Airworthiness Directives; Airbus Airplanes, 5906-5912 [2018-02359]
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Federal Register / Vol. 83, No. 29 / Monday, February 12, 2018 / Rules and Regulations
(j) Material Incorporated by Reference
None.
for and locating Docket No. FAA–2017–
0707.
Issued in Renton, Washington, on January
2, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
Examining the AD Docket
[FR Doc. 2018–02751 Filed 2–9–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0707; Product
Identifier 2016–NM–014–AD; Amendment
39–19185; AD 2018–03–12]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A318 series airplanes;
Model A319 series airplanes; Model
A320–211, –212, –214, –231, –232, and
–233 airplanes; and Model A321–111,
–112, –131, –211, –212, –213, –231, and
–232 airplanes. This AD was prompted
by reports of fatigue damage in the
structure for the door stop fittings on
certain fuselage frames (FR). This AD
requires repetitive rototest inspections
for cracking of the fastener holes in
certain door stop fittings, and repair if
necessary. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective March 19,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 19, 2018.
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, 1601
Lind Avenue SW, Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
It is also available on the internet at
https://www.regulations.gov by searching
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SUMMARY:
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You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0707; 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 street 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, 1601 Lind
Avenue SW, Renton, WA 98057–3356;
telephone: 425–227–1405; fax: 425–
227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus Model A318
series airplanes; Model A319 series
airplanes; Model A320–211, –212, –214,
–231, –232, and –233 airplanes; and
Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
The NPRM published in the Federal
Register on July 25, 2017 (82 FR 34449)
(‘‘the NPRM’’). The NPRM was
prompted by reports of fatigue damage
in the structure for the door stop fittings
on certain fuselage frames. The NPRM
proposed to require repetitive rototest
inspections for cracking of the fastener
holes in certain door stop fittings, and
repair if necessary. We are issuing this
AD to detect and correct cracking at the
door stop fitting holes of fuselage FR66
and FR68. Such cracking could result in
reduced structural integrity of the
airplane due to the failure of structural
components.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2016–0238,
dated December 2, 2016; corrected
January 4, 2017 (referred to after this as
the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus Model A318 series
airplanes; Model A319 series airplanes;
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Model A320–211, –212, –214, –231,
–232, and –233 airplanes; and Model
A321–111, –112, –131, –211, –212,
–213, –231, and –232 airplanes. The
MCAI states:
During an A320 fatigue test campaign, it
was determined that fatigue damage could
appear at the door stop fitting holes of
fuselage frame (FR) 66 and FR 68 on left hand
(LH) and right hand (RH) sides.
This condition, if not detected and
corrected, could affect the structural integrity
of the airframe.
Two inspections, Airworthiness
Limitations Item (ALI) tasks 534129 and
534130, were introduced in the
Airworthiness Limitations Section (ALS) Part
2 with the April 2012 revision and with some
compliance time changes with Revision 3 of
ALS Part 2 of October 2014.
Since these ALI tasks were implemented,
a significant number of reports [were]
received concerning non-critical damage and
early crack findings. Prompted by these
reports, Airbus published SB A320–53–1288
and SB A320–53–1290, providing inspection
instructions to improve damage management
and modification instructions.
Consequently, EASA issued AD 2016–
0015, requiring repetitive rototest inspections
of the affected door stop fitting holes and,
depending on findings, repair of any cracked
area(s).
Since that [EASA] AD was issued, ALS
Part 2 Revision 04 and later on Revision 05
were published, introducing updated
thresholds and/or intervals for some tasks as
specified in Airbus SB A320–53–1288,
introducing new configuration of aeroplane
with RETRO WING having accomplished SB
A320–57–1193 (mod 160080), and keeping
the threshold or interval only in flight cycles
(FC).
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2016–0015, which is superseded, but
requires those actions within the updated
thresholds and intervals. In addition, a
corrected threshold for pre-mod 160021 A321
aeroplanes is introduced and the
Applicability is reduced to exclude
configurations that are not affected.
This [EASA] AD is republished to clarify
some requirements in Appendix 1 [in this
EASA 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–
0707.
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 Add a Grace Period for
Certain Repetitive Inspections
United Airlines (UAL) requested that
we revise paragraph (h) of the proposed
AD to allow a 60-day grace period after
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the effective date of this AD to give
operators time to update their
maintenance programs. UAL noted that
for airplanes on which inspections were
previously accomplished as specified in
airworthiness limitation item (ALI) task
534129 or 534130, paragraph (h) of the
proposed AD requires future inspections
be done in accordance with Airbus
Service Bulletin A320–53–1288,
Revision 01, including Appendixes 01,
02, and 03, dated October 3, 2016. UAL
noted that operators who are not yet
incorporating Airbus Service Bulletin
A320–53–1288, Revision 01, including
Appendixes 01, 02, and 03, dated
October 3, 2016, may have to schedule
special inspection visits instead of
doing the inspections during scheduled
maintenance.
We agree with the commenter’s
request to add a grace period to
paragraph (h) of this AD to allow
operators to plan for the new inspection
interval. However, since the commenter
did not provide adequate justification to
support a 60-day grace period, we have
determined that a 30-day grace period is
appropriate. Additionally, under the
provisions of paragraph (q)(1) of this
AD, we will consider requests for
approval of an extension of the
compliance time if sufficient data are
submitted to substantiate that the new
compliance time would provide an
acceptable level of safety. We have
revised paragraph (h) of this AD to
include a 30-day grace period.
Request To Allow Deviations From the
Service Information for Certain
Modified Airplanes
UAL requested that either the service
information or the proposed AD be
revised to provide alternate instructions
for airplanes with modified hardware.
UAL noted that ‘‘paragraph (i)’’ of the
proposed AD requires repetitive
inspections on airplanes modified by
cold working fastener holes, which
includes installing oversize hardware.
UAL pointed out that the inspections
must be done in accordance with Airbus
Service Bulletin A320–53–1288,
Revision 01, including Appendixes 01,
02, and 03, dated October 3, 2016,
which requires using nominal size
hardware that no longer exists on
modified airplanes.
We infer that the commenter meant to
refer to paragraph (j) of the proposed
AD, which discusses post-modification
inspections, rather than paragraph (i) of
the proposed AD, which discusses an
optional modification. We agree with
the commenter’s request. We
acknowledge that Airbus Service
Bulletin A320–53–1288, Revision 01,
including Appendixes 01, 02, and 03,
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18:49 Feb 09, 2018
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dated October 3, 2016, does not
specifically address oversize hardware;
however, EASA has stated that ‘‘the
same inspection principle applies for
post SB [Service Bulletin] 53–1290
configuration.’’ Therefore, we have
retained Airbus Service Bulletin A320–
53–1288, Revision 01, including
Appendixes 01, 02, and 03, dated
October 3, 2016, in paragraph (j) of this
AD. We have also revised paragraph (j)
of this AD to include an option for
operators to obtain inspection
instructions using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or
EASA; or Airbus’s EASA Design
Organization Approval (DOA).
Request To Remove a Reference to a
Non-Terminating Action
UAL requested that we remove the
statement ‘‘repair of an airplane as
required by this paragraph does not
constitute terminating action for the
repetitive inspections required by
paragraph (g) or (j) of this AD for that
repair, unless specified otherwise’’ from
paragraph (k) of the proposed AD. UAL
suggested that statement be replaced
with one instructing operators to
accomplish inspections as specified in
the repair instructions.
UAL noted that paragraph (k) of the
proposed AD states that a crack repair
must be done using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or
EASA; or Airbus’s EASA DOA and says
that such a repair does not constitute
terminating action for the repetitive
inspections done in accordance with
Airbus Service Bulletin A320–53–1288,
Revision 01, including Appendixes 01,
02, and 03, dated October 3, 2016,
unless specified otherwise.
UAL pointed out that Airbus Service
Bulletin A320–53–1288, Revision 01,
including Appendixes 01, 02, and 03,
dated October 3, 2016, contains
language to allow operators to
accomplish crack repairs in accordance
with structural repair manual (SRM) 53–
41–12, and then perform inspections of
the repaired area in accordance with
SRM 53–41–12. UAL noted that the
SRM repair instructions do not state that
they terminate the inspections in Airbus
Service Bulletin A320–53–1288,
Revision 01, including Appendixes 01,
02, and 03, dated October 3, 2016. UAL
further noted that Airbus Service
Bulletin A320–53–1288, Revision 01,
including Appendixes 01, 02, and 03,
dated October 3, 2016, only applies to
unrepaired areas with nominal size
holes (the repaired areas would have
oversized holes).
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5907
We disagree with the commenter’s
request. We acknowledge that Airbus
Service Bulletin A320–53–1288,
Revision 01, including Appendixes 01,
02, and 03, dated October 3, 2016,
allows repairs to be done using an SRM.
However, this AD does not include that
allowance since SRMs published before
the effective date of this AD might not
address the unsafe condition identified
in this AD. Therefore, paragraph (k) of
this AD requires repairs to be done
using a method approved by the
Manager, International Section,
Transport Standards Branch, FAA; or
EASA; or Airbus’s EASA DOA.
Additionally, the statement that the
commenter requested us to remove from
paragraph (k) of this proposed AD aligns
with the MCAI. The statement is meant
to clarify that doing a repair does not
necessarily terminate the repetitive
inspections; the repetitive inspections
would only be terminated if the repair
approved by the Manager, International
Section, Transport Standards Branch,
FAA; or EASA; or Airbus’s EASA DOA
specifically states that the inspections
are terminated. If the approved repair
does not state that the inspections are
terminated, operators must continue to
inspect using Airbus Service Bulletin
A320–53–1288, Revision 01, including
Appendixes 01, 02, and 03, dated
October 3, 2016, or using a method
approved by the Manager, International
Section, Transport Standards Branch,
FAA; or EASA; or Airbus’s EASA DOA.
Therefore, we have not changed the
requirements in paragraph (k) of this AD
nor have we removed the statement
identified by the commenter. However,
we have revised paragraph (g) of this AD
to include an option for operators to
obtain inspection instructions using a
method approved by the Manager,
International Section, Transport
Standards Branch, FAA; or EASA; or
Airbus’s EASA DOA.
Request To Remove Requirement To
Obtain Certain Inspection Instructions
UAL requested that we remove
paragraph (l)(2) of the proposed AD
because it has no real purpose. UAL
noted that paragraph (l)(2) of the
proposed AD requires operators to
obtain inspection instructions and
corrective actions for all repaired
fastener holes by contacting the
Manager, International Section,
Transport Standards Branch, FAA; or
EASA; or Airbus’s EASA DOA. UAL
claimed that if a repair was
accomplished using the instructions in
an SRM or repair design approval sheet
(RDAS), the repair approval contains, at
a minimum, the initial compliance
threshold. UAL added that it is standard
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practice for operators to contact Airbus
prior to the inspection threshold if the
compliance method and intervals are
not yet defined.
We disagree with the commenter’s
request. Airbus intends to provide
specific instructions for airplanes
inspected in accordance with ALI task
534129 or task 534130 and repaired in
accordance with an SRM or RDAS
published before the effective date of
this AD. Since repair instructions
published before the effective date of
this AD might not address the unsafe
condition identified in this AD, the
SRM or RDAS instructions might need
to be re-evaluated or revised to address
the unsafe condition. In addition, we do
not rely on an operator’s standard
practices, and instead require operators
to obtain inspections and corrective
actions to address the unsafe condition.
We have not revised this AD regarding
this issue.
Request To Clarify Actions for
Airplanes With Certain Repairs
UAL requested that we delete
paragraph (n) of the proposed AD. UAL
noted that paragraph (n) of the proposed
AD requires operators to determine if a
repair was done using an RDAS that is
unrelated to ALI task 534129 or task
534130. UAL suggested that the repair
instructions would have to state that the
damage was found as a result of the
applicable ALI, but noted that the ALI
task is an inspection that may not be
referenced in a documented repair. UAL
questioned the relevance of whether or
not a repair was related to ALI task
534129 or task 534130, noting that the
same considerations are given to repair
instructions, regardless of how damage
was found. UAL stated that operators
would know to seek an alternative
method of compliance (AMOC) if they
cannot inspect a previously repaired
area in accordance with Airbus Service
Bulletin A320–53–1288, Revision 01,
including Appendixes 01, 02, and 03,
dated October 3, 2016.
We disagree with the commenter’s
request. The intent of paragraph (n) of
the proposed AD is to require operators
to re-evaluate existing repairs performed
using an Airbus RDAS unrelated to ALI
task 534129 or task 534130 because
those repairs may not address the
findings from the specific inspection
types required by the ALI tasks.
Therefore, the corresponding repairs
might not address the unsafe condition
and operators might need new
instructions. We have not changed this
AD in this regard.
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 minor 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.
Request To Verify the Latest Service
Information is Referenced
UAL requested that, prior to the
release of this final rule, we verify that
we are referencing the latest revisions of
Airbus Service Bulletin A320–53–1288,
Revision 01, including Appendixes 01,
02, and 03, dated October 3, 2016; and
Airbus Service Bulletin A320–53–1290,
Revision 01, dated October 3, 2016.
We agree with the commenter’s
request. We have verified that no later
revisions of the service information
have been issued, and no change is
needed to this AD.
Related Service Information Under 1
CFR Part 51
Explanation of Change to the Final Rule
In the proposed AD, Table 1 to
paragraphs (g) and (j) of this AD and
Table 2 to paragraphs (g) and (j) of this
AD included a compliance time that
stated ‘‘. . . or before November 30,
2017. . . .’’ Since this final rule will
become effective after November 30,
2017, we have changed this statement to
read ‘‘. . . or within 30 days after the
effective date of this AD. . . .’’ We have
determined that this revised compliance
time addresses the unsafe condition.
Conclusion
We reviewed the relevant data,
considered the comments received, and
Airbus has issued the following
service information.
• Airbus Service Bulletin A320–53–
1288, Revision 01, including
Appendixes 01, 02, and 03, dated
October 3, 2016. This service
information describes procedures for
rototest inspections for cracking of the
fastener holes in the airframe structure
for the door stop fittings installation in
FR66 and FR68.
• Airbus Service Bulletin A320–53–
1290, Revision 01, dated October 3,
2016. This service information describes
procedures for cold working the fastener
holes in the airframe structure for the
door stop fittings installation in FR66
and FR68.
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 1,084
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Inspections ........
23 work-hours × $85 per hour = $1,955 per
inspection cycle.
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We estimate the following costs to do
any necessary repairs that would be
Parts cost
Cost per product
$0
$1,955 per inspection cycle ..
required based on the results of the
required inspection. We have no way of
Cost on U.S. operators
$2,119,220 per inspection
cycle.
determining the number of aircraft that
might need this repair.
ON-CONDITION COSTS
Action
Labor cost
Repair ...........................................................................
27 work-hours × $85 per hour = $2,295 ......................
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Parts cost
12FER1
$610
Cost per
product
$2,905
Federal Register / Vol. 83, No. 29 / Monday, February 12, 2018 / Rules and Regulations
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.
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.
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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;
18:49 Feb 09, 2018
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:
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
Jkt 244001
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2018–03–12 Airbus: Amendment 39–19185;
Docket No. FAA–2017–0707; Product
Identifier 2016–NM–014–AD.
(a) Effective Date
This AD is effective March 19, 2018.
None.
(c) Applicability
This AD applies to Airbus Model A318–
111, –112, –121, and –122 airplanes; Model
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; Model A320–211,
–212, –214, 231, –232, and –233 airplanes;
and Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes;
certificated in any category; all manufacturer
serial numbers, except airplanes specified in
paragraphs (c)(1), (c)(2), and (c)(3) of this AD.
(1) Airplanes on which Airbus
modification (Mod) 157039 has been
embodied in production.
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(2) Model A319 series airplanes on which
Mod 28238, Mod 28162, and Mod 28342
have been embodied in production.
(3) Model A318 series airplanes on which
Mod 39195 has been embodied in production
or Airbus Service Bulletin A320–00–1219 has
been embodied in service.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of
fatigue damage in the structure for the door
stop fittings on certain fuselage frames (FR).
We are issuing this AD to detect and correct
cracking at the door stop fitting holes of
fuselage FR66 and FR68. Such cracking could
result in reduced structural integrity of the
airplane due to the failure of structural
components.
(f) Compliance
PART 39—AIRWORTHINESS
DIRECTIVES
(b) Affected ADs
Regulatory Findings
VerDate Sep<11>2014
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.
5909
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Rototest Inspections
Within the applicable compliance times
specified in table 1 to paragraphs (g) and (j)
of this AD and table 2 to paragraphs (g) and
(j) of this AD: Do a rototest inspection of all
holes below each door stop fitting at fuselage
FR66 and FR68, both left-hand (LH) and
right-hand (RH) sides, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1288, Revision 01,
including Appendixes 01, 02, and 03, dated
October 3, 2016; or 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). Repeat the inspections
thereafter at the applicable compliance times
specified in table 1 to paragraphs (g) and (j)
of this AD and table 2 to paragraphs (g) and
(j) of this AD, until the modification specified
in paragraph (i) of this AD is done. Where the
‘‘Threshold’’ column of table 1 to paragraphs
(g) and (j) of this AD and table 2 to
paragraphs (g) and (j) of this AD, specifies
compliance times in ‘‘FC’’ (flight cycles),
those compliance times are total flight cycles
since the first flight of the airplane.
BILLING CODE 4910–13–P
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Table 1 to paragraphs (g) and G) of this AD -Aft passenger/crew door cut-out door
stop fittings holes at FR 66 WEB LH/RH
Airplanes affected
Threshold
Interval (not to
exceed)
A318-PAX (A318-passenger)
Before 33,800 FC
5,900 FC
A319-PAX pre-mod 160001 and
pre-mod 160080
Before 42,700 FC
7,500 FC
A319-PAXpost-mod 160001 OR
A319-PAX post-mod 160080
Before 40,300 FC
7,200 FC
A320 pre-mod 160001 and
pre-mod 160080
Before 48,000 FC
9,700 FC
A320 post-mod 160001 OR A320
post-mod 160080
Before 45,000 FC
7,800 FC
A321 pre-mod 160021
Before 34,500 FC or within
30 days after the effective
date of this AD, whichever
is later without exceeding
the accumulation of 42,300
FC since first flight
17,000 FC
A321 post-mod 160021
39,400 FC
8,500 FC
Table 2 to paragraphs (g) and G) of this AD - Aft passenger/crew door cut-out door
stop fittings holes at FR68 WEB LH/RH
5,900 FC
Before 34,400 FC
7,500 FC
A319-PAXpost-mod 160001
OR A319-PAX post-mod
160080
Before 33,500 FC
7,200 FC
18:49 Feb 09, 2018
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A319-PAX pre-mod 160001
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Threshold
A318-PAX
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Airplanes affected
Interval (not to
exceed)
Federal Register / Vol. 83, No. 29 / Monday, February 12, 2018 / Rules and Regulations
(h) Airworthiness Limitations Item (ALI)
Inspections Accomplished Before the
Effective Date of This AD
Inspections accomplished as specified in
ALI task 534129 or task 534130 before the
effective date of this AD are acceptable for
compliance with the initial inspection
required by paragraph (g) of this AD. As of
30 days after the effective date of this AD,
repetitive inspections must be continued as
required by paragraph (g) of this AD.
daltland on DSKBBV9HB2PROD with RULES
(i) Optional Modification
For airplanes on which no cracks were
detected during any rototest inspection
required by paragraph (g) of this AD:
Modifying the affected area by cold working
the fastener holes before further flight after
no cracks were detected, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A320–53–1290, Revision 01,
dated October 3, 2016, terminates the
repetitive inspections required by paragraph
(g) of this AD for the modified area only.
(j) Post-Modification Repetitive Inspections
For airplanes on which the modification
specified in paragraph (i) of this AD has been
done: At the compliance time specified in
paragraphs (j)(1), (j)(2), or (j)(3) of this AD, as
applicable, accomplish a rototest inspection
of all holes at the door stop fitting locations
at fuselage FR66 and FR68, both LH and RH
sides, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1288, Revision 01,
including Appendixes 01, 02, and 03, dated
October 3, 2016; or 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). Repeat the inspection
thereafter at intervals not to exceed the
applicable compliance times specified in
table 1 to paragraphs (g) and (j) of this AD
and table 2 to paragraphs (g) and (j) of this
AD.
(1) For airplanes with less than 1,800 flight
cycles accumulated since first flight of the
airplane at the time of accomplishing the
modification specified in paragraph (i) of this
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18:49 Feb 09, 2018
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AD: At the applicable initial compliance time
specified in table 1 to paragraphs (g) and (j)
of this AD and table 2 to paragraphs (g) and
(j) of this AD.
(2) For airplanes with 1,800 flight cycles or
more and less than 13,800 flight cycles
accumulated since first flight of the airplane
at the time of accomplishing the modification
specified in paragraph (i) of this AD: Before
the accumulation of 48,000 flight cycles since
first flight of the airplane.
(3) For airplanes with 13,800 flight cycles
or more accumulated since first flight of the
airplane at the time of accomplishing the
modification specified in paragraph (i) of this
AD: Before the accumulation of 60,000 flight
cycles since first flight of the airplane.
(k) Repair
If, during any inspection required by
paragraph (g) or (j) of this AD, any crack is
detected, before further flight, repair using a
method approved by the Manager,
International Section, Transport Standards
Branch, FAA; or EASA; or Airbus’s EASA
DOA. Repair of an airplane as required by
this paragraph does not constitute
terminating action for the repetitive
inspections required by paragraph (g) or (j) of
this AD for that airplane, unless specified
otherwise in instructions obtained using a
method approved by the Manager,
International Section, Transport Standards
Branch, FAA; or EASA; or Airbus’s EASA
DOA.
(l) Post-Repair Actions for Certain Airplanes
For an airplane that has been inspected as
specified in ALI task 534129 or task 534130
and repaired before the effective date of this
AD as specified in the applicable structural
repair manual (SRM) or as specified in an
Airbus repair design approval sheet (RDAS):
Comply with the requirements of paragraphs
(l)(1) and (l)(2) of this AD.
(1) For all fastener holes where no damage
or cracks were detected (i.e., those not
repaired), accomplish the actions required by
paragraph (g) of this AD, unless the
terminating action specified in paragraph (m)
of this AD has been done.
(2) For all repaired fastener holes: Within
30 days after the effective date of this AD, or
within a compliance time approved by the
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Manager, International Section, Transport
Standards Branch, FAA; or EASA; or
Airbus’s EASA DOA, whichever occurs later,
contact the Manager, International Section,
Transport Standards Branch, FAA; or EASA;
or Airbus’s EASA DOA; for inspection
instructions and applicable corrective
actions, and do the inspections and
applicable corrective actions accordingly.
(m) Terminating Action for Certain
Airplanes
For airplanes that have been inspected, as
specified in ALI task 534129 or task 534130,
and repaired before the effective date of this
AD, as specified in the applicable SRM, or as
specified in an Airbus RDAS: Modification of
the four fastener holes at door stop locations
where no damage or crack was detected (i.e.,
door stop locations not repaired) by cold
working holes before further flight after no
cracks were detected, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1290, Revision 01,
dated October 3, 2016, constitutes
terminating action for the repetitive
inspections of those four fastener holes at
those door stop locations as required by
paragraphs (g) or (l)(1) of this AD for that
airplane.
(n) Actions for Airplanes With Certain
Repairs
For an airplane that has been repaired
before the effective date of this AD in the
areas described in this AD using an Airbus
RDAS unrelated to ALI task 534129 or task
534130: Before exceeding the compliance
times specified in paragraph (g) of this AD,
contact the Manager, International Section,
Transport Standards Branch, FAA; or EASA;
or Airbus’s EASA DOA; for corrective action
instructions and accomplish those
instructions accordingly. Accomplishment of
corrective action(s) on an airplane, as
required by this paragraph, does not
constitute terminating action for the
repetitive inspections as required by
paragraphs (g) or (j) of this AD for that
airplane, as applicable, unless specified
otherwise in the instructions.
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Federal Register / Vol. 83, No. 29 / Monday, February 12, 2018 / Rules and Regulations
(o) Terminating Action for ALI Tasks
(1) Accomplishment of inspections on an
airplane, as required by paragraphs (g), (j), or
(l) of this AD, as applicable, constitutes
terminating action for the inspection
requirements of ALI task 534129 or task
534130, as applicable, for that airplane.
(2) Modification of the four fastener holes
at a door stop location of an airplane as
specified in paragraphs (i) or (m) of this AD,
as applicable, and subsequent initial
inspection required by paragraph (j) of this
AD, constitutes terminating action for the
inspection requirements of ALI task 534129
or task 534130, as applicable, for those holes
for that airplane. Subsequent repetitive
inspections are required by paragraph (j) of
this AD.
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(p) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraphs (g) and (j) of
this AD, if those actions were performed
before the effective date of this AD using
Airbus Service Bulletin A320–53–1288,
including Appendixes 01 and 02, dated
October 10, 2014.
(2) This paragraph provides credit for
actions required by paragraphs (i) and (m) of
this AD, if those actions were performed
before the effective date of this AD using
Airbus Service Bulletin A320–53–1290,
dated October 10, 2014.
(q) 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 Section, send it
to the attention of the person identified in
paragraph (r)(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: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or EASA;
or Airbus’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): 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
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18:49 Feb 09, 2018
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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.
DEPARTMENT OF TRANSPORTATION
(r) Related Information
[Docket No. FAA–2017–0901; Product
Identifier 2017–NM–106–AD; Amendment
39–19183; AD 2018–03–10]
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0238, dated December 2, 2016;
corrected January 4, 2017, 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–2017–0707.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW,
Renton, WA 98057–3356; telephone: 425–
227–1405; fax: 425–227–1149.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (s)(3) and (s)(4) of this AD.
(s) 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.
(i) Airbus Service Bulletin A320–53–1288,
Revision 01, including Appendixes 01, 02,
and 03, dated October 3, 2016.
(ii) Airbus Service Bulletin A320–53–1290,
Revision 01, dated October 3, 2016.
(3) 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.
(4) You may view this service information
at the FAA, Transport Standards Branch,
1601 Lind Avenue SW, Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) 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 January
29, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–02359 Filed 2–9–18; 8:45 am]
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Federal Aviation Administration
14 CFR Part 39
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 757–300 series
airplanes. This AD was prompted by
reports of scribe line damage on fuselage
skin. This AD requires detailed
inspections of fuselage skin for the
presence of scribe lines, and applicable
on-condition actions. We are issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective March 19,
2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 19, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC
110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet
https://www.myboeingfleet.com. You
may view this service information at the
FAA, Transport Standards Branch, 1601
Lind Avenue SW, Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–
0901.
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–
0901; 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 final rule, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
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]]>Agencies
[Federal Register Volume 83, Number 29 (Monday, February 12, 2018)]
[Rules and Regulations]
[Pages 5906-5912]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-02359]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0707; Product Identifier 2016-NM-014-AD; Amendment
39-19185; AD 2018-03-12]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A318 series airplanes; Model A319 series airplanes; Model
A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-
111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD
was prompted by reports of fatigue damage in the structure for the door
stop fittings on certain fuselage frames (FR). This AD requires
repetitive rototest inspections for cracking of the fastener holes in
certain door stop fittings, and repair if necessary. We are issuing
this AD to address the unsafe condition on these products.
DATES: This AD is effective March 19, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 19,
2018.
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, 1601 Lind Avenue
SW, Renton, WA. For information on the availability of this material at
the FAA, call 425-227-1221. It is also available on the internet at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2017-0707.
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-
0707; 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 street 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, 1601 Lind
Avenue SW, Renton, WA 98057-3356; telephone: 425-227-1405; fax: 425-
227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Airbus Model A318
series airplanes; Model A319 series airplanes; Model A320-211, -212, -
214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -
211, -212, -213, -231, and -232 airplanes. The NPRM published in the
Federal Register on July 25, 2017 (82 FR 34449) (``the NPRM''). The
NPRM was prompted by reports of fatigue damage in the structure for the
door stop fittings on certain fuselage frames. The NPRM proposed to
require repetitive rototest inspections for cracking of the fastener
holes in certain door stop fittings, and repair if necessary. We are
issuing this AD to detect and correct cracking at the door stop fitting
holes of fuselage FR66 and FR68. Such cracking could result in reduced
structural integrity of the airplane due to the failure of structural
components.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2016-0238, dated December 2, 2016; corrected January 4, 2017 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A318 series airplanes; Model A319 series airplanes; Model A320-211, -
212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -
131, -211, -212, -213, -231, and -232 airplanes. The MCAI states:
During an A320 fatigue test campaign, it was determined that
fatigue damage could appear at the door stop fitting holes of
fuselage frame (FR) 66 and FR 68 on left hand (LH) and right hand
(RH) sides.
This condition, if not detected and corrected, could affect the
structural integrity of the airframe.
Two inspections, Airworthiness Limitations Item (ALI) tasks
534129 and 534130, were introduced in the Airworthiness Limitations
Section (ALS) Part 2 with the April 2012 revision and with some
compliance time changes with Revision 3 of ALS Part 2 of October
2014.
Since these ALI tasks were implemented, a significant number of
reports [were] received concerning non-critical damage and early
crack findings. Prompted by these reports, Airbus published SB A320-
53-1288 and SB A320-53-1290, providing inspection instructions to
improve damage management and modification instructions.
Consequently, EASA issued AD 2016-0015, requiring repetitive
rototest inspections of the affected door stop fitting holes and,
depending on findings, repair of any cracked area(s).
Since that [EASA] AD was issued, ALS Part 2 Revision 04 and
later on Revision 05 were published, introducing updated thresholds
and/or intervals for some tasks as specified in Airbus SB A320-53-
1288, introducing new configuration of aeroplane with RETRO WING
having accomplished SB A320-57-1193 (mod 160080), and keeping the
threshold or interval only in flight cycles (FC).
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2016-0015, which is superseded, but requires
those actions within the updated thresholds and intervals. In
addition, a corrected threshold for pre-mod 160021 A321 aeroplanes
is introduced and the Applicability is reduced to exclude
configurations that are not affected.
This [EASA] AD is republished to clarify some requirements in
Appendix 1 [in this EASA 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-
0707.
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 Add a Grace Period for Certain Repetitive Inspections
United Airlines (UAL) requested that we revise paragraph (h) of the
proposed AD to allow a 60-day grace period after
[[Page 5907]]
the effective date of this AD to give operators time to update their
maintenance programs. UAL noted that for airplanes on which inspections
were previously accomplished as specified in airworthiness limitation
item (ALI) task 534129 or 534130, paragraph (h) of the proposed AD
requires future inspections be done in accordance with Airbus Service
Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and
03, dated October 3, 2016. UAL noted that operators who are not yet
incorporating Airbus Service Bulletin A320-53-1288, Revision 01,
including Appendixes 01, 02, and 03, dated October 3, 2016, may have to
schedule special inspection visits instead of doing the inspections
during scheduled maintenance.
We agree with the commenter's request to add a grace period to
paragraph (h) of this AD to allow operators to plan for the new
inspection interval. However, since the commenter did not provide
adequate justification to support a 60-day grace period, we have
determined that a 30-day grace period is appropriate. Additionally,
under the provisions of paragraph (q)(1) of this AD, we will consider
requests for approval of an extension of the compliance time if
sufficient data are submitted to substantiate that the new compliance
time would provide an acceptable level of safety. We have revised
paragraph (h) of this AD to include a 30-day grace period.
Request To Allow Deviations From the Service Information for Certain
Modified Airplanes
UAL requested that either the service information or the proposed
AD be revised to provide alternate instructions for airplanes with
modified hardware. UAL noted that ``paragraph (i)'' of the proposed AD
requires repetitive inspections on airplanes modified by cold working
fastener holes, which includes installing oversize hardware. UAL
pointed out that the inspections must be done in accordance with Airbus
Service Bulletin A320-53-1288, Revision 01, including Appendixes 01,
02, and 03, dated October 3, 2016, which requires using nominal size
hardware that no longer exists on modified airplanes.
We infer that the commenter meant to refer to paragraph (j) of the
proposed AD, which discusses post-modification inspections, rather than
paragraph (i) of the proposed AD, which discusses an optional
modification. We agree with the commenter's request. We acknowledge
that Airbus Service Bulletin A320-53-1288, Revision 01, including
Appendixes 01, 02, and 03, dated October 3, 2016, does not specifically
address oversize hardware; however, EASA has stated that ``the same
inspection principle applies for post SB [Service Bulletin] 53-1290
configuration.'' Therefore, we have retained Airbus Service Bulletin
A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated
October 3, 2016, in paragraph (j) of this AD. We have also revised
paragraph (j) of this AD to include an option for operators to obtain
inspection instructions using a method approved by the Manager,
International Section, Transport Standards Branch, FAA; or EASA; or
Airbus's EASA Design Organization Approval (DOA).
Request To Remove a Reference to a Non-Terminating Action
UAL requested that we remove the statement ``repair of an airplane
as required by this paragraph does not constitute terminating action
for the repetitive inspections required by paragraph (g) or (j) of this
AD for that repair, unless specified otherwise'' from paragraph (k) of
the proposed AD. UAL suggested that statement be replaced with one
instructing operators to accomplish inspections as specified in the
repair instructions.
UAL noted that paragraph (k) of the proposed AD states that a crack
repair must be done using a method approved by the Manager,
International Section, Transport Standards Branch, FAA; or EASA; or
Airbus's EASA DOA and says that such a repair does not constitute
terminating action for the repetitive inspections done in accordance
with Airbus Service Bulletin A320-53-1288, Revision 01, including
Appendixes 01, 02, and 03, dated October 3, 2016, unless specified
otherwise.
UAL pointed out that Airbus Service Bulletin A320-53-1288, Revision
01, including Appendixes 01, 02, and 03, dated October 3, 2016,
contains language to allow operators to accomplish crack repairs in
accordance with structural repair manual (SRM) 53-41-12, and then
perform inspections of the repaired area in accordance with SRM 53-41-
12. UAL noted that the SRM repair instructions do not state that they
terminate the inspections in Airbus Service Bulletin A320-53-1288,
Revision 01, including Appendixes 01, 02, and 03, dated October 3,
2016. UAL further noted that Airbus Service Bulletin A320-53-1288,
Revision 01, including Appendixes 01, 02, and 03, dated October 3,
2016, only applies to unrepaired areas with nominal size holes (the
repaired areas would have oversized holes).
We disagree with the commenter's request. We acknowledge that
Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes
01, 02, and 03, dated October 3, 2016, allows repairs to be done using
an SRM. However, this AD does not include that allowance since SRMs
published before the effective date of this AD might not address the
unsafe condition identified in this AD. Therefore, paragraph (k) of
this AD requires repairs to be done using a method approved by the
Manager, International Section, Transport Standards Branch, FAA; or
EASA; or Airbus's EASA DOA.
Additionally, the statement that the commenter requested us to
remove from paragraph (k) of this proposed AD aligns with the MCAI. The
statement is meant to clarify that doing a repair does not necessarily
terminate the repetitive inspections; the repetitive inspections would
only be terminated if the repair approved by the Manager, International
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA
specifically states that the inspections are terminated. If the
approved repair does not state that the inspections are terminated,
operators must continue to inspect using Airbus Service Bulletin A320-
53-1288, Revision 01, including Appendixes 01, 02, and 03, dated
October 3, 2016, or using a method approved by the Manager,
International Section, Transport Standards Branch, FAA; or EASA; or
Airbus's EASA DOA. Therefore, we have not changed the requirements in
paragraph (k) of this AD nor have we removed the statement identified
by the commenter. However, we have revised paragraph (g) of this AD to
include an option for operators to obtain inspection instructions using
a method approved by the Manager, International Section, Transport
Standards Branch, FAA; or EASA; or Airbus's EASA DOA.
Request To Remove Requirement To Obtain Certain Inspection Instructions
UAL requested that we remove paragraph (l)(2) of the proposed AD
because it has no real purpose. UAL noted that paragraph (l)(2) of the
proposed AD requires operators to obtain inspection instructions and
corrective actions for all repaired fastener holes by contacting the
Manager, International Section, Transport Standards Branch, FAA; or
EASA; or Airbus's EASA DOA. UAL claimed that if a repair was
accomplished using the instructions in an SRM or repair design approval
sheet (RDAS), the repair approval contains, at a minimum, the initial
compliance threshold. UAL added that it is standard
[[Page 5908]]
practice for operators to contact Airbus prior to the inspection
threshold if the compliance method and intervals are not yet defined.
We disagree with the commenter's request. Airbus intends to provide
specific instructions for airplanes inspected in accordance with ALI
task 534129 or task 534130 and repaired in accordance with an SRM or
RDAS published before the effective date of this AD. Since repair
instructions published before the effective date of this AD might not
address the unsafe condition identified in this AD, the SRM or RDAS
instructions might need to be re-evaluated or revised to address the
unsafe condition. In addition, we do not rely on an operator's standard
practices, and instead require operators to obtain inspections and
corrective actions to address the unsafe condition. We have not revised
this AD regarding this issue.
Request To Clarify Actions for Airplanes With Certain Repairs
UAL requested that we delete paragraph (n) of the proposed AD. UAL
noted that paragraph (n) of the proposed AD requires operators to
determine if a repair was done using an RDAS that is unrelated to ALI
task 534129 or task 534130. UAL suggested that the repair instructions
would have to state that the damage was found as a result of the
applicable ALI, but noted that the ALI task is an inspection that may
not be referenced in a documented repair. UAL questioned the relevance
of whether or not a repair was related to ALI task 534129 or task
534130, noting that the same considerations are given to repair
instructions, regardless of how damage was found. UAL stated that
operators would know to seek an alternative method of compliance (AMOC)
if they cannot inspect a previously repaired area in accordance with
Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes
01, 02, and 03, dated October 3, 2016.
We disagree with the commenter's request. The intent of paragraph
(n) of the proposed AD is to require operators to re-evaluate existing
repairs performed using an Airbus RDAS unrelated to ALI task 534129 or
task 534130 because those repairs may not address the findings from the
specific inspection types required by the ALI tasks. Therefore, the
corresponding repairs might not address the unsafe condition and
operators might need new instructions. We have not changed this AD in
this regard.
Request To Verify the Latest Service Information is Referenced
UAL requested that, prior to the release of this final rule, we
verify that we are referencing the latest revisions of Airbus Service
Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and
03, dated October 3, 2016; and Airbus Service Bulletin A320-53-1290,
Revision 01, dated October 3, 2016.
We agree with the commenter's request. We have verified that no
later revisions of the service information have been issued, and no
change is needed to this AD.
Explanation of Change to the Final Rule
In the proposed AD, Table 1 to paragraphs (g) and (j) of this AD
and Table 2 to paragraphs (g) and (j) of this AD included a compliance
time that stated ``. . . or before November 30, 2017. . . .'' Since
this final rule will become effective after November 30, 2017, we have
changed this statement to read ``. . . or within 30 days after the
effective date of this AD. . . .'' We have determined that this revised
compliance time addresses the unsafe condition.
Conclusion
We reviewed the relevant data, considered 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 minor 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 the following service information.
Airbus Service Bulletin A320-53-1288, Revision 01,
including Appendixes 01, 02, and 03, dated October 3, 2016. This
service information describes procedures for rototest inspections for
cracking of the fastener holes in the airframe structure for the door
stop fittings installation in FR66 and FR68.
Airbus Service Bulletin A320-53-1290, Revision 01, dated
October 3, 2016. This service information describes procedures for cold
working the fastener holes in the airframe structure for the door stop
fittings installation in FR66 and FR68.
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 1,084 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
----------------------------------------------------------------------------------------------------------------
Inspections................ 23 work-hours x $85 $0 $1,955 per inspection $2,119,220 per
per hour = $1,955 cycle. inspection cycle.
per inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the required inspection. We
have no way of determining the number of aircraft that might need this
repair.
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Repair..................................... 27 work-hours x $85 per hour = $610 $2,905
$2,295.
----------------------------------------------------------------------------------------------------------------
[[Page 5909]]
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. 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 adding the following new airworthiness
directive (AD):
2018-03-12 Airbus: Amendment 39-19185; Docket No. FAA-2017-0707;
Product Identifier 2016-NM-014-AD.
(a) Effective Date
This AD is effective March 19, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A318-111, -112, -121, and -122
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes; Model A320-211, -212, -214, 231, -232, and -233
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes; certificated in any category; all manufacturer
serial numbers, except airplanes specified in paragraphs (c)(1),
(c)(2), and (c)(3) of this AD.
(1) Airplanes on which Airbus modification (Mod) 157039 has been
embodied in production.
(2) Model A319 series airplanes on which Mod 28238, Mod 28162,
and Mod 28342 have been embodied in production.
(3) Model A318 series airplanes on which Mod 39195 has been
embodied in production or Airbus Service Bulletin A320-00-1219 has
been embodied in service.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of fatigue damage in the
structure for the door stop fittings on certain fuselage frames
(FR). We are issuing this AD to detect and correct cracking at the
door stop fitting holes of fuselage FR66 and FR68. Such cracking
could result in reduced structural integrity of the airplane due to
the failure of structural components.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Rototest Inspections
Within the applicable compliance times specified in table 1 to
paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and
(j) of this AD: Do a rototest inspection of all holes below each
door stop fitting at fuselage FR66 and FR68, both left-hand (LH) and
right-hand (RH) sides, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1288, Revision 01,
including Appendixes 01, 02, and 03, dated October 3, 2016; or 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). Repeat
the inspections thereafter at the applicable compliance times
specified in table 1 to paragraphs (g) and (j) of this AD and table
2 to paragraphs (g) and (j) of this AD, until the modification
specified in paragraph (i) of this AD is done. Where the
``Threshold'' column of table 1 to paragraphs (g) and (j) of this AD
and table 2 to paragraphs (g) and (j) of this AD, specifies
compliance times in ``FC'' (flight cycles), those compliance times
are total flight cycles since the first flight of the airplane.
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(h) Airworthiness Limitations Item (ALI) Inspections Accomplished
Before the Effective Date of This AD
Inspections accomplished as specified in ALI task 534129 or task
534130 before the effective date of this AD are acceptable for
compliance with the initial inspection required by paragraph (g) of
this AD. As of 30 days after the effective date of this AD,
repetitive inspections must be continued as required by paragraph
(g) of this AD.
(i) Optional Modification
For airplanes on which no cracks were detected during any
rototest inspection required by paragraph (g) of this AD: Modifying
the affected area by cold working the fastener holes before further
flight after no cracks were detected, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-53-1290,
Revision 01, dated October 3, 2016, terminates the repetitive
inspections required by paragraph (g) of this AD for the modified
area only.
(j) Post-Modification Repetitive Inspections
For airplanes on which the modification specified in paragraph
(i) of this AD has been done: At the compliance time specified in
paragraphs (j)(1), (j)(2), or (j)(3) of this AD, as applicable,
accomplish a rototest inspection of all holes at the door stop
fitting locations at fuselage FR66 and FR68, both LH and RH sides,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and
03, dated October 3, 2016; or 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). Repeat the inspection thereafter at
intervals not to exceed the applicable compliance times specified in
table 1 to paragraphs (g) and (j) of this AD and table 2 to
paragraphs (g) and (j) of this AD.
(1) For airplanes with less than 1,800 flight cycles accumulated
since first flight of the airplane at the time of accomplishing the
modification specified in paragraph (i) of this AD: At the
applicable initial compliance time specified in table 1 to
paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and
(j) of this AD.
(2) For airplanes with 1,800 flight cycles or more and less than
13,800 flight cycles accumulated since first flight of the airplane
at the time of accomplishing the modification specified in paragraph
(i) of this AD: Before the accumulation of 48,000 flight cycles
since first flight of the airplane.
(3) For airplanes with 13,800 flight cycles or more accumulated
since first flight of the airplane at the time of accomplishing the
modification specified in paragraph (i) of this AD: Before the
accumulation of 60,000 flight cycles since first flight of the
airplane.
(k) Repair
If, during any inspection required by paragraph (g) or (j) of
this AD, any crack is detected, before further flight, repair using
a method approved by the Manager, International Section, Transport
Standards Branch, FAA; or EASA; or Airbus's EASA DOA. Repair of an
airplane as required by this paragraph does not constitute
terminating action for the repetitive inspections required by
paragraph (g) or (j) of this AD for that airplane, unless specified
otherwise in instructions obtained using a method approved by the
Manager, International Section, Transport Standards Branch, FAA; or
EASA; or Airbus's EASA DOA.
(l) Post-Repair Actions for Certain Airplanes
For an airplane that has been inspected as specified in ALI task
534129 or task 534130 and repaired before the effective date of this
AD as specified in the applicable structural repair manual (SRM) or
as specified in an Airbus repair design approval sheet (RDAS):
Comply with the requirements of paragraphs (l)(1) and (l)(2) of this
AD.
(1) For all fastener holes where no damage or cracks were
detected (i.e., those not repaired), accomplish the actions required
by paragraph (g) of this AD, unless the terminating action specified
in paragraph (m) of this AD has been done.
(2) For all repaired fastener holes: Within 30 days after the
effective date of this AD, or within a compliance time approved by
the Manager, International Section, Transport Standards Branch, FAA;
or EASA; or Airbus's EASA DOA, whichever occurs later, contact the
Manager, International Section, Transport Standards Branch, FAA; or
EASA; or Airbus's EASA DOA; for inspection instructions and
applicable corrective actions, and do the inspections and applicable
corrective actions accordingly.
(m) Terminating Action for Certain Airplanes
For airplanes that have been inspected, as specified in ALI task
534129 or task 534130, and repaired before the effective date of
this AD, as specified in the applicable SRM, or as specified in an
Airbus RDAS: Modification of the four fastener holes at door stop
locations where no damage or crack was detected (i.e., door stop
locations not repaired) by cold working holes before further flight
after no cracks were detected, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1290, Revision 01,
dated October 3, 2016, constitutes terminating action for the
repetitive inspections of those four fastener holes at those door
stop locations as required by paragraphs (g) or (l)(1) of this AD
for that airplane.
(n) Actions for Airplanes With Certain Repairs
For an airplane that has been repaired before the effective date
of this AD in the areas described in this AD using an Airbus RDAS
unrelated to ALI task 534129 or task 534130: Before exceeding the
compliance times specified in paragraph (g) of this AD, contact the
Manager, International Section, Transport Standards Branch, FAA; or
EASA; or Airbus's EASA DOA; for corrective action instructions and
accomplish those instructions accordingly. Accomplishment of
corrective action(s) on an airplane, as required by this paragraph,
does not constitute terminating action for the repetitive
inspections as required by paragraphs (g) or (j) of this AD for that
airplane, as applicable, unless specified otherwise in the
instructions.
[[Page 5912]]
(o) Terminating Action for ALI Tasks
(1) Accomplishment of inspections on an airplane, as required by
paragraphs (g), (j), or (l) of this AD, as applicable, constitutes
terminating action for the inspection requirements of ALI task
534129 or task 534130, as applicable, for that airplane.
(2) Modification of the four fastener holes at a door stop
location of an airplane as specified in paragraphs (i) or (m) of
this AD, as applicable, and subsequent initial inspection required
by paragraph (j) of this AD, constitutes terminating action for the
inspection requirements of ALI task 534129 or task 534130, as
applicable, for those holes for that airplane. Subsequent repetitive
inspections are required by paragraph (j) of this AD.
(p) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraphs (g) and (j) of this AD, if those actions were performed
before the effective date of this AD using Airbus Service Bulletin
A320-53-1288, including Appendixes 01 and 02, dated October 10,
2014.
(2) This paragraph provides credit for actions required by
paragraphs (i) and (m) of this AD, if those actions were performed
before the effective date of this AD using Airbus Service Bulletin
A320-53-1290, dated October 10, 2014.
(q) 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 Section, send it to the attention of
the person identified in paragraph (r)(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: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA
DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
(3) Required for Compliance (RC): 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.
(r) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0238, dated December 2, 2016; corrected January
4, 2017, 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-2017-0707.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone:
425-227-1405; fax: 425-227-1149.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (s)(3) and (s)(4) of this AD.
(s) 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.
(i) Airbus Service Bulletin A320-53-1288, Revision 01, including
Appendixes 01, 02, and 03, dated October 3, 2016.
(ii) Airbus Service Bulletin A320-53-1290, Revision 01, dated
October 3, 2016.
(3) 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.
(4) You may view this service information at the FAA, Transport
Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information
on the availability of this material at the FAA, call 425-227-1221.
(5) 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 January 29, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-02359 Filed 2-9-18; 8:45 am]
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