[Federal Register Volume 79, Number 190 (Wednesday, October 1, 2014)]
[Proposed Rules]
[Pages 59160-59162]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-23366]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0652; Directorate Identifier 2014-NM-076-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt 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 series airplanes. This
proposed AD was prompted by reports of cracks that could be initiated
at the waste water service panel area and the potable water service
panel area. This proposed AD would require modification of the potable
water service panel and waste water service panel, including doing
applicable related investigative and corrective actions. We are
proposing this AD to prevent any cracking at the waste water service
panel area and the potable water service panel area, which could affect
the structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by November 17,
2014.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email [email protected]; Internet 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.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0652; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: 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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0652;
Directorate Identifier 2014-NM-076-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2014-0081, dated March 31, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A319; Model A320-211, -212, -214, -231, -232, and -233; and Model A321
series airplanes. The MCAI states:
During the full scale fatigue test on A320-200, it has been
noticed that, due to fatigue, cracks could be initiated at the waste
water service panel area and the potable water service panel area.
This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
Prompted by these findings, ALS [airworthiness limitations
section] Part 2 tasks have been introduced for the affected A320
family aeroplanes. Since those actions were taken, Airbus developed
production mod 160055 and mod 160056 to embody reinforcements (cold
working on certain rivet rows) of the potable water and waste water
service panels, and published associated Airbus Service Bulletin
(SB) A320-53-1272 (retrofit mod 153074) and SB A320-53-1267
(retrofit mod 153073) for in-service embodiment.
Following complementary Design Office studies, it appears that
the Sharklet installations on certain aeroplanes have a significant
impact on the aeroplane structure (particularly, A319 and A320 post-
mod 160001, and A321 post-mod 160021), leading to different
compliance times, depending on aeroplane configuration.
For the reasons described above, this [EASA] AD requires
reinforcement of the potable water and waste water service panels.
Accomplishment of these modifications cancels the need for the
related ALS Part 2 Tasks.
The modification includes doing applicable related investigative
and corrective actions. Related investigative
[[Page 59161]]
actions include measuring the diameter of a hole of a fastener and a
rotating probe inspection. Corrective actions include repairs. You may
examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0652.
Relevant Service Information
Airbus has issued Service Bulletin A320-53-1267, Revision 01, dated
October 2, 2013; and Service Bulletin A320-53-1272, Revision 02, dated
May 19, 2014. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 851 airplanes of U.S.
registry.
We also estimate that it would take about 25 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $420
per product. Based on these figures, we estimate the cost of this
proposed AD on U.S. operators to be $2,165,795, or $2,545 per product.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2014-0652; Directorate Identifier 2014-NM-
076-AD.
(a) Comments Due Date
We must receive comments by November 17, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category,
all manufacturer serial numbers, except those on which Airbus
Modification 160055 or Airbus Modification 160056 has been embodied
in production.
(1) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(2) Airbus Model A320-211, -212, -214, -231, -232, and -233
airplanes.
(3) Airbus Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracks that could be
initiated at the waste water service panel area and the potable
water service panel area. We are issuing this AD to prevent any
cracking at the waste water service panel area and the potable water
service panel area, which could affect the structural integrity of
the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Modification
(1) Within the compliance time specified in paragraphs
(g)(1)(i), (g)(1)(ii), (g)(1)(iii), (g)(1)(iv), and (g)(1)(v) of
this AD, as applicable, modify the potable water service panel,
including doing all applicable related investigative and corrective
actions, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-53-1272, Revision 02, dated May 19,
2014, except where Airbus Service Bulletin A320-53-1272, Revision
02, dated May 19, 2014, specifies to contact Airbus, repair before
further flight 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). Do all applicable related investigative
and corrective actions within the compliance time identified in
paragraphs (g)(1)(i), (g)(1)(ii), (g)(1)(iii), (g)(1)(iv), and
(g)(1)(v) of this AD.
(i) For Model A319 airplanes pre-modification 160001: Within
48,500 flight cycles or 97,000 flight hours, whichever occurs first
since the airplane's first flight.
(ii) For Model A319 airplanes post-modification 160001: Within
46,000 flight cycles or 92,000 flight hours, whichever occurs first
since the airplane's first flight.
(iii) For Model A320 airplanes pre-modification 160001: Within
54,200 flight cycles or 108,400 flight hours, whichever occurs first
since the airplane's first flight.
(iv) For Model A320 airplanes post-modification 160001: Within
36,000 flight cycles or 72,000 flight hours, whichever occurs first
since the airplane's first flight.
(v) For Model A321 airplanes: Within 60,000 flight cycles or
120,000 flight hours, whichever occurs first since the airplane's
first flight.
(2) Within the compliance time specified in paragraphs
(g)(2)(i), (g)(2)(ii), (g)(2)(iii), (g)(2)(iv), (g)(2)(v), and
(g)(2(vi) of this AD, as applicable, modify the waste water service
panel, including doing all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-
[[Page 59162]]
53-1267, Revision 01, dated October 2, 2013, except where Airbus
Service Bulletin A320-53-1267, Revision 01, dated October 2, 2013,
specifies to contact Airbus, repair before further flight using a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA
DOA. Do all applicable related investigative and corrective actions
within the compliance time identified in paragraphs (g)(2)(i),
(g)(2)(ii), (g)(2)(iii), (g)(2)(iv), and (g)(2)(v) of this AD.
(i) For Airbus A319 airplanes pre-modification 160001: Within
44,400 flight cycles or 88,800 flight hours, whichever occurs first
since the airplane's first flight.
(ii) For Airbus A319 airplanes post-modification 160001: Within
43,600 flight cycles or 87,200 flight hours, whichever occurs first
since the airplane's first flight.
(iii) For Airbus A320 airplanes pre-modification 160001, within
the compliance times identified in paragraph (g)(2)(iii)(A) or
(g)(2)(iii)(B) of this AD, whichever occurs later:
(A) Within 46,400 flight cycles or 92,800 flight hours,
whichever occurs first since the airplane's first flight.
(B) Within 2,300 flight cycles or 4,600 flight hours, whichever
occurs first since last accomplishment of Airworthiness Limitation
Section (ALS) Part 2 Task No. 534126-01-3 without exceeding 48,000
flight cycles or 96,000 flight hours, whichever occurs first since
the airplane's first flight.
(iv) For Airbus A320 airplanes post-modification 160001: Within
39,200 flight cycles or 78,400 flight hours, whichever occurs first
since the airplane's first flight.
(v) For Airbus A321 airplanes pre-modification 160021: Within
51,600 flight cycles or 103,200 flight hours, whichever occurs first
since the airplane's first flight.
(vi) For Airbus A321 airplanes post-modification 160021: Within
51,200 flight cycles or 102,400 flight hours, whichever occurs first
since the airplane's first flight.
(h) Corrective Action
For Airbus A320 airplanes having pre-modification 160001, that
have exceeded 46,400 flight cycles or 92,800 flight hours, whichever
occurred first since the airplane's first flight: If any crack is
found during accomplishment of ALS Part 2 Task 534126-01-3 done,
before further flight, repair using a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the EASA; or Airbus's EASA DOA.
(i) Terminating Action for ALS Task
(1) Modification of an airplane as required by paragraph (g)(1)
of this AD, terminates the requirement for the ALS Part 2 Task for
that airplane as identified in paragraphs (i)(1)(i), (i)(1)(ii),
(i)(1)(iii), (i)(1)(iv), (i)(1)(v), and (i)(1)(vi) of this AD, as
applicable.
(i) For Airbus A319 airplanes pre-modification 160001: ALS Part
2 Task No. 534125-01-2.
(ii) For Airbus A319 airplanes post-modification 160001: ALS
Part 2 Task No. 534125-01-5.
(iii) For Airbus A320 airplanes pre-modification 160001: ALS
Part 2 Task No. 534125-01-3.
(iv) For Airbus A320 airplanes post-modification 160001: ALS
Part 2 Task No. 534125-01-6.
(v) For Airbus A321 airplanes pre-modification 160021: ALS Part
2 Task No. 534125-01-4.
(vi) For Airbus A321 airplanes post-modification 160021: ALS
Part 2 Task No. 534125-01-7.
(2) Modification of an airplane as required by paragraphs (g)(2)
and (g)(3) of this AD, terminates the requirement for the ALS Part 2
task for that airplane as identified in paragraphs (i)(2)(i),
(i)(2)(ii), (i)(2)(iii), (i)(2)(iv), (i)(2)(v), and (i)(2)(vi) of
this AD, as applicable.
(i) For Airbus A319 airplanes pre-modification 160001: ALS Part
2 Task No. 534126-01-2.
(ii) For Airbus A319 airplanes post-modification 160001: ALS
Part 2 Task No. 534126-01-5.
(iii) For Airbus A320 airplanes pre-modification 160001: ALS
Part 2 Task No. 534126-01-3.
(iv) For Airbus A320 airplanes post-modification 160001: ALS
Part 2 Task No. 534126-01-6.
(v) For Airbus A321 airplanes pre-modification 160021: ALS Part
2 Task No. 534126-01-4.
(vi) For Airbus A321 airplanes post-modification 160021: ALS
Part 2 Task No. 534126-01-7.
(j) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (g)(1) of this AD, if those actions were performed before
the effective date of this AD using Airbus Service Bulletin A320-53-
1272, dated January 10, 2013; and Airbus Service Bulletin A320-53-
1272, Revision 01, dated August 6, 2013; which are not incorporated
by reference in this AD.
(2) This paragraph provides credit for actions required by
paragraph (g)(2) of this AD, if those actions were performed before
the effective date of this AD using Airbus Service Bulletin A320-53-
1267, dated June 24, 2013, which is not incorporated by reference in
this AD.
(k) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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: [email protected]. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. 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 the EASA;
or Airbus's EASA DOA. If approved by the DOA, the approval must
include the DOA-authorized signature.
(l) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0081, dated March 31, 2014,
for related information. This MCAI may be found in the AD docket on
the Internet at http://www.regulations.gov by searching for and
locating Docket No. FAA-2014-0652.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email [email protected]; Internet http://www.airbus.com. 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.
Issued in Renton, Washington, on September 20, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-23366 Filed 9-30-14; 8:45 am]
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