80 FR 52182 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 167 (August 28, 2015)

Page Range		52182-52185
FR Document		2015-20951

We are adopting a new airworthiness directive (AD) for all Airbus Model A319, A320, and A321 series airplanes. This AD was prompted by reports that during a full scale fatigue test, several broken frames in certain areas of the cargo compartment have been found, especially on the cargo floor support fittings and open tack holes on the left-hand side. This AD requires a rototest inspection of the open tack holes and rivet holes at the cargo floor support fittings of the fuselage, including doing all applicable related investigative actions, and repair if necessary. We are issuing this AD to detect and correct cracking in the open tack holes and rivet holes at the cargo floor support fittings of the fuselage, which could affect the structural integrity of the airplane.

Federal Register, Volume 80 Issue 167 (Friday, August 28, 2015)

[Federal Register Volume 80, Number 167 (Friday, August 28, 2015)]
[Rules and Regulations]
[Pages 52182-52185]
From the Federal Register Online [www.thefederalregister.org]
[FR Doc No: 2015-20951]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0455; Directorate Identifier 2014-NM-006-AD;
Amendment 39-18247; AD 2015-17-14]
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 all
Airbus Model A319, A320, and A321 series airplanes. This AD was
prompted by reports that during a full scale fatigue test, several
broken frames in certain areas of the cargo compartment have been
found, especially on the cargo floor support fittings and open tack
holes on the left-hand side. This AD requires a rototest inspection of
the open tack holes and rivet holes at the cargo floor support fittings
of the fuselage, including doing all applicable related investigative
actions, and repair if necessary. We are issuing this AD to detect and
correct cracking in the open tack holes and rivet holes at the cargo
floor support fittings of the fuselage, which could affect the
structural integrity of the airplane.

DATES: This AD becomes effective October 2, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 2,
2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0455; or in person at the
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.
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 http://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0455.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, 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 all Airbus Model A319,
A320, and A321 series airplanes. The NPRM published in the Federal
Register on July 23, 2014 (79 FR 42716).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2013-0310, dated December 20, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A319, A320, and A321 series airplanes. The MCAI states:

During a full scale fatigue test, several broken frames in the
cargo compartment area between Frame (FR) 50 and FR 63, have been
found, especially on the cargo floor support fittings and open tack
holes on [the] left hand side.
This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
For the reason described above, this [EASA] AD requires
repetitive inspections of the frames in the cargo compartment area
and of the cargo floor support fittings and open tack holes on the
left hand (LH) side, and depending on findings, the accomplishment
of applicable corrective action(s). This [EASA] AD also requires a
modification, which constitutes terminating action for the
repetitive inspections required by this [EASA] AD.

The actions in this AD include a rototest inspection for cracking of
the open tack holes and rivet holes at the cargo floor support fittings
of the fuselage; modification of the fuselage, including doing all
applicable related investigative actions; and repair if necessary.
Related investigative actions include rotating probe inspections for
cracking of the holes. You may examine the MCAI in the AD docket on the
Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-
0455-0002.

Comments

We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (79
FR 42716, July 23, 2014) and the FAA's response to each comment.

Requests To Remove Service Information Not Applicable to the U.S. Fleet

Delta Air Lines (DAL), United Airlines (UAL), and US Airways
requested that certain service information be removed from the NPRM (79
FR 42716, July 23, 2014) as it is not applicable to the U.S. fleet.
DAL stated that Airbus Service Bulletin A320-53-1261, dated
December 21, 2012, which provides a terminating modification for the
repetitive inspections specified in the NPRM (79 FR 42716, July 23,
2014), is one of eight structural modification service bulletins
required to operate Model A320 airplanes beyond 48,000 flight cycles/
96,000 flight hours (referred to as extended service goal (ESG)). DAL
stated that Airbus Service Bulletin A320-53-1261, dated December 21,
2012, does not affect DAL or any other U.S. operator, since Airbus only
recognizes airplane effectivity for those operators that have
accomplished this service bulletin (which can only be purchased from
Airbus) through ESG embodiment.
UAL and US Airways stated that, in paragraph (h) of the proposed AD
(79 FR 42716, July 23, 2014), modification of the fuselage in
accordance with Airbus

[[Page 52183]]

Service Bulletin A320-53-1261, dated December 21, 2012, must be
accomplished before exceeding 48,000 total flight cycles or 96,000
total flight hours, whichever occurs first. UAL and US Airways stated
that Airbus Service Bulletin A320-53-1261, dated December 21, 2012, is
not effective for all manufacturer serial numbers specified in the
service information and is only applicable to a select number of
operators. UAL commented that Airbus Service Bulletin A320-53-1261,
dated December 21, 2012, was originally related to the ESG modification
requirements and has not yet been revised to match the effective
manufacturer serial numbers in specified Airbus Service Bulletin A320-
53-1257, dated December 21, 2012.
We agree with these commenters' requests. Airbus Service Bulletin
A320-53-1261, dated December 21, 2012, does not apply to the U.S. fleet
because the terminating action is not applicable for all manufacturer
serial numbers. Therefore, we have deleted the modification requirement
that was specified in paragraph (h) of the proposed AD (79 FR 42716,
July 23, 2014), and have redesignated subsequent paragraphs
accordingly.

Request To Revise Certain Service Information

DAL also requested that the FAA ask Airbus to update the
Effectivity in Airbus Service Bulletin A320-53-1261, dated December 21,
2012, along with the other structural modification service information
required for operation beyond 48,000 total flight cycles/96,000 total
flight hours.
We disagree with this request. As we stated previously, we have
deleted the modification requirement that was specified in paragraph
(h) of the proposed AD (79 FR 42716, July 23, 2014). In addition, we do
not agree with delaying this action for mitigating safety risks
addressed in this AD until after the release of the manufacturer's
additional planned service bulletin(s). We have not changed this AD in
this regard.

Request for Separate AD for the Structural Modification

DAL requested that a separate AD be issued that would specify all
required service information for the modification in paragraph (h) of
the proposed AD (79 FR 42716, July 23, 2014), which must be
accomplished prior to operation beyond 48,000 total flight cycles/
96,000 total flight hours for affected manufacturer serial numbers.
We disagree with issuing a separate AD action that would require
all modifications associated with operations exceeding 48,000 total
flight cycles/96,000 total flight hours (referred to as ESG). ESG is
not related to the unsafe condition in this AD. ESG is not a
requirement, but an option to operate with an extended operational
limit of 60,000 total flight cycles/120,000 total flight hours and is
contingent on accomplishment of specific modifications. This AD is
specific to mitigating the risks associated with the identified unsafe
condition, which were identified during full scale fatigue testing.
Choosing the option to operate airplanes exceeding 48,000 total flight
cycles/96,000 total flight hours lies with the operator and has no
bearing on the mitigation of the unsafe condition identified in this
AD. We have not changed this AD in this regard.

Requests To Identify Actions Required for Compliance

DAL and UAL requested a statement in the NPRM (79 FR 42716, July
23, 2014) to specify the actions that are required for compliance (RC)
in Airbus Service Bulletin A320-53-1257, dated December 21, 2012.
UAL stated that paragraph 3.C. of the Accomplishment Instructions
of Airbus Service Bulletin A320-53-1257, dated December 21, 2012, meets
the technical intent of the inspection in the service information as
that paragraph specifies removal of the affected fasteners,
accomplishment of the rototest inspection, and re-installation of the
fasteners. UAL stated that the access and close-up actions may then be
specified by the operator as deemed necessary. UAL commented that
paragraph (g) of the proposed AD (79 FR 42716, July 23, 2014) could
specify that the inspection be performed in accordance with paragraph
3.C. of the Accomplishment Instructions of Airbus Service Bulletin
A320-53-1257, dated December 21, 2012.
DAL stated that the FAA issued Advisory Circular (AC) 20-176 in
December 2011 and AC 20-176A in June 2014 (http://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgAdvisoryCircular.nsf/0/
979ddd1479e1ec6f86257cfc0052d4e9/$FILE/AC%2020-176A.pdf); and Order
8110.117A, dated June 18, 2014 (http://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgOrders.nsf/0/
d715cdfc08ac0ddc86257cfc00528297/$FILE/110.117A.pdf), which provides
guidance for issuing service information related to ADs. DAL commented
that paragraph 2-10 of AC 20-176A states that ``steps that have a
direct effect on detecting, preventing, resolving, or eliminating the
unsafe condition in an AD should be identified in a SB with ``RC''
(Required for Compliance''). DAL stated that there are no ``RC''
identifiers in the work steps of Airbus Service Bulletin A320-53-1257,
dated December 21, 2012.
DAL also requested that the FAA evaluate service bulletins for
adherence to the guidance provided in AC 20-176A, dated June 16, 2014
(http://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgAdvisoryCircular.nsf/0/979ddd1479e1ec6f86257cfc0052d4e9/$FILE/
AC%2020-176A.pdf); and Order 8110.117A, dated June 18, 2014 (http://
rgl.faa.gov/Regulatory_and_Guidance_Library/rgOrders.nsf/0/
d715cdfc08ac0ddc86257cfc00528297/$FILE/110.117A.pdf), when proposing
new AD's.
We agree with the concept of minimizing AD requirements when
appropriate. The FAA released AC 20-176A, dated June 16, 2014 (http://
rgl.faa.gov/Regulatory_and_Guidance_Library/rgAdvisoryCircular.nsf/0/
979ddd1479e1ec6f86257cfc0052d4e9/$FILE/AC%2020-176A.pdf); and Order
8110.117A, dated June 18, 2014 (http://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgOrders.nsf/0/
d715cdfc08ac0ddc86257cfc00528297/$FILE/110.117A.pdf), which include the
concept of RC. The FAA has begun implementing this concept in ADs when
we receive service information containing RC steps. While some design
approval holders have implemented the RC concept, the implementation is
voluntary. The FAA does not intend to develop or revise AD requirements
to incorporate the RC concept if it is not included in the service
information.
However for this AD, we reviewed Airbus Service Bulletin A320-53-
1257, dated December 21, 2012, and determined that the procedures in
paragraph 3.C., ``Procedure,'' are necessary to address the identified
unsafe condition. All other steps in the Accomplishment Instructions
may be deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining approval
of an alternative method of compliance (AMOC), provided the procedures
in paragraph 3.C., ``Procedures,'' can be done and the airplane can be
put back in a serviceable condition. We have revised paragraph (g) of
this AD to refer to procedures in paragraph 3.C., ``Procedures,'' of
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1257, dated December 21, 2012.

Conclusion

We reviewed the relevant data, considered the comments received,
and

[[Page 52184]]

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 (79 FR 42716, July 23, 2014) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 42716, July 23, 2014).
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

We reviewed Airbus Service Bulletin A320-53-1257, dated December
21, 2012. The service information describes procedures for a rototest
inspection of the open tack holes and rivet holes at the cargo floor
support fittings between frame (FR) 50 and FR 63 (left-hand side only)
for Model A320 and A321 series airplanes and FR 53 and FR 63 (left-hand
side only) for Model A319 series airplanes of the fuselage, including
other actions, and repair if necessary. 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 of this AD.

Costs of Compliance

We estimate that this AD affects 847 airplanes of U.S. registry.
We also estimate that it would take about 471 work-hours per
product to comply with the basic requirements of this AD. The average
labor rate is $85 per work-hour. Required parts (for the modification)
would cost about $6,570 per product. Based on these figures, we
estimate the cost of this AD on U.S. operators to be $39,474,435, or
$46,605 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions 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.

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.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0455; 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 Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

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):

2015-17-14 Airbus: Amendment 39-18247. Docket No. FAA-2014-0455;
Directorate Identifier 2014-NM-006-AD.

(a) Effective Date

This AD becomes effective October 2, 2015.

(b) Affected ADs

None.

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;
all manufacturer serial numbers.

(d) Subject

Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

This AD was prompted by reports that, during a full scale
fatigue test, several broken frames in certain areas of the cargo
compartment have been found, especially on the cargo floor support
fittings and open tack holes on the left-hand (LH) side. We are
issuing this AD to detect and correct cracking in the open tack
holes and rivet holes at the cargo floor support fittings of the
fuselage, which could affect the structural integrity of the
airplane.

(f) Compliance

Comply with this AD within the compliance times specified,
unless already done.

(g) Inspection

At the applicable compliance times specified in paragraphs
(g)(1) through (g)(3) of this AD: Do a rototest inspection for
cracking of the open tack holes and rivet holes at the cargo floor
support fittings of the fuselage between frame (FR) 50 and FR 63
left-hand (LH) side only for Model A320 series airplanes, and A321
series airplanes; and between FR 53 and FR 63 LH side only for Model
A319 series airplanes; in accordance with paragraph 3.C.,
``Procedures,'' of the Accomplishment Instructions of Airbus Service
Bulletin A320-53-1257, dated December 21, 2012. Repeat the
inspection thereafter at intervals not to exceed 5,000 flight cycles
or 10,000 flight hours, whichever occurs first.
(1) For airplanes that have equal to or more than 45,000 total
flight cycles or 90,000 total flight hours as of the effective date
of this AD: Do the rototest inspection within 1,000 flight cycles or
2,000 flight hours after the effective date of this AD, whichever
occurs first.
(2) For airplanes that have equal to or more than 36,200 total
flight cycles or 72,400 total flight hours, but less than 45,000
total flight cycles or 90,000 total flight hours as of the

[[Page 52185]]

effective date of this AD: Do the rototest inspection within 2,000
flight cycles or 4,000 flight hours after the effective date of this
AD, whichever occurs first, but no later than before the
accumulation of 46,000 total flight cycles or 92,000 total flight
hours, whichever occurs first.
(3) For airplanes that have less than 36,200 total flight cycles
or 72,400 total flight hours as of the effective date of this AD: Do
the rototest inspection before exceeding 38,200 total flight cycles
or 76,400 total flight hours, whichever occurs first.

(h) Corrective Action

If any crack is found during any inspection required by this AD:
Before further flight, repair using a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA). If approved by the
DOA, the approval must include the DOA-authorized signature.

(i) Other FAA AD Provisions

The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the International
Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149. 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. The AMOC approval letter must
specifically reference this AD.
(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
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA DOA. If approved by the DOA, the approval must include
the DOA-authorized signature.

(j) Related Information

Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA Airworthiness Directive 2013-0310, dated December 20, 2013, for
related information. This MCAI may be found in the AD docket on the
Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-
0455-0002.

(k) 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 A320-53-1257, dated December 21,
2012.
(ii) Reserved.
(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 http://www.airbus.com.
(4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

Issued in Renton, Washington, on August 13, 2015.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-20951 Filed 8-27-15; 8:45 am]
BILLING CODE 4910-13-P

52182 Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Rules and Regulations

(i) Bombardier Service Bulletin 601R–35– DATES: This AD becomes effective This condition, if not detected and
018, dated May 21, 2013. October 2, 2015. corrected, could affect the structural integrity
(ii) Reserved. of the aeroplane.
(3) For service information identified in
The Director of the Federal Register For the reason described above, this
this AD, contact Bombardier, Inc., 400 Côte- approved the incorporation by reference [EASA] AD requires repetitive inspections of
Vertu Road West, Dorval, Québec H4S 1Y9, of certain publications listed in this AD the frames in the cargo compartment area and
Canada; telephone 514–855–5000; fax 514– as of October 2, 2015. of the cargo floor support fittings and open
855–7401; email ADDRESSES: You may examine the AD
tack holes on the left hand (LH) side, and
thd.crj@aero.bombardier.com; Internet http:// depending on findings, the accomplishment
www.bombardier.com. docket on the Internet at http:// of applicable corrective action(s). This
(4) You may view this service information www.regulations.gov/ [EASA] AD also requires a modification,
at the FAA, Transport Airplane Directorate, #!docketDetail;D=FAA-2014-0455; or in which constitutes terminating action for the
1601 Lind Avenue SW., Renton, WA. For person at the Docket Management repetitive inspections required by this
information on the availability of this Facility, U.S. Department of [EASA] AD.
material at the FAA, call 425–227–1221. Transportation, Docket Operations, M–
(5) You may view this service information
The actions in this AD include a rototest
30, West Building Ground Floor, Room inspection for cracking of the open tack
that is incorporated by reference at the W12–140, 1200 New Jersey Avenue SE.,
National Archives and Records holes and rivet holes at the cargo floor
Administration (NARA). For information on Washington, DC. support fittings of the fuselage;
the availability of this material at NARA, call For service information identified in modification of the fuselage, including
202–741–6030, or go to: http:// this AD, contact Airbus, Airworthiness doing all applicable related investigative
www.archives.gov/federal-register/cfr/ibr- Office—EIAS, 1 Rond Point Maurice actions; and repair if necessary. Related
locations.html. Bellonte, 31707 Blagnac Cedex, France; investigative actions include rotating
Issued in Renton, Washington, on August telephone +33 5 61 93 36 96; fax +33 5 probe inspections for cracking of the
17, 2015. 61 93 44 51; email account.airworth- holes. You may examine the MCAI in
Kevin Hull, eas@airbus.com; Internet http:// the AD docket on the Internet at http://
Acting Manager, Transport Airplane www.airbus.com. You may view this www.regulations.gov/
Directorate, Aircraft Certification Service. referenced service information at the #!documentDetail;D=FAA-2014-0455-
[FR Doc. 2015–20959 Filed 8–27–15; 8:45 am] FAA, Transport Airplane Directorate, 0002.
BILLING CODE 4910–13–P 1601 Lind Avenue SW., Renton, WA.
For information on the availability of Comments
this material at the FAA, call 425–227– We gave the public the opportunity to
DEPARTMENT OF TRANSPORTATION 1221. It is also available on the Internet participate in developing this AD. The
at http://www.regulations.gov by following presents the comments
Federal Aviation Administration searching for and locating Docket No. received on the NPRM (79 FR 42716,
FAA–2015–0455. July 23, 2014) and the FAA’s response
14 CFR Part 39 to each comment.
FOR FURTHER INFORMATION CONTACT:
[Docket No. FAA–2014–0455; Directorate Sanjay Ralhan, Aerospace Engineer, Requests To Remove Service
Identifier 2014–NM–006–AD; Amendment International Branch, ANM–116, Information Not Applicable to the U.S.
39–18247; AD 2015–17–14] Transport Airplane Directorate, FAA, Fleet
RIN 2120–AA64 1601 Lind Avenue SW., Renton, WA Delta Air Lines (DAL), United
98057–3356; telephone 425–227–1405; Airlines (UAL), and US Airways
Airworthiness Directives; Airbus fax 425–227–1149. requested that certain service
Airplanes SUPPLEMENTARY INFORMATION: information be removed from the NPRM
AGENCY: Federal Aviation Discussion (79 FR 42716, July 23, 2014) as it is not
Administration (FAA), Department of applicable to the U.S. fleet.
Transportation (DOT). We issued a notice of proposed DAL stated that Airbus Service
ACTION: Final rule. rulemaking (NPRM) to amend 14 CFR Bulletin A320–53–1261, dated
part 39 by adding an AD that would December 21, 2012, which provides a
SUMMARY: We are adopting a new apply to all Airbus Model A319, A320, terminating modification for the
airworthiness directive (AD) for all and A321 series airplanes. The NPRM repetitive inspections specified in the
Airbus Model A319, A320, and A321 published in the Federal Register on NPRM (79 FR 42716, July 23, 2014), is
series airplanes. This AD was prompted July 23, 2014 (79 FR 42716). one of eight structural modification
by reports that during a full scale fatigue The European Aviation Safety Agency service bulletins required to operate
test, several broken frames in certain (EASA), which is the Technical Agent Model A320 airplanes beyond 48,000
areas of the cargo compartment have for the Member States of the European flight cycles/96,000 flight hours
been found, especially on the cargo floor Union, has issued EASA Airworthiness (referred to as extended service goal
support fittings and open tack holes on Directive 2013–0310, dated December (ESG)). DAL stated that Airbus Service
the left-hand side. This AD requires a 20, 2013 (referred to after this as the Bulletin A320–53–1261, dated
rototest inspection of the open tack Mandatory Continuing Airworthiness December 21, 2012, does not affect DAL
holes and rivet holes at the cargo floor Information, or ‘‘the MCAI’’), to correct or any other U.S. operator, since Airbus
support fittings of the fuselage, an unsafe condition for all Airbus only recognizes airplane effectivity for
including doing all applicable related Model A319, A320, and A321 series those operators that have accomplished
investigative actions, and repair if airplanes. The MCAI states: this service bulletin (which can only be
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necessary. We are issuing this AD to purchased from Airbus) through ESG
During a full scale fatigue test, several
detect and correct cracking in the open broken frames in the cargo compartment area embodiment.
tack holes and rivet holes at the cargo between Frame (FR) 50 and FR 63, have been UAL and US Airways stated that, in
floor support fittings of the fuselage, found, especially on the cargo floor support paragraph (h) of the proposed AD (79 FR
which could affect the structural fittings and open tack holes on [the] left hand 42716, July 23, 2014), modification of
integrity of the airplane. side. the fuselage in accordance with Airbus

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52184 Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Rules and Regulations

determined that air safety and the General requirements.’’ Under that Authority: 49 U.S.C. 106(g), 40113, 44701.
public interest require adopting this AD section, Congress charges the FAA with
§ 39.13 [Amended]
with the changes described previously promoting safe flight of civil aircraft in
and minor editorial changes. We have air commerce by prescribing regulations ■ 2. The FAA amends § 39.13 by adding
determined that these minor changes: for practices, methods, and procedures the following new airworthiness
• Are consistent with the intent that the Administrator finds necessary for directive (AD):
was proposed in the NPRM (79 FR safety in air commerce. This regulation 2015–17–14 Airbus: Amendment 39–18247.
42716, July 23, 2014) for correcting the is within the scope of that authority Docket No. FAA–2014–0455; Directorate
unsafe condition; and because it addresses an unsafe condition Identifier 2014–NM–006–AD.
• Do not add any additional burden that is likely to exist or develop on (a) Effective Date
upon the public than was already products identified in this rulemaking
This AD becomes effective October 2, 2015.
proposed in the NPRM (79 FR 42716, action.
July 23, 2014). (b) Affected ADs
We also determined that these Regulatory Findings
None.
changes will not increase the economic We determined that this AD will not
burden on any operator or increase the have federalism implications under (c) Applicability
scope of this AD. Executive Order 13132. This AD will This AD applies to Airbus Model A319–
not have a substantial direct effect on 111, –112, –113, –114, –115, –131, –132, and
Related Service Information Under 1 the States, on the relationship between –133 airplanes; Model A320–211, –212, –214,
CFR Part 51 the national government and the States, –231, –232, and –233 airplanes; and Model
A321–111, –112, –131, –211, –212, –213,
We reviewed Airbus Service Bulletin or on the distribution of power and –231, and –232 airplanes; certificated in any
A320–53–1257, dated December 21, responsibilities among the various category; all manufacturer serial numbers.
2012. The service information describes levels of government.
procedures for a rototest inspection of For the reasons discussed above, I (d) Subject
the open tack holes and rivet holes at certify that this AD: Air Transport Association (ATA) of
the cargo floor support fittings between 1. Is not a ‘‘significant regulatory America Code 53, Fuselage.
frame (FR) 50 and FR 63 (left-hand side action’’ under Executive Order 12866; (e) Reason
only) for Model A320 and A321 series 2. Is not a ‘‘significant rule’’ under the
This AD was prompted by reports that,
airplanes and FR 53 and FR 63 (left- DOT Regulatory Policies and Procedures during a full scale fatigue test, several broken
hand side only) for Model A319 series (44 FR 11034, February 26, 1979); frames in certain areas of the cargo
airplanes of the fuselage, including 3. Will not affect intrastate aviation in compartment have been found, especially on
other actions, and repair if necessary. Alaska; and the cargo floor support fittings and open tack
This service information is reasonably 4. Will not have a significant holes on the left-hand (LH) side. We are
available because the interested parties economic impact, positive or negative, issuing this AD to detect and correct cracking
have access to it through their normal on a substantial number of small entities in the open tack holes and rivet holes at the
under the criteria of the Regulatory cargo floor support fittings of the fuselage,
course of business or by the means which could affect the structural integrity of
identified in the ADDRESSES section of Flexibility Act.
the airplane.
this AD. Examining the AD Docket
(f) Compliance
Costs of Compliance You may examine the AD docket on Comply with this AD within the
We estimate that this AD affects 847 the Internet at http:// compliance times specified, unless already
airplanes of U.S. registry. www.regulations.gov/ done.
We also estimate that it would take #!docketDetail;D=FAA-2014-0455; or in
(g) Inspection
about 471 work-hours per product to person at the Docket Management
Facility between 9 a.m. and 5 p.m., At the applicable compliance times
comply with the basic requirements of specified in paragraphs (g)(1) through (g)(3)
this AD. The average labor rate is $85 Monday through Friday, except Federal
of this AD: Do a rototest inspection for
per work-hour. Required parts (for the holidays. The AD docket contains this
cracking of the open tack holes and rivet
modification) would cost about $6,570 AD, the regulatory evaluation, any holes at the cargo floor support fittings of the
per product. Based on these figures, we comments received, and other fuselage between frame (FR) 50 and FR 63
estimate the cost of this AD on U.S. information. The street address for the left-hand (LH) side only for Model A320
operators to be $39,474,435, or $46,605 Docket Operations office (telephone series airplanes, and A321 series airplanes;
per product. 800–647–5527) is in the ADDRESSES and between FR 53 and FR 63 LH side only
section. for Model A319 series airplanes; in
We have received no definitive data
accordance with paragraph 3.C.,
that would enable us to provide cost List of Subjects in 14 CFR Part 39 ‘‘Procedures,’’ of the Accomplishment
estimates for the on-condition actions Instructions of Airbus Service Bulletin A320–
Air transportation, Aircraft, Aviation
specified in this AD. 53–1257, dated December 21, 2012. Repeat
safety, Incorporation by reference,
the inspection thereafter at intervals not to
Authority for This Rulemaking Safety.
exceed 5,000 flight cycles or 10,000 flight
Title 49 of the United States Code Adoption of the Amendment hours, whichever occurs first.
specifies the FAA’s authority to issue Accordingly, under the authority
(1) For airplanes that have equal to or more
rules on aviation safety. Subtitle I, than 45,000 total flight cycles or 90,000 total
delegated to me by the Administrator, flight hours as of the effective date of this
section 106, describes the authority of the FAA amends 14 CFR part 39 as
the FAA Administrator. ‘‘Subtitle VII: AD: Do the rototest inspection within 1,000
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follows: flight cycles or 2,000 flight hours after the
Aviation Programs,’’ describes in more effective date of this AD, whichever occurs
detail the scope of the Agency’s PART 39—AIRWORTHINESS first.
authority. DIRECTIVES (2) For airplanes that have equal to or more
We are issuing this rulemaking under than 36,200 total flight cycles or 72,400 total
the authority described in ‘‘Subtitle VII, ■ 1. The authority citation for part 39 flight hours, but less than 45,000 total flight
Part A, Subpart III, Section 44701: continues to read as follows: cycles or 90,000 total flight hours as of the

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Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Rules and Regulations 52185

effective date of this AD: Do the rototest paragraph under 5 U.S.C. 552(a) and 1 CFR engine in-flight shutdown, forced
inspection within 2,000 flight cycles or 4,000 part 51. landing, and damage to the helicopter.
flight hours after the effective date of this AD, (2) You must use this service information
DATES: This AD becomes effective
whichever occurs first, but no later than as applicable to do the actions required by
before the accumulation of 46,000 total flight this AD, unless this AD specifies otherwise. October 2, 2015.
cycles or 92,000 total flight hours, whichever (i) Airbus Service Bulletin A320–53–1257, The Director of the Federal Register
occurs first. dated December 21, 2012. approved the incorporation by reference
(3) For airplanes that have less than 36,200 (ii) Reserved. of a certain publication listed in this AD
total flight cycles or 72,400 total flight hours (3) For service information identified in as of October 2, 2015.
as of the effective date of this AD: Do the this AD, contact Airbus, Airworthiness ADDRESSES: For service information
rototest inspection before exceeding 38,200 Office—EIAS, 1 Rond Point Maurice identified in this AD, contact
total flight cycles or 76,400 total flight hours, Bellonte, 31707 Blagnac Cedex, France;
Turbomeca S.A., 40220 Tarnos, France;
whichever occurs first. telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@ phone: 33 (0)5 59 74 40 00; telex: 570
(h) Corrective Action airbus.com; Internet http://www.airbus.com. 042; fax: 33 (0)5 59 74 45 15. You may
If any crack is found during any inspection (4) You may view this service information view this service information at the
required by this AD: Before further flight, at the FAA, Transport Airplane Directorate, FAA, Engine & Propeller Directorate, 12
repair using a method approved by the 1601 Lind Avenue SW., Renton, WA. For New England Executive Park,
Manager, International Branch, ANM–116, information on the availability of this Burlington, MA. For information on the
Transport Airplane Directorate, FAA; or the material at the FAA, call 425–227–1221. availability of this material at the FAA,
European Aviation Safety Agency (EASA); or (5) You may view this service information call 781–238–7125. It is also available
Airbus’s EASA Design Organization that is incorporated by reference at the
on the Internet at http://
Approval (DOA). If approved by the DOA, National Archives and Records
Administration (NARA). For information on www.regulations.gov by searching for
the approval must include the DOA-
authorized signature. the availability of this material at NARA, call and locating Docket No. FAA–2015–
202–741–6030, or go to: http:// 0900.
(i) Other FAA AD Provisions www.archives.gov/federal-register/cfr/ibr-
Examining the AD Docket
The following provisions also apply to this locations.html.
AD: You may examine the AD docket on
(1) Alternative Methods of Compliance Issued in Renton, Washington, on August the Internet at http://
(AMOCs): The Manager, International 13, 2015. www.regulations.gov by searching for
Branch, ANM–116, FAA, has the authority to Suzanne Masterson, and locating Docket No. FAA–2015–
approve AMOCs for this AD, if requested Acting Manager, Transport Airplane 0900; or in person at the Docket
using the procedures found in 14 CFR 39.19. Directorate, Aircraft Certification Service.
In accordance with 14 CFR 39.19, send your
Management Facility between 9 a.m.
request to your principal inspector or local [FR Doc. 2015–20951 Filed 8–27–15; 8:45 am] and 5 p.m., Monday through Friday,
Flight Standards District Office, as BILLING CODE 4910–13–P except Federal holidays. The AD docket
appropriate. If sending information directly contains this AD, the mandatory
to the International Branch, send it to ATTN: continuing airworthiness information
Sanjay Ralhan, Aerospace Engineer, DEPARTMENT OF TRANSPORTATION (MCAI), the regulatory evaluation, any
International Branch, ANM–116, Transport comments received, and other
Airplane Directorate, FAA, 1601 Lind Federal Aviation Administration information. The address for the Docket
Avenue SW., Renton, WA 98057–3356; Office (phone: 800–647–5527) is
telephone 425–227–1405; fax 425–227–1149. 14 CFR Part 39
Information may be emailed to: 9–ANM–116–
Document Management Facility, U.S.
AMOC–REQUESTS@faa.gov. Before using [Docket No. FAA–2015–0900; Directorate Department of Transportation, Docket
any approved AMOC, notify your appropriate Identifier 2015–NE–12–AD; Amendment 39– Operations, M–30, West Building
principal inspector, or lacking a principal 18251; AD 2015–17–18] Ground Floor, Room W12–140, 1200
inspector, the manager of the local flight New Jersey Avenue SE., Washington,
standards district office/certificate holding RIN 2120–AA64 DC 20590.
district office. The AMOC approval letter FOR FURTHER INFORMATION CONTACT:
must specifically reference this AD. Airworthiness Directives; Turbomeca
Philip Haberlen, Aerospace Engineer,
(2) Contacting the Manufacturer: For any S.A. Turboshaft Engines
requirement in this AD to obtain corrective Engine Certification Office, FAA, Engine
actions from a manufacturer, the action must AGENCY: Federal Aviation & Propeller Directorate, 12 New England
be accomplished using a method approved Administration (FAA), DOT. Executive Park, Burlington, MA 01803;
by the Manager, International Branch, ANM– ACTION: Final rule. phone: 781–238–7770; fax: 781–238–
116, Transport Airplane Directorate, FAA; or 7199; email: philip.haberlen@faa.gov.
EASA; or Airbus’s EASA DOA. If approved SUMMARY: We are adopting a new SUPPLEMENTARY INFORMATION:
by the DOA, the approval must include the airworthiness directive (AD) for certain
DOA-authorized signature. Turbomeca S.A. Arrius 2F turboshaft Discussion
(j) Related Information engines with a certain part number oil We issued a notice of proposed
Refer to Mandatory Continuing pump installed. This AD requires rulemaking (NPRM) to amend 14 CFR
Airworthiness Information (MCAI) EASA inspection, and if necessary, part 39 by adding an AD that would
Airworthiness Directive 2013–0310, dated replacement before further flight of the apply to the specified products. The
December 20, 2013, for related information. oil pump driver assembly and/or the oil NPRM was published in the Federal
This MCAI may be found in the AD docket pump shaft, or the oil pump itself. This Register on May 21, 2015 (80 FR 29224).
on the Internet at http:// AD was prompted by cases of The NPRM proposed to correct an
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www.regulations.gov/ deterioration of the gas generator front unsafe condition for the specified
#!documentDetail;D=FAA-2014-0455-0002.
bearing due to a link loss between the products. The MCAI states:
(k) Material Incorporated by Reference pump driver and the oil pump shaft. We A risk of an in-flight shutdown (IFSD) has
(1) The Director of the Federal Register are issuing this AD to prevent link loss been identified on an ARRIUS 2F engine, due
approved the incorporation by reference between the pump driver and the oil to deterioration of gas generator front bearing.
(IBR) of the service information listed in this pump shaft, which could lead to an This could be the result of lack of lubrication,

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Document Created: 2015-12-15 11:04:45
Document Modified: 2015-12-15 11:04:45

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule.
Dates		This AD becomes effective October 2, 2015.
Contact		Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149.
FR Citation		80 FR 52182
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

80 FR 52182 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 167 (August 28, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration