Airworthiness Directives; Airbus Airplanes, 13387-13395 [2018-05019]
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(iv) With the t-bolt in the 12 o’clock
position, visually inspect the coupling for the
attachment of the outer band to the v-retainer
coupling segments by inspecting for gaps
between the outer band and the v-retainer
coupling segments between approximately
the 1 o’clock through 11 o’clock position. It
is recommended to use backlighting to see
gaps. If gaps between the outer band and the
v-retainer coupling segments are found, do
not re-install the v-band coupling. Before
further flight, you must install a new v-band
coupling and restart the hours TIS for the
repetitive replacement of the v-band
coupling.
(v) Visually inspect the bend radii of the
coupling v-retainer coupling segments for
cracks. Inspect the radii throughout the
length of the segment. See figure 1 to
paragraphs (k)(1)(iii) and (v) of this AD. If
any cracks are found, do not re-install the vband coupling. Before further flight, you
must install a new v-band coupling and
restart the hours TIS for the repetitive
replacement of the v-band coupling.
(vi) Visually inspect the outer band
opposite the t-bolt for damage (distortion,
creases, bulging, or cracks), which may be
caused from excessive spreading of the
coupling during installation and/or removal.
If any damage is found, do not re-install the
v-band coupling. Before further flight, you
must install a new v-band coupling and
restart the hours TIS for the repetitive
replacement of the v-band coupling.
(2) If the removed exhaust tailpipe v-band
coupling passes all of the inspection steps
listed in paragraphs (k)(1)(i) through (vi) of
this AD, you may re-install the same v-band
coupling. After the coupling is re-installed
and torqued as specified in Replacement of
the V-Band Coupling, paragraph (i) of this
AD, verify there is space between each vretainer coupling segment below the t-bolt. If
there is no space between each v-retainer
coupling segment below the t-bolt, before
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further flight, you must install a new v-band
coupling and restart the hours TIS for the
repetitive replacement of the v-band
coupling.
(3) The inspections required in paragraphs
(k)(1) and (2) of this AD only apply to reinstalling the same exhaust tailpipe v-band
coupling that was removed as specified in
paragraph (j) of this AD. It does not apply to
installation of a new v-band coupling. These
inspections do not terminate the 500-hour
TIS repetitive replacement of the v-band
coupling and do not restart the hours TIS for
the repetitive replacement of the v-band
coupling.
(4) As of May 3, 2018 (the effective date of
this AD), do not install a used exhaust
tailpipe v-band coupling on the airplane
except for the reinstallation of the inspected
exhaust tailpipe v-band coupling that was
removed as specified in paragraphs (j) and (k)
of this AD.
(l) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Wichita ACO Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. The Manager,
Chicago ACO Branch, FAA, has the authority
to approve AMOCs concerning STC
SA1035WE, 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 Wichita ACO Branch,
send it to the attention of the person
identified in paragraph (m) of this AD. If
sending information directly to the manager
of the Chicago ACO Branch, send it to the
attention of John Tallarovic, Aerospace
Engineer, AIR–7C3 Chicago ACO Branch,
2300 East Devon Avenue, Des Plaines, IL
60018–4696; telephone: (847) 294–8180; fax:
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(847) 294–7834; email: john.m.tallarovic@
faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(m) Related Information
For more information about this AD,
contact Thomas Teplik, Aerospace Engineer,
Wichita ACO Branch, FAA, 1801 Airport
Road, Room 100, Wichita, Kansas 67209;
phone: (316) 946–4196; fax: (316) 946–4107;
email: thomas.teplik@faa.gov.
(n) Material Incorporated by Reference
None.
Issued in Kansas City, Missouri, on March
20, 2018.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division,
Aircraft Certification Service.
[FR Doc. 2018–06092 Filed 3–28–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0902; Product
Identifier 2016–NM–188–AD; Amendment
39–19224; AD 2018–06–04]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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Federal Register / Vol. 83, No. 61 / Thursday, March 29, 2018 / Rules and Regulations
13388
ACTION:
Federal Register / Vol. 83, No. 61 / Thursday, March 29, 2018 / Rules and Regulations
Final rule.
We are superseding
Airworthiness Directive (AD) 2004–03–
07, which applied to certain Airbus
Model A320–111, –211, –212, and –231
series airplanes. AD 2004–03–07
required repetitive inspections for
fatigue cracking around the fasteners
attaching the pressure panel to the
flexible bracket at a certain frame (FR),
adjacent to the longitudinal beams on
the left and right sides of the airplane;
and repair as necessary. This new AD
retains certain requirements of AD
2004–03–07, expands the applicability,
and requires an inspection of the
fastener holes on the pressure panel and
modification or repair as applicable.
This AD was prompted by fatigue tests
which revealed cracking around the
fasteners attaching the pressure panel to
the flexible bracket, and by the
discovery of additional cracks under the
longitudinal beams at locations that are
not included in the inspection area
required by AD 2004–03–07. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective May 3, 2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of May 3, 2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of March 15, 2004 (69 FR
5907, February 9, 2004).
ADDRESSES: For service information
identified in this final rule, contact
Airbus, Airworthiness Office—EIAS, 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5
61 93 36 96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
internet https://www.airbus.com. 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. It is also available
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0902.
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SUMMARY:
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–
0902; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
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other information. The address for the
Docket Office (telephone 800–647–5527)
is Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone 206–231–3223; fax 206–231–
3398.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2004–03–07,
Amendment 39–13451 (69 FR 5907,
February 9, 2004) (‘‘AD 2004–03–07’’).
AD 2004–03–07 applied to certain
Airbus Model A320–111, –211, –212,
and –231 series airplanes. The NPRM
published in the Federal Register on
October 6, 2017 (82 FR 46729). The
NPRM was prompted by fatigue tests
which revealed cracking around the
fasteners attaching the pressure panel to
the flexible bracket at FR 36, adjacent to
the longitudinal beams on the left and
right sides of the airplane, and by the
discovery of additional cracks under the
longitudinal beams at locations that are
not included in the inspection area
required by AD 2004–03–07. The NPRM
proposed to continue to require certain
requirements of AD 2004–03–07. The
NPRM also proposed to expand the
applicability and require an inspection
of the fastener holes on the pressure
panel between FR 35 and FR 36 under
the longitudinal beam and modification
or repair as applicable. We are issuing
this AD to detect and correct fatigue
cracking around the fasteners attaching
the pressure panel to the flexible bracket
at the FR 36 adjacent to the longitudinal
beams, which could result in reduced
structural integrity of the airplane and
possible rapid decompression of the
airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2016–0206, dated October 13,
2016; corrected October 14, 2016
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for certain Airbus Model
A318 and Model A319 series airplanes,
Model A320–211, –212, –214, –231,
–232, and –233 airplanes, and Model
A321–111, –112, –131,–211, –21–, 213,
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–231, and –232 airplanes. The MCAI
states:
During fatigue tests, cracks were found
around the fasteners connecting the pressure
panel with the flexible bracket at fuselage
frame (FR) 36, adjacent to the longitudinal
beams on left-hand (LH) and right-hand (RH)
sides.
This condition, if not detected and
corrected, could impair the structural
integrity of the aeroplane.
To address this unsafe condition, DGAC
´ ´
[Direction Generale de l’Aviation Civile]
France issued [French] AD 2000–531–155(B)
[which corresponds with FAA AD 2004–03–
07] to require repetitive inspections of the
longitudinal beams of the FR 36 pressure
panel and, depending on findings, the
accomplishment of a repair.
Since that [French] AD was issued,
additional cracks have been found under the
beams, but in locations not covered by the
required inspections. Fatigue and damage
tolerance analyses were performed, the
results of which indicated that all the holes
in the pressure panel above all the
longitudinal beams have to be cold worked.
For the reasons described above, this
[EASA] AD retains the requirements of DGAC
France AD 2000–531–155(B), which is
superseded, extends the applicability to all
A320 family aeroplanes and requires [a
special detailed inspection of the fastener
holes on the pressure panel between FR35
and FR36 under the longitudinal beam and]
modification [or repair] of all the affected
holes.
This [EASA] AD is republished to correct
the number of the superseded DGAC AD.
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–
0902.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To Remove Reporting
Requirement
United Airlines (UAL) requested that
we omit paragraph (k)(2)(ii) of the
proposed AD, which would require
operators to report any findings of
cracking that exceeded the limits
specified in Airbus Service Bulletin
A320–53–1264, Revision 01, excluding
Appendix 01, dated July 4, 2016, from
the proposed AD. UAL stated that
paragraph (k)(2)(ii) of the proposed AD
is confusing and unjustified because
there is no explanation for why it is
required when it was not included in
EASA AD 2016–0206. UAL stated the
requirement to report findings in
paragraph (k)(2)(ii) is redundant with
the actions of paragraph (k)(2)(i) of the
proposed AD. UAL noted that for the
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crack repair specified in paragraph
(k)(2)(i) of the proposed AD, the
findings would be reported. UAL
suggested the paragraph (k)(2)(ii) of the
proposed AD required using an
unconventional means to report
findings that might require additional
procedures and training specific to the
proposed AD. UAL also stated that
restricting reporting to a website may
cause issues if the sender does not have
access and that Airbus Service Bulletin
A320–53–1264, Revision 01, excluding
Appendix 01, dated July 4, 2016, lists
alternative options for reporting, like
email, fax, or mail.
We agree to remove the reporting
requirement specified in paragraph
(k)(2)(ii) of the proposed AD from this
AD. Neither Airbus Service Bulletin
A320–53–1264, Revision 01, excluding
Appendix 01, dated July 4, 2016, nor the
MCAI specifically includes reporting to
a website as specified in paragraph
(k)(2)(ii) of the proposed AD. We note
that Airbus Service Bulletin A320–53–
1264, Revision 01, excluding Appendix
01, dated July 4, 2016, does include
reporting within the required for
compliance (RC) procedure for the
repair, which indicates that reporting
would be required regardless of whether
reporting was called out in the MCAI.
We also verified with EASA that
reporting should be done as defined in
the service information. However, we
have determined that a specific
reporting requirement is not necessary.
As stated by the commenter, operators
will report findings to obtain the repair,
which is specified in paragraph (k)(2)(i)
of the proposed AD. We have removed
paragraphs (k)(2)(i) and (k)(2)(ii) from
this AD and revised paragraph (k)(2) of
this AD to include the information that
was in paragraph (k)(2)(i) of the
proposed AD. We have also added
paragraph (n) to this AD to specify that
reporting is not required for this AD and
redesignated the subsequent paragraphs
accordingly.
Request To Refer to Latest Service
Information
Two commenters requested that we
refer to the latest service information.
UAL requested that we update
paragraph (k) of the proposed AD to use
Airbus Service Bulletin A320–53–1264,
Revision 02, dated March 14, 2017,
which corrects an error with the fastener
lengths for part number (P/N)
EN6115K3. We infer that UAL intended
to refer to Airbus Service Bulletin
A320–53–1240, Revision 02, dated
March 14, 2017, because there is no
Revision 02 for Airbus Service Bulletin
A320–53–1264, and because P/N
EN6115K3 is referenced in Airbus
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Service Bulletin A320–53–1240,
Revision 02, dated March 14, 2017.
Airbus requested that we refer to Airbus
Service Bulletin A320–53–1240,
Revision 02, dated March 14, 2017, in
the proposed AD.
We agree to refer to the latest service
information in this AD. In addition to
Airbus Service Bulletin A320–53–1240,
Revision 02, dated March 14, 2017, we
have also reviewed Airbus Service
Bulletin A320–53–1263, Revision 02,
excluding Appendix 01 and including
Appendix 02, dated December 6, 2017,
which updates kit information and
figures among other minor changes. We
have revised paragraph (k)(1) of this AD
accordingly. We have also provided
credit for Airbus Service Bulletin A320–
53–1240, Revision 01, dated April 4,
2016; and Airbus Service Bulletin
A320–53–1263, Revision 01, dated
February 29, 2016; in paragraphs
(o)(3)(ii) and (o)(3)(iv) of this AD,
respectively.
Request To Include Additional
Airplane Models in the Applicability
Airbus requested that Model A320–
215 and Model A320–216 airplanes be
in included in the applicability of the
proposed AD. The commenter noted
that these airplane models are included
in the MCAI.
We do not agree with the commenter’s
request. We have not certified Model
A320–215 airplanes for operation in the
U.S., and therefore, we did not include
that model in the applicability of this
AD. We did not include Model A320–
216 airplanes in the applicability of this
AD because the MCAI was already
added to the required airworthiness
action list (RAAL) for Model A320–216
airplanes. We have not changed this AD
in this regard.
Request To Revise Service Bulletin
Descriptions in the Related Service
Information Under 1 CFR Part 51
Paragraph in the Preamble of the
NPRM
Airbus stated that the proposed AD
identifies the means of inspection, i.e.,
rototest inspection, using three different
wordings in the descriptions of the
service bulletins specified in the Related
Service Information under 1 CFR part 51
paragraph in the preamble of the NPRM.
Airbus also stated that Service Bulletin
A320–53–1240, Revision 02, dated
March 14, 2017, no longer contains a
rototest inspection requirement. In
addition, Airbus noted that Service
Bulletin A320–53–1240, Revision 02,
dated March 14, 2017, does not contain
repair instructions. We infer the
commenter is requesting that we revise
the service bulletin descriptions in the
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Related Service Information under 1
CFR part 51 paragraph in the preamble
of the NPRM.
We acknowledge the description of
the rototest inspection is different for
each service bulletin specified in the
Related Service Information under 1
CFR part 51 paragraph in the preamble
of the NPRM. In the NPRM, we matched
the description of the inspection as
given in each service bulletin specified
in the Related Service Information
under 1 CFR part 51 paragraph. We have
revised the description of Airbus
Service Bulletin A320–53–1240,
Revision 02, dated March 14, 2017, to
remove the reference to an inspection
and repair.
Request To Clarify What Prompted the
Proposed AD
Airbus requested that we revise
paragraph (e) of the proposed AD to
clarify that the proposed AD was
prompted by a report of cracking in an
additional area. Airbus stated that
paragraph (e) of the proposed AD
describes only the fatigue test results
that prompted AD 2004–03–07.
We agree to revise paragraph (e) of
this AD for clarity. This AD was
prompted by the original report of
cracking and the additional report. We
have revised paragraph (e) of this AD to
include the additional cracking that
prompted the issuance of this AD.
Request To Revise Repair Language in
Paragraph (k)(2)(i) of the Proposed AD
Airbus requested that we revise the
language in paragraph (k)(2)(i) of the
proposed AD, which specifies to repair
any cracking in accordance with Airbus
Service Bulletin A320–53–1264,
Revision 01, excluding Appendix 01,
dated July 4, 2016. Airbus stated that
this service information does not
provide direct repair instructions and
instead specifies to contact Airbus.
We agree to clarify the language in
paragraph (k)(2) of this AD (which
corresponds with paragraph (k)(2)(i) of
the proposed AD). Paragraph (k)(2) of
this AD also specifies that where Airbus
Service Bulletin A320–53–1264,
Revision 01, excluding Appendix 01,
dated July 4, 2016, specifies to contact
Airbus for appropriate action, and
specifies that action as ‘‘RC’’ (Required
for Compliance), operators must request
approval of repair instructions using a
method approved in accordance with
the procedures specified in paragraph
(p)(2) of this AD, and accomplish the
repair accordingly within the
compliance time specified in those
instructions. We have not changed this
AD in this regard.
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Request To Include Wording From the
MCAI in Paragraph (m)(1)(iii) of the
Proposed AD
Airbus requested that we revise
paragraph (m)(1)(iii) of the proposed
AD. Airbus stated the wording is similar
to paragraph (9) of the MCAI except that
the important wording ‘‘in accordance
with Airbus approved instructions that
identify the repair as technically
equivalent to the accomplishment of
Airbus SB A320–53–1240 or SB A320–
53–1263’’ is omitted.
We disagree with the commenter’s
request. The intent of paragraph
(m)(1)(iii) of this AD is to obtain
corrective actions from the
manufacturer that are approved by the
FAA, EASA, or Airbus’s EASA Design
Organization Approval (DOA). These
approved instructions will provide an
equivalent level of safety. We have not
changed this AD in this regard.
Conclusion
We reviewed the available data,
including the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
1263, Revision 02, excluding Appendix
01 and including Appendix 02, dated
December 6, 2017, which describe
procedures for modifying the pressure
panel above the left and right
longitudinal beams, including related
investigative actions (e.g., eddy current
rotating probe inspection of the fastener
holes) and corrective actions (e.g.,
repair), by adding a doubler and a filler,
and cold expansion of the holes under
the longitudinal beam at FR 36 for
airplanes on which cracking was found.
These documents are distinct because
they are different revision levels.
Airbus has also issued Service
Bulletin A320–53–1264, Revision 01,
excluding Appendix 01, dated July 4,
2016. The service information describes
procedures for a special detailed
inspection (rotating probe) for cracking
of the fastener holes on the pressure
panel between FR 35 and FR 36 under
the longitudinal beam and repair of any
crack.
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.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–53–1029, Revision 01, including
Appendix 01, dated April 29, 2002. The
service information describes
procedures for repairing cracking.
Airbus has also issued Service
Bulletin A320–53–1240, Revision 01,
dated April 4, 2016; and A320–53–1240,
Revision 02, dated March 14, 2017,
which describe procedures for
modifying the pressure panel above the
left and right longitudinal beams, by
cold working the attachment holes
under the longitudinal beam at FR 36
for airplanes on which no cracking was
found. Service Bulletin A320–53–1240,
Revision 01, dated April 4, 2016 also
includes related investigative action
(e.g., high frequency eddy current
(rototest) inspection of all the removed
fastener holes) and corrective actions
(e.g., repair). These documents are
distinct since they are different revision
levels.
Airbus has also issued Service
Bulletin A320–53–1263, Revision 01,
dated February 29, 2016; and A320–53–
Costs of Compliance
We estimate that this AD affects 737
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Inspection [Retained from AD 2004–03–
07].
Inspection [new proposed requirement]
Up to 2 work-hours × $85 per hour =
$170 per inspection cycle.
13 work-hours × $85 per hour = $1,105
We estimate the following costs to do
any necessary modifications that will be
Cost per product
Parts cost
$0
$0
required based on the results of the
inspection. We have no way of
Cost on U.S.
operators
Up to $170 per inspection cycle.
$1,105 ....................
Up to $125,290 per
inspection cycle.
$814,385.
determining the number of aircraft that
might need these modifications:
ON-CONDITION COSTS
Labor cost
Parts cost
Modification ......................................................
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Action
Up to 213 work-hours × $85 per hour =
$18,105.
Up to $8,510 ..............
We have received no definitive data
that will enable us to provide a cost
estimate for the on-condition repairs
specified in this AD.
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
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:
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Cost per product
Up to $26,615.
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 AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
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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 AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive
(Airworthiness Directive (AD) 2004–03–
07, Amendment 39–13451 (69 FR 5907,
February 9, 2004), and adding the
following new AD:
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■
2018–06–04 Airbus: Amendment 39–19224;
Docket No. FAA–2017–0902; Product
Identifier 2016–NM–188–AD.
(a) Effective Date
This AD is effective May 3, 2018.
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Jkt 244001
(b) Affected ADs
This AD replaces AD 2004–03–07,
Amendment 39–13451 (69 FR 5907, February
9, 2004) (‘‘AD 2004–03–07’’).
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(4)
of this AD, certificated in any category,
except for airplanes on which Airbus
Modification 151574 was embodied in
production.
(1) Model A318–111, –112, –121, and –122
airplanes.
(2) Model A319–111, –112, –113, –114,
–115, –131, –132, and –133 airplanes.
(3) Model A320–211, –212, –214, –231,
–232, and –233 airplanes.
(4) Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by fatigue tests
which revealed cracking around the fasteners
attaching the pressure panel to the flexible
bracket at frame (FR) 36, adjacent to the
longitudinal beams on the left and right sides
of the airplane, and by the discovery of
additional cracks under the longitudinal
beams at locations that are not included in
the inspection area required by AD 2004–03–
07. We are issuing this AD to detect and
correct fatigue cracking around the fasteners
attaching the pressure panel to the flexible
bracket at the FR 36 adjacent to the
longitudinal beams, which could result in
reduced structural integrity of the airplane
and possible rapid decompression of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspection and Follow-on
Actions, With No Changes
This paragraph restates the requirements of
paragraphs (a) and (b) of AD 2004–03–07,
with no changes.
(1) For Model A320–211, –212, and –231
series airplanes having serial numbers 0002
through 0107 inclusive, except those
airplanes on which Airbus Modification
21202/K1432 has been incorporated in
production, or on which Airbus Service
Bulletin A320–53–1029, Revision 01,
including Appendix 01, dated April 29, 2002,
has been incorporated in service: Prior to the
accumulation of 30,000 total flight cycles, do
a rotating probe inspection on airplanes with
a center fuel tank, or a detailed inspection on
airplanes without a center fuel tank, to detect
cracking around the fasteners that attach the
pressure panel to the flexible bracket at FR
36, adjacent to the longitudinal beams on the
left and right sides of the airplane, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1030, Revision 01, excluding Appendix
01, dated May 21, 2002.
(2) If no crack is detected by the inspection
required by paragraph (g)(1) of this AD,
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13391
repeat the applicable inspection thereafter at
intervals not to exceed 6,000 flight cycles for
airplanes without a center fuel tank, and at
intervals not to exceed 18,000 flight cycles
for airplanes with a center fuel tank.
(h) Retained Corrective Actions, With
Specific Delegation Approval Language
This paragraph restates the requirements of
paragraphs (c) and (d) of AD 2004–03–07,
with specific delegation approval language.
(1) If any crack is detected during any
inspection required by paragraph (g)(1) of
this AD, before further flight, repair the
affected structure by accomplishing all
applicable actions in accordance with
paragraphs 3.B. through 3.E. of the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1030, Revision 01,
excluding Appendix 01, dated May 21, 2002.
Repeat the applicable inspection thereafter at
intervals not to exceed 6,000 flight cycles for
airplanes without a center fuel tank, and at
intervals not to exceed 18,000 flight cycles
for airplanes with a center fuel tank. For any
area where cracking is repaired, the repair
constitutes terminating action for the
repetitive inspection of that area.
Note 1 to paragraph (h)(1) of this AD:
Airbus Service Bulletin A320–53–1030
references Airbus Service Bulletin A320–53–
1029, Revision 01, including Appendix 01,
dated April 29, 2002, as an additional source
of service information for certain repairs.
(2) If Airbus Service Bulletin A320–53–
1030, Revision 01, excluding Appendix 01,
dated May 21, 2002, specifies to contact the
manufacturer for appropriate action: Before
further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (p)(2) of this AD.
(i) Retained Optional Terminating Action,
With Revised Compliance Language
This paragraph restates the requirements of
paragraph (e) of AD 2004–03–07, with
revised compliance language, to provide
optional terminating action for paragraphs (g)
and (h) of this AD. For Model A320–211,
–212, and –231 series airplanes having serial
numbers 0002 through 0107 inclusive, except
those airplanes on which Airbus
Modification 21202/K1432 has been
incorporated in production, or Airbus
Service Bulletin A320–53–1029, Revision 01,
including Appendix 01, dated April 29, 2002,
has been incorporated in service:
Modification, before the effective date of this
AD, of the structure around the fasteners that
attach the pressure panel to the flexible
bracket at FR 36, adjacent to the longitudinal
beams on the left and right sides of the
airplane, by accomplishing all applicable
actions in accordance with paragraphs 3.A.
through 3.E. of the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1029, Revision 01, including Appendix
01, dated April 29, 2002, constitutes
terminating action for the actions required by
paragraphs (g) and (h) of this AD.
(j) New Requirement of This AD: Inspection
For all airplanes, except for airplanes
identified in paragraph (l) of this AD: At the
applicable time specified in table 1 to
paragraph (j) of this AD, do a special detailed
inspection for cracking of the fastener holes
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Federal Register / Vol. 83, No. 61 / Thursday, March 29, 2018 / Rules and Regulations
on the pressure panel between FR 35 and FR
36 under the longitudinal beam, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1264, Revision 01, excluding Appendix
01, dated July 4, 2016.
Table 1 to Paragraph (j) of this AD - Pressure Panel Inspection /Modification Threshold
Affected airplanes
Time accumulated by the airplane on the
effective date of this AD
Compliance time
(flight cycles and flight hours since the airplane's
first flight)
(flight cycles or flight hours, whichever occurs
first)
A: Before accumulating 12,000 flight cycles or 24,000
flight hours since the airplane's first flight; or
All airplanes, except Model
A318 Elite airplanes; Model
A319CJ airplanes (Corporate
Jet - airplanes equipped with
Modifications 28238, 28162,
and 28342); Airbus Model
A319 series airplanes on
which the actions specified in
Airbus Service Bulletin
A320-57-ll93 have been
embodied (sharklets installed
as retrofit); Airbus Model
A320 series airplanes on
which the actions specified in
Airbus Service Bulletin
A320-57-1193 have been
embodied (sharklets installed
as retrofit)
Less than 12,000 flight cycles and 24,000 flight hours
B: Within 5,000 flight cycles or 10,000 flight hours
after the effective date of this AD;
whichever occurs later, A orB
Within 5,000 flight cycles or 10,000 flight hours after
the effective date of this AD, without exceeding
33,000 flight cycles or 66,000 flight hours since the
airplane's first flight
30,000 flight cycles or 60,000 flight hours or more, but
less than 40,000 flight cycles and 80,000 flight hours
Within 3,000 flight cycles or 6,000 flight hours after
the effective date of this AD, without exceeding
41,800 flight cycles or 83,600 flight hours since the
airplane's first flight
40,000 flight cycles or 80,000 flight hours or more, but
less than 44,000 flight cycles and 88,000 flight hours
Within 1,800 flight cycles or 3,600 flight hours after
the effective date of this AD, without exceeding
44,600 flight cycles or 89,200 flight hours since the
airplane's first flight
44,000 flight cycles or 88,000 flight hours or more
Affected airplanes
12,000 flight cycles or 24,000 flight hours or more, but
less than 30,000 flight cycles and 60,000 flight hours
Within 600 flight cycles or 1,200 flight hours after the
effective date of this AD
Time accumulated by the airplane on the
effective date of this AD
Compliance time
(flight cycles and flight hours since the airplane's
first flight)
(flight cycles or flight hours, whichever occurs
first)
A: Before accumulating 11,300 flight cycles or
33,900 flight hours since airplane first flight; or
Less than 11,300 flight cycles and 33,900 flight hours
B: Within 2,500 flight cycles or 7,600 flight hours
after the effective date of this AD;
Model A318 Elite airplanes
whichever occurs later, A orB
Within 2,500 flight cycles or 7,600 flight hours after
the effective date of this AD
11,300 flight cycles or 33,900 flight hours or more
A: Before accumulating 6,300 flight cycles or 27,000
flight hours since airplane first flight; or
B: Within 2,300 flight cycles or 11,300 flight hours
after the effective date of this AD;
whichever occurs later, A orB
15:09 Mar 28, 2018
Within 2,300 flight cycles or 11,300 flight hours after
the effective date of this AD, without exceeding
15,700 flight cycles or 75,100 flight hours since the
airplane's first flight
14,300 flight cycles or 68,300 flight hours or more
VerDate Sep<11>2014
6,300 flight cycles or 27,000 flight hours or more, but
less than 14,300 flight cycles and 68,300 flight hours
Within 1,400 flight cycles or 6,800 flight hours after
the effective date of this AD
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ER29MR18.008</GPH>
Model A319CJ airplanes on
which the actions specified in
Airbus Service Bulletin
A320-57-1193 havenotbeen
embodied (sharklets not
installed)
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Less than 6,300 flight cycles and 27,000 flight hours
Federal Register / Vol. 83, No. 61 / Thursday, March 29, 2018 / Rules and Regulations
Time accumulated by the airplane on the
effective date of this AD
Affected airplanes
13393
Compliance time
(flight cycles or flight hours, whichever occurs
first)
(flight cycles and flight hours since the airplane's
first flight)
A: Before accumulating 9,800 flight cycles or 19,600
flight hours since the airplane's first flight; or
Less than 9,000 flight cycles and 18,000 flight hours
B: Within 3,300 flight cycles or 6,600 flight hours
after the effective date of this AD;
whichever occurs later, A orB*
Model A319 and A320 series
airplanes on which the actions
specified in Airbus Service
Bulletin A320-57-1193 have
been embodied (sharklets
installed)
9,000 flight cycles or 18,000 flight hours or more, but
less than 24,000 flight cycles and 48,000 flight hours
24,000 flight cycles or 48,000 flight hours or more, but
less than 30,000 flight cycles and 60,000 flight hours
30,000 flight cycles or 60,000 flight hours or more, but
less than 32,000 flight cycles and 64,000 flight hours
32,000 flight cycles or 64,000 flight hours or more, but
less than 33,000 flight cycles and 66,000 flight hours
Within 3,300 flight cycles or 6,600 flight hours after
the effective date of this AD, without exceeding
25,300 flight cycles or 50,600 flight hours since the
airplane's first flight*
Within 1,300 flight cycles or 2,600 flight hours after
the effective date of this AD, without exceeding
30,700 flight cycles or 61,400 flight hours since the
airplane's first flight*
Within 700 flight cycles or 1,400 flight hours after the
effective date of this AD, without exceeding 32,300
flight cycles or 64,600 flight hours since the airplane's
first flight*
Within 300 flight cycles or 600 flight hours after the
effective date of this AD, without exceeding 33,000
flight cycles or 66,000 flight hours since the airplane's
first flight; or within 30 days after the effective date of
this AD; whichever occurs later*
Time accumulated by the airplane on the
effective date of this AD
Affected airplanes
(flight cycles and flight hours since the
airplane's first flight)
Compliance time
(flight cycles or flight hours, whichever occurs
first)
Less than 4,200 flight cycles and 18,000 flight
hours
4,200 flight cycles or 18,000 flight hours or
more, but less than 14,300 flight cycles and
61,400 flight hours
Within 1,600 flight cycles or 6,800 flight hours
after the effective date of this AD, without
exceeding 15,300 flight cycles or 65,700 flight
hours since the airplane's first flight**
14,300 flight cycles or 61,400 flight hours or
more but less than 18,000 flight cycles or
77,400 flight hours
Model A319 airplanes used as CJ post Airbus
Service Bulletin A320-57 -1193
A: Before accumulating 4,500 flight cycles or
19,600 flight hours since the airplane's first
flight; or
B: Within 1,600 flight cycles or 6,800 flight
hours after the effective date of this AD;
whichever occurs later, A orB**
Within 1,000 flight cycles or 4,300 flight hours
after the effective date of this AD**
For A319 and A320 airplanes with a sharklet installed as a retrofit (post-Airbus Service Bulletin A320-57-1193 (post-mod 160080)): Guidance on
determining an alternative compliance time for the initial inspection can be found in in "Compliance Time" of Part 2, Damage Tolerant
Airworthiness Limitation Items, of the Model A318/A319/A320/A321 Airworthiness Limitations Section; however, to use that alternative
compliance time, operators must request an alternative method of compliance using a method approved in accordance with the procedures
specified in paragraph (p)(l) ofthis AD.
* Without exceeding the time at which an inspection is required through the threshold or compliance time of a Model A320 airplane, pre-Airbus
Service Bulletin A320-57 -1193 (pre-mod 160080).
(1) If, during any inspection required by
paragraph (j) of this AD, no cracking is found,
or cracking is found that is within the limits
specified in Airbus Service Bulletin A320–
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15:09 Mar 28, 2018
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53–1264, Revision 01, excluding Appendix
01, dated July 4, 2016: Before further flight,
modify the pressure panel above the left and
right longitudinal beams, including doing all
applicable related investigative and
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corrective actions, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1240, Revision 02,
dated March 14, 2017; or Service Bulletin
A320–53–1263, Revision 02, excluding
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ER29MR18.010</GPH>
(k) On-Condition Actions
ER29MR18.009</GPH>
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**Without exceeding the time at which an inspection is required through the threshold or compliance time of a Model A319CJ airplane,
pre-Airbus Service Bulletin A320-57 -1193 (pre-mod 160080).
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Appendix 01 and including Appendix 02,
dated December 6, 2017, as applicable. Do all
related investigative and corrective actions
before further flight. Where Airbus Service
Bulletin A320–53–1240, Revision 02, dated
March 14, 2017; or Service Bulletin A320–
53–1263, Revision 02, excluding Appendix
01 and including Appendix 02, dated
December 6, 2017; specify to contact Airbus
for appropriate action: Before further flight,
accomplish the repair using a method
approved in accordance with the procedures
specified in paragraph (p)(2) of this AD.
(2) If, during any inspection required by
paragraph (j) of this AD, any cracking is
found that exceeds the limits specified in
Airbus Service Bulletin A320–53–1264,
Revision 01, excluding Appendix 01, dated
July 4, 2016: Before further flight, repair any
cracking in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1264, Revision 01,
excluding Appendix 01, dated July 4, 2016.
Where Airbus Service Bulletin A320–53–
1264, Revision 01, excluding Appendix 01,
dated July 4, 2016, specifies to contact Airbus
for appropriate action, and specifies that
action as ‘‘RC’’ (Required for Compliance),
before further flight, request approval of
repair instructions using a method approved
in accordance with the procedures specified
in paragraph (p)(2) of this AD, and
accomplish the repair accordingly within the
compliance time specified in those
instructions. If no compliance time is defined
in the repair instructions, accomplish the
repair before further flight.
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(l) Actions for Certain Airplanes
For Model A319 and Model A320 series
airplanes on which the actions specified in
Airbus Service Bulletin A320–57–1193 have
been embodied and the airplane has
accumulated 33,000 flight cycles or 66,000
flight hours or more since the airplane’s first
flight on the effective date of this AD: Within
30 days after the effective date of this AD,
contact the Manager, International Section,
Transport Standards Branch FAA; or the
European Aviation Safety Agency (EASA); or
Airbus’s EASA Design Organization
Approval (DOA) for approved repair
instructions and within the compliance time
specified in those instructions, accomplish
the repair accordingly. If approved by the
DOA, the approval must include the DOAauthorized signature. If no compliance time
is defined in the repair instructions,
accomplish the repair before the next flight.
(m) Terminating Action for Repetitive
Inspections
(1) Modification of an airplane as specified
in paragraph (m)(1)(i), (m)(1)(ii), or (m)(1)(iii)
of this AD constitutes terminating action for
the repetitive inspection required by
paragraph (g)(2) of this AD for that airplane
only.
(i) Modification of an airplane as required
by paragraph (k)(1) of this AD.
(ii) Modification of an airplane prior to the
effective date of this AD, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A320–53–1240, Revision 01,
dated April 4, 2016; or Airbus Service
Bulletin A320–53–1263, Revision 01, dated
February 29, 2016; as applicable.
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15:09 Mar 28, 2018
Jkt 244001
(iii) Modification of an airplane using
instructions obtained in accordance with the
procedures specified in paragraph (p)(2) of
this AD.
(2) Repair of an airplane as required by
paragraph (k)(2) of this AD constitutes
terminating action for the repetitive
inspections required by paragraph (g)(2) of
this AD for that airplane, unless specified
otherwise in the repair instructions 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 DOAauthorized signature.
(n) No Reporting Requirement
Although Airbus Service Bulletin A320–
53–1264, Revision 01, excluding Appendix
01, dated July 4, 2016, specifies to submit
certain information to the manufacturer, and
specifies that action as ‘‘RC’’ (Required for
Compliance), this AD does not include that
requirement.
(o) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraphs (g) and (h)(1)
of this AD, if those actions were performed
before March 15, 2004 (the effective date of
AD 2004–03–07) using Airbus Service
Bulletin A320–53–1030, dated January 5,
2000; or Airbus Service Bulletin A320–53–
1029, dated January 5, 2000.
(2) This paragraph provides credit for
actions required by paragraph (j) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A320–53–1264, dated March 19,
2015.
(3) This paragraph provides credit for
actions required by paragraph (k)(1) of this
AD, if those actions were performed before
the effective date of this AD using the
applicable service information specified in
paragraphs (o)(3)(i) through (o)(3)(iv) of this
AD, for that airplane only.
(i) Airbus Service Bulletin A320–53–1240,
dated March 19, 2015.
(ii) Airbus Service Bulletin A320–53–1240,
Revision 01, dated April 4, 2016.
(iii) Airbus Service Bulletin A320–53–
1263, dated March 19, 2015.
(iv) Airbus Service Bulletin A320–53–
1263, Revision 01, dated February 29, 2016.
(4) This paragraph provides credit for
actions required by paragraph (m)(1)(ii) of
this AD if those actions were performed
before the effective date of this AD using
Airbus Service Bulletin A320–53–1240,
dated March 19, 2015; or Service Bulletin
A320–53–1263, dated March 19, 2015.
(p) 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 International Branch, send it
to the attention of the person identified in
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Fmt 4700
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paragraph (q)(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 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.
(3) Required for Compliance (RC): Except
as required by paragraphs (k)(2) and (n) 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.
(q) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0206, dated October 13, 2016; corrected
October 14, 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–2017–0902.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone 206–231–
3223; fax 206–231–3398.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (r)(5) and (r)(6) of this AD.
(r) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on May 3, 2018.
(i) Airbus Service Bulletin A320–53–1029,
Revision 01, including Appendix 01, dated
April 29, 2002.
(ii) Airbus Service Bulletin A320–53–1240,
Revision 01, dated April 4, 2016.
(iii) Airbus Service Bulletin A320–53–
1240, Revision 02, dated March 14, 2017.
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(iv) Airbus Service Bulletin A320–53–
1263, Revision 01, dated February 29, 2016.
(v) Airbus Service Bulletin A320–53–1263,
Revision 02, excluding Appendix 01 and
including Appendix 02, dated December 6,
2017.
(vi) Airbus Service Bulletin A320–53–
1264, Revision 01, excluding Appendix 01,
dated July 4, 2016.
(4) The following service information was
approved for IBR on March 15, 2004 (69 FR
5907, February 9, 2004).
(i) Airbus Service Bulletin A320–53–1030,
Revision 01, excluding Appendix 01, dated
May 21, 2002.
(ii) Reserved.
(5) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; internet https://www.airbus.com.
(6) 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.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on March 2,
2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–05019 Filed 3–28–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0940; Product
Identifier 2017–SW–058–AD; Amendment
39–19233; AD 2018–07–02]
RIN 2120–AA64
Airworthiness Directives; Agusta
S.p.A. Helicopters
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Agusta
S.p.A. (Agusta) Model A109E, A109S,
AW109SP, A119, and AW119 MKII
helicopters. This AD requires inspecting
the main rotor blade (MRB) tip cap for
disbonding. This AD is prompted by a
report of the in-flight loss of an MRB tip
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SUMMARY:
VerDate Sep<11>2014
15:09 Mar 28, 2018
Jkt 244001
cap. The actions of this AD are intended
to prevent an unsafe condition on these
products.
DATES: This AD becomes effective April
13, 2018.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of April 13, 2018.
We must receive comments on this
AD by May 29, 2018.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
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–
0940; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this AD, the
European Aviation Safety Agency
(EASA) AD, any incorporated-byreference service information, the
economic evaluation, any comments
received, and other information. The
street address for Docket Operations
(telephone 800- 647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
For service information identified in
this final rule, contact Leonardo S.p.A.
Helicopters, Matteo Ragazzi, Head of
Airworthiness, Viale G.Agusta 520,
21017 C.Costa di Samarate (Va) Italy;
telephone +39–0331–711756; fax +39–
0331–229046; or at https://
www.leonardocompany.com/-/bulletins.
You may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321,
Fort Worth, TX 76177. It is also
available on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0940.
Matt
Fuller, Senior Aviation Safety Engineer,
Safety Management Section, Rotorcraft
FOR FURTHER INFORMATION CONTACT:
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
13395
Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email
matthew.fuller@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments prior to it becoming effective.
However, we invite you to participate in
this rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that resulted from
adopting this AD. The most helpful
comments reference a specific portion of
the AD, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit them only one time. We will file
in the docket all comments that we
receive, as well as a report summarizing
each substantive public contact with
FAA personnel concerning this
rulemaking during the comment period.
We will consider all the comments we
receive and may conduct additional
rulemaking based on those comments.
Discussion
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued AD No. 2017–0176–
E, dated September 14, 2017, to correct
an unsafe condition for Leonardo S.p.A.
(previously Agusta) Model A109E,
A109LUH, A109S, AW109SP, A119,
and AW119 MKII helicopters. EASA
advises of an in-flight loss of an MRB tip
cap on an AW109SP helicopter where
the pilot was able to safely land the
helicopter. EASA further advises that an
investigation determined the cause as
incorrect bonding procedures used
between specific dates and identified
the affected MRBs by part number and
serial number. According to EASA, this
condition could result in loss of an MRB
tip cap, increased pilot workload, and
reduced control of the helicopter. To
address this unsafe condition, the EASA
AD requires repetitive inspections of the
MRB tip caps and replacing certain partnumbered MRBs.
The FAA is in the process of updating
Agusta’s name change to Leonardo
Helicopters on its type certificate.
Because this name change is not yet
effective, this AD specifies Agusta.
E:\FR\FM\29MRR1.SGM
29MRR1
]]>Agencies
[Federal Register Volume 83, Number 61 (Thursday, March 29, 2018)]
[Rules and Regulations]
[Pages 13387-13395]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-05019]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0902; Product Identifier 2016-NM-188-AD; Amendment
39-19224; AD 2018-06-04]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
[[Page 13388]]
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2004-03-07,
which applied to certain Airbus Model A320-111, -211, -212, and -231
series airplanes. AD 2004-03-07 required repetitive inspections for
fatigue cracking around the fasteners attaching the pressure panel to
the flexible bracket at a certain frame (FR), adjacent to the
longitudinal beams on the left and right sides of the airplane; and
repair as necessary. This new AD retains certain requirements of AD
2004-03-07, expands the applicability, and requires an inspection of
the fastener holes on the pressure panel and modification or repair as
applicable. This AD was prompted by fatigue tests which revealed
cracking around the fasteners attaching the pressure panel to the
flexible bracket, and by the discovery of additional cracks under the
longitudinal beams at locations that are not included in the inspection
area required by AD 2004-03-07. We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective May 3, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of May 3, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of March
15, 2004 (69 FR 5907, February 9, 2004).
ADDRESSES: For service information identified in this final rule,
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email [email protected]; internet
https://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. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0902.
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-
0902; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone 206-231-3223; fax 206-231-
3398.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2004-03-07, Amendment 39-13451 (69 FR 5907,
February 9, 2004) (``AD 2004-03-07''). AD 2004-03-07 applied to certain
Airbus Model A320-111, -211, -212, and -231 series airplanes. The NPRM
published in the Federal Register on October 6, 2017 (82 FR 46729). The
NPRM was prompted by fatigue tests which revealed cracking around the
fasteners attaching the pressure panel to the flexible bracket at FR
36, adjacent to the longitudinal beams on the left and right sides of
the airplane, and by the discovery of additional cracks under the
longitudinal beams at locations that are not included in the inspection
area required by AD 2004-03-07. The NPRM proposed to continue to
require certain requirements of AD 2004-03-07. The NPRM also proposed
to expand the applicability and require an inspection of the fastener
holes on the pressure panel between FR 35 and FR 36 under the
longitudinal beam and modification or repair as applicable. We are
issuing this AD to detect and correct fatigue cracking around the
fasteners attaching the pressure panel to the flexible bracket at the
FR 36 adjacent to the longitudinal beams, which could result in reduced
structural integrity of the airplane and possible rapid decompression
of the airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2016-0206, dated October 13, 2016; corrected
October 14, 2016 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for certain Airbus Model A318 and Model A319 series
airplanes, Model A320-211, -212, -214, -231, -232, and -233 airplanes,
and Model A321-111, -112, -131,-211, -21-, 213, -231, and -232
airplanes. The MCAI states:
During fatigue tests, cracks were found around the fasteners
connecting the pressure panel with the flexible bracket at fuselage
frame (FR) 36, adjacent to the longitudinal beams on left-hand (LH)
and right-hand (RH) sides.
This condition, if not detected and corrected, could impair the
structural integrity of the aeroplane.
To address this unsafe condition, DGAC [Direction
G[eacute]n[eacute]rale de l'Aviation Civile] France issued [French]
AD 2000-531-155(B) [which corresponds with FAA AD 2004-03-07] to
require repetitive inspections of the longitudinal beams of the FR
36 pressure panel and, depending on findings, the accomplishment of
a repair.
Since that [French] AD was issued, additional cracks have been
found under the beams, but in locations not covered by the required
inspections. Fatigue and damage tolerance analyses were performed,
the results of which indicated that all the holes in the pressure
panel above all the longitudinal beams have to be cold worked.
For the reasons described above, this [EASA] AD retains the
requirements of DGAC France AD 2000-531-155(B), which is superseded,
extends the applicability to all A320 family aeroplanes and requires
[a special detailed inspection of the fastener holes on the pressure
panel between FR35 and FR36 under the longitudinal beam and]
modification [or repair] of all the affected holes.
This [EASA] AD is republished to correct the number of the
superseded DGAC AD.
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-
0902.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Request To Remove Reporting Requirement
United Airlines (UAL) requested that we omit paragraph (k)(2)(ii)
of the proposed AD, which would require operators to report any
findings of cracking that exceeded the limits specified in Airbus
Service Bulletin A320-53-1264, Revision 01, excluding Appendix 01,
dated July 4, 2016, from the proposed AD. UAL stated that paragraph
(k)(2)(ii) of the proposed AD is confusing and unjustified because
there is no explanation for why it is required when it was not included
in EASA AD 2016-0206. UAL stated the requirement to report findings in
paragraph (k)(2)(ii) is redundant with the actions of paragraph
(k)(2)(i) of the proposed AD. UAL noted that for the
[[Page 13389]]
crack repair specified in paragraph (k)(2)(i) of the proposed AD, the
findings would be reported. UAL suggested the paragraph (k)(2)(ii) of
the proposed AD required using an unconventional means to report
findings that might require additional procedures and training specific
to the proposed AD. UAL also stated that restricting reporting to a
website may cause issues if the sender does not have access and that
Airbus Service Bulletin A320-53-1264, Revision 01, excluding Appendix
01, dated July 4, 2016, lists alternative options for reporting, like
email, fax, or mail.
We agree to remove the reporting requirement specified in paragraph
(k)(2)(ii) of the proposed AD from this AD. Neither Airbus Service
Bulletin A320-53-1264, Revision 01, excluding Appendix 01, dated July
4, 2016, nor the MCAI specifically includes reporting to a website as
specified in paragraph (k)(2)(ii) of the proposed AD. We note that
Airbus Service Bulletin A320-53-1264, Revision 01, excluding Appendix
01, dated July 4, 2016, does include reporting within the required for
compliance (RC) procedure for the repair, which indicates that
reporting would be required regardless of whether reporting was called
out in the MCAI. We also verified with EASA that reporting should be
done as defined in the service information. However, we have determined
that a specific reporting requirement is not necessary. As stated by
the commenter, operators will report findings to obtain the repair,
which is specified in paragraph (k)(2)(i) of the proposed AD. We have
removed paragraphs (k)(2)(i) and (k)(2)(ii) from this AD and revised
paragraph (k)(2) of this AD to include the information that was in
paragraph (k)(2)(i) of the proposed AD. We have also added paragraph
(n) to this AD to specify that reporting is not required for this AD
and redesignated the subsequent paragraphs accordingly.
Request To Refer to Latest Service Information
Two commenters requested that we refer to the latest service
information. UAL requested that we update paragraph (k) of the proposed
AD to use Airbus Service Bulletin A320-53-1264, Revision 02, dated
March 14, 2017, which corrects an error with the fastener lengths for
part number (P/N) EN6115K3. We infer that UAL intended to refer to
Airbus Service Bulletin A320-53-1240, Revision 02, dated March 14,
2017, because there is no Revision 02 for Airbus Service Bulletin A320-
53-1264, and because P/N EN6115K3 is referenced in Airbus Service
Bulletin A320-53-1240, Revision 02, dated March 14, 2017. Airbus
requested that we refer to Airbus Service Bulletin A320-53-1240,
Revision 02, dated March 14, 2017, in the proposed AD.
We agree to refer to the latest service information in this AD. In
addition to Airbus Service Bulletin A320-53-1240, Revision 02, dated
March 14, 2017, we have also reviewed Airbus Service Bulletin A320-53-
1263, Revision 02, excluding Appendix 01 and including Appendix 02,
dated December 6, 2017, which updates kit information and figures among
other minor changes. We have revised paragraph (k)(1) of this AD
accordingly. We have also provided credit for Airbus Service Bulletin
A320-53-1240, Revision 01, dated April 4, 2016; and Airbus Service
Bulletin A320-53-1263, Revision 01, dated February 29, 2016; in
paragraphs (o)(3)(ii) and (o)(3)(iv) of this AD, respectively.
Request To Include Additional Airplane Models in the Applicability
Airbus requested that Model A320-215 and Model A320-216 airplanes
be in included in the applicability of the proposed AD. The commenter
noted that these airplane models are included in the MCAI.
We do not agree with the commenter's request. We have not certified
Model A320-215 airplanes for operation in the U.S., and therefore, we
did not include that model in the applicability of this AD. We did not
include Model A320-216 airplanes in the applicability of this AD
because the MCAI was already added to the required airworthiness action
list (RAAL) for Model A320-216 airplanes. We have not changed this AD
in this regard.
Request To Revise Service Bulletin Descriptions in the Related Service
Information Under 1 CFR Part 51 Paragraph in the Preamble of the NPRM
Airbus stated that the proposed AD identifies the means of
inspection, i.e., rototest inspection, using three different wordings
in the descriptions of the service bulletins specified in the Related
Service Information under 1 CFR part 51 paragraph in the preamble of
the NPRM. Airbus also stated that Service Bulletin A320-53-1240,
Revision 02, dated March 14, 2017, no longer contains a rototest
inspection requirement. In addition, Airbus noted that Service Bulletin
A320-53-1240, Revision 02, dated March 14, 2017, does not contain
repair instructions. We infer the commenter is requesting that we
revise the service bulletin descriptions in the Related Service
Information under 1 CFR part 51 paragraph in the preamble of the NPRM.
We acknowledge the description of the rototest inspection is
different for each service bulletin specified in the Related Service
Information under 1 CFR part 51 paragraph in the preamble of the NPRM.
In the NPRM, we matched the description of the inspection as given in
each service bulletin specified in the Related Service Information
under 1 CFR part 51 paragraph. We have revised the description of
Airbus Service Bulletin A320-53-1240, Revision 02, dated March 14,
2017, to remove the reference to an inspection and repair.
Request To Clarify What Prompted the Proposed AD
Airbus requested that we revise paragraph (e) of the proposed AD to
clarify that the proposed AD was prompted by a report of cracking in an
additional area. Airbus stated that paragraph (e) of the proposed AD
describes only the fatigue test results that prompted AD 2004-03-07.
We agree to revise paragraph (e) of this AD for clarity. This AD
was prompted by the original report of cracking and the additional
report. We have revised paragraph (e) of this AD to include the
additional cracking that prompted the issuance of this AD.
Request To Revise Repair Language in Paragraph (k)(2)(i) of the
Proposed AD
Airbus requested that we revise the language in paragraph (k)(2)(i)
of the proposed AD, which specifies to repair any cracking in
accordance with Airbus Service Bulletin A320-53-1264, Revision 01,
excluding Appendix 01, dated July 4, 2016. Airbus stated that this
service information does not provide direct repair instructions and
instead specifies to contact Airbus.
We agree to clarify the language in paragraph (k)(2) of this AD
(which corresponds with paragraph (k)(2)(i) of the proposed AD).
Paragraph (k)(2) of this AD also specifies that where Airbus Service
Bulletin A320-53-1264, Revision 01, excluding Appendix 01, dated July
4, 2016, specifies to contact Airbus for appropriate action, and
specifies that action as ``RC'' (Required for Compliance), operators
must request approval of repair instructions using a method approved in
accordance with the procedures specified in paragraph (p)(2) of this
AD, and accomplish the repair accordingly within the compliance time
specified in those instructions. We have not changed this AD in this
regard.
[[Page 13390]]
Request To Include Wording From the MCAI in Paragraph (m)(1)(iii) of
the Proposed AD
Airbus requested that we revise paragraph (m)(1)(iii) of the
proposed AD. Airbus stated the wording is similar to paragraph (9) of
the MCAI except that the important wording ``in accordance with Airbus
approved instructions that identify the repair as technically
equivalent to the accomplishment of Airbus SB A320-53-1240 or SB A320-
53-1263'' is omitted.
We disagree with the commenter's request. The intent of paragraph
(m)(1)(iii) of this AD is to obtain corrective actions from the
manufacturer that are approved by the FAA, EASA, or Airbus's EASA
Design Organization Approval (DOA). These approved instructions will
provide an equivalent level of safety. We have not changed this AD in
this regard.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-53-1029, Revision 01,
including Appendix 01, dated April 29, 2002. The service information
describes procedures for repairing cracking.
Airbus has also issued Service Bulletin A320-53-1240, Revision 01,
dated April 4, 2016; and A320-53-1240, Revision 02, dated March 14,
2017, which describe procedures for modifying the pressure panel above
the left and right longitudinal beams, by cold working the attachment
holes under the longitudinal beam at FR 36 for airplanes on which no
cracking was found. Service Bulletin A320-53-1240, Revision 01, dated
April 4, 2016 also includes related investigative action (e.g., high
frequency eddy current (rototest) inspection of all the removed
fastener holes) and corrective actions (e.g., repair). These documents
are distinct since they are different revision levels.
Airbus has also issued Service Bulletin A320-53-1263, Revision 01,
dated February 29, 2016; and A320-53-1263, Revision 02, excluding
Appendix 01 and including Appendix 02, dated December 6, 2017, which
describe procedures for modifying the pressure panel above the left and
right longitudinal beams, including related investigative actions
(e.g., eddy current rotating probe inspection of the fastener holes)
and corrective actions (e.g., repair), by adding a doubler and a
filler, and cold expansion of the holes under the longitudinal beam at
FR 36 for airplanes on which cracking was found. These documents are
distinct because they are different revision levels.
Airbus has also issued Service Bulletin A320-53-1264, Revision 01,
excluding Appendix 01, dated July 4, 2016. The service information
describes procedures for a special detailed inspection (rotating probe)
for cracking of the fastener holes on the pressure panel between FR 35
and FR 36 under the longitudinal beam and repair of any crack.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 737 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection [Retained from AD Up to 2 work-hours x $0 Up to $170 per Up to $125,290 per
2004-03-07]. $85 per hour = $170 inspection cycle. inspection cycle.
per inspection cycle.
Inspection [new proposed 13 work-hours x $85 per $0 $1,105............ $814,385.
requirement]. hour = $1,105.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary modifications
that will be required based on the results of the inspection. We have
no way of determining the number of aircraft that might need these
modifications:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Modification....................... Up to 213 work-hours x $85 Up to $8,510.......... Up to $26,615.
per hour = $18,105.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that will enable us to provide
a cost estimate for the on-condition repairs specified in this 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
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 AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C.
[[Page 13391]]
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 AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive
(Airworthiness Directive (AD) 2004-03-07, Amendment 39-13451 (69 FR
5907, February 9, 2004), and adding the following new AD:
2018-06-04 Airbus: Amendment 39-19224; Docket No. FAA-2017-0902;
Product Identifier 2016-NM-188-AD.
(a) Effective Date
This AD is effective May 3, 2018.
(b) Affected ADs
This AD replaces AD 2004-03-07, Amendment 39-13451 (69 FR 5907,
February 9, 2004) (``AD 2004-03-07'').
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category,
except for airplanes on which Airbus Modification 151574 was
embodied in production.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by fatigue tests which revealed cracking
around the fasteners attaching the pressure panel to the flexible
bracket at frame (FR) 36, adjacent to the longitudinal beams on the
left and right sides of the airplane, and by the discovery of
additional cracks under the longitudinal beams at locations that are
not included in the inspection area required by AD 2004-03-07. We
are issuing this AD to detect and correct fatigue cracking around
the fasteners attaching the pressure panel to the flexible bracket
at the FR 36 adjacent to the longitudinal beams, which could result
in reduced structural integrity of the airplane and possible rapid
decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection and Follow-on Actions, With No Changes
This paragraph restates the requirements of paragraphs (a) and
(b) of AD 2004-03-07, with no changes.
(1) For Model A320-211, -212, and -231 series airplanes having
serial numbers 0002 through 0107 inclusive, except those airplanes
on which Airbus Modification 21202/K1432 has been incorporated in
production, or on which Airbus Service Bulletin A320-53-1029,
Revision 01, including Appendix 01, dated April 29, 2002, has been
incorporated in service: Prior to the accumulation of 30,000 total
flight cycles, do a rotating probe inspection on airplanes with a
center fuel tank, or a detailed inspection on airplanes without a
center fuel tank, to detect cracking around the fasteners that
attach the pressure panel to the flexible bracket at FR 36, adjacent
to the longitudinal beams on the left and right sides of the
airplane, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-53-1030, Revision 01, excluding
Appendix 01, dated May 21, 2002.
(2) If no crack is detected by the inspection required by
paragraph (g)(1) of this AD, repeat the applicable inspection
thereafter at intervals not to exceed 6,000 flight cycles for
airplanes without a center fuel tank, and at intervals not to exceed
18,000 flight cycles for airplanes with a center fuel tank.
(h) Retained Corrective Actions, With Specific Delegation Approval
Language
This paragraph restates the requirements of paragraphs (c) and
(d) of AD 2004-03-07, with specific delegation approval language.
(1) If any crack is detected during any inspection required by
paragraph (g)(1) of this AD, before further flight, repair the
affected structure by accomplishing all applicable actions in
accordance with paragraphs 3.B. through 3.E. of the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1030, Revision 01,
excluding Appendix 01, dated May 21, 2002. Repeat the applicable
inspection thereafter at intervals not to exceed 6,000 flight cycles
for airplanes without a center fuel tank, and at intervals not to
exceed 18,000 flight cycles for airplanes with a center fuel tank.
For any area where cracking is repaired, the repair constitutes
terminating action for the repetitive inspection of that area.
Note 1 to paragraph (h)(1) of this AD: Airbus Service Bulletin
A320-53-1030 references Airbus Service Bulletin A320-53-1029,
Revision 01, including Appendix 01, dated April 29, 2002, as an
additional source of service information for certain repairs.
(2) If Airbus Service Bulletin A320-53-1030, Revision 01,
excluding Appendix 01, dated May 21, 2002, specifies to contact the
manufacturer for appropriate action: Before further flight, repair
using a method approved in accordance with the procedures specified
in paragraph (p)(2) of this AD.
(i) Retained Optional Terminating Action, With Revised Compliance
Language
This paragraph restates the requirements of paragraph (e) of AD
2004-03-07, with revised compliance language, to provide optional
terminating action for paragraphs (g) and (h) of this AD. For Model
A320-211, -212, and -231 series airplanes having serial numbers 0002
through 0107 inclusive, except those airplanes on which Airbus
Modification 21202/K1432 has been incorporated in production, or
Airbus Service Bulletin A320-53-1029, Revision 01, including
Appendix 01, dated April 29, 2002, has been incorporated in service:
Modification, before the effective date of this AD, of the structure
around the fasteners that attach the pressure panel to the flexible
bracket at FR 36, adjacent to the longitudinal beams on the left and
right sides of the airplane, by accomplishing all applicable actions
in accordance with paragraphs 3.A. through 3.E. of the
Accomplishment Instructions of Airbus Service Bulletin A320-53-1029,
Revision 01, including Appendix 01, dated April 29, 2002,
constitutes terminating action for the actions required by
paragraphs (g) and (h) of this AD.
(j) New Requirement of This AD: Inspection
For all airplanes, except for airplanes identified in paragraph
(l) of this AD: At the applicable time specified in table 1 to
paragraph (j) of this AD, do a special detailed inspection for
cracking of the fastener holes
[[Page 13392]]
on the pressure panel between FR 35 and FR 36 under the longitudinal
beam, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-53-1264, Revision 01, excluding Appendix 01,
dated July 4, 2016.
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(k) On-Condition Actions
(1) If, during any inspection required by paragraph (j) of this
AD, no cracking is found, or cracking is found that is within the
limits specified in Airbus Service Bulletin A320-53-1264, Revision
01, excluding Appendix 01, dated July 4, 2016: Before further
flight, modify the pressure panel above the left and right
longitudinal beams, including doing all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-53-1240,
Revision 02, dated March 14, 2017; or Service Bulletin A320-53-1263,
Revision 02, excluding
[[Page 13394]]
Appendix 01 and including Appendix 02, dated December 6, 2017, as
applicable. Do all related investigative and corrective actions
before further flight. Where Airbus Service Bulletin A320-53-1240,
Revision 02, dated March 14, 2017; or Service Bulletin A320-53-1263,
Revision 02, excluding Appendix 01 and including Appendix 02, dated
December 6, 2017; specify to contact Airbus for appropriate action:
Before further flight, accomplish the repair using a method approved
in accordance with the procedures specified in paragraph (p)(2) of
this AD.
(2) If, during any inspection required by paragraph (j) of this
AD, any cracking is found that exceeds the limits specified in
Airbus Service Bulletin A320-53-1264, Revision 01, excluding
Appendix 01, dated July 4, 2016: Before further flight, repair any
cracking in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-53-1264, Revision 01, excluding
Appendix 01, dated July 4, 2016. Where Airbus Service Bulletin A320-
53-1264, Revision 01, excluding Appendix 01, dated July 4, 2016,
specifies to contact Airbus for appropriate action, and specifies
that action as ``RC'' (Required for Compliance), before further
flight, request approval of repair instructions using a method
approved in accordance with the procedures specified in paragraph
(p)(2) of this AD, and accomplish the repair accordingly within the
compliance time specified in those instructions. If no compliance
time is defined in the repair instructions, accomplish the repair
before further flight.
(l) Actions for Certain Airplanes
For Model A319 and Model A320 series airplanes on which the
actions specified in Airbus Service Bulletin A320-57-1193 have been
embodied and the airplane has accumulated 33,000 flight cycles or
66,000 flight hours or more since the airplane's first flight on the
effective date of this AD: Within 30 days after the effective date
of this AD, contact the Manager, International Section, Transport
Standards Branch FAA; or the European Aviation Safety Agency (EASA);
or Airbus's EASA Design Organization Approval (DOA) for approved
repair instructions and within the compliance time specified in
those instructions, accomplish the repair accordingly. If approved
by the DOA, the approval must include the DOA-authorized signature.
If no compliance time is defined in the repair instructions,
accomplish the repair before the next flight.
(m) Terminating Action for Repetitive Inspections
(1) Modification of an airplane as specified in paragraph
(m)(1)(i), (m)(1)(ii), or (m)(1)(iii) of this AD constitutes
terminating action for the repetitive inspection required by
paragraph (g)(2) of this AD for that airplane only.
(i) Modification of an airplane as required by paragraph (k)(1)
of this AD.
(ii) Modification of an airplane prior to the effective date of
this AD, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-53-1240, Revision 01, dated April 4,
2016; or Airbus Service Bulletin A320-53-1263, Revision 01, dated
February 29, 2016; as applicable.
(iii) Modification of an airplane using instructions obtained in
accordance with the procedures specified in paragraph (p)(2) of this
AD.
(2) Repair of an airplane as required by paragraph (k)(2) of
this AD constitutes terminating action for the repetitive
inspections required by paragraph (g)(2) of this AD for that
airplane, unless specified otherwise in the repair instructions
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.
(n) No Reporting Requirement
Although Airbus Service Bulletin A320-53-1264, Revision 01,
excluding Appendix 01, dated July 4, 2016, specifies to submit
certain information to the manufacturer, and specifies that action
as ``RC'' (Required for Compliance), this AD does not include that
requirement.
(o) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraphs (g) and (h)(1) of this AD, if those actions were
performed before March 15, 2004 (the effective date of AD 2004-03-
07) using Airbus Service Bulletin A320-53-1030, dated January 5,
2000; or Airbus Service Bulletin A320-53-1029, dated January 5,
2000.
(2) This paragraph provides credit for actions required by
paragraph (j) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A320-53-
1264, dated March 19, 2015.
(3) This paragraph provides credit for actions required by
paragraph (k)(1) of this AD, if those actions were performed before
the effective date of this AD using the applicable service
information specified in paragraphs (o)(3)(i) through (o)(3)(iv) of
this AD, for that airplane only.
(i) Airbus Service Bulletin A320-53-1240, dated March 19, 2015.
(ii) Airbus Service Bulletin A320-53-1240, Revision 01, dated
April 4, 2016.
(iii) Airbus Service Bulletin A320-53-1263, dated March 19,
2015.
(iv) Airbus Service Bulletin A320-53-1263, Revision 01, dated
February 29, 2016.
(4) This paragraph provides credit for actions required by
paragraph (m)(1)(ii) of this AD if those actions were performed
before the effective date of this AD using Airbus Service Bulletin
A320-53-1240, dated March 19, 2015; or Service Bulletin A320-53-
1263, dated March 19, 2015.
(p) 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 International Branch, send it to the attention of
the person identified in paragraph (q)(2) of this AD. Information
may be emailed to: [email protected]. 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 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.
(3) Required for Compliance (RC): Except as required by
paragraphs (k)(2) and (n) 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.
(q) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0206, dated October 13, 2016; corrected October
14, 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-2017-0902.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
206-231-3223; fax 206-231-3398.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (r)(5) and (r)(6) of this AD.
(r) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
May 3, 2018.
(i) Airbus Service Bulletin A320-53-1029, Revision 01, including
Appendix 01, dated April 29, 2002.
(ii) Airbus Service Bulletin A320-53-1240, Revision 01, dated
April 4, 2016.
(iii) Airbus Service Bulletin A320-53-1240, Revision 02, dated
March 14, 2017.
[[Page 13395]]
(iv) Airbus Service Bulletin A320-53-1263, Revision 01, dated
February 29, 2016.
(v) Airbus Service Bulletin A320-53-1263, Revision 02, excluding
Appendix 01 and including Appendix 02, dated December 6, 2017.
(vi) Airbus Service Bulletin A320-53-1264, Revision 01,
excluding Appendix 01, dated July 4, 2016.
(4) The following service information was approved for IBR on
March 15, 2004 (69 FR 5907, February 9, 2004).
(i) Airbus Service Bulletin A320-53-1030, Revision 01, excluding
Appendix 01, dated May 21, 2002.
(ii) Reserved.
(5) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email [email protected]; internet https://www.airbus.com.
(6) 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.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on March 2, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-05019 Filed 3-28-18; 8:45 am]
BILLING CODE 4910-13-P
