Document ID: FAA-2014-0011-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2014-02-10T05:00Z

[Federal Register Volume 79, Number 27 (Monday, February 10, 2014)]
[Proposed Rules]
[Pages 7592-7596]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-02711]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0011; Directorate Identifier 2013-NM-046-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) 98-13-23, 
which applies to certain Airbus 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). AD 98-13-23 
requires inspections to detect corrosion and cracking of the lower 
horizontal stabilizer cutout longeron, the corner fitting, the skin 
strap, and the outer skin; and repair, if necessary. Since we issued AD 
98-13-23, we have determined that the risk of cracking is higher than 
initially determined. This proposed AD would reduce the compliance 
times and repetitive intervals, and changes the inspection procedures. 
We are proposing this AD to prevent cracking of the lower horizontal 
stabilizer cutout longeron, the corner fitting, the skin strap, and the 
outer skin, which could result in reduced structural integrity of the 
horizontal-stabilizer cutout longeron.

DATES: We must receive comments on this proposed AD by March 27, 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

[[Page 7593]]

a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed 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. 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-
0011; or in person at the Docket Management Facility 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 
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: 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:

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-2014-0011; 
Directorate Identifier 2013-NM-046-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 June 15, 1998, we issued AD 98-13-23, Amendment 39-10614 (63 FR 
34576, June 25, 1998). That AD requires actions intended to address an 
unsafe condition on the products listed above.
    Since we issued AD 98-13-23, Amendment 39-10614 (63 FR 34576, June 
25, 1998), a fleet survey and updated fatigue and damage tolerance 
analyses showed that the risk of cracks for these airplanes is higher 
than initially determined. The European Aviation Safety Agency (EASA), 
which is the Technical Agent for the Member States of the European 
Community, has issued EASA Airworthiness Directive 2013-0048, dated 
March 4, 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 a full scale fatigue test, a crack was found at the lower 
corner of the assembly of the horizontal stabilizer cut-out, between 
Frame (FR)87 and FR89 and between Stringer (STGR)24 and STGR27, Left 
Hand (LH) and Right Hand (RH) sides.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the aeroplane.
    DGAC France issued AD * * * to require repetitive visual and 
High Frequency Eddy Current (HFEC) rotating probe inspections of the 
affected areas and subsequent corrective action, in case of cracks.
    Since that [DGAC France] AD was issued, a fleet survey and 
updated Fatigue and Damage Tolerance analyses have been performed to 
substantiate the second A300-600 Extended Service Goal (ESG2) 
exercise. The results of these analyses have shown that the risk of 
cracks for these aeroplanes is higher than initially determined and 
that, consequently, the thresholds and intervals must be reduced to 
allow timely detection of these cracks and accomplishment of an 
applicable corrective action.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD * * *, which is superseded, and 
requires the accomplishment of these actions within the new 
thresholds and intervals defined in Revision 03 of Airbus Service 
Bulletin (SB) A300-53-6042 [dated August 30, 2012].

The initial compliance times for airplanes with an average flight time 
greater than 1.5 hours, depending on the inspection area, are between 
before 18,000 total flight cycles and 38,100 total flight hours, 
whichever occurs first; and before 42,500 total flight cycles or 89,000 
total flight hours, whichever occurs first. The repetitive compliance 
times for airplanes with an average flight time above 1.5 hours, 
depending on the inspection area, are between intervals not to exceed 
3,900 flight cycles or 8,200 flight hours, whichever occurs first; and 
intervals not to exceed 6,000 flight cycles or 12,700 flight hours, 
whichever occurs first.
    The initial compliance times for airplanes with an average flight 
time of 1.5 hours or less, depending on the inspection area, are 
between before 19,900 total flight cycles and 29,800 total flight 
hours, whichever occurs first; and before 47,100 total flight cycles or 
70,500 total flight hours, whichever occurs first. The repetitive 
compliance times for airplanes with an average flight time of 1.5 hours 
or less, depending on inspection area, are between intervals not to 
exceed 4,300 flight cycles or 6,400 flight hours, whichever occurs 
first, and intervals not to exceed 6,600 flight cycles or 9,900 flight 
hours, whichever occurs first.
    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-2014-0011.

Explanation of Change to Applicability

    We have revised the applicability of this AD to identify model 
designations as published in the most recent type certificate data 
sheet for the affected models.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A300-53-6042, Revision 
03, dated August 30, 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.
    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.

[[Page 7594]]

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, certain new requirements of 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 the 
DAH with State of Design Authority design organization approval, as 
applicable'' in this proposed AD to refer to a DAH authorized to 
approve newly required repairs for this proposed AD.

Costs of Compliance

    We estimate that this proposed AD would affect about 5 products of 
U.S. registry. We estimate the following costs to comply with this 
proposed AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                             Parts                              Cost on U.S.
              Action                      Labor cost          cost      Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspections [retained actions from  268 work-hour x $85           $0  $22,780 per           $45,560 per
 AD 98-13-23, Amendment 39-10614     per hour = $22,780                inspection cycle.     inspection cycle (2
 (63 FR 34576, June 25, 1998].       per inspection cycle.                                   airplanes)
Inspections [new proposed action].  88 work-hour x $85             0  $7,480 per            $37,400 per
                                     per hour = $7,480                 inspection cycle.     inspection cycle
                                     per inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the proposed inspection. We 
have no way of determining the number of aircraft that might need these 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                  Action                                Labor cost                 Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair....................................  155 work-hours x $85 per hour =                 $0          $13,175
                                             $13,175.
----------------------------------------------------------------------------------------------------------------

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) 
98-13-23, Amendment 39-10614 (63 FR 34576, June 25, 1998), and adding 
the following new AD:

Airbus: Docket No. FAA-2014-0011; Directorate Identifier 2013-NM-
046-AD.

(a) Comments Due Date

    We must receive comments by March 27, 2014.

(b) Affected ADs

    This AD supersedes AD 98-13-23, Amendment 39-10614 (63 FR 34576, 
June 25, 1998).

(c) Applicability

    This AD applies to 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 Model A300 C4-605R Variant F 
airplanes; certificated in any

[[Page 7595]]

category; on which Airbus Modification 6146 has not been installed.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracking found at the lower 
corner of the horizontal stabilizer cutout longeron during a full 
scale fatigue test, and a determination that the risk of cracking is 
higher than initially determined. We are issuing this AD to prevent 
cracking of the lower horizontal stabilizer cutout longeron, the 
corner fitting, the skin strap, and the outer skin, which could 
result in reduced structural integrity of the horizontal-stabilizer 
cutout longeron.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Inspections and Corrective Actions

    This paragraph restates the requirements of paragraphs (a), (b), 
(c), (d), and (e) of AD 98-13-23, Amendment 39-10614 (63 FR 34576, 
June 25, 1998), with revised service information.
    (1) Prior to the accumulation of 18,000 total landings, or 
within 2,000 landings after July 30, 1998 (the effective date of AD 
98-13-23, Amendment 39-10614 (63 FR 34576, June 25, 1998)), 
whichever occurs later: Perform a visual and eddy current inspection 
to detect cracks and/or corrosion of Areas 1 and 2 of the lower 
horizontal stabilizer cutout longeron, in accordance with Airbus 
Service Bulletin A300-53-6042, Revision 1, dated February 20, 1995; 
or Airbus Mandatory Service Bulletin A300-53-6042, Revision 03, 
dated August 30, 2012. As of the effective date of this AD, use only 
Airbus Mandatory Service Bulletin A300-53-6042, Revision 03, dated 
August 30, 2012, to do the actions required by this paragraph.
    (2) At the later of the times specified in paragraphs (g)(2)(i) 
and (g)(2)(ii) of this AD: Perform a visual and an eddy current 
inspection to detect cracks and corrosion of Area 3 of the lower 
horizontal stabilizer cutout longeron, in accordance with Airbus 
Service Bulletin A300-53-6042, Revision 1, dated February 20, 1995; 
or Airbus Mandatory Service Bulletin A300-53-6042, Revision 03, 
dated August 30, 2012. As of the effective date of this AD, use only 
Airbus Mandatory Service Bulletin A300-53-6042, Revision 03, dated 
August 30, 2012, to do the actions required by this paragraph.
    (i) Prior to the accumulation of 24,000 total landings, but not 
before the accumulation of 18,000 total landings; or
    (ii) Prior to the accumulation of 2,000 landings after July 30, 
1998 (the effective date of AD 98-13-23, Amendment 39-10614 (63 FR 
34576, June 25, 1998)).
    (3) If no cracking is detected during any inspection required by 
paragraph (g)(1) or (g)(2) of this AD: Before further flight, cold 
work and ream the vacated fastener holes, in accordance with Airbus 
Service Bulletin A300-53-6042, Revision 1, dated February 20, 1995; 
or Airbus Mandatory Service Bulletin A300-53-6042, Revision 03, 
dated August 30, 2012; and perform the requirements of paragraph 
(g)(3)(i) or (g)(3)(ii) of this AD, as applicable. As of the 
effective date of this AD, use only Airbus Mandatory Service 
Bulletin A300-53-6042, Revision 03, dated August 30, 2012, to do the 
actions required by this paragraph.
    (i) For airplanes on which no cracking is found in Area 1 or 2: 
Repeat the inspections required by paragraph (g)(1) of this AD 
thereafter at intervals not to exceed 6,000 flight cycles.
    (ii) For airplanes on which no cracking is found in Area 3: 
Perform the various follow-on actions in accordance with Airbus 
Service Bulletin A300-53-6042, Revision 1, dated February 20, 1995; 
or Airbus Mandatory Service Bulletin A300-53-6042, Revision 03, 
dated August 30, 2012. (The follow-on actions include installing a 
new corner fitting, installing a new longeron, and performing a cold 
working procedure.) After accomplishment of these follow-on actions, 
no further action is required by this AD. After the effective date 
of this AD, use only Airbus Mandatory Service Bulletin A300-53-6042, 
Revision 03, dated August 30, 2012, to do the actions required by 
this paragraph.
    (4) If any cracking is detected during any inspection required 
by paragraph (g)(1) or (g)(2) of this AD, perform the requirements 
of paragraph (g)(4)(i) or (g)(4)(ii) of this AD, as applicable.
    (i) If any cracking is found in Area 1 or 3 that is within the 
limits specified in Airbus Service Bulletin A300-53-6042, Revision 
1, dated February 20, 1995; or Airbus Mandatory Service Bulletin 
A300-53-6042, Revision 03, dated August 30, 2012: Before further 
flight, repair in accordance with Airbus Service Bulletin A300-53-
6042, Revision 1, dated February 20, 1995; or Airbus Mandatory 
Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012. 
As of the effective date of this AD, use only Airbus Mandatory 
Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012, 
to do the actions required by this paragraph.
    (ii) If any cracking is found in Area 2, or if any cracking is 
found in any area and that cracking is beyond the limits described 
in Airbus Service Bulletin A300-53-6042, Revision 1, dated February 
20, 1995; or Airbus Mandatory Service Bulletin A300-53-6042, 
Revision 03, dated August 30, 2012: 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).
    (5) If any corrosion is detected during any inspection required 
by paragraph (g) of this AD, prior to further flight, repair the 
corrosion, in accordance with Airbus Service Bulletin A300-53-6042, 
Revision 1, dated February 20, 1995; or Airbus Mandatory Service 
Bulletin A300-53-6042, Revision 03, dated August 30, 2012. As of the 
effective date of this AD, use only Airbus Mandatory Service 
Bulletin A300-53-6042, Revision 03, dated August 30, 2012, to do the 
actions required by this paragraph.

(h) New Inspections

    At the applicable times specified in paragraph 1.E., 
``Compliance,'' of Airbus Mandatory Service Bulletin A300-53-6042, 
Revision 03, dated August 30, 2012, except as provided by paragraph 
(j)(1) and (j)(2) of this AD: Do the actions specified in paragraphs 
(h)(1), (h)(2), and (h)(3) of this AD, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-53-6042, Revision 03, dated August 30, 2012. Repeat the 
inspections, thereafter, at the applicable intervals specified in 
paragraph 1.E., ``Compliance,'' of Airbus Mandatory Service Bulletin 
A300-53-6042, Revision 03, dated August 30, 2012. Doing the initial 
inspections required by paragraph (h) of this AD and applicable 
corrective actions required by paragraph (i) of this AD terminates 
the requirements of paragraph (g) of this AD.
    (1) Do a general visual inspection for cracking and corrosion of 
the lower horizontal stabilizer cut-out longeron, the corner 
fitting, the skin strap, and the skin between frame (FR)87 and FR89 
and between stringers (STGR)24 and STGR27, left- and right-hand 
sides.
    (2) Do a high frequency eddy current (HFEC) inspection for 
cracking of the flanges of the lower corner fittings and the edges 
of the outer skin and the edges of the longeron, the skin strap, and 
the skin at the run-out of the corner fitting above the last eight 
fasteners.
    (3) Do a rotating probe inspection for cracking of the fastener 
holes. If no cracking is found during the rotating probe inspection, 
before further flight, do a cold expansion of the fastener holes, in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012.

(i) New Corrective Actions

    (1) If any corrosion is found during any inspection required by 
paragraph (h) of this AD, before further flight, repair, in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012.
    (2) If any cracking is found during any inspection required by 
paragraph (h) of this AD, before further flight, repair in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A300-53-6042, Revision 03, dated August 30, 2012, 
except where Airbus Mandatory Service Bulletin A300-53-6042, 
Revision 03, dated August 30, 2012, specifies to contact Airbus, 
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 the Design Approval Holder (DAH) with EASA 
design organization approval). For a repair method to be approved, 
the repair approval must specifically refer to this AD.

(j) Exception

    (1) Where Airbus Mandatory Service Bulletin A300-53-6042, 
Revision 03, dated August 30, 2012, specifies a grace period of 1950 
flight cycles or 4100 flight hours, this

[[Page 7596]]

AD specifies the grace period after the effective date of this AD.
    (2) Where Airbus Mandatory Service Bulletin A300-53-6042, 
Revision 03, dated August 30, 2012, specifies a compliance time 
``after receipt of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.

(k) Credit for Previous Actions

    This paragraph provides credit for the corresponding actions 
required by paragraph (g) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A300-53-6042, Revision 01, dated February 20, 1995; or 
Airbus Service Bulletin A300-53-6042, Revision 02, dated April 28, 
1998; which are not incorporated by reference in this AD.

(l) 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; telephone 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. AMOCs 
approved for AD 98-13-23, Amendment 39-10614 (63 FR 34576, June 25, 
1998), are approved as AMOCs for the corresponding requirements of 
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.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency (EASA) Airworthiness 
Directive 2013-0048, dated March 4, 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 it in Docket No. 
FAA-2014-0011.
    (2) 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. 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.

    Issued in Renton, Washington, on January 27, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-02711 Filed 2-7-14; 8:45 am]
BILLING CODE 4910-13-P