
[Federal Register Volume 79, Number 190 (Wednesday, October 1, 2014)]
[Proposed Rules]
[Pages 59160-59162]
From the Federal Register Online via the Government Printing 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 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.

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: 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 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 account.airworth-eas@airbus.com; 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]
BILLING CODE 4910-13-P


