[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: [email protected]; 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
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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.
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(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: [email protected]. 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: [email protected]; 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