
[Federal Register Volume 78, Number 227 (Monday, November 25, 2013)]
[Rules and Regulations]
[Pages 70207-70209]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-27832]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0418; Directorate Identifier 2012-NM-200-AD; 
Amendment 39-17668; AD 2013-23-13]
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 A300 series airplanes; Model A300 B4-600, B4-600R, and F4-
600R series airplanes; and Model A300 C4-605R Variant F airplanes 
(collectively called Model A300-600 series airplanes). This AD was 
prompted by a report that cracking was found in area 2 of the frame 
base fittings between frame 41 and frame 46. This AD requires a check 
of maintenance records to determine if certain repairs were done in 
area 1 of the frame base fittings, and, for affected airplanes, a 
detailed inspection for cracking in area 2 of the frame base fittings 
between frame 41 and frame 46, and repair if necessary. We are issuing 
this AD to detect and correct cracking in area 2 of the frame base 
fittings between frame 41 and frame 46, which could adversely affect 
the structural integrity of the airplane.

DATES: This AD becomes effective December 30, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 30, 
2013.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0418 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: (425) 227-2125; 
fax: (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to the specified products. The 
NPRM was published in the Federal Register on May 14, 2013 (78 FR 
28159). The NPRM proposed to correct an unsafe condition for the 
specified products. The European Aviation Safety Agency (EASA), which 
is the Technical Agent for the Member States of the European Community, 
has issued EASA Airworthiness Directive 2012-0229, dated October 31, 
2012 (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 accomplishment of Airbus SB [service bulletin] A300-53-
6111, which addresses detailed visual inspections of the lower frame 
fittings between Frame (FR) 41 and FR 46, on one A300-600 aeroplane 
a crack was detected in the area 2 of the foot of frame FR 46 at 
junction radius level.
    This frame, that was previously repaired due to a crack finding 
in the area 1, was not due to be inspected before reaching the post-
repair inspection threshold, i.e., 45,400 FC [flight cycles], from 
repair embodiment.
    It has been determined that the current repairs proposed in 
Airbus SB A300-53-6111 and Airbus [SB] A300-53-0337 are of limited 
effect to prevent cracking in the area 2 of the lower frame 
fittings.
    Consequently, as a temporary action and until an improvement of 
the existing repairs is made available, this [EASA] AD requires a 
one-time detailed visual inspection [for cracking] of [the] frame 
base fittings that were repaired in accordance with Airbus SB A300-
53-0337, original issue or Rev. 1, or Airbus SB A300-53-6111 
original issue up to Rev. 4 * * *.

The unsafe condition is cracking in the frame base fittings, which 
could adversely affect the structural integrity of the airplane. The 
required actions include repairing any cracking found. You may obtain 
further information by examining the MCAI in the AD docket on the 
Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-
0418-0002.

Comments

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

Request To Correct Typographical Error in SUMMARY Section

    UPS noted there is a typographical error in the SUMMARY section of 
the NPRM (78 FR 28159, May 14, 2013). UPS stated that the third line 
includes the phrase ``frame brace fittings,'' but throughout the rest 
of the document the terminology used is ``frame base fittings.'' UPS 
suggested that for

[[Page 70208]]

consistency throughout the document ``brace'' be changed to ``base.''
    We agree that the word ``brace'' should be changed to ``base'' and 
have changed the SUMMARY section of this final rule accordingly. The 
error only appeared in the SUMMARY section so no additional changes 
were necessary.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes and the 
correction of the typographical error in the SUMMARY section of this 
final rule. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 28159, May 14, 2013) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 28159, May 14, 2013).

Costs of Compliance

    We estimate that this AD affects 124 airplanes of U.S. registry.
    We estimate it will take about 4 work-hours per product to comply 
with the basic requirements of this AD. The average labor rate is $85 
per work-hour. Based on these figures, we estimate the cost of this AD 
on U.S. operators to be $42,160, or $340 per product.
    In addition, we estimate that any necessary follow-on actions will 
take up to 350 work-hours and require parts costing up to $56,469 for a 
cost of $86,219 per product. 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/#!docketDetail;D=FAA-2013-0418; 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 
MCAI, 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:

2013-23-13 Airbus: Amendment 39-17668. Docket No. FAA-2013-0418; 
Directorate Identifier 2012-NM-200-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective December 30, 
2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes, on which any repair has been done as 
specified in Airbus Service Bulletin A300-53-0337, dated February 4, 
1999; or Airbus Service Bulletin A300-53-0337, Revision 01, dated 
March 17, 2003.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-
605R and F4-622R airplanes; and A300 C4-605R Variant F airplanes; on 
which any repair has been done as specified in any of the service 
information identified in paragraphs (c)(2)(i), (c)(2)(ii), 
(c)(2)(iii), (c)(2)(iv), (c)(2)(v), and (c)(2)(vi) of this AD.
    (i) Airbus Service Bulletin A300-53-6111, dated February 4, 
1999.
    (ii) Airbus Service Bulletin A300-53-6111, Revision 01, dated 
March 17, 2003.
    (iii) Airbus Service Bulletin A300-53-6111, Revision 02, dated 
September 13, 2004.
    (iv) Airbus Service Bulletin A300-53-6111, Revision 03, dated 
September 30, 2009.
    (v) Airbus Mandatory Service Bulletin A300-53-6111, Revision 04, 
dated August 25, 2011.
    (vi) Airbus Mandatory Service Bulletin A300-53-6111, Revision 
05, dated January 28, 2013.

(d) Subject

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

(e) Reason

    This AD was prompted by a report that cracking was found in area 
2 of the frame base fittings between frame 41 and frame 46. We are 
issuing this AD to detect and correct cracking in area 2 of the 
frame base fittings between frame 41 and frame 46, which could 
adversely 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) Maintenance Records Check and Frame Base Fitting Inspection

    Within 1,000 flight hours after the effective date of this AD: 
Check the airplane maintenance records to determine if repairs were 
done in area 1 of the frame base fittings as defined in Appendix 1 
of Airbus Alert Operators Transmission A53W001-12, dated July 4, 
2012.

[[Page 70209]]

(h) Frame Base Fitting Inspection

    If, during any records check required by paragraph (g) of this 
AD, it is determined that area 1 of the frame base fittings was 
repaired: Within 1,000 flight hours after the effective date of this 
AD, do a detailed inspection of the frame base fittings between 
frame 41 and frame 46 in area 2 as defined in Appendix 1 of Airbus 
Alert Operators Transmission A53W001-12, dated July 4, 2012.

(i) Corrective Action

    If any cracking is found during any detailed inspection required 
by paragraph (h) of this AD: Before further flight, repair the 
cracking 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).

(j) 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: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-227-2125; 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) 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.

(k) Related Information

    Refer to Mandatory Continuing Airworthiness Information European 
Aviation Safety Agency Airworthiness Directive 2012-0229, dated 
October 31, 2012, for related information, which can be found in the 
AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0418-0002.

(l) 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 Alert Operators Transmission A53W001-12, dated July 
4, 2012, including Appendix 1 and Appendix 2 and excluding Appendix 
3.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 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.
    (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 November 6, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-27832 Filed 11-22-13; 8:45 am]
BILLING CODE 4910-13-P


