[Federal Register Volume 79, Number 38 (Wednesday, February 26, 2014)]
[Proposed Rules]
[Pages 10707-10710]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-04140]



[[Page 10707]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0058; Directorate Identifier 2013-NM-116-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 supersede airworthiness directive (AD) 94-12-03 
that applies to certain Airbus Model A320 series airplanes. AD 94-12-03 
requires modification of the belly fairing structure. Since we issued 
AD 94-12-03, fatigue testing of Model A320 series airplanes showed 
cracks at the lower riveting of the four titanium angles that connect 
the belly fairing to the keel beam side panels on both sides of the 
fuselage. This proposed AD also would require repetitive inspections 
for cracking of the four titanium angles between the belly fairing and 
the keel beam side panel, an inspection for cracking of the open holes 
if any cracking is found, and repair or replacement if necessary. This 
proposed AD would also expand the applicability of AD 94-12-03. We are 
proposing this AD to detect and correct cracking of the titanium angles 
that connect the belly fairing to the keel beam side panels on both 
sides of the fuselage, which could affect the structural integrity of 
the airplane.

DATES: We must receive comments on this proposed AD by April 14, 2014.

ADDRESSES: You may send comments 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-
0058; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
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-2014-0058; 
Directorate Identifier 2013-NM-116-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

    On May 26, 1994, we issued AD 94-12-03, Amendment 39-8930 (59 FR 
28763, June 3, 1994). AD 94-12-03 superseded AD 93-24-11, Amendment 39-
8760 (58 FR 64875, December 10, 1993). AD 94-12-03 requires actions 
intended to address an unsafe condition on Airbus Model A320 series 
airplanes having serial numbers 0003 through 0092 inclusive. These 
serial numbers apply to Model A320-111, -211, and -231 series 
airplanes.
    Since we issued AD 94-12-03, Amendment 39-8930 (59 FR 28763, June 
3, 1994), The European Aviation Safety Agency (EASA), which is the 
Technical Agent for the Member States of the European Community, has 
issued EASA Airworthiness Directive 2013-0122, dated June 5, 2013 
(referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    During the fatigue test campaign of the A320 family type design, 
cracks have been found at the lower riveting of the four titanium 
angles which connect the belly fairing to the keel beam side panels 
between frames FR40 and FR42, on both sides of the fuselage.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    In 1992, DGAC France issued AD 92-201-030 (http://ad.easa.europa.eu/blob/19922010tb_superseded.pdf/AD_F-1992-201-030_1) (which corresponds to FAA AD 94-12-03, Amendment 39-8930 (59 
FR 28763, June 3, 1994)) to require reinforcement of the belly 
fairing structure, which addressed part of the unsafe condition.
    For the reason described above, this [EASA] AD retains the 
requirements of DGAC France AD 92-201-030, which is superseded, and 
requires repetitive detailed inspections [for cracking] of the 
affected titanium angles and, depending on findings, repair or 
replacement of parts.

    As an option to extend the repetitive inspection interval, after 
the first detailed inspection is accomplished and on condition of no 
crack findings, this proposed AD would allow operators to remove the 
four titanium angles, perform a rototest for cracking on the open holes 
and, provided no cracks are found, install new titanium angles, 
followed by post-modification detailed inspections of the new titanium 
angles.
    For any titanium angle crack findings, this proposed AD would 
require removing any cracked angle, performing a rototest for cracking 
on the open holes and, provided no cracks are found, installing a new 
titanium angle, followed detailed inspections of the new titanium 
angles.
    For any hole cracking found during any rototest, this proposed AD 
would require repair.
    This proposed AD expands the applicability of AD 94-12-03, 
Amendment 39-8930 (59 FR 28763, June 3, 1994) to include all Airbus 
Model A318, Model A319, Model A320, and Model A321 series airplanes.

[[Page 10708]]

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2014-0058.

Relevant Service Information

    Airbus has issued Service Bulletin A320-53-1014, Revision 02, dated 
September 1, 1994; and Service Bulletin A320-53-1259, dated November 6, 
2012. 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 the same 
type design.

Repair Approvals

    In many FAA transport ADs, when the service information specifies 
to contact the manufacturer for further instructions if certain 
discrepancies are found, we typically include in the AD a requirement 
to accomplish the action using a method approved by either the FAA or 
the State of Design Authority (or its delegated agent).
    We have recently been notified that certain laws in other countries 
do not allow such delegation of authority, but some countries do 
recognize design approval organizations. In addition, we have become 
aware that some U.S. operators have used repair instructions that were 
previously approved by a State of Design Authority or a Design Approval 
Holder (DAH) as a method of compliance with this provision in FAA ADs. 
Frequently, in these cases, the previously approved repair instructions 
come from the airplane structural repair manual or the DAH repair 
approval statements that were not specifically developed to address the 
unsafe condition corrected by the AD. Using repair instructions that 
were not specifically approved for a particular AD creates the 
potential for doing repairs that were not developed to address the 
unsafe condition identified by the MCAI AD, the FAA AD, or the 
applicable service information, which could result in the unsafe 
condition not being fully corrected.
    To prevent the use of repairs that were not specifically developed 
to correct the unsafe condition, this proposed AD would require that 
the repair approval specifically refer to the FAA AD. This change is 
intended to clarify the method of compliance and to provide operators 
with better visibility of repairs that are specifically developed and 
approved to correct the unsafe condition. In addition, we use the 
phrase ``its delegated agent, or by the DAH with State of Design 
Authority design organization approval, as applicable'' in this 
proposed AD to refer to an DAH authorized to approve required repairs 
for this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 851 airplanes of U.S. 
registry.
    The actions that are required by AD 94-12-03, Amendment 39-8930 (59 
FR 28763, June 3, 1994), and retained in this proposed AD take about 
288 work-hours per product, at an average labor rate of $85 per work-
hour. Required parts cost about $1,045 per product. Based on these 
figures, the estimated cost of the actions that were required by AD 94-
12-03 is $25,525 per product.
    We also estimate that it would take about 7 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 $506,345, or $595 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions and optional action costs 
specified in this proposed 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 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 removing airworthiness directive (AD) 
94-12-03, Amendment 39-8930 (59 FR 28763, June 3, 1994), and adding the 
following new AD:

Airbus: Docket No. FAA-2014-0058; Directorate Identifier 2013-NM-
116-AD.

(a) Comments Due Date

    We must receive comments by April 14, 2014.

(b) Affected ADs

    This AD supersedes AD 94-12-03, Amendment 39-8930 (59 FR 28763, 
June 3, 1994).

(c) Applicability

    This AD applies to the Airbus airplanes specified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.

[[Page 10709]]

    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-111, -211, -212, -214, -231, -232, and -
233 airplanes.
    (4) 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 at the lower riveting 
of the four titanium angles that connect the belly fairing to the 
keel beam side panels on both sides of the fuselage. We are issuing 
this AD to detect and correct cracking of the titanium angles that 
connect the belly fairing to the keel beam side panels on both sides 
of the fuselage, which could affect the structural integrity of the 
airplane.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Retained Modification

    This paragraph restates the requirements of paragraph (a) of AD 
94-12-03, Amendment 39-8930 (59 FR 28763, June 3, 1994), with new 
service information. For Model A320-111, -211, and -231 series 
airplanes, manufacturer serial numbers 0003 through 0092 inclusive: 
Prior to the accumulation of 12,000 total landings on the airplane, 
or within 300 days after January 10, 1994 (the effective date of AD 
93-24-11, Amendment 39-8760 (58 FR 64875, December 10, 1993)), 
whichever occurs later, modify the belly fairing structure, in 
accordance with the Accomplishment Instructions of an Airbus service 
bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this 
AD. As of the effective date of this AD, use only the Airbus service 
bulletin specified in paragraph (g)(3) of this AD.
    (1) Airbus Service Bulletin A320-53-1014, dated June 25, 1992.
    (2) Airbus Service Bulletin A320-53-1014, Revision 1, dated May 
26, 1993.
    (3) Airbus Service Bulletin A320-53-1014, Revision 2, dated 
September 1, 1994.

(h) New Requirement of This AD: Repetitive Inspection

    At the latest of the compliance times specified in paragraphs 
(h)(1), (h)(2), and (h)(3) of this AD: Do a detailed inspection for 
cracking of the four titanium angles between the belly fairing and 
the keel beam side panel, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1259, dated November 
6, 2012.
    (1) Before the accumulation of 30,000 total flight cycles or 
60,000 total flight hours, whichever occurs first after first flight 
of the airplane.
    (2) Within 30,000 flight cycles or 60,000 flight hours, 
whichever occurs first after modification of the airplane as 
required by paragraph (g) of this AD, or after installation of new 
titanium angles, provided that, prior to installation, a rototest 
for cracking on the open holes has been accomplished with no crack 
findings, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1259, dated November 6, 2012.
    (3) Within 3,000 flight cycles or 6,000 flight hours, whichever 
occurs first after the effective date of this AD.

(i) New Requirement of This AD: Post-Inspection Actions for No Crack 
Findings

    If, during any inspection required by paragraph (h) of this AD, 
there is no crack finding: Accomplish the actions specified in 
either paragraph (i)(1) or (i)(2) of this AD.
    (1) Repeat the inspection required by paragraph (h) of this AD 
at intervals not to exceed 5,000 flight cycles or 10,000 flight 
hours, whichever occurs first.
    (2) Before further flight after the inspection required by 
paragraph (h) of this AD, remove all inspected titanium angles, 
accomplish a rototest for cracking on the open holes and, provided 
no cracks are found, install new titanium angles, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1259, dated November 6, 2012.

(j) New Requirement of This AD: Post-Inspection Actions for Any Crack 
Findings

    If, during any inspection required by paragraph (h) of this AD, 
there is any crack finding: Before further flight, remove the 
affected titanium angle(s), accomplish a rototest for cracking on 
the open holes, and, provided no cracks are found, install new 
titanium angles, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-53-1259, dated November 6, 2012.

(k) New Requirement of This AD: Post-Installation Repetitive 
Inspections

    For airplanes on which new titanium angles were installed as 
specified in paragraph (i)(2) or (j) of this AD: Within 30,000 
flight cycles or 60,000 flight hours, whichever occurs first after 
the installation: Accomplish a detailed inspection for cracking of 
the four titanium angles between the belly fairing and the keel beam 
side panel, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1259, dated November 6, 2012. Repeat 
the inspection thereafter at intervals not to exceed 5,000 flight 
cycles or 10,000 flight hours, whichever occurs first.

(l) New Requirement of This AD: Post Inspection Actions for Any Crack 
Findings During Post-Installation Inspections

    If, during any inspection as required by paragraph (k) of this 
AD, there is any crack finding: Before further flight, remove the 
affected titanium angles, accomplish a rototest for cracking on the 
open holes, and, provided no cracks are found, install new titanium 
angles, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-53-1259, dated November 6, 2012.

(m) New Requirement of This AD: Corrective Action for Rototest Crack 
Finding

    If, during any rototest as required by paragraph (i), (j), or 
(l) of this AD, any crack is found: 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 its delegated agent, or by the Design 
Approval Holder (DAH) with EASA design organization approval, as 
applicable). For a repair method to be approved, the repair approval 
must specifically refer to this AD.

(n) New Provision of This AD: No Termination Action for Repetitive 
Inspections

    Repair or replacement of parts as specified in this AD does not 
terminate the repetitive inspections required by this AD.

(o) 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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer, use these actions if they 
are FAA approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or the Design Approval Holder with a State of 
Design Authority's design organization approval, as applicable). You 
are required to ensure the product is airworthy before it is 
returned to service.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2013-
0122, dated June 5, 2013, 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-2014-0058.
    (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

[[Page 10710]]

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: February 18, 2014.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-04140 Filed 2-25-14; 8:45 am]
BILLING CODE 4910-13-P