AD 2013-16-26

[Federal Register Volume 78, Number 169 (Friday, August 30, 2013)]
[Rules and Regulations]
[Pages 53640-53642]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2013-19923]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0424; Directorate Identifier 2013-NM-014-AD; 
Amendment 39-17564; AD 2013-16-26]
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 all 
Airbus Model A330-200 Freighter series airplanes; Model A330-200 and -
300 series airplanes, and Model A340-200 and -300 series airplanes. 
This AD was prompted by reports of cracked adjacent frame forks of a 
forward cargo door. This AD requires repetitive detailed inspections 
for cracks and sheared, loose, or missing rivets of the forward cargo 
door and, for certain airplanes, of the aft cargo door, and repair if 
necessary. We are issuing this AD to detect and correct cracked or 
ruptured cargo door frames, which could result in reduced structural 
integrity of the forward or aft cargo door.

DATES: This AD becomes effective October 4, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 4, 
2013.

ADDRESSES: You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-1138; 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 May 20, 2013 (78 FR 
29261). 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 2012-0274, dated December 21, 
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:

    One A330 operator recently reported a case where two adjacent 
frame (FR) forks of a forward cargo door were found cracked. FR20B 
was found cracked through, FR21 was found cracked half through. At 
the time of the findings, the affected aeroplane had accumulated 
around 21 000 flight cycles (FC) and it had already been inspected 
in accordance with EASA AD 2011-0007R1 [(<a href="http://ad.easa.europa.eu/blob/easa_ad_2011_0007_R1.pdf/AD_2011-0007R1_1">http://ad.easa.europa.eu/blob/easa_ad_2011_0007_R1.pdf/AD_2011-0007R1_1</a>)] [which 
corresponds to FAA AD 2012-12-12, Amendment 39-17092 (77 FR 37797, 
June 25, 2012)] and ALI [airworthiness limitation instructions] Task 
523106-01-1. However, during those inspections, the forward cargo 
door handle access panel is not required to be removed, which 
explains why the cracks at these two internal frame locations were 
not detected.
    After further analysis, it was determined that, in case of 
cracked or ruptured (forward or aft) cargo door frame, the loads 
will be transferred to the remaining structural elements. However, 
the second load path is able to sustain the loads for a limited 
number of flight cycles only.
    This condition, if not detected and corrected, could lead to 
rupture of two vertical frames, resulting in reduced structural 
integrity of the forward or aft cargo door.
    To address this condition, Airbus issued four separate Alert 
Operators Transmissions (AOT), giving instructions for repetitive 
inspections of the affected areas.
    For the reasons described above, this [EASA] AD requires 
repetitive detailed visual inspections of aft cargo door at FR60 and 
FR60A [for certain airplanes] and forward cargo door at FR21 and 
FR20B [for all airplanes], where the cargo door handle access panels 
are located, as follow:

--Outer skin rivets for sheared, loose or missing rivets at frame 
fork ends,
--whole inner forks for cracks and for sheared, loose or missing 
rivets at frame web and flange after removal of handle access 
panels, and

the accomplishment of the applicable corrective actions [which 
include repair, in accordance with a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA.]
    Note: Accomplishment of the above inspections does not cancel 
accomplishment of the inspections as required by EASA [AD] 2011-
0007R1, nor accomplishment of those in accordance with ALI Task 
523106-01-1.

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

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (78 FR 29261, May 20, 
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. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (78 FR 29261, May 20, 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 29261, May 20, 2013).

Costs of Compliance

    We estimate that this AD affects 66 airplanes of U.S. registry. We 
also estimate that it takes 1 work-hour 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 on U.S. operators to 
be $5,610, or $85 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.

[[Page 53641]]

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">http://www.regulations.gov</a>; 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:

2013-16-26 Airbus: Amendment 39-17564. Docket No. FAA-2013-0424; 
Directorate Identifier 2013-NM-014-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective October 4, 
2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes; and Model A340-211, -212, -213, -311, -312, and 
-313 airplanes; certificated in any category; all manufacturer 
serial numbers (MSNs).

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by reports of cracked adjacent frame forks 
of a forward cargo door. We are issuing this AD to detect and 
correct cracked or ruptured cargo door frames, which could result in 
reduced structural integrity of the forward or aft cargo door.

(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 for Certain Airplanes

    For Model A330-200, -200 Freighter, and -300 airplanes up to MSN 
0162 inclusive, except those on which Airbus Service Bulletin A330-
52-3044 has been embodied in service; and for Model A340-200 and -
300 airplanes up to MSN 0164 inclusive, except those on which Airbus 
Service Bulletin A340-52-4054 has been embodied in service: Before 
the accumulation of 15,800 total flight cycles since the airplane's 
first flight or within 100 flight cycles after the effective date of 
this AD, whichever occurs later, do a detailed inspection of the 
outer skin rivets at the frame fork end of frame (FR)60 and FR60A of 
the aft cargo door for sheared, loose, or missing rivets; and do a 
detailed inspection of the whole FR60 and FR60A forks for cracking 
and for sheared, loose, or missing rivets at the frame web and 
flanges; in accordance with Airbus Alert Operator Transmission (AOT) 
A330-A52L001-12, dated December 3, 2012; or Airbus AOT A340-A52L002-
12, dated December 3, 2012; as applicable. Repeat the inspections 
thereafter at intervals not to exceed 400 flight cycles.

(h) Inspections for All Airplanes

    Within the applicable compliance time specified in paragraph 
(h)(1) or (h)(2) of this AD, do a detailed inspection of outer skin 
rivets at the frame fork end of FR21 and FR20B of the forward cargo 
door for sheared, loose, or missing rivets; and do a detailed 
inspection of the whole FR21 and FR20B forks for cracks and for 
sheared, loose, or missing rivets at the frame web and flanges; in 
accordance with Airbus AOT A330-A52L003-12, dated December 3, 2012; 
or Airbus AOT A340-A52L004-12, dated December 3, 2012; as 
applicable. Repeat this inspection thereafter at intervals not to 
exceed 800 flight cycles.
    (1) For airplanes having less than 18,400 total flight cycles 
since the airplane's first flight as of the effective date of this 
AD: Before the accumulation of 10,600 total flight cycles since the 
airplane's first flight, or within 100 flight cycles after the 
effective date of this AD, whichever occurs later.
    (2) For airplanes having 18,400 total flight cycles or more 
since the airplane's first flight as of the effective date of this 
AD: Within 50 flight cycles after the effective date of this AD.

(i) Repair

    If any cracking, or sheared, loose, or missing rivet is found 
during any inspection required by this AD, before further flight, 
repair using a method approved by either the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA) (or its delegated agent).

(j) Non-Terminating Action

    Doing the repair required by paragraph (i) of this AD is not 
terminating action for the repetitive inspections required by 
paragraphs (g) and (h) of this AD for that cargo door, unless the 
repair instruction specifically states it is terminating action.

(k) 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: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport

[[Page 53642]]

Airplane Directorate, FAA 1601 Lind Avenue SW., Renton, Washington 
98057-3356; telephone (425) 227-1138; fax (425) 227-1149. 
Information may be emailed to: <a href="/cdn-cgi/l/email-protection#4e77630f0003637f7f78630f03010d631c0b1f1b0b1d1a1d0e282f2f60292138"><span class="__cf_email__" data-cfemail="96afbbd7d8dbbba7a7a0bbd7dbd9d5bbc4d3c7c3d3c5c2c5d6f0f7f7b8f1f9e0">[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.

(l) Related Information

    Refer to Mandatory Continuing Airworthiness Information EASA 
Airworthiness Directive 2012-0274, dated December 21, 2012, for 
related information, which can be found in the AD docket on the 
Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a>.

(m) 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 Operator Transmission A330-A52L001-12, dated 
December 3, 2012. The first page of this document contains the 
document number and date; no other pages contain this information.
    (ii) Airbus Alert Operator Transmission A330-A52L003-12, dated 
December 3, 2012. The first page of this document contains the 
document number and date; no other pages contain this information.
    (iii) Airbus Alert Operator Transmission A340-A52L002-12, dated 
December 3, 2012. The first page of this document contains the 
document number and date; no other pages contain this information.
    (iv) Airbus Alert Operator Transmission A340-A52L004-12, dated 
December 3, 2012. The first page of this document contains the 
document number and date; no other pages contain this information.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email <a href="/cdn-cgi/l/email-protection#65040c17120a17110d0c0b0016164b24565655482456515525040c170710164b060a08"><span class="__cf_email__" data-cfemail="13727a61647c61677b7a7d7660603d522020233e5220272353727a617166603d707c7e">[email&#160;protected]</span></a>; 
Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (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: <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 August 9, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-19923 Filed 8-29-13; 8:45 am]
BILLING CODE 4910-13-P