
[Federal Register Volume 81, Number 207 (Wednesday, October 26, 2016)]
[Proposed Rules]
[Pages 74354-74358]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-25662]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9298; Directorate Identifier 2015-NM-161-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 adopt a new airworthiness directive (AD) for all 
Airbus Model A300 series airplanes. This AD was prompted by an 
evaluation by the design approval holder (DAH) that indicates a section 
of the wing and aft fuselage is subject to widespread fatigue damage 
(WFD). This proposed AD would require an inspection to determine if 
certain modifications have been done. For airplanes on which the 
specified modifications have not been done, this proposed AD would 
require accomplishing those modifications, including doing related 
investigative and corrective actions if necessary. We are proposing 
this AD to prevent reduced structural integrity of these airplanes due 
to the failure of certain structural components.

DATES: We must receive comments on this proposed AD by December 12, 
2016.

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 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this NRPM, 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: continued.airworthiness-wb.external@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.

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-2016-
9298; 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 
Operations 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: 

[[Page 74355]]

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-2016-9298; 
Directorate Identifier 2015-NM-161-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

    Structural fatigue damage is progressive. It begins as minute 
cracks, and those cracks grow under the action of repeated stresses. 
This can happen because of normal operational conditions and design 
attributes, or because of isolated situations or incidents such as 
material defects, poor fabrication quality, or corrosion pits, dings, 
or scratches. Fatigue damage can occur locally, in small areas or 
structural design details, or globally. Global fatigue damage is 
general degradation of large areas of structure with similar structural 
details and stress levels. Multiple-site damage is global damage that 
occurs in a large structural element such as a single rivet line of a 
lap splice joining two large skin panels. Global damage can also occur 
in multiple elements such as adjacent frames or stringers. Multiple-
site-damage and multiple-element-damage cracks are typically too small 
initially to be reliably detected with normal inspection methods. 
Without intervention, these cracks will grow, and eventually compromise 
the structural integrity of the airplane, in a condition known as WFD. 
As an airplane ages, WFD will likely occur, and will certainly occur if 
the airplane is operated long enough without any intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all transport 
category airplanes that will be certificated in the future. For 
existing and future airplanes subject to the WFD rule, the rule 
requires that DAHs establish a limit of validity (LOV) of the 
engineering data that support the structural maintenance program. 
Operators affected by the WFD rule may not fly an airplane beyond its 
LOV, unless an extended LOV is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive AD 2015-0173, dated August 24, 2015 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A300 
series airplanes. The MCAI states:

    A widespread fatigue damage (WFD) analysis conducted on A300 
aeroplanes identified areas which are susceptible to crack 
development.
    This condition, if not corrected, could affect the structural 
integrity of the aeroplane.
    To address this issue, Airbus developed a modification (mod) to 
reinforce the structure of the aeroplane.
    Airbus issued Service Bulletin (SB) A300-53-0271 to provide 
instructions for a cold expansion of the foot attachment holes of 
certain fuselage frames, and DGAC [Direction G[eacute]n[eacute]rale 
de l'Aviation Civile] France issued AD F-2004-001 to require this 
mod [which corresponds with certain requirements in FAA AD 2004-23-
20, Amendment 39-13875 (69 FR 68779, November 26, 2004)].
    Since that [DGAC] AD was issued, Airbus released twelve other 
mods with corresponding SBs, to complete the set of inspections and 
repairs in the frame of the A300 WFD campaign. EASA issued AD 2015-
0115 to require ten of these mods through section 3 of ALS 
[Airworthiness Limitations Section] Part 2, and decision is made to 
delete section 3 from ALS Part 2.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD F-2004-001, which is superseded, and 
requires implementation of the additional inspection, modification 
and/or repair actions, as applicable to aeroplane model.

    Required actions include an inspection to determine if certain 
modifications have been done. For airplanes on which the specified 
modifications have not been done, this proposed AD would require 
accomplishing those modifications, including doing related 
investigative and corrective actions if necessary. Depending on 
airplane configuration, the compliance times for modifying the airplane 
structure range between 13,300 flight cycles and 48,000 flight cycles 
since first flight of the airplane,. You may examine the MCAI in the AD 
docket on the Internet at http://www.regulations.gov by searching for 
and locating Docket No. FAA-2016-9298.

Related Service Information Under 1 CFR Part 51

    Airbus issued the following service information:
     Airbus Service Bulletin A300-53-0239, Revision 02, dated 
March 6, 2000. This service information describes procedures to modify 
the longitudinal junction. The modification includes the addition of 
external doublers and installation of interference fit attachments and 
related investigative and corrective actions. The related investigative 
actions are rotary probe inspections for cracking of the fastener 
holes. The corrective action is repair.
     Airbus Service Bulletin A300-53-0247, Revision 02, dated 
July 20, 1990. This service information describes procedures to modify 
the fuselage upper door frame structure, which consists of eddy current 
inspections of certain structure for cracks, and structural 
modification or repair.
     Airbus Mandatory Service Bulletin A300-53-0271, Revision 
05, dated June 21, 2013. This service information describes procedures 
to modify the fuselage frame (FR), which includes cold expansion of the 
fastener holes between FR 41 and FR 54, and related investigative and 
corrective actions. The related investigative actions including rotary 
probe inspections for cracking of the fastener holes. The corrective 
action is repair.
     Airbus Mandatory Service Bulletin A300-53-0366, dated 
April 7, 2005. This service information describes procedures to modify 
the fuselage

[[Page 74356]]

frame, which includes installing an additional external doubler on the 
fuselage lap joint at fuselage stringers (STGR) 22, left and right, 
between FR 26 and FR 40.
     Airbus Service Bulletin A300-53-0368, dated April 7, 2005. 
This service information describes procedures to modify the rear 
fuselage, which includes installing an additional external doubler on 
the fuselage lap joint at STGR 51, left and right, between FR 72 and FR 
80.
     Airbus Mandatory Service Bulletin A300-53-0369, Revision 
03, dated September 1, 2010. This service information describes 
procedures to modify the rear fuselage, which includes reinforcing the 
butt joint at FR 72 by installation of an additional external doubler 
at the butt joint of FR 72 at STGR 14, left and right.
     Airbus Mandatory Service Bulletin A300-53-0373, Revision 
03, dated September 1, 2010. This service information describes 
procedures to modify the rear fuselage, which includes reinforcing the 
butt joint at FR 65 by installation of an additional external doubler 
at the butt joint of FR 65 between STGR 13 left and right.
     Airbus Mandatory Service Bulletin A300-53-0374, Revision 
04, dated July 5, 2013. This service information describes procedures 
to modify the rear fuselage, which includes reinforcing the butt joints 
at FR 55 and FR 58 by installation of additional external doublers 
without cutout at certain butt joints.
     Airbus Mandatory Service Bulletin A300-53-0375, Revision 
01, dated June 24, 2013. This service information describes procedures 
to modify the forward fuselage, which includes reinforcing the fuselage 
circumferential butt joint at FR 26 by installation of an additional 
external doubler at the butt joint of FR 26 between STGR 13 left and 
STGR 13 right.
     Airbus Mandatory Service Bulletin A300-53-0393, dated 
September 27, 2013. This service information describes procedures to 
modify the fuselage frame which includes reinforcing the longitudinal 
butt joints with additional butt straps at certain fuselage frames and 
stringers.
     Airbus Mandatory Service Bulletin A300-57-0203, Revision 
04, dated February 18, 2015. This service information describes 
procedures to modify the outer wing, which includes removal of the wing 
stringer and run-out plate at STGR 19 on the bottom wing skin; 
replacement of the taper-lok bolts with interference fit parallel 
bolts; and related investigative and corrective actions. Related 
investigative actions include detailed visual and high frequency eddy 
current (HFEC) inspections for cracks and damage in the stringer run-
outs; and eddy current inspections for cracks initiating from certain 
fastener holes. Corrective actions include repair.
     Airbus Mandatory Service Bulletin A300-57-0258, dated 
September 30, 2014. This service information describes procedures to 
modify the wing structure, which includes a first oversize of the 
critical holes on certain wing stringers, and related investigative and 
corrective actions. Related investigated actions include detailed 
visual inspections for damage of the top wing skin external surface and 
the stringer joint; and roto-probe inspections for damage of the 
fastener holes. Corrective actions include repair.
     Airbus Mandatory Service Bulletin A300-57-0259, dated 
September 30, 2014. This service information describes procedures to 
modify the wing structure, which includes a first oversize of the 
critical holes on certain wing stringers, and related investigative and 
corrective actions. Related investigated actions include detailed 
visual inspections for damage of the top wing skin external surface and 
the stringer joint; and roto-probe inspections for damage of the 
fastener holes. Corrective actions include repair.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

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.

Costs of Compliance

    We estimate that this proposed AD affects 8 airplanes of U.S. 
registry.
    We also estimate that it will take about 3,291 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Required parts would cost 
about $142,845 per product. Based on these figures, we estimate the 
cost of this proposed AD on U.S. operators to be $3,380,640, or 
$422,580 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 15 work-hours and require parts costing $10,000, for a cost 
of $11,275 per product. We have no way of determining the number of 
aircraft that might need this action.

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,

[[Page 74357]]

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 adding the following new Airworthiness 
Directive (AD):

Airbus: Docket No. FAA-2016-9298; Directorate Identifier 2015-NM-
161-AD.

(a) Comments Due Date

    We must receive comments by December 12, 2016.

(b) Affected ADs

    This AD affects AD 2004-23-20, Amendment 39-13875 (69 FR 68779, 
November 26, 2004) (``AD 2004-23-20'').

(c) Applicability

    This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-
203, B4-2C, B4-103, and B4-203 airplanes, certificated in any 
category, all manufacturer serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder (DAH) that indicates a section of the wing and aft fuselage 
is subject to widespread fatigue damage (WFD). We are issuing this 
AD to prevent reduced structural integrity of these airplanes due to 
the failure of certain structural components.

(f) Compliance

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

(g) Verification of Embodied Modifications

    Within 4 months after the effective date of this AD, verify 
whether the Airbus modifications listed in table 1 to paragraphs 
(g), (h), and (i) of this AD, as applicable to airplane model, have 
been embodied on the airplane in accordance with the Accomplishment 
Instructions of the applicable Airbus service bulletin listed in 
table 1 to paragraphs (g), (h), and (i) of this AD. A review of the 
airplane maintenance records is acceptable to accomplish the 
verification required by this paragraph, provided those records can 
conclusively determine whether the modifications have been embodied.

 Table 1 to Paragraphs (g), (h), and (i) of This AD--Airbus Modification
                     and Applicable Service Bulletin
------------------------------------------------------------------------
                                      Airbus         Applicable airbus
              Set                  modification       service bulletin
------------------------------------------------------------------------
Set 1A........................  751..............  A300-53-0247,
                                                    Revision 02, dated
                                                    July 20, 1990.
                                7301.............  A300-53-0239,
                                                    Revision 02, dated
                                                    March 6, 2000.
                                10326............  A300-57-0203,
                                                    Revision 04, dated
                                                    February 18, 2015.
                                12735............  A300-53-0366, dated
                                                    April 7, 2005.
                                12736............  A300-53-0368, dated
                                                    April 7, 2005.
                                12737............  A300-53-0369,
                                                    Revision 03, dated
                                                    September 1, 2010.
                                12798............  A300-53-0375,
                                                    Revision 01, dated
                                                    June 24, 2013.
                                07757 and 12977..  A300-53-0271,
                                                    Revision 05, dated
                                                    June 21, 2013.
                                13611............  A300-57-0258, dated
                                                    September 30, 2014.
                                13692............  A300-53-0393, dated
                                                    September 27, 2013.
                                13716............  A300-57-0259, dated
                                                    September 30, 2014.
Set 1B........................  12794............  A300-53-0374,
                                                    Revision 04, dated
                                                    July 5, 2013.
                                12796............  A300-53-0373,
                                                    Revision 03, dated
                                                    September 1, 2010.
------------------------------------------------------------------------

(h) Corrective Actions for Modifications Which Have Not Been Embodied

    If, during the verification required by paragraph (g) of this 
AD, it is determined that any modification has not been embodied, do 
the applicable actions specified in paragraphs (h)(1), (h)(2), and 
(h)(3) of this AD.
    (1) If it is determined that any Airbus modification, specified 
in the applicable Airbus Service Bulletin, identified in ``Set 1A'' 
of table 1 to paragraphs (g), (h), and (i) of this AD is not 
embodied: Within the applicable compliance time specified in the 
applicable Airbus Service Bulletin identified in ``Set 1A'' of table 
1 to paragraphs (g), (h), and (i) of this AD, or within 4 months 
after the effective date of this AD, whichever occurs later, do the 
applicable actions specified in paragraphs (h)(1)(i) through 
(h)(1)(xi) of this AD, except as required by paragraph (i) of this 
AD. Do all applicable related investigative and corrective actions 
before further flight.
    (i) For airplanes on which Airbus Service Bulletin A300-53-0239, 
Revision 02, dated March 6, 2000, has not been embodied: Modify the 
longitudinal junction and do all applicable related investigative 
and corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-0239, Revision 02, 
dated March 6, 2000.
    (ii) For airplanes on which Airbus Service Bulletin A300-53-
0247, Revision 02, dated July 20, 1990, has not been embodied: 
Modify the fuselage upper door frame structure by doing eddy current 
inspections for cracks of the structure specified in Airbus Service 
Bulletin A300-53-0247, Revision 02, dated July 20, 1990, and a 
structural modification or repair, as applicable, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
0247, Revision 02, dated July 20, 1990.
    (iii) For airplanes on which Airbus Mandatory Service Bulletin 
A300-53-0271, Revision 05, dated June 21, 2013, has not been 
embodied: Modify the fuselage frame, and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-53-0271, Revision 05, dated June 21, 2013.
    (iv) For airplanes on which Airbus Mandatory Service Bulletin 
A300-53-0366, dated April 7, 2005, has not been embodied: Modify the 
fuselage frame, in accordance with the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A300-53-0366, dated April 7, 
2005.
    (v) For airplanes on which Airbus Service Bulletin A300-53-0368, 
dated April 7, 2005, has not been embodied: Modify the rear 
fuselage, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A300-53-0366, dated April 7, 2005.
    (vi) For airplanes on which Airbus Mandatory Service Bulletin 
A300-53-0369, Revision 03, dated September 1, 2010, has not been 
embodied: Modify the rear fuselage, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-53-0369, Revision 03, dated September 1, 2010.
    (vii) For airplanes on which Airbus Mandatory Service Bulletin 
A300-53-0375, Revision 01, dated June 24, 2013, has not been 
embodied: Modify the forward fuselage, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-53-0375, Revision 01, dated June 24, 2013.
    (viii) For airplanes on which Airbus Mandatory Service Bulletin 
A300-53-0393, dated September 27, 2013, has not been embodied: 
Modify the fuselage frame, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A300-53-0393, 
dated September 27, 2013.
    (ix) For airplanes on which Airbus Mandatory Service Bulletin 
A300-57-0203, Revision 04, dated February 18, 2015, has not

[[Page 74358]]

been embodied: Modify the outer wing, and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-57-0203, Revision 04, dated February 18, 2015.
    (x) For airplanes on which Airbus Mandatory Service Bulletin 
A300-57-0258, dated September 30, 2014, has not been embodied: 
Modify the wing structure and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-57-0258, dated September 30, 2014.
    (xi) For airplanes on which Airbus Mandatory Service Bulletin 
A300-57-0259, dated September 30, 2014, has not been embodied: 
Modify the wing structure, and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-57-0259, dated September 30, 2014.
    (2) If it is determined that Airbus Service Bulletin A300-53-
0374, Revision 04, dated July 5, 2013 (mod 12794) has not been 
embodied: Within the compliance time specified in paragraphs 
(h)(2)(i), (h)(2)(ii), (h)(2)(iii), and (h)(2)(iv) of this AD, as 
applicable, modify the rear fuselage, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-0374, 
Revision 04, dated July 5, 2013, except as required by paragraph (i) 
of this AD.
    (i) For Model A300 B2 and A300 B4-100 airplanes, fuselage frame 
(FR) 55: Within 31,300 flight cycles since first flight of the 
airplane, or within 4 months after the effective date of this AD, 
whichever occurs later.
    (ii) For Model A300 B2 and A300 B4-100 airplanes, FR 58: Within 
49,700 flight cycles since first flight of the airplane, or within 4 
months after the effective date of this AD, whichever occurs later.
    (iii) For Model A300 B4-200 airplanes, FR 55: Within 33,600 
flight cycles since first flight of the airplane, or within 4 months 
after the effective date of this AD, whichever occurs later.
    (iv) For Model A300 B4-200 airplanes, FR 58: Within 55,800 
flight cycles since first flight of the airplane, or within 4 months 
after the effective date of this AD, whichever occurs later.
    (3) If it is determined that Airbus Service Bulletin A300-53-
0373, Revision 03, dated September 1, 2010 (mod 12796) has not been 
embodied: Within the compliance time specified in paragraphs 
(h)(3)(i), (h)(3)(ii), and (h)(3)(iii) of this AD, as applicable, 
modify the rear fuselage, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-0373, Revision 03, 
dated September 1, 2010, except as required by paragraph (i) of this 
AD.
    (i) For Model A300 B2 airplanes: Within 42,700 flight cycles 
since first flight of the airplane, or within 4 months after the 
effective date of this AD, whichever occurs later.
    (ii) For Model A300 B4-100 airplanes: Within 41,700 flight 
cycles since first flight of the airplane, or within 4 months after 
the effective date of this AD, whichever occurs later.
    (iii) For Model A300 B4-200 airplanes: Within 47,900 flight 
cycles since first flight of the airplane, or within 4 months after 
the effective date of this AD, whichever occurs later.

(i) Service Information Exception

    Where any service information identified in table 1 to 
paragraphs (g), (h), and (i) of this AD specifies to contact the 
manufacturer for instructions or solutions, 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 Airbus's EASA Design Organization 
Approval (DOA).

(j) Terminating Action for Certain Requirements in AD 2004-23-20

    Accomplishing the modification required by paragraph (h)(1)(iii) 
of this AD terminates the modification required by paragraph (i) of 
AD 2004-23-20 for that airplane only.

(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: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-2125. 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) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2015-0173, dated August 24, 2015, for related 
information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2016-9298.
    (2) For service information identified in this final rule, 
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: continued.airworthiness-wb.external@airbus.com; Internet http://www.airbus.com. 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.

    Issued in Renton, Washington, on October 13, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-25662 Filed 10-25-16; 8:45 am]
 BILLING CODE 4910-13-P


