AD 2013-20-10

[Federal Register Volume 78, Number 208 (Monday, October 28, 2013)]
[Rules and Regulations]
[Pages 64159-64162]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2013-25295]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0539; Directorate Identifier 2012-NM-145-AD; 
Amendment 39-17616; AD 2013-20-10]
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 superseding airworthiness directive (AD) 2000-12-11, 
for certain Model A300 B4-600 and Model A300 B4-600R series airplanes. 
AD 2000-12-11 required repetitive inspections to detect cracks in the 
bolt holes inboard and outboard of rib 9 on the bottom booms of the 
front and rear wing spars, and repair if necessary. This new AD reduces 
the initial inspection compliance time and repetitive inspection 
interval. This AD was prompted by a fleet survey and an updated fatigue 
and damage tolerance analysis indicating a high risk for fatigue 
cracking on the front and rear spar bottom booms. We are issuing this 
AD to detect and correct fatigue cracks in the bolt holes of the wing 
spars, which could result in reduced structural integrity of a wing 
spar.

DATES: This AD becomes effective December 2, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 2, 
2013.

ADDRESSES: You may examine the AD docket on the Internet at <a href="http://www.regulations.gov/#!docketDetail">http://www.regulations.gov/#!docketDetail</a>;D=FAA-2013-0539; 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 service information identified in this AD, contact Airbus SAS--
EAW (Airworthiness Office), 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#c6a7a5a5a9b3a8b2e8a7afb4b1a9b4b2aeeba3a7b586a7afb4a4b3b5e8a5a9ab"><span class="__cf_email__" data-cfemail="a9c8cacac6dcc7dd87c8c0dbdec6dbddc184ccc8dae9c8c0dbcbdcda87cac6c4">[email&#160;protected]</span></a>; Internet <a href="http://www.airbus.com">http://www.airbus.com</a>. 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.

FOR FURTHER INFORMATION CONTACT: 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.

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 published in the Federal Register on July 3, 2013 (78 FR 
40069), and proposed to supersede AD 2000-12-11, Amendment 39-11789 (65 
FR 37853, June 19, 2000). 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 2012-0138, dated July 26, 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:

    Full fatigue tests carried out by the manufacturer revealed 
crack initiation from the bolts holes at inboard and outboard of rib 
9, on the front and rear spar bottom booms. Similar cracks at the 
same area were reported by A300-600 aeroplane operators.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To address this unsafe condition, [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] DGAC France issued AD 
94-208-169(B)R2 (<a href="http://ad.easa.europa.eu/blob/19942082tb_superseded.pdf/AD_F-1994-208-169R2_2">http://ad.easa.europa.eu/blob/19942082tb_superseded.pdf/AD_F-1994-208-169R2_2</a>) [which corresponds to FAA AD 
95-07-05, Amendment 39-9187 (60 FR 17990, April 10, 1995)] to 
require an ultrasonic inspection of holes inboard and outboard of 
rib 9 on the front and rear spar bottom booms on Left Hand and Right 
Hand wings.
    Since that [DGAC] AD was issued, a fleet survey and updated 
Fatigue and Damage

[[Page 64160]]

Tolerance analysis have been performed in order to substantiate the 
second A300-600 Extended Service Goal (ESG2) exercise. The results 
of these analyses have shown that the risk for these aeroplanes is 
higher than initially determined and that, consequently, the 
inspection threshold and interval must be reduced to allow timely 
detection of cracks and the accomplishment of an applicable 
corrective action [and related investigative action].
    For the reasons explained above, this new [EASA] AD retains the 
requirements of DGAC France AD 94-208-169(B)R2, which is superseded, 
and requires the accomplishment instructions within the new 
thresholds and intervals specified in Revision 04 of Airbus 
Mandatory Service Bulletin (SB) A300-57-6037 [dated February 24, 
2011].

The related investigative action includes doing inspections for 
cracking. The corrective actions include oversizing holes and 
installing new fasteners, and for certain conditions, contacting the 
FAA or EASA (or its delegated agent) for instructions. You may examine 
the MCAI in the AD docket on the Internet at <a href="http://www.regulations.gov/#!documentDetail">http://www.regulations.gov/#!documentDetail</a>;D=FAA-2013-0539-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (78 FR 40069, July 3, 
2013) or on the determination of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed--except for 
minor editorial changes and re-formatting of the estimates cost data. 
The estimated cost data has not been changed. We have determined that 
these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (78 FR 40069, July 3, 2013) for correcting the unsafe condition; 
and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 40069, July 3, 2013).

Costs of Compliance

    We estimate that this AD affects 29 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                    Labor cost         Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection [new action].........  18 work-hours x $85              $0   $1,530 [per          $44,370 [per
                                   per hour = $1,530                     inspection cycle].   inspection cycle].
                                   [per inspection
                                   cycle].
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition work-hours specified in this AD. 
The on-condition parts cost estimate is $2,874.
    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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 <a href="http://www.regulations.gov/#!docketDetail">http://www.regulations.gov/#!docketDetail</a>;D=FAA-2013-0539; 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 removing airworthiness directive (AD) 
2000-12-11, Amendment 39-11789 (65 FR 37853, June 19, 2000), and adding 
the following new AD:

2013-20-10 Airbus: Amendment 39-17616. Docket No. FAA-2013-0539; 
Directorate Identifier 2012-NM-145-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective December 2, 
2013.

(b) Affected ADs

    This AD supersedes AD 2000-12-11, Amendment 39-11789 (65 FR 
37853, June 19, 2000).

[[Page 64161]]

(c) Applicability

    This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, B4-
622, B4-605R, and B4-622R airplanes; certificated in any category; 
all manufacturer serial numbers, except airplanes on which Airbus 
Modification 10161 has been incorporated in production.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by a fleet survey and an updated fatigue 
and damage tolerance analysis indicating a high risk for fatigue 
cracking on the front and rear spar bottom booms. We are issuing 
this AD to detect and correct fatigue cracks in the bolt holes of 
the wing spars, which could result in reduced structural integrity 
of a wing spar.

(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) Repetitive Inspections

    At the applicable time specified in paragraph (g)(1) or (g)(2) 
of this AD: Perform an ultrasonic inspection to detect fatigue 
cracking of the bolt holes inboard and outboard of rib 9 on the 
bottom booms of the front and rear wing spars, in accordance with 
the Accomplishment Instruction of Airbus Mandatory Service Bulletin 
A300-57-6037, Revision 04, dated February 24, 2011, except as 
specified in paragraph (k) of this AD. Repeat the inspection 
thereafter at intervals not to exceed the applicable time specified 
in paragraph (h) of this AD.
    (1) For normal range airplanes, at the later of the times in 
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
    (i) Within 14,100 flight cycles or 30,400 flight hours since 
airplane first flight or within 14,100 flight cycles or 30,400 
flight hours since airplane modification done as specified in the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6039 
(which is not incorporated by reference in this AD), whichever 
occurs first.
    (ii) Within 1,600 flight cycles or 3,400 flight hours, whichever 
occurs first after the effective date of this AD.
    (2) For short range airplanes, at the later of the times in 
paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
    (i) Within 15,200 flight cycles or 22,800 flight hours since 
airplane first flight, or since airplane modification done as 
specified in the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-6039 (which is not incorporated by reference in 
this AD), whichever occurs first.
    (ii) Within 1,700 flight cycles or 2,500 flight hours, whichever 
occurs first after the effective date of this AD.

(h) Repetitive Inspection Compliance Times

    At the applicable time specified in paragraph (h)(1) or (h)(2) 
of this AD, repeat the inspection required by paragraph (g) of this 
AD.
    (1) For normal range airplanes: Repeat the inspection thereafter 
at intervals not to exceed 3,900 flight cycles or 8,400 flight 
hours, whichever occurs first.
    (2) For short range airplanes: Repeat the inspection thereafter 
at intervals not to exceed 4,200 flight cycles or 6,300 flight 
hours, whichever occurs first.

(i) Corrective Action for Cracking

    If any crack is found during any inspection required by 
paragraph (g) of this AD: Before further flight, repair the cracking 
including applicable related investigative and corrective actions, 
in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-57-6037, Revision 04, dated February 
24, 2011, except as specified in paragraph (k) of this AD. Do 
related investigative and corrective actions before further flight. 
Thereafter, repeat the inspection required by paragraph (g) of this 
AD at intervals not to exceed the applicable time specified in 
paragraph (h) of this AD. Corrective actions required by this 
paragraph do not constitute terminating action for the repetitive 
inspections required by paragraph (h) of this AD.

(j) Definition of Short Range and Long Range Airplanes

    For purposes of this AD, short range airplanes are those with an 
average flight time lower than 1.5 flight hours, and normal range 
airplanes are those with an average flight time equal to or higher 
than 1.5 flight hours.

(k) Exception to Service Information

    Where the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A300-57-6037, Revision 04, dated February 24, 2011, 
specify contacting Airbus for an approved repair: Before further 
flight, contact either the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, or the European Aviation Safety 
Agency (EASA) (or its delegated agent), for instructions and do 
those instructions.

(l) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using any of the service 
bulletins specified in paragraphs (l)(1) through (l)(4) of this AD.
    (1) Airbus Mandatory Service Bulletin A300-57-6037, dated August 
1, 1994, which was incorporated by reference in AD 2000-12-11, 
Amendment 39-11789 (65 FR 37853, June 19, 2000).
    (2) Airbus Mandatory Service Bulletin A300-57-6037, Revision 01, 
dated August 31, 1995, which was incorporated by reference in AD 
2000-12-11, Amendment 39-11789 (65 FR 37853, June 19, 2000).
    (3) Airbus Mandatory Service Bulletin A300-57-6037, Revision 02, 
dated January 9, 2001, which is not incorporated by reference in 
this AD.
    (4) Airbus Mandatory Service Bulletin A300-57-6037, Revision 03, 
dated January 11, 2002, which is not incorporated by reference in 
this AD.

(m) 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: <a href="/cdn-cgi/l/email-protection#675e4a26292a4a5656514a262a28244a35223632223433342701060649000811"><span class="__cf_email__" data-cfemail="6f56422e2122425e5e59422e22202c423d2a3e3a2a3c3b3c2f090e0e41080019">[email&#160;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) 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.
    (3) AMOCs Approved Previously: AMOCs approved previously in 
accordance with AD 2000-12-11, Amendment 39-11789 (65 FR 37853, June 
19, 2000), are approved as AMOCs for the corresponding provisions of 
this AD.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information EASA 
Airworthiness Directive 2012-0138, dated July 26, 2012, for related 
information. You may examine the MCAI in the AD docket on the 
Internet at <a href="http://www.regulations.gov/#!documentDetail">http://www.regulations.gov/#!documentDetail</a>;D=FAA-2013-
0539-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference may be obtained at the addresses specified 
in paragraphs (o)(4) and (o)(5) of this AD.

(o) 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 this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
December 2, 2013.
    (i) Airbus Mandatory Service Bulletin A300-57-6037, Revision 04, 
dated February 24, 2011.
    (ii) Reserved.
    (4) For service information identified in this AD, contact 
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61

[[Page 64162]]

93 44 51; email <a href="/cdn-cgi/l/email-protection#d5b4b6b6baa0bba1fbb4bca7a2baa7a1bdf8b0b4a695b4bca7b7a0a6fbb6bab8"><span class="__cf_email__" data-cfemail="38595b5b574d564c1659514a4f574a4c50155d594b7859514a5a4d4b165b5755">[email&#160;protected]</span></a>; Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (5) 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.
    (6) 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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.


    Issued in Renton, Washington, on September 18, 2013.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-25295 Filed 10-25-13; 8:45 am]
BILLING CODE 4910-13-P