Airworthiness Directives; Airbus Airplanes

[Federal Register Volume 78, Number 164 (Friday, August 23, 2013)]
[Rules and Regulations]
[Pages 52414-52416]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-19459]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1076; Directorate Identifier 2011-NM-274-AD; 
Amendment 39-17556; AD 2013-16-18]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A320-214, -232 and -233 airplanes; and Model A321-211, -
213, and -231 airplanes. This AD was prompted by a report of a missing 
fastener between certain stringers of the fuselage frame that connects 
the frame to a tee. This AD requires an inspection for a missing 
fastener, and a rototest inspection and a modification or repair of the 
fuselage frame at the affected area if necessary. We are issuing this 
AD to detect and correct cracking in the fuselage that could result in 
reduced structural integrity of the airplane.

DATES: This AD becomes effective September 27, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 
27, 2013.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.

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 to include an AD that would apply to the specified products. 
The NPRM was published in the Federal Register on October 16, 2012 (77 
FR 63270). The NPRM proposed to correct an unsafe condition for the 
specified products. The European Aviation Safety Agency (EASA), which 
is the aviation authority for the Member States of the European 
Community, has issued EASA Airworthiness Directive 2011-0229, dated 
December 6, 2011 (referred to after this as ``the MCAI''), to correct 
an unsafe condition for the specified products. The MCAI states:

    During a quality check in production of an A320 family 
aeroplane, it was discovered that a fastener was missing at [frame] 
FR 24 between stringer (STRG) 25 and STRG 26 on the right-hand (RH) 
side. The purpose of the missing fastener, a 4 [millimeter] mm 
diameter aluminum rivet, Part Number (P/N) ASNA2050DXJ040, is to 
connect the FR 24 to the FR 24 Tee. The hole where the fastener was 
missing was not drilled.
    Further investigations revealed that the drilling was missing on 
the milling grid used for frame assembly of a limited group of 
aeroplanes.
    This condition, if not corrected, could impair the structural 
integrity of the affected aeroplanes.
    For the reasons described above, this [EASA] AD requires a 
special detailed inspection (SDI) [rototest inspection for cracking] 
of the affected area, and the accomplishment of the associated 
corrective actions [modification and/or repair].

You may obtain further information by examining the MCAI in the AD 
docket.

[[Page 52415]]

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.

Request To Include Latest Revision of Service Information

    Airbus requested that we revise the NPRM (77 FR 63270, October 16, 
2012) to reflect the latest revision of the service information to add 
an inspection for a missing fastener that is included in that revised 
service information. Airbus stated that the rototest inspection is 
required only when it is confirmed that the fastener is missing.
    We agree with the commenter's request. Airbus has issued Airbus 
Mandatory Service Bulletin A320-53-1247, Revision 01, dated October 15, 
2012. That service bulletin was revised to include procedures for a 
general visual inspection for a missing fastener. For airplanes on 
which no fastener is missing, the rototest inspection would no longer 
be necessary. We have changed paragraph (g) of this final rule to 
provide instructions for accomplishing the general visual inspection, 
which if accomplished and no fastener is missing, would eliminate the 
need for the rototest inspection. We have included the repair and 
modification that were part of paragraph (g) of the NPRM (77 FR 63270, 
October 16, 2012) as new paragraph (h) of this final rule and changed 
subsequent identifiers accordingly.

Conclusion

    We reviewed the available data, including the comment received, and 
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 changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (77 FR 63270, October 16, 2012) for correcting the unsafe 
condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 63270, October 16, 2012).

Costs of Compliance

    We estimate that this AD will affect 111 products of U.S. registry. 
We also estimate that it will take about 6 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts will cost about $85 per product. 
Where the service information lists required parts costs that are 
covered under warranty, we have assumed that there will be no charge 
for these parts. As we do not control warranty coverage for affected 
parties, some parties may incur costs higher than estimated here. Based 
on these figures, we estimate the cost of this AD to the U.S. operators 
to be $66,045, or $595 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. We 
have no way of determining the number of products that may 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 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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 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 AD:

2013-16-18 Airbus: Amendment 39-17556. Docket No. FAA-2012-1076; 
Directorate Identifier 2011-NM-274-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective September 
27, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A320-214, -232, and -233 
airplanes; and Model A321-211, -213, and -231 airplanes; 
certificated in any category; manufacturer serial numbers 4338, 
4371, 4374, 4375, 4377, 4381 through 4384 inclusive, 4386, 4387, 
4388, 4390 through 4402 inclusive, 4404 through 4409 inclusive, 4411 
through 4417 inclusive, 4419, 4420, 4421, 4423, 4424, 4426, 4429 
through 4436 inclusive, 4438 through 4443 inclusive, 4445 through 
4450 inclusive, 4453, 4454, 4456 through 4469 inclusive, 4471, 4472, 
4474 through 4481 inclusive, 4483 through 4498 inclusive, 4500, 
4504, 4505, 4506, and 4509.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of a missing fastener between 
certain stringers of the fuselage frame that connects the frame to a 
tee. We are issuing this AD to detect and correct cracking in the 
fuselage that could result in reduced structural integrity of the 
airplane.

[[Page 52416]]

(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) Inspections

    Before the accumulation of 24,000 total flight cycles since 
first flight of the airplane, or within 30 days after the effective 
date of this AD, whichever occurs later, do the actions specified in 
paragraph (g)(1) or (g)(2) of this AD.
    (1) Do a general visual inspection for a missing fastener 
between the two fasteners at fuselage frame (FR) 24 between stringer 
25 and stringer 26 right-hand side, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A320-53-1247, Revision 01, dated October 15, 2012.
    (i) If the fastener is not missing, no further action is 
required by paragraph (g) of this AD.
    (ii) If the fastener is missing, before further flight, do the 
actions required by paragraph (g)(2) of this AD.
    (2) Do a rototest inspection for cracking of the two adjacent 
fastener holes at
    fuselage FR 24 between stringer 25 and stringer 26 right-hand 
side, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-53-1247, dated July 15, 2011; or Airbus 
Mandatory Service Bulletin A320-53-1247, Revision 01, dated October 
15, 2012.

(h) Repair

    (1) If, during the rototest inspection specified by paragraph 
(g)(2) 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).
    (2) If, during the rototest inspection specified by paragraph 
(g)(2) of this AD, no crack is found, before the accumulation of 
24,000 total flight cycles since first flight of the airplane, or 
within 30 days after the effective date of this AD, whichever occurs 
later: Modify fuselage FR 24 between stringer 25 and stringer 26 
right-hand side, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-53-1247, dated July 15, 2011; or 
Airbus Mandatory Service Bulletin A320-53-1247, Revision 01, dated 
October 15, 2012.

(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, 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 or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(j) Related Information

    Refer to mandatory continuing airworthiness information (MCAI) 
EASA Airworthiness Directive 2011-0229, dated December 6, 2011, for 
related information. The MCAI may be viewed on the Internet at 
http://ad.easa.europa.eu/ad/2011-0229. EASA ADs are at http://ad.easa.europa.eu/.

(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 the AD specifies otherwise.
    (i) Airbus Mandatory Service Bulletin A320-53-1247, Revision 01, 
dated October 15, 2012.
    (ii) Airbus Service Bulletin A320-53-1247, dated July 15, 2011.
    (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 [email protected]; Internet http://www.airbus.com.
    (4) You may review copies of the 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 2, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-19459 Filed 8-22-13; 8:45 am]
BILLING CODE 4910-13-P

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