[Federal Register Volume 80, Number 15 (Friday, January 23, 2015)]
[Proposed Rules]
[Pages 3533-3535]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-00943]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-1047; Directorate Identifier 2014-NM-157-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 A318, A319, A320, and A321 series airplanes. This 
proposed AD was prompted by a report that, during the assembly process, 
several gaps between the two parts of the girt bar fittings for the aft 
passenger doors were found to exceed tolerances. This proposed AD would 
require an inspection of the gap between the two parts of the girt bar 
fittings on left-hand (LH) and right-hand (RH) aft passenger doors, and 
corrective actions if necessary. We are proposing this AD to detect and 
correct incorrect gaps between the girt bar fittings. Detachment of a 
girt bar could lead to the separation of the slide or slide-raft from 
the fuselage, making the emergency exit inoperative, which could impede 
an emergency evacuation.

DATES: We must receive comments on this proposed AD by March 9, 2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 <a href="/cdn-cgi/l/email-protection#68090b0b071d061c4609011a1f071a1c00450d091b2809011a0a1d1b460b0705"><span class="__cf_email__" data-cfemail="caaba9a9a5bfa4bee4aba3b8bda5b8bea2e7afabb98aaba3b8a8bfb9e4a9a5a7">[email protected]</span></a>; 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-
1047; 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-2014-1047; 
Directorate Identifier 2014-NM-157-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

[[Page 3534]]

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 Union, has issued EASA 
Airworthiness Directive 2014-0178, dated July 25, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A318, A319, A320, and A321 series airplanes. The MCAI states:

    During final assembly line process, several AFT passenger door 
lower fitting gaps were found excessive and out of tolerance between 
two parts of the girt bar fittings. The gap contributes to the 
correct locking of the girt bar during the door lifting movement, 
ensuring the retention of the girt bar when the loads applied on the 
girt by the slide are directed from the outside to the inside. If 
the gap is too large, there is a risk that the girt bar, when 
subjected to these loads, will detach from one of the girt bar 
fittings.
    This condition, if not detected and corrected, could lead to the 
separation of the slide/slide-raft from the fuselage, making the 
emergency exit inoperative and, consequently, significantly reducing 
the safety margin for the occupants during an evacuation.
    For the reason described above, this [EASA] AD requires a 
detailed inspection (DET) to check the gap between the two parts of 
the girt bar fittings, on AFT passenger doors, left-hand (LH) and 
right-hand (RH) sides, and, depending on findings, accomplishment of 
the applicable corrective actions [such as modifiying or replacing 
the automatic latch].

    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-
1047.

Related Service Information

    Airbus has issued Service Bulletin A320-53-1289, dated May 28, 
2014. The service information describes procedures for a detailed 
inspection of the gap in the girt bar fittings of the aft passenger 
doors, LH and RH sides, and corrective actions. 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.

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directives Implementation Aviation Rulemaking Committee 
(AD ARC), to enhance the AD system. One enhancement was a new process 
for annotating which procedures and tests in the service information 
are required for compliance with an AD. Differentiating these 
procedures and tests from other tasks in the service information is 
expected to improve an owner's/operator's understanding of crucial AD 
requirements and help provide consistent judgment in AD compliance. The 
actions specified in the service information identified previously 
include procedures and tests that are identified as RC (required for 
compliance) because these procedures have a direct effect on detecting, 
preventing, resolving, or eliminating an identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of the 
specified service information, procedures and tests identified as RC 
must be done to comply with the proposed AD. However, procedures and 
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 alternative method 
of compliance (AMOC), provided the procedures and tests identified as 
RC can be done and the airplane can be put back in a serviceable 
condition. Any substitutions or changes to procedures or tests 
identified as RC will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 838 airplanes of U.S. 
registry.
    We also estimate that it would take about 3 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $213,690, or $255 
per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 4 work-hours and require parts costing $435, for a cost of 
$775 per product. We have no way of determining the number of aircraft 
that might need these actions.

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:

[[Page 3535]]

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-2014-1047; Directorate Identifier 2014-NM-
157-AD.

(a) Comments Due Date

    We must receive comments by March 9, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, 
except those on which Airbus Modification 154966 has been embodied 
during production.
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
    (4) 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 a report that, during the assembly 
process, several gaps between the two parts of the girt bar fittings 
for the aft passenger doors were found to exceed tolerances. We are 
issuing this AD to detect and correct incorrect gaps between the 
girt bar fittings. Detachment of a girt bar could lead to the 
separation of the slide or slide-raft from the fuselage, making the 
emergency exit inoperative, which could impede an emergency 
evacuation.

(f) Compliance

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

(g) Inspection and Corrective Action

    Except as provided by paragraph (h) of this AD, within 36 months 
after the effective date of this AD, do a detailed inspection of the 
gap in the girt bar fittings of the aft passenger doors, LH and RH 
sides, and do all applicable corrective actions, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1289, dated May 28, 2014. Do all applicable corrective actions 
before further flight.

(h) Exception

    For any airplane that has been modified to a configuration where 
one or both LH and RH aft passenger doors are permanently 
inoperative or deactivated: If any aft passenger door is 
reactivated, after reactivation but before further flight, do the 
detailed inspection of the reactivated aft passenger door(s) and all 
applicable corrective actions, as required by paragraph (g) of this 
AD.

(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, 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: <a href="/cdn-cgi/l/email-protection#4871650906056579797e650905070b651a0d191d0d1b1c1b082e2929662f273e"><span class="__cf_email__" data-cfemail="83baaec2cdceaeb2b2b5aec2ceccc0aed1c6d2d6c6d0d7d0c3e5e2e2ade4ecf5">[email protected]</span></a>. 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) Required for Compliance (RC): If the 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 and 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 a serviceable 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.
    (3) 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 
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.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency (EASA) Airworthiness 
Directive 2014-0178, dated July 25, 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-
2014-1047.
    (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 <a href="/cdn-cgi/l/email-protection#b6d7d5d5d9c3d8c298d7dfc4c1d9c4c2de9bd3d7c5f6d7dfc4d4c3c598d5d9db"><span class="__cf_email__" data-cfemail="afceccccc0dac1db81cec6ddd8c0dddbc782cacedcefcec6ddcddadc81ccc0c2">[email protected]</span></a>; 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 January 14, 2015.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-00943 Filed 1-22-15; 8:45 am]
BILLING CODE 4910-13-P


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