -212, and -213 airplanes.
(5) Model A340-311, -312, and -313 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports that cracks were found on an
adjacent hole of certain frames of the center wing box (CWB). We are
issuing this AD to detect and correct cracking of certain holes of
certain frames of the CWB, which could affect the structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Service Information
(1) For the actions required by paragraphs (h), (i), and (j) of
this AD, use the applicable service information specified in
paragraphs (g)(1)(i) through (g)(1)(vi) of this AD.
(i) Airbus Service Bulletin A330-57-3114, Revision 01, dated
January 13, 2017 (CWB inspection area: Below) (for Model A330-300
series airplanes in pre-modification 44360 configuration).
(ii) Airbus Service Bulletin A330-57-3115, Revision 01,
including Appendices 01 and 02, dated November 23, 2016 (CWB
inspection area: Above) (for Model A330-200 and -300 series
airplanes in pre-modification 55306 and pre-modification 55792
configuration).
(iii) Airbus Service Bulletin A330-57-3116, Revision 01,
including Appendices 01 and 02, dated November 23, 2016 (CWB
inspection area: Below) (for Model A330-200 and -300 series
airplanes in post-modification 44360 configuration).
(iv) Airbus Service Bulletin A340-57-4123, Revision 01, dated
January 13, 2017 (CWB inspection area: Below) (for Model A340-200
and -300 series airplanes in pre-modification 44360 configuration).
(v) Airbus Service Bulletin A340-57-4124, Revision 02, including
Appendices 01 and 02, dated November 23, 2016 (CWB inspection area:
Above) (for Model A340-200 and -300 series airplanes in pre-
modification 55306 and pre-modification 55792 configuration).
(vi) Airbus Service Bulletin A340-57-4125, Revision 01,
including Appendices 01 and 02, dated November 23, 2016 (CWB
inspection area: Below) (for Model A340-200 and -300 series
airplanes in post-modification 44360 configuration).
(2) For the modification required by paragraph (o)(1) of this
AD, use the applicable service information specified in paragraphs
(g)(2)(i) through (g)(2)(vi) of this AD.
(i) Airbus Service Bulletin A330-57-3130, dated November 23,
2016 (for Model A330-200 and -300 series airplanes in post-
modification 44360, post-Airbus Service Bulletin A330-57-3131, and
pre-modification 49202 configuration).
(ii) Airbus Service Bulletin A330-57-3131, dated November 23,
2016 (for Model A330-200 and -300 series airplanes in post-
modification 44360 and pre-modification 55306 configuration).
(iii) Airbus Service Bulletin A330-57-3132, including Appendices
01 and 02, dated November 23, 2016 (for Model A330-200 and -300
series airplanes in post-modification 44360 configuration).
(iv) Airbus Service Bulletin A340-57-4137, dated November 23,
2016 (for Model A340-200 and -300 series airplanes in post-
modification 44360, post-Airbus Service Bulletin A340-57-4138, and
pre-modification 49202 configuration).
(v) Airbus Service Bulletin A340-57-4138, dated November 23,
2016 (for Model A340-200 and -300 series airplanes in post-
modification 44360 and pre-modification 55306 configuration).
(vi) Airbus Service Bulletin A340-57-4139, including Appendices
01 and 02, dated November 23, 2016 (for Model A340-200 and -300
series airplanes in post-modification 44360 configuration).
(h) Repetitive Inspections and Certain Repairs
Except as specified in paragraphs (l)(2), (l)(3), (p) of this
AD: Before exceeding the applicable threshold specified in paragraph
1.E., ``Compliance'' of the applicable service information specified
in paragraph (g)(1) of this AD, or within the compliance time
specified in table 1 to paragraph (h) of this AD, whichever occurs
later; remove the fasteners and accomplish a special detailed
inspection (SDI) of the fastener holes at frame (FR) 40 vertical
web, on both LH and RH sides, of the affected CWB lower panel area,
and, as applicable, check for the existence of a repair done as
specified by a repair design approval sheet (RDAS), in accordance
with the Accomplishment Instructions of the
[[Page 8205]]
applicable service information specified in paragraph (g)(1) of this
AD, and if any RDAS repair is found before further flight, repair
using a method approved by the Manager, International Section,
Transport Standards Branch, 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. Repeat the SDI thereafter at the applicable intervals
specified in paragraph 1.E., ``Compliance,'' of the applicable
service information identified in paragraph (g)(1) of this AD.
[GRAPHIC] [TIFF OMITTED] TP26FE18.000
(i) Follow-On Actions: No Cracking
If no crack is found during any inspection required by paragraph
(h) of this AD: Before further flight, install new fasteners in the
transition fit, in accordance with the Accomplishment Instructions
of the applicable service information specified in paragraph (g)(1)
of this AD.
(j) Follow-On Actions: Cracking
If any crack is found during any inspection required by
paragraph (h) of this AD: Before further flight, oversize the holes
to the first oversize in comparison with the current hole diameter,
and do an SDI for cracks, in accordance with the Accomplishment
Instructions of the applicable service information identified in
paragraph (g)(1) of this AD.
(1) If no cracking is found during the SDI required by the
introductory text of paragraph (j) of this AD: Before further
flight, install new fasteners in the transition fit, in accordance
with the Accomplishment Instructions of the applicable service
information identified in paragraph (g)(1) of this AD.
(2) If any cracking is found during the SDI required by the
introductory text of paragraph (j) of this AD: Before further
flight, repair using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA
DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
(k) No Reporting Required
Although the applicable service information specified in
paragraph (g)(1) of this AD specifies to submit certain information
to the manufacturer, and specifies that action as ``RC'' (Required
for Compliance), this AD does not include that requirement.
(l) Exceptions to Service Information
(1) Where the applicable service information identified in
paragraphs (g) and (m) of this AD specifies contacting Airbus for
appropriate action: Before further flight, repair using a method
approved by the Manager, International Section, Transport Standards
Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA,
the approval must include the DOA-authorized signature.
(2) Where paragraph 1.E., ``Compliance,'' of the applicable
service information specified in paragraph (g)(1) of this AD
specifies a compliance time in terms of a ``Threshold'' and ``Grace
Period,'' this AD requires compliance at the later of the applicable
threshold and grace period.
(3) When it is determined that no RDAS is found to exist for the
FR40 area it is acceptable to accomplish the first SDI before
exceeding the applicable threshold, instead of ``before next
flight'', as specified in the applicable service information
specified in paragraph (g)(1)(ii), (g)(1)(iii), (g)(1)(v) and
(g)(1)(vi) of this AD.
(m) Modification for Airplanes in Post-Modification 55306 and Pre-
Modification 205225 Configuration
For airplanes in post-modification 55306 and pre-modification
205225 configuration: Before exceeding the applicable compliance
time specified in table 2 to paragraph (m) of this AD, as
applicable, or within 18 months after the effective date of this AD,
whichever occurs later; modify the inside CWB (above bottom skin),
including doing a rotating probe inspection for cracking and all
applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-57-3129, dated October 5, 2016; or Airbus Service
Bulletin A340-57-4136, dated October 5, 2016; as applicable; except
as required by paragraph (l)(1) of this AD. Do all applicable
related investigative and corrective actions before further flight.
[[Page 8206]]
[GRAPHIC] [TIFF OMITTED] TP26FE18.001
(n) Terminating Action for Certain Airworthiness Limitation Item (ALI)
Tasks
(1) Accomplishment on an airplane of the initial and repetitive
inspections required by paragraph (h) of this AD terminates the
requirements of ALI task 57-11-02 and task 57-11-04 of the
applicable Airbus Airworthiness Limitation Section (ALS) Part 2,
Damage Tolerant (DT) ALI, for that airplane.
(2) Modification of an airplane as required by paragraph (m) of
this AD terminates the requirements of ALI task 57-11-02 of the
applicable Airbus ALS Part 2, DT ALI, for that airplane.
(o) Terminating Action for Repetitive SDI Inspections
(1) Modification of a post-modification 44360 airplane by
multiple cold working, including doing a rotating probe inspection
for cracking and all applicable related investigative and corrective
actions, in accordance with the Accomplishment Instructions of the
applicable Airbus service information specified in paragraph (g)(2)
of this AD, except as required by paragraph (l)(1) of this AD,
constitutes terminating action for the repetitive SDI required by
paragraph (h) of this AD for that airplane, provided the
modification is accomplished within the applicable compliance times
specified in the applicable Airbus service information specified in
paragraph (g)(1) of this AD.
(2) If, during any inspection of a post-modification 44360
airplane, as required by paragraph (h) of this AD, a crack
previously repaired by an Airbus RDAS is detected only on the LH or
RH side, it is permitted to do the modification specified in
paragraph (o)(1) of this AD on the non-repaired side. Doing the
modification constitutes terminating action for the repetitive SDI
required by paragraph (h) of this AD on the modified side only.
(p) Extension to Compliance Time for Certain Airplanes
For post-modification 44360 airplanes and pre-modification 55306
airplanes that have been inspected before the effective date of this
AD as required by AD 2016-12-09: It is permitted to defer the next
due inspection to 18 months after the effective date of this AD,
provided the previous inspection interval, as applicable, depending
on airplane configuration and utilization, as specified in the
service information used in the previous inspection is not exceeded.
(q) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraphs (h) through (j) of this AD, if those actions were
performed before the effective date of this AD using the applicable
service information specified in paragraphs (q)(1)(i) through
(q)(1)(vi) of this AD. This service information was incorporated by
reference in AD 2016-09-11, Amendment 39-18509 (81 FR 27986, May 9,
2016).
(i) Airbus Service Bulletin A330-57-3114, dated March 12, 2013.
(ii) Airbus Service Bulletin A330-57-3115, April 4, 2013.
(iii) Airbus Service Bulletin A330-57-3116, dated March 12,
2013.
(iv) Airbus Service Bulletin A340-57-4123, dated March 12, 2013.
(v) Airbus Service Bulletin A340-57-4124, Revision 01, dated
August 22, 2013.
(vi) Airbus Service Bulletin A340-57-4125, dated March 12, 2013.
(2) This paragraph provides credit for the actions required by
paragraphs (h) through (j) of this AD, if those actions were
performed before the effective date of this AD using Airbus Service
Bulletin A340-57-4124, dated April 4, 2013. This service information
is not incorporated by reference in this AD.
(3) This paragraph provides credit for the actions required by
paragraphs (h) through (j) of this AD, if those actions were
performed before the effective date of this AD using the applicable
service information specified in paragraphs (q)(3)(i) through
(q)(3)(viii) of this AD. This service information is not
incorporated by reference in this AD.
(i) Airbus Technical Disposition LR57D11023270, Issue B, dated
July 12, 2011.
(ii) Airbus Technical Disposition LR57D11029170, Issue C, dated
September 6, 2011.
(iii) Airbus Technical Disposition LR57D11029171, Issue B, dated
September 6, 2011.
(iv) Airbus Technical Disposition LR57D11029172, Issue B, dated
September 6, 2011.
(v) Airbus Technical Disposition LR57D11029173, Issue B, dated
September 6, 2011.
(vi) Airbus Technical Disposition LR57D11023714, Issue B, dated
July 12, 2011.
(vii) Airbus Technical Disposition LR57D11030740, Issue C, dated
September 22, 2011.
(viii) Airbus Technical Disposition LR57D11030741, Issue B,
dated September 22, 2011.
(r) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, 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 International Section, send it to the
attention of the person identified in paragraph (s)(2) of this AD.
Information may be emailed to: [email protected].
Before using any approved AMOC, notify your appropriate
[[Page 8207]]
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 Section, Transport Standards
Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA,
the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraphs (k) and (l)(1) of this AD: If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(s) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0069, dated April 25, 2017, for related
information. This MCAI may be found in the AD docket on the internet
at http://www.regulations.gov by searching for and locating Docket
No. FAA-2018-0113.
(2) For more information about this AD, contact, Vladimir
Ulyanov, Aerospace Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198;
telephone and fax: 206-231-3229.
(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: [email protected];
internet: http://www.airbus.com. You may view this service
information at the FAA, Transport Standards Branch, 2200 South 216th
St., Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195.
Issued in Renton, Washington, on February 14, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-03599 Filed 2-23-18; 8:45 am]
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