Airworthiness Directives; Airbus Airplanes, 56158-56163 [2017-23349]
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56158
Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) For Group 1 Airplanes: Inspection and
Corrective Actions
For airplanes identified as Group 1 in
Boeing Alert Service Bulletin 737–57A1329,
dated January 16, 2017: Within 120 days after
the effective date of this AD, do an inspection
for cracking of the upper aft skin of the
wings, and do all applicable corrective
actions, using a method approved in
accordance with the procedures specified in
paragraph (j) of this AD.
(h) For Groups 2 and 3 Airplanes: Repetitive
Inspections and Repair
For Groups 2 and 3 airplanes identified in
Boeing Alert Service Bulletin 737–57A1329,
dated January 16, 2017: At the applicable
time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–57A1329, dated January 16,
2017, except as required by paragraph (i) of
this AD, do the applicable inspection for
cracking of the upper aft skin of the wings
from wing buttock line (WBL) 159 to WBL
220, in accordance with the Work
Instructions of Boeing Alert Service Bulletin
737–57A1329, dated January 16, 2017. If any
cracking is found, repair before further flight,
in accordance with the procedures specified
in paragraph (j) of this AD. Repeat the
inspection thereafter at the applicable time
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–57A1329,
dated January 16, 2017.
jstallworth on DSKBBY8HB2PROD with RULES
(i) Exceptions to the Service Information
(1) Where Boeing Alert Service Bulletin
737–57A1329, dated January 16, 2017,
specifies a compliance time ‘‘after the
original issue date of this service bulletin,’’
paragraph (h) of this AD requires compliance
within the specified compliance time after
the effective date of this AD.
(2) Although Boeing Alert Service Bulletin
737–57A1329, dated January 16, 2017,
specifies to contact Boeing for repair
instructions, and specifies that action as
‘‘RC’’ (Required for Compliance), this AD
requires repair in accordance with the
procedures specified in paragraph (j) of this
AD.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles ACO Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your
principal inspector or local Flight Standards
District Office, as appropriate. If sending
information directly to the manager of the
certification office, send it to the attention of
the person identified in paragraph (k) of this
AD. Information may be emailed to: 9-ANMLAACO-AMOC-Requests@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.
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(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO Branch, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (i)(2)
of this AD: For service information that
contains steps that are labeled as RC, the
provisions of paragraphs (j)(4)(i) and (j)(4)(ii)
of this AD apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
Issued in Renton, Washington, on
November 15, 2017.
Chris Spangenberg,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2017–25379 Filed 11–27–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0478; Product
Identifier 2016–NM–174–AD; Amendment
39–19087; AD 2017–22–07]
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 A319 series airplanes;
Model A320–211, –212, –214, –231,
–232, and –233 airplanes; and Model
(k) Related Information
A321–111, –112, –131, –211, –212,
For more information about this AD,
contact Payman Soltani, Aerospace Engineer, –213, –231, and –232 airplanes. This AD
was prompted by a report of cracks on
Airframe Section, FAA, Los Angeles ACO
frame forks and outer skin on the
Branch, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627– forward and aft cargo compartment
5313; fax: 562–627–5210; email:
doors. This AD requires repetitive
payman.soltani@faa.gov.
inspections of the frame forks, and
corrective actions if necessary. This AD
(l) Material Incorporated by Reference
also includes optional modifications
(1) The Director of the Federal Register
that constitute terminating action. We
approved the incorporation by reference
are issuing this AD to address the unsafe
(IBR) of the service information listed in this
condition on these products.
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
DATES: This AD is effective January 2,
(2) You must use this service information
2018.
as applicable to do the actions required by
The Director of the Federal Register
this AD, unless the AD specifies otherwise.
approved the incorporation by reference
(i) Boeing Alert Service Bulletin 737–
of certain publications listed in this AD
57A1329, dated January 16, 2017.
as of January 2, 2018.
(ii) Reserved.
(3) For service information identified in
ADDRESSES: For service information
this AD, contact Boeing Commercial
identified in this final rule, contact
Airplanes, Attention: Contractual & Data
Airbus, Airworthiness Office—EIAS,
Services (C&DS), 2600 Westminster Blvd.,
1 Rond Point Maurice Bellonte, 31707
MC 110–SK57, Seal Beach, CA 90740;
Blagnac Cedex, France; telephone: +33 5
telephone 562–797–1717; Internet https://
61 93 36 96; fax: +33 5 61 93 44 51;
www.myboeingfleet.com.
email: account.airworth-eas@
(4) You may view this service information
airbus.com; Internet: https://
at the FAA, Transport Standards Branch,
1601 Lind Avenue SW., Renton, WA. For
www.airbus.com. You may view this
information on the availability of this
referenced service information at the
material at the FAA, call 425–227–1221.
FAA, Transport Standards Branch, 1601
(5) You may view this service information
Lind Avenue SW., Renton, WA. For
that is incorporated by reference at the
information on the availability of this
National Archives and Records
material at the FAA, call 425–227–1221.
Administration (NARA). For information on
the availability of this material at NARA, call It is also available on the Internet at
https://www.regulations.gov by searching
202–741–6030, or go to: https://
for and locating Docket No. FAA–2017–
www.archives.gov/federal-register/cfr/ibrlocations.html.
0478.
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SUMMARY:
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Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations
jstallworth on DSKBBY8HB2PROD with RULES
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–
0478; 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 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 May 22, 2017 (82 FR 23160)
(‘‘the NPRM’’). The NPRM was
prompted by a report of cracks on frame
forks and outer skin on the forward and
aft cargo compartment doors. The
NPRM proposed to require repetitive
inspections of the frame forks, and
corrective actions if necessary. The
NPRM also included optional
modifications that constitute
terminating action. We are issuing this
AD to detect and correct cracks on the
frame forks and outer skin on the
forward and aft cargo compartment
doors, which could lead to reduced
structural integrity and failure of the
cargo compartment door, possible
decompression of the airplane, and
injury to occupants.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2016–0187,
dated September 19, 2016 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus Model A319 series
airplanes; Model A320–211, –212, –214,
–231, –232, and –233 airplanes; and
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Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
The MCAI states:
During full scale fatigue test, cracks have
been found on frame forks and outer skin on
forward and aft cargo doors.
To improve the fatigue behaviour of the
frame forks, Airbus introduced modification
(mod) 22948 in production, and issued
inspection Service Bulletin (SB) A320–52–
1032 and modification SB A320–52–1042,
both recommended.
Since those actions were taken, further
improved cargo compartment doors have
been introduced in production through
Airbus mod 26213, on aeroplanes having
[manufacturer serial number] MSN 0759 and
up. This modification, which is not available
for in-service retrofit, also includes
provisions that exclude installation of premod 26213 aft and forward compartment
cargo doors on an aeroplane.
In the frame of the Widespread Fatigue
Damage (WFD) study, it has been determined
that repetitive inspections are necessary for
aft and forward cargo compartment doors on
aeroplanes that do not (or no longer) embody
mod 22948 (or SB A320–52–1042), and those
that do not embody mod 26213. Failure to
detect cracks would reduce the cargo door
structural integrity.
This condition, if not detected and
corrected, could lead to cargo door failure,
possibly resulting in decompression of the
aeroplane and injury to occupants.
To address this unsafe condition, Airbus
issued SB A320–52–1171 to provide
inspection instructions. This SB was later
revised to correct the list of affected cargo
doors. Airbus also issued SB A320–52–1170,
introducing a door modification which
constitutes terminating action for the
repetitive special detailed inspection (SDI).
For the reason described above, this
[EASA] AD requires accomplishment of
repetitive SDI by rototest of all frame forks
in beam 4 area to detect cracks, and,
depending on findings, accomplishment of
applicable corrective action(s) [repair or
replacement]. This AD also provides an
optional [modification that constitutes]
terminating action for the repetitive SDI
required by this [EASA] AD.
One of the optional modifications
includes related investigative and
corrective actions. The related
investigative action is a high frequency
eddy current (HFEC) rotating probe
inspection for cracks, and the corrective
action is a repair. 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–2017–0478.
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.
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56159
Requests To Refer to Updated Service
Information
Delta Air Lines and United Airlines
requested that we revise the NPRM to
refer to Airbus Service Bulletin A320–
52–1171, Revision 02, dated April 10,
2017. United Airlines mentioned that
Airbus has made number of updates and
clarifications in Airbus Service Bulletin
A320–52–1171, Revision 02, dated April
10, 2017. Additionally, United Airlines
pointed out that EASA AD 2016–0187,
dated September 19, 2016, quoted in the
‘‘Discussion’’ section of the NPRM,
allows for use of later approved
revisions.
We agree with the commenters for the
reasons provided. We have revised this
AD to refer to Airbus Service Bulletin
A320–52–1171, Revision 02, dated April
10, 2017. We have also redesignated
paragraph (m) (of the proposed AD) as
paragraph (m)(1) of this AD and added
paragraph (m)(2) to provide credit for
actions done before the effective date of
this AD, if those actions were done
using Airbus Service Bulletin A320–52–
1171, Revision 01, dated September 5,
2016.
Request To Clarify That Certain Service
Information Cancels the Requirements
of Certain Other Service Information
United Airlines requested that we
clarify that Airbus Service Bulletin
A320–52–1171, Revision 02, dated April
10, 2017, cancels the requirements of
Airbus Service Bulletin A320–52–1032.
The commenter indicated that a
statement regarding this subject would
clarify the required actions for
operators. The commenter also pointed
out that a statement is listed in Airbus
Service Bulletin A320–52–1171,
Revision 02, dated April 10, 2017, that
specifies the cancellation of the
requirements of Airbus Service Bulletin
A320–52–1032.
We agree to clarify. Airbus Service
Bulletin A320–52–1171, Revision 02,
dated April 10, 2017, does include a
statement indicating that the actions
specified in Airbus Service Bulletin
A320–52–1171, Revision 02, dated April
10, 2017, cancel the actions specified in
Airbus Service Bulletin A320–52–1032.
However, the actions specified in
Airbus Service Bulletin A320–52–1032
are not required by any AD, and
therefore, we do not specifically address
Airbus Service Bulletin A320–52–1032
in this AD (except for the compliance
time reference in paragraph (h)(4) of this
AD). We have not changed this AD in
this regard.
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Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations
Request To Update the NPRM To
Include Modifications 22948 and 26213
Delta Air Lines requested that we
revise paragraphs (c) and (g) of the
proposed AD to refer to Modifications
22948 and 26213. Specifically, Delta Air
Lines requested that we include
information that elaborates on the
specific airplanes affected by the NPRM.
Delta Air Lines pointed out that EASA
AD 2016–0187, dated September 19,
2016, quoted in the ‘‘Discussion’’
section of the NPRM, and Airbus
Service Bulletin A320–52–1042,
Revision 2, dated January 14, 1997,
already refer to the modifications. Delta
Air Lines also mentioned that it has 40
forward and aft cargo compartment
doors affected by the NPRM, which are
pre-Modifications 22948 and 26213 and
under manufacturer serial number 0758.
We disagree to refer to Modifications
22948 and 26213 in paragraphs (c) and
(g) of this AD; however, we agree that
clarification is necessary. The
applicability of this AD refers to the
affected models having manufacturer
serial numbers through 0758 inclusive;
all airplanes having these serial
numbers are affected by the identified
unsafe condition. Airbus introduced
modification 22948 in production, and
issued Airbus Service Bulletin A320–
52–1032 for recommended inspections
and Airbus Service Bulletin A320–52–
1042 for recommended modification
22948. Since that service information
was issued, Airbus has introduced
further improved forward and aft cargo
compartment doors (modification
26213) in production on airplanes
having manufacturer serial number 0759
and above; however, this modification is
unavailable for in-service retrofit.
Modification 26213 includes provisions
that prohibit installation of earlier
configurations of forward or aft cargo
compartment doors (pre-modification
26213). Airplanes having manufacturer
serial numbers 0759 and subsequent
have modification 26213 installed in
production. We have not changed this
AD in this regard.
numbers that are affected by the
proposed AD.
We partially agree with the
commenter. Airplanes originally
delivered with the affected doors are
subject to the requirements of this AD.
Paragraph (h) of this AD only requires
actions on affected doors. It is not
physically possible to install the
affected doors on serial numbers 0759
and above; therefore, parts rotability
does not need to be addressed in this
AD.
In addition, paragraph (n) of this AD
provides a parts installation limitation
for the forward or aft cargo compartment
doors for the airplanes identified in
paragraph (c) of this AD. We have no
practical method to provide a
manufacturer serial number list of
affected airplanes on which a nonaffected door might have been installed
or to predict an airplane configuration
in the worldwide fleet. Therefore, we
have not changed this AD in this regard.
jstallworth on DSKBBY8HB2PROD with RULES
Request To Include Instructions for
Rotable Parts
Request To Clarify Optional
Terminating Actions
United Airlines requested that we
clarify the optional terminating actions
specified in paragraph (j) of the
proposed AD. The commenter requested
we include a statement that specifies
modification of all affected doors of an
airplane in accordance with the
requirements of paragraphs (j)(1), (j)(2),
or (j)(3) of this AD constitutes
terminating action. The commenter
pointed out that EASA AD 2016–0187,
dated September 19, 2016, quoted in the
‘‘Discussion’’ section of the NPRM,
allows for modification of an airplane as
specified in Airbus Service Bulletin
A320–52–1042, Revision 2, dated
January 14, 1997; or Airbus Service
Bulletin A320–52–1170, dated
September 5, 2016; and either is
considered terminating action for the
repetitive inspections.
We agree that clarification is
necessary. We have revised paragraph (j)
of this AD to include introductory text
with the statement: ‘‘Modification of all
affected doors of an airplane in
accordance with the requirements of
paragraph (j)(1), (j)(2), or (j)(3) of this AD
constitutes terminating action . . . .’’
Delta Air Lines requested that we
include instructions for rotable parts in
paragraph (g) of the proposed AD. The
commenter mentioned that forward or
aft cargo compartment doors could be
migrated from manufacturer serial
number 0759 and above to airplanes
that are affected, and asked if those
airplanes are still affected. The
commenter also requested that Airbus
provide a list of manufacturer serial
Request To Include Compliance Times
for Optional Terminating Actions
Mr. Petit requested that we add
compliance times for the optional
terminating actions specified in the
proposed AD. Mr. Petit indicated that 14
CFR 26.21 might require a mandatory
terminating action before 56,300 flight
cycles. Mr. Petit also recommended that
the optional terminating action not be
embodied before 21,700 flight cycles.
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We disagree with the commenter’s
request to include compliance times for
the optional terminating action
specified in this AD. 14 CFR 26.21
mandates the limit of validity (LOV) and
does not specify compliance times for
the optional terminating action
specified in this AD. This AD mandates
repetitive inspections of the frame forks
as specified in the service information
provided by the design approval holder
(DAH) to meet the LOV. In addition, we
do not include compliance times for
optional actions in ADs because doing
so would make the actions mandatory.
We intend for the terminating actions in
this AD to be optional, which aligns
with the MCAI.
Regarding the commenter’s
recommendation to prohibit
accomplishing the optional terminating
action before 21,700 flight cycles, the
commenter provided no substantiation
for this prohibition. We have received
no data indicating that the optional
terminating action should not be
accomplished before 21,700 flight
cycles. Therefore, we have not changed
this AD in this regard.
Clarification of Exception
Paragraph (i)(2) of the proposed AD,
which refers to Airbus Service Bulletin
A320–52–1170, dated September 5,
2016, includes an exception as specified
in paragraph (k) of the proposed AD.
However, paragraph (k) of the proposed
AD does not mention Airbus Service
Bulletin A320–52–1170, dated
September 5, 2016. We have added
Airbus Service Bulletin A320–52–1170,
dated September 5, 2016, to the
exception specified in paragraph (k) of
this AD.
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.
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Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations
• Airbus Service Bulletin A320–52–
1171, Revision 02, dated April 10, 2017,
describes procedures for repetitive
special detailed inspections of all frame
forks in the beam 4 area of any affected
door, and corrective actions.
• Airbus Service Bulletin A320–52–
1042, Revision 2, dated January 14,
1997, describes procedures for
modification of all affected forward and
aft cargo compartment doors of an
airplane.
• Airbus Service Bulletin A320–52–
1170, dated September 5, 2016,
describes modification of all affected
forward and aft cargo compartment
doors of an airplane, including related
investigative and corrective actions.
This service information is reasonably
available because the interested parties
56161
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 88
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Special detailed inspection .....
25 work-hours × $85 per hour = $2,125 ................................
Cost per
product
Parts cost
$0
$2,125
Cost on U.S.
operators
$187,000
OPTIONAL ACTIONS
Action
Labor cost
Parts cost
Modification .............................
24 work-hours × $85 per hour = $2,040 ...........................................................
Up to $240 .....
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition repairs
and replacements specified in this AD.
jstallworth on DSKBBY8HB2PROD with RULES
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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Regulatory Findings
§ 39.13
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.
Cost per
product
Up to $2,280.
■
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.
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[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
2017–22–07 Airbus: Amendment 39–19087;
Docket No. FAA–2017–0478; Product
Identifier 2016–NM–174–AD.
(a) Effective Date
This AD is effective January 2, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus 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, manufacturer serial numbers
through 0758 inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 52, Doors.
(e) Reason
This AD was prompted by a report of
cracks on the frame forks and outer skin on
the forward and aft cargo compartment doors.
We are issuing this AD to detect and correct
cracks on the frame forks and outer skin on
the forward and aft cargo compartment doors,
which could lead to reduced structural
integrity and failure of the cargo
compartment door, possible decompression
of the airplane, and injury to occupants.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Definition of Affected Door
For the purpose of this AD, an ‘‘affected
door’’ is a forward or aft cargo compartment
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Bulletin A320–52–1042 or Airbus Service
Bulletin A320–52–1170 is embodied.
(i) Corrective Actions
If any crack is found during any inspection
required by paragraph (h) of this AD, before
further flight, do all applicable corrective
actions in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–52–1171, Revision 02,
dated April 10, 2017, except as specified in
paragraphs (k) and (l) of this AD.
Accomplishment of applicable corrective
actions does not constitute terminating action
for the repetitive inspections.
At the latest of the compliance times listed
in paragraphs (h)(1) through (h)(4) of this AD:
Do a special detailed inspection of all frame
forks in the beam 4 area of any affected door
as defined in paragraph (g) of this AD, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
52–1171, Revision 02, dated April 10, 2017,
except as specified in paragraphs (k) and (l)
of this AD. Repeat the inspection thereafter
at intervals not to exceed 3,000 flight cycles.
A review of the airplane delivery or
maintenance records is acceptable to identify
any affected door installed on the airplane,
provided that the cargo compartment door
part number can be conclusively determined
from that review.
(1) Before exceeding 37,500 flight cycles
since first installation of the door on an
airplane.
(2) Within 900 flight cycles after the
effective date of this AD, without exceeding
41,950 flight cycles since first installation of
the door on an airplane.
(3) Within 50 flight cycles after the
effective date of this AD, for a door having
reached or exceeded 41,900 flight cycles
since first installation on an airplane.
(4) Within 3,000 flight cycles since the last
inspection of the door as specified in Airbus
Service Bulletin A320–52–1032.
VerDate Sep<11>2014
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(j) Optional Terminating Action
Modification of all affected doors of an
airplane in accordance with the requirements
of paragraph (j)(1), (j)(2), or (j)(3) of this AD,
constitutes terminating action for the
repetitive inspections specified in paragraph
(h) of this AD for that airplane.
(1) Modification of all affected doors of an
airplane in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–52–1042, Revision 2,
dated January 14, 1997, constitutes
terminating action for the repetitive
inspections specified in paragraph (h) of this
AD for that airplane, provided that, after
modification, no affected door is re-installed
on that airplane.
(2) Modification of all affected doors of an
airplane including accomplishment of all
applicable related investigative and
corrective actions in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–52–1170, dated
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Fmt 4700
Sfmt 4700
September 5, 2016, except as specified in
paragraph (k) of this AD, constitutes
terminating action for the repetitive
inspections specified in paragraph (h) of this
AD for that airplane, provided that, after
modification, no affected door is re-installed
on that airplane.
(3) Modification of all affected doors on an
airplane, in case of finding damaged frame
forks, as specified in an Airbus Repair Design
Approval Sheet (RDAS), and done in
accordance with 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);
constitutes terminating action for the
repetitive inspection specified in paragraph
(h) of this AD for that airplane, provided that,
after modification, no affected door is reinstalled on that airplane.
(k) Exception to Service Information
Where Airbus Service Bulletin A320–52–
1170, dated September 5, 2016; or Airbus
Service Bulletin A320–52–1171, Revision 02,
dated April 10, 2017; specifies to contact
Airbus for appropriate action, and specifies
that action as ‘‘RC’’ (Required for
Compliance): Before further flight,
accomplish corrective actions in accordance
with the procedures specified in paragraph
(o)(2) of this AD.
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ER28NO17.017</GPH>
(h) Repetitive Special Detailed Inspection of
Frame Forks
jstallworth on DSKBBY8HB2PROD with RULES
door, having any part number listed in table
1 to paragraph (g) of this AD, except a cargo
compartment door on which Airbus Service
Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations
(l) No Reporting Requirement
Although Airbus Service Bulletin A320–
52–1171, Revision 02, dated April 10, 2017,
specifies to submit certain information to the
manufacturer, and specifies that action as
‘‘RC,’’ this AD does not include that
requirement.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraphs (h) and (i) of
this AD, if those actions were performed
before the effective date of this AD using
Airbus Service Bulletin A320–52–1171,
dated October 29, 2015, provided that it can
be conclusively determined that any part
number D52371000018 was also inspected as
specified in paragraph (h) of this AD.
(2) This paragraph provides credit for the
actions required by paragraphs (h) and (i) of
this AD, if those actions were performed
before the effective date of this AD using
Airbus Service Bulletin A320–52–1171,
Revision 01, dated September 5, 2016.
jstallworth on DSKBBY8HB2PROD with RULES
(n) Parts Installation Limitation
As of the effective date of this AD, no
person may install, on any airplane, an
affected door specified in paragraph (g) of
this AD, unless it has been inspected in
accordance with the requirements of
paragraph (h) of this AD and all applicable
corrective actions have been done in
accordance with paragraph (i) of this AD.
(o) 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 (p)(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): Except
as specified in paragraphs (k) and (l) 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
VerDate Sep<11>2014
15:23 Nov 27, 2017
Jkt 244001
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.
(p) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0187, dated September 19, 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–2017–0478.
(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 (q)(3) and (q)(4) of this AD.
(q) 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 A320–52–1042,
Revision 2, dated January 14, 1997 (pages 5,
9, and 19 through 22 of this document are
identified as Revision 1, dated November 22,
1993).
(ii) Airbus Service Bulletin A320–52–1170,
dated September 5, 2016, including
Appendices 01 and 02, dated September 5,
2016.
(iii) Airbus Service Bulletin A320–52–
1171, Revision 02, dated April 10, 2017.
(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 October
17, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2017–23349 Filed 11–27–17; 8:45 am]
BILLING CODE 4910–13–P
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56163
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0933; Product
Identifier 2017–SW–051–AD; Amendment
39–19106; AD 2017–24–02]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters Deutschland GmbH
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 Airbus
Helicopters Deutschland GmbH (Airbus
Helicopters) Model MBB–BK 117 D–2
helicopters. This AD requires amending
the rotorcraft flight manual to establish
a minimum airspeed limitation for the
autopilot cruise height mode. This AD
is prompted by two reports of
uncommanded helicopter climbs and
descents. The actions of this AD are
intended to address an unsafe condition
on these products.
DATES: This AD becomes effective
December 13, 2017.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of December 13, 2017.
We must receive comments on this
AD by January 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.
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–
0933; or in person at the Docket
Operations Office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
E:\FR\FM\28NOR1.SGM
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]]>Agencies
[Federal Register Volume 82, Number 227 (Tuesday, November 28, 2017)]
[Rules and Regulations]
[Pages 56158-56163]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-23349]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0478; Product Identifier 2016-NM-174-AD; Amendment
39-19087; AD 2017-22-07]
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 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 a report of
cracks on frame forks and outer skin on the forward and aft cargo
compartment doors. This AD requires repetitive inspections of the frame
forks, and corrective actions if necessary. This AD also includes
optional modifications that constitute terminating action. We are
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective January 2, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 2,
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 for and locating Docket No.
FAA-2017-0478.
[[Page 56159]]
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-
0478; 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 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 May 22,
2017 (82 FR 23160) (``the NPRM''). The NPRM was prompted by a report of
cracks on frame forks and outer skin on the forward and aft cargo
compartment doors. The NPRM proposed to require repetitive inspections
of the frame forks, and corrective actions if necessary. The NPRM also
included optional modifications that constitute terminating action. We
are issuing this AD to detect and correct cracks on the frame forks and
outer skin on the forward and aft cargo compartment doors, which could
lead to reduced structural integrity and failure of the cargo
compartment door, possible decompression of the airplane, and injury to
occupants.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2016-0187, dated September 19, 2016 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Airbus 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 full scale fatigue test, cracks have been found on frame
forks and outer skin on forward and aft cargo doors.
To improve the fatigue behaviour of the frame forks, Airbus
introduced modification (mod) 22948 in production, and issued
inspection Service Bulletin (SB) A320-52-1032 and modification SB
A320-52-1042, both recommended.
Since those actions were taken, further improved cargo
compartment doors have been introduced in production through Airbus
mod 26213, on aeroplanes having [manufacturer serial number] MSN
0759 and up. This modification, which is not available for in-
service retrofit, also includes provisions that exclude installation
of pre-mod 26213 aft and forward compartment cargo doors on an
aeroplane.
In the frame of the Widespread Fatigue Damage (WFD) study, it
has been determined that repetitive inspections are necessary for
aft and forward cargo compartment doors on aeroplanes that do not
(or no longer) embody mod 22948 (or SB A320-52-1042), and those that
do not embody mod 26213. Failure to detect cracks would reduce the
cargo door structural integrity.
This condition, if not detected and corrected, could lead to
cargo door failure, possibly resulting in decompression of the
aeroplane and injury to occupants.
To address this unsafe condition, Airbus issued SB A320-52-1171
to provide inspection instructions. This SB was later revised to
correct the list of affected cargo doors. Airbus also issued SB
A320-52-1170, introducing a door modification which constitutes
terminating action for the repetitive special detailed inspection
(SDI).
For the reason described above, this [EASA] AD requires
accomplishment of repetitive SDI by rototest of all frame forks in
beam 4 area to detect cracks, and, depending on findings,
accomplishment of applicable corrective action(s) [repair or
replacement]. This AD also provides an optional [modification that
constitutes] terminating action for the repetitive SDI required by
this [EASA] AD.
One of the optional modifications includes related investigative
and corrective actions. The related investigative action is a high
frequency eddy current (HFEC) rotating probe inspection for cracks, and
the corrective action is a repair. 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-2017-0478.
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.
Requests To Refer to Updated Service Information
Delta Air Lines and United Airlines requested that we revise the
NPRM to refer to Airbus Service Bulletin A320-52-1171, Revision 02,
dated April 10, 2017. United Airlines mentioned that Airbus has made
number of updates and clarifications in Airbus Service Bulletin A320-
52-1171, Revision 02, dated April 10, 2017. Additionally, United
Airlines pointed out that EASA AD 2016-0187, dated September 19, 2016,
quoted in the ``Discussion'' section of the NPRM, allows for use of
later approved revisions.
We agree with the commenters for the reasons provided. We have
revised this AD to refer to Airbus Service Bulletin A320-52-1171,
Revision 02, dated April 10, 2017. We have also redesignated paragraph
(m) (of the proposed AD) as paragraph (m)(1) of this AD and added
paragraph (m)(2) to provide credit for actions done before the
effective date of this AD, if those actions were done using Airbus
Service Bulletin A320-52-1171, Revision 01, dated September 5, 2016.
Request To Clarify That Certain Service Information Cancels the
Requirements of Certain Other Service Information
United Airlines requested that we clarify that Airbus Service
Bulletin A320-52-1171, Revision 02, dated April 10, 2017, cancels the
requirements of Airbus Service Bulletin A320-52-1032. The commenter
indicated that a statement regarding this subject would clarify the
required actions for operators. The commenter also pointed out that a
statement is listed in Airbus Service Bulletin A320-52-1171, Revision
02, dated April 10, 2017, that specifies the cancellation of the
requirements of Airbus Service Bulletin A320-52-1032.
We agree to clarify. Airbus Service Bulletin A320-52-1171, Revision
02, dated April 10, 2017, does include a statement indicating that the
actions specified in Airbus Service Bulletin A320-52-1171, Revision 02,
dated April 10, 2017, cancel the actions specified in Airbus Service
Bulletin A320-52-1032. However, the actions specified in Airbus Service
Bulletin A320-52-1032 are not required by any AD, and therefore, we do
not specifically address Airbus Service Bulletin A320-52-1032 in this
AD (except for the compliance time reference in paragraph (h)(4) of
this AD). We have not changed this AD in this regard.
[[Page 56160]]
Request To Update the NPRM To Include Modifications 22948 and 26213
Delta Air Lines requested that we revise paragraphs (c) and (g) of
the proposed AD to refer to Modifications 22948 and 26213.
Specifically, Delta Air Lines requested that we include information
that elaborates on the specific airplanes affected by the NPRM. Delta
Air Lines pointed out that EASA AD 2016-0187, dated September 19, 2016,
quoted in the ``Discussion'' section of the NPRM, and Airbus Service
Bulletin A320-52-1042, Revision 2, dated January 14, 1997, already
refer to the modifications. Delta Air Lines also mentioned that it has
40 forward and aft cargo compartment doors affected by the NPRM, which
are pre-Modifications 22948 and 26213 and under manufacturer serial
number 0758.
We disagree to refer to Modifications 22948 and 26213 in paragraphs
(c) and (g) of this AD; however, we agree that clarification is
necessary. The applicability of this AD refers to the affected models
having manufacturer serial numbers through 0758 inclusive; all
airplanes having these serial numbers are affected by the identified
unsafe condition. Airbus introduced modification 22948 in production,
and issued Airbus Service Bulletin A320-52-1032 for recommended
inspections and Airbus Service Bulletin A320-52-1042 for recommended
modification 22948. Since that service information was issued, Airbus
has introduced further improved forward and aft cargo compartment doors
(modification 26213) in production on airplanes having manufacturer
serial number 0759 and above; however, this modification is unavailable
for in-service retrofit. Modification 26213 includes provisions that
prohibit installation of earlier configurations of forward or aft cargo
compartment doors (pre-modification 26213). Airplanes having
manufacturer serial numbers 0759 and subsequent have modification 26213
installed in production. We have not changed this AD in this regard.
Request To Include Instructions for Rotable Parts
Delta Air Lines requested that we include instructions for rotable
parts in paragraph (g) of the proposed AD. The commenter mentioned that
forward or aft cargo compartment doors could be migrated from
manufacturer serial number 0759 and above to airplanes that are
affected, and asked if those airplanes are still affected. The
commenter also requested that Airbus provide a list of manufacturer
serial numbers that are affected by the proposed AD.
We partially agree with the commenter. Airplanes originally
delivered with the affected doors are subject to the requirements of
this AD. Paragraph (h) of this AD only requires actions on affected
doors. It is not physically possible to install the affected doors on
serial numbers 0759 and above; therefore, parts rotability does not
need to be addressed in this AD.
In addition, paragraph (n) of this AD provides a parts installation
limitation for the forward or aft cargo compartment doors for the
airplanes identified in paragraph (c) of this AD. We have no practical
method to provide a manufacturer serial number list of affected
airplanes on which a non-affected door might have been installed or to
predict an airplane configuration in the worldwide fleet. Therefore, we
have not changed this AD in this regard.
Request To Clarify Optional Terminating Actions
United Airlines requested that we clarify the optional terminating
actions specified in paragraph (j) of the proposed AD. The commenter
requested we include a statement that specifies modification of all
affected doors of an airplane in accordance with the requirements of
paragraphs (j)(1), (j)(2), or (j)(3) of this AD constitutes terminating
action. The commenter pointed out that EASA AD 2016-0187, dated
September 19, 2016, quoted in the ``Discussion'' section of the NPRM,
allows for modification of an airplane as specified in Airbus Service
Bulletin A320-52-1042, Revision 2, dated January 14, 1997; or Airbus
Service Bulletin A320-52-1170, dated September 5, 2016; and either is
considered terminating action for the repetitive inspections.
We agree that clarification is necessary. We have revised paragraph
(j) of this AD to include introductory text with the statement:
``Modification of all affected doors of an airplane in accordance with
the requirements of paragraph (j)(1), (j)(2), or (j)(3) of this AD
constitutes terminating action . . . .''
Request To Include Compliance Times for Optional Terminating Actions
Mr. Petit requested that we add compliance times for the optional
terminating actions specified in the proposed AD. Mr. Petit indicated
that 14 CFR 26.21 might require a mandatory terminating action before
56,300 flight cycles. Mr. Petit also recommended that the optional
terminating action not be embodied before 21,700 flight cycles.
We disagree with the commenter's request to include compliance
times for the optional terminating action specified in this AD. 14 CFR
26.21 mandates the limit of validity (LOV) and does not specify
compliance times for the optional terminating action specified in this
AD. This AD mandates repetitive inspections of the frame forks as
specified in the service information provided by the design approval
holder (DAH) to meet the LOV. In addition, we do not include compliance
times for optional actions in ADs because doing so would make the
actions mandatory. We intend for the terminating actions in this AD to
be optional, which aligns with the MCAI.
Regarding the commenter's recommendation to prohibit accomplishing
the optional terminating action before 21,700 flight cycles, the
commenter provided no substantiation for this prohibition. We have
received no data indicating that the optional terminating action should
not be accomplished before 21,700 flight cycles. Therefore, we have not
changed this AD in this regard.
Clarification of Exception
Paragraph (i)(2) of the proposed AD, which refers to Airbus Service
Bulletin A320-52-1170, dated September 5, 2016, includes an exception
as specified in paragraph (k) of the proposed AD. However, paragraph
(k) of the proposed AD does not mention Airbus Service Bulletin A320-
52-1170, dated September 5, 2016. We have added Airbus Service Bulletin
A320-52-1170, dated September 5, 2016, to the exception specified in
paragraph (k) of this AD.
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.
[[Page 56161]]
Airbus Service Bulletin A320-52-1171, Revision 02, dated
April 10, 2017, describes procedures for repetitive special detailed
inspections of all frame forks in the beam 4 area of any affected door,
and corrective actions.
Airbus Service Bulletin A320-52-1042, Revision 2, dated
January 14, 1997, describes procedures for modification of all affected
forward and aft cargo compartment doors of an airplane.
Airbus Service Bulletin A320-52-1170, dated September 5,
2016, describes modification of all affected forward and aft cargo
compartment doors of an airplane, including related investigative and
corrective actions.
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 88 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Special detailed inspection........ 25 work-hours x $85 per $0 $2,125 $187,000
hour = $2,125.
----------------------------------------------------------------------------------------------------------------
Optional Actions
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Modification............................ 24 work-hours x $85 per Up to $240........... Up to $2,280.
hour = $2,040.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition repairs and replacements 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. 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):
2017-22-07 Airbus: Amendment 39-19087; Docket No. FAA-2017-0478;
Product Identifier 2016-NM-174-AD.
(a) Effective Date
This AD is effective January 2, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus 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,
manufacturer serial numbers through 0758 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 52, Doors.
(e) Reason
This AD was prompted by a report of cracks on the frame forks
and outer skin on the forward and aft cargo compartment doors. We
are issuing this AD to detect and correct cracks on the frame forks
and outer skin on the forward and aft cargo compartment doors, which
could lead to reduced structural integrity and failure of the cargo
compartment door, possible decompression of the airplane, and injury
to occupants.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Definition of Affected Door
For the purpose of this AD, an ``affected door'' is a forward or
aft cargo compartment
[[Page 56162]]
door, having any part number listed in table 1 to paragraph (g) of
this AD, except a cargo compartment door on which Airbus Service
Bulletin A320-52-1042 or Airbus Service Bulletin A320-52-1170 is
embodied.
[GRAPHIC] [TIFF OMITTED] TR28NO17.017
(h) Repetitive Special Detailed Inspection of Frame Forks
At the latest of the compliance times listed in paragraphs
(h)(1) through (h)(4) of this AD: Do a special detailed inspection
of all frame forks in the beam 4 area of any affected door as
defined in paragraph (g) of this AD, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-52-1171,
Revision 02, dated April 10, 2017, except as specified in paragraphs
(k) and (l) of this AD. Repeat the inspection thereafter at
intervals not to exceed 3,000 flight cycles. A review of the
airplane delivery or maintenance records is acceptable to identify
any affected door installed on the airplane, provided that the cargo
compartment door part number can be conclusively determined from
that review.
(1) Before exceeding 37,500 flight cycles since first
installation of the door on an airplane.
(2) Within 900 flight cycles after the effective date of this
AD, without exceeding 41,950 flight cycles since first installation
of the door on an airplane.
(3) Within 50 flight cycles after the effective date of this AD,
for a door having reached or exceeded 41,900 flight cycles since
first installation on an airplane.
(4) Within 3,000 flight cycles since the last inspection of the
door as specified in Airbus Service Bulletin A320-52-1032.
(i) Corrective Actions
If any crack is found during any inspection required by
paragraph (h) of this AD, before further flight, do all applicable
corrective actions in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-52-1171, Revision 02,
dated April 10, 2017, except as specified in paragraphs (k) and (l)
of this AD. Accomplishment of applicable corrective actions does not
constitute terminating action for the repetitive inspections.
(j) Optional Terminating Action
Modification of all affected doors of an airplane in accordance
with the requirements of paragraph (j)(1), (j)(2), or (j)(3) of this
AD, constitutes terminating action for the repetitive inspections
specified in paragraph (h) of this AD for that airplane.
(1) Modification of all affected doors of an airplane in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-52-1042, Revision 2, dated January 14, 1997,
constitutes terminating action for the repetitive inspections
specified in paragraph (h) of this AD for that airplane, provided
that, after modification, no affected door is re-installed on that
airplane.
(2) Modification of all affected doors of an airplane including
accomplishment of all applicable related investigative and
corrective actions in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-52-1170, dated
September 5, 2016, except as specified in paragraph (k) of this AD,
constitutes terminating action for the repetitive inspections
specified in paragraph (h) of this AD for that airplane, provided
that, after modification, no affected door is re-installed on that
airplane.
(3) Modification of all affected doors on an airplane, in case
of finding damaged frame forks, as specified in an Airbus Repair
Design Approval Sheet (RDAS), and done in accordance with 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); constitutes
terminating action for the repetitive inspection specified in
paragraph (h) of this AD for that airplane, provided that, after
modification, no affected door is re-installed on that airplane.
(k) Exception to Service Information
Where Airbus Service Bulletin A320-52-1170, dated September 5,
2016; or Airbus Service Bulletin A320-52-1171, Revision 02, dated
April 10, 2017; specifies to contact Airbus for appropriate action,
and specifies that action as ``RC'' (Required for Compliance):
Before further flight, accomplish corrective actions in accordance
with the procedures specified in paragraph (o)(2) of this AD.
[[Page 56163]]
(l) No Reporting Requirement
Although Airbus Service Bulletin A320-52-1171, Revision 02,
dated April 10, 2017, specifies to submit certain information to the
manufacturer, and specifies that action as ``RC,'' this AD does not
include that requirement.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraphs (h) and (i) of this AD, if those actions were performed
before the effective date of this AD using Airbus Service Bulletin
A320-52-1171, dated October 29, 2015, provided that it can be
conclusively determined that any part number D52371000018 was also
inspected as specified in paragraph (h) of this AD.
(2) This paragraph provides credit for the actions required by
paragraphs (h) and (i) of this AD, if those actions were performed
before the effective date of this AD using Airbus Service Bulletin
A320-52-1171, Revision 01, dated September 5, 2016.
(n) Parts Installation Limitation
As of the effective date of this AD, no person may install, on
any airplane, an affected door specified in paragraph (g) of this
AD, unless it has been inspected in accordance with the requirements
of paragraph (h) of this AD and all applicable corrective actions
have been done in accordance with paragraph (i) of this AD.
(o) 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 (p)(2) of this AD. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA
DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
(3) Required for Compliance (RC): Except as specified in
paragraphs (k) and (l) 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.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0187, dated September 19, 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-2017-0478.
(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 (q)(3) and (q)(4) of this AD.
(q) 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 A320-52-1042, Revision 2, dated
January 14, 1997 (pages 5, 9, and 19 through 22 of this document are
identified as Revision 1, dated November 22, 1993).
(ii) Airbus Service Bulletin A320-52-1170, dated September 5,
2016, including Appendices 01 and 02, dated September 5, 2016.
(iii) Airbus Service Bulletin A320-52-1171, Revision 02, dated
April 10, 2017.
(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/ibr-locations.html.
Issued in Renton, Washington, on October 17, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-23349 Filed 11-27-17; 8:45 am]
BILLING CODE 4910-13-P
