81 FR 19509 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 65 (April 5, 2016)

Page Range		19509-19511
FR Document		2016-07575
We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A300 series airplanes; and 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). This proposed AD was prompted by the determination that certain existing inspection thresholds and intervals must be reduced. This proposed AD would require repetitive detailed inspections for corrosion, and related investigative and corrective actions if necessary. We are proposing this AD to detect and correct corrosion and cracking on the lower wing root joint, which could reduce the structural integrity of the airframe.
Federal Register, Volume 81 Issue 65 (Tuesday, April 5, 2016)
[Federal Register Volume 81, Number 65 (Tuesday, April 5, 2016)]
[Proposed Rules]
[Pages 19509-19511]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-07575]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5040; Directorate Identifier 2013-NM-192-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 
certain Airbus Model A300 series airplanes; and 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). This 
proposed AD was prompted by the determination that certain existing 
inspection thresholds and intervals must be reduced. This proposed AD 
would require repetitive detailed inspections for corrosion, and 
related investigative and corrective actions if necessary. We are 
proposing this AD to detect and correct corrosion and cracking on the 
lower wing root joint, which could reduce the structural integrity of 
the airframe.

DATES: We must receive comments on this proposed AD by May 20, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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. 
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-2016-
5040; 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: 

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-2016-5040; 
Directorate Identifier 2013-NM-192-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0230, dated September 24, 2013 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300 and A300-600 series airplanes. The MCAI states:

    Several cases of corrosion on the lower wing root joint, located 
in the wing bottom skin inboard and outboard of the external lower 
surface splice, have been reported by operators.
    This condition, if not detected and corrected, could affect the 
structural integrity of the airframe.
    Prompted by these findings, [Directorate General for Civil 
Aviation] (DGAC) France issued AD 1997-006-210 [which corresponds to 
FAA AD 98-21-34, Amendment 39-10842 (63 FR 55524, October 16, 1998)] 
to require repetitive inspections to detect the presence of 
corrosion and prevent crack propagation at the wing bottom skin, 
inboard and outboard of the Rib 1 external lower surface splice, 
between Frame (FR) 40 and FR47.
    DGAC France * * * issued [an AD] to expand the choice of 
applicable Service Bulletins (SB). [The] DGAC France AD * * * was 
issued to allow A300-600 operators to use Revision 04 of Airbus SB 
A300-57-6047, converting flight cycles/``Fatigue rating'' into 
flight cycles (FC)/flight hours (FH).
    Subsequently, Airbus modification 10599 was developed to improve 
the corrosion behaviour of the area. This improvement allowed 
refining the inspection programme of the A300-600 aeroplane. For 
post-modification 10599 A300-600 aeroplanes, the application of the 
Maintenance Review Board Report (MRBR) inspection tasks was deemed 
sufficient for maintaining an adequate level of safety on these 
aeroplanes.
    Consequently, EASA issued AD 2008-0208 [http://ad.easa.europa.eu/blob/easa_ad_2008_0208_R2.pdf/AD_2008-0208R2_1] 
(later revised), retaining the requirements of [a] DGAC France AD * 
* *, which was superseded, to require the use of Airbus SB A300-57-
6047 Revision 05 for the inspections and to exclude post-
modification

[[Page 19510]]

10599 A300-600 aeroplanes from the Applicability.
    Since EASA AD 2008-0208R1 was issued, a fleet survey and updated 
Fatigue and Damage Tolerance analyses have been performed in order 
to substantiate the second A300-600 Extended Service Goal (ESG2) 
exercise. The results of these analyses determined that the 
threshold and interval must be reduced to allow timely detection of 
these cracks and the accomplishment of an applicable corrective 
action.
    For the reasons described above, this [EASA] AD takes over and 
retains the requirements for A300 and A300-600 aeroplanes from EASA 
AD 2008-0208R1 (which has been revised, remaining applicable only to 
A310 aeroplanes) and requires accomplishment of the inspections 
within the new thresholds and intervals.

    Required actions include repetitive detailed inspections for 
corrosion of the rib 1 external lower surface splice between FR40 and 
FR47, and repetitive fatigue inspections for cracking of the fasteners 
and on the surface of the forward and aft lower surface panels if 
necessary, and corrective actions (including application of new 
protective coating, removal of corrosion, and measurement of the 
reworked depth) if necessary. 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-2016-5040.

Related Rulemaking

    AD 98-21-34, Amendment 39-10842 (63 FR 55524, October 16, 1998) 
(``AD 98-21-34''), applies to all Model A300, A300-600, and A310 series 
airplanes. This NPRM proposes to apply to only certain Model A300 and 
A300-600 series airplanes. The actions in this proposed AD are the same 
as those required by AD 98-21-34, but with certain revised compliance 
times. Accomplishment of the initial inspection specified in this 
proposed AD would terminate the repetitive inspection requirements of 
AD 98-21-34 for the affected airplanes. Certain modified Model A300-600 
series airplanes would not be subject to the inspection requirements of 
this AD, and would no longer be subject to the repetitive inspection 
requirements of AD 98-21-34.

Related Service Information Under 1 CFR Part 51

    We reviewed Service Bulletin A300-57-0204, Revision 01, dated April 
2, 1999; and Airbus Service Bulletin A300-57-6047, Revision 06, dated 
October 17, 2011. This service information describes procedures for 
repetitive detailed inspections for corrosion of the rib 1 external 
lower surface splice between FR40 and FR47, repetitive fatigue 
inspections for cracking of the fasteners and on the surface of the 
forward and aft lower surface panels if necessary, and corrective 
actions (including application of new protective coating, removal of 
corrosion, and measurement of the reworked depth) if necessary. 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 these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 29 airplanes of U.S. 
registry. We also estimate that it would take about 8 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Based on these figures, we 
estimate the cost of this proposed AD on U.S. operators to be $19,270, 
or $680 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 8 work-hours, for a cost of $680 per product. We have no way 
of determining the number of aircraft that might need these actions.

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 adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2016-5040; Directorate Identifier 2013-NM-
192-AD.

(a) Comments Due Date

    We must receive comments by May 20, 2016.

(b) Affected ADs

    This AD affects AD 98-21-34, Amendment 39-10842 (63 FR 55524, 
October 16, 1998) (``AD 98-21-34'').

(c) Applicability

    This AD applies to all Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1) and (c)(2) of this AD.

[[Page 19511]]

    (1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and 
B4-203 airplanes.
    (2) Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, 
F4-605R, F4-622R, and C4-605R Variant F airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by the determination that certain existing 
inspection thresholds and intervals must be reduced. We are issuing 
this AD to detect and correct corrosion and cracking on the lower 
wing root joint, which could reduce the structural integrity of the 
airframe.

(f) Compliance

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

(g) Airplanes Excluded From Requirements of This AD and AD 98-21-34

    For airplanes identified in paragraph (c)(2) of this AD on which 
Airbus modification 10599 has been incorporated:
    (1) No action is required by this AD; and
    (2) As of the effective date of this AD, the actions specified 
in AD 98-21-34 are no longer required.

(h) Inspection and Corrective Actions

    Within 60 months since the airplane's first flight, or within 60 
months since accomplishment of the last inspection specified in 
Airbus Service Bulletin A300-57-0204 or A300-57-6047, whichever 
occurs later: Do a detailed inspection for corrosion of the rib 1 
external lower surface splice between frame (FR)40 and FR47, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus 
Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; 
as applicable. Repeat the inspection thereafter at intervals not to 
exceed 60 months. Accomplishment of the initial inspection required 
by this paragraph terminates the requirements of AD 98-21-34 for 
Model A300 and A300-600 series airplanes.

(i) Corrective Actions for Corrosion

    If any corrosion is found during any inspection required by 
paragraph (h) of this AD, do the actions specified in paragraph 
(i)(1) and (i)(2) of this AD.
    (1) Before further flight, do all applicable corrective actions 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus 
Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; 
as applicable; except as required by paragraph (j)(1) of this AD.
    (2) At the applicable time specified in paragraph (i)(2)(i) or 
(i)(2)(ii) of this AD, except as required by paragraph (j)(2) of 
this AD: Do fatigue inspections to detect cracks of the fasteners 
and on the surface of the forward and aft lower surface panels, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus 
Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; 
as applicable. Repeat the fatigue inspections thereafter at the 
applicable interval specified in paragraph B.(5) of Airbus Service 
Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Figure 
A-FBGAA, Sheet 01, of Airbus Service Bulletin A300-57-6047, Revision 
06, dated October 17, 2011; as applicable; except as required by 
paragraph (j)(2) of this AD. If any cracking is found during any 
fatigue inspection required by this paragraph: 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).
    (i) For Model A300 series airplanes: Do the initial inspection 
at the applicable time specified in paragraph B.(5) of Airbus 
Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999.
    (ii) For Model A300-600 series airplanes: Do the initial 
inspection at the later of the times specified in paragraphs 
(i)(2)(ii)(A) and (i)(2)(ii)(B) of this AD.
    (A) At the applicable time specified in Figure A-FBGAA, Sheet 
01, of Airbus Service Bulletin A300-57-6047, Revision 06, dated 
October 17, 2011.
    (B) Within 500 flight cycles or 1,050 flight hours after the 
effective date of this AD, whichever occurs first, without exceeding 
the time specified in paragraph (i)(2)(ii)(A) of this AD.

(j) Exceptions to Service Bulletin Specifications

    (1) Where Airbus Service Bulletin A300-57-0204, Revision 01, 
dated April 2, 1999; or Airbus Service Bulletin A300-57-6047, 
Revision 06, dated October 17, 2011; specifies to contact Airbus for 
appropriate corrective action, this AD requires repair before 
further flight using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA DOA.
    (2) Where Airbus Service Bulletin A300-57-6047, Revision 06, 
dated October 17, 2011, specifies to contact Airbus for the 
appropriate threshold or repetitive interval, this AD requires that 
the compliance time be determined using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or Airbus's EASA DOA.

(k) Calculating Average Flight Time (AFT)

    The accumulated flight hours (counted from the takeoff up to the 
landing) divided by the number of accumulated flight cycles is the 
AFT per flight cycle.

(l) Credit for Previous Actions

    This paragraph provides credit for the inspections and 
corrective actions required by paragraphs (h) and (i) of this AD, if 
those actions were performed before the effective date of this AD 
using the applicable service information specified in paragraphs 
(l)(1) through (l)(3) of this AD.
    (1) Airbus Service Bulletin A300-57-6047, Revision 02, dated 
April 2, 1999, which is not incorporated by reference in this AD.
    (2) Airbus Service Bulletin A300-57-6047, Revision 03, dated 
September 28, 1999, which is not incorporated by reference in this 
AD.
    (3) Airbus Service Bulletin A300-57-6047, Revision 05, dated May 
27, 2008, which is not incorporated by reference in this AD.

(m) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone (425) 227-2125; fax (425) 227-1149. 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 the EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0230, dated September 24, 
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 Docket No. FAA-2016-5040.
    (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 [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 March 24, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-07575 Filed 4-4-16; 8:45 am]
BILLING CODE 4910-13-P
19510 Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules

10599 A300–600 aeroplanes from the surface splice between FR40 and FR47, is within the scope of that authority
Applicability. repetitive fatigue inspections for because it addresses an unsafe condition
Since EASA AD 2008–0208R1 was issued, cracking of the fasteners and on the that is likely to exist or develop on
a fleet survey and updated Fatigue and surface of the forward and aft lower products identified in this rulemaking
Damage Tolerance analyses have been
performed in order to substantiate the second
surface panels if necessary, and action.
A300–600 Extended Service Goal (ESG2) corrective actions (including application
Regulatory Findings
exercise. The results of these analyses of new protective coating, removal of
determined that the threshold and interval corrosion, and measurement of the We determined that this proposed AD
must be reduced to allow timely detection of reworked depth) if necessary. This would not have federalism implications
these cracks and the accomplishment of an service information is reasonably under Executive Order 13132. This
applicable corrective action. available because the interested parties proposed AD would not have a
For the reasons described above, this have access to it through their normal substantial direct effect on the States, on
[EASA] AD takes over and retains the course of business or by the means the relationship between the national
requirements for A300 and A300–600
identified in the ADDRESSES section. Government and the States, or on the
aeroplanes from EASA AD 2008–0208R1
(which has been revised, remaining distribution of power and
FAA’s Determination and Requirements
applicable only to A310 aeroplanes) and responsibilities among the various
of This Proposed AD
requires accomplishment of the inspections levels of government.
within the new thresholds and intervals. This product has been approved by For the reasons discussed above, I
the aviation authority of another certify this proposed regulation:
Required actions include repetitive country, and is approved for operation
detailed inspections for corrosion of the 1. Is not a ‘‘significant regulatory
in the United States. Pursuant to our action’’ under Executive Order 12866;
rib 1 external lower surface splice bilateral agreement with the State of
between FR40 and FR47, and repetitive 2. Is not a ‘‘significant rule’’ under the
Design Authority, we have been notified DOT Regulatory Policies and Procedures
fatigue inspections for cracking of the of the unsafe condition described in the
fasteners and on the surface of the (44 FR 11034, February 26, 1979);
MCAI and service information 3. Will not affect intrastate aviation in
forward and aft lower surface panels if referenced above. We are proposing this
necessary, and corrective actions Alaska; and
AD because we evaluated all pertinent 4. Will not have a significant
(including application of new protective information and determined an unsafe
coating, removal of corrosion, and economic impact, positive or negative,
condition exists and is likely to exist or on a substantial number of small entities
measurement of the reworked depth) if develop on other products of these same
necessary. You may examine the MCAI under the criteria of the Regulatory
type designs. Flexibility Act.
in the AD docket on the Internet at
http://www.regulations.gov by searching Costs of Compliance List of Subjects in 14 CFR Part 39
for and locating Docket No. FAA–2016– We estimate that this proposed AD
5040. Air transportation, Aircraft, Aviation
affects 29 airplanes of U.S. registry. We safety, Incorporation by reference,
Related Rulemaking also estimate that it would take about 8 Safety.
work-hours per product to comply with
AD 98–21–34, Amendment 39–10842 the basic requirements of this proposed The Proposed Amendment
(63 FR 55524, October 16, 1998) (‘‘AD AD. The average labor rate is $85 per
98–21–34’’), applies to all Model A300, Accordingly, under the authority
work-hour. Based on these figures, we delegated to me by the Administrator,
A300–600, and A310 series airplanes. estimate the cost of this proposed AD on
This NPRM proposes to apply to only the FAA proposes to amend 14 CFR part
U.S. operators to be $19,270, or $680 per 39 as follows:
certain Model A300 and A300–600 product.
series airplanes. The actions in this In addition, we estimate that any PART 39—AIRWORTHINESS
proposed AD are the same as those necessary follow-on actions would take DIRECTIVES
required by AD 98–21–34, but with about 8 work-hours, for a cost of $680
certain revised compliance times. per product. We have no way of ■ 1. The authority citation for part 39
Accomplishment of the initial determining the number of aircraft that continues to read as follows:
inspection specified in this proposed might need these actions. Authority: 49 U.S.C. 106(g), 40113, 44701.
AD would terminate the repetitive
inspection requirements of AD 98–21– Authority for This Rulemaking
§ 39.13 [Amended]
34 for the affected airplanes. Certain Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by adding
modified Model A300–600 series specifies the FAA’s authority to issue the following new airworthiness
airplanes would not be subject to the rules on aviation safety. Subtitle I, directive (AD):
inspection requirements of this AD, and section 106, describes the authority of
would no longer be subject to the the FAA Administrator. ‘‘Subtitle VII: Airbus: Docket No. FAA–2016–5040;
repetitive inspection requirements of Aviation Programs,’’ describes in more Directorate Identifier 2013–NM–192–AD.
AD 98–21–34. detail the scope of the Agency’s (a) Comments Due Date
authority. We must receive comments by May 20,
Related Service Information Under 1 We are issuing this rulemaking under
CFR Part 51 2016.
the authority described in ‘‘Subtitle VII,
(b) Affected ADs
Lhorne on DSK5TPTVN1PROD with PROPOSALS

We reviewed Service Bulletin A300– Part A, Subpart III, Section 44701:
57–0204, Revision 01, dated April 2, General requirements.’’ Under that This AD affects AD 98–21–34, Amendment
1999; and Airbus Service Bulletin section, Congress charges the FAA with 39–10842 (63 FR 55524, October 16, 1998)
A300–57–6047, Revision 06, dated promoting safe flight of civil aircraft in (‘‘AD 98–21–34’’).
October 17, 2011. This service air commerce by prescribing regulations (c) Applicability
information describes procedures for for practices, methods, and procedures This AD applies to all Airbus airplanes,
repetitive detailed inspections for the Administrator finds necessary for certificated in any category, identified in
corrosion of the rib 1 external lower safety in air commerce. This regulation paragraphs (c)(1) and (c)(2) of this AD.

VerDate Sep<11>2014 13:17 Apr 04, 2016 Jkt 238001 PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 E:\FR\FM\05APP1.SGM 05APP1
Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules 19511

(1) Model A300 B2–1A, B2–1C, B2K–3C, 57–0204, Revision 01, dated April 2, 1999; or (2) Airbus Service Bulletin A300–57–6047,
B2–203, B4–2C, B4–103, and B4–203 Airbus Service Bulletin A300–57–6047, Revision 03, dated September 28, 1999,
airplanes. Revision 06, dated October 17, 2011; as which is not incorporated by reference in this
(2) Model A300 B4–601, B4–603, B4–620, applicable. Repeat the fatigue inspections AD.
B4–622, B4–605R, B4–622R, F4–605R, F4– thereafter at the applicable interval specified (3) Airbus Service Bulletin A300–57–6047,
622R, and C4–605R Variant F airplanes. in paragraph B.(5) of Airbus Service Bulletin Revision 05, dated May 27, 2008, which is
A300–57–0204, Revision 01, dated April 2, not incorporated by reference in this AD.
(d) Subject 1999; or Figure A–FBGAA, Sheet 01, of
Air Transport Association (ATA) of Airbus Service Bulletin A300–57–6047, (m) Other FAA AD Provisions
America Code 57, Wings. Revision 06, dated October 17, 2011; as The following provisions also apply to this
applicable; except as required by paragraph AD:
(e) Reason (j)(2) of this AD. If any cracking is found (1) Alternative Methods of Compliance
This AD was prompted by the during any fatigue inspection required by (AMOCs): The Manager, International
determination that certain existing inspection this paragraph: Before further flight, repair Branch, ANM–116, Transport Airplane
thresholds and intervals must be reduced. using a method approved by the Manager, Directorate, FAA, has the authority to
We are issuing this AD to detect and correct International Branch, ANM–116, Transport approve AMOCs for this AD, if requested
corrosion and cracking on the lower wing Airplane Directorate, FAA; or the European using the procedures found in 14 CFR 39.19.
root joint, which could reduce the structural Aviation Safety Agency (EASA); or Airbus’s In accordance with 14 CFR 39.19, send your
integrity of the airframe. EASA Design Organization Approval (DOA). request to your principal inspector or local
(i) For Model A300 series airplanes: Do the Flight Standards District Office, as
(f) Compliance
initial inspection at the applicable time appropriate. If sending information directly
Comply with this AD within the specified in paragraph B.(5) of Airbus Service
compliance times specified, unless already to the International Branch, send it to ATTN:
Bulletin A300–57–0204, Revision 01, dated Dan Rodina, Aerospace Engineer,
done. April 2, 1999.
International Branch, ANM–116, Transport
(g) Airplanes Excluded From Requirements (ii) For Model A300–600 series airplanes:
Airplane Directorate, FAA, 1601 Lind
of This AD and AD 98–21–34 Do the initial inspection at the later of the
Avenue SW., Renton, WA 98057–3356;
times specified in paragraphs (i)(2)(ii)(A) and
For airplanes identified in paragraph (c)(2) telephone (425) 227–2125; fax (425) 227–
(i)(2)(ii)(B) of this AD.
of this AD on which Airbus modification 1149. Information may be emailed to: 9-
(A) At the applicable time specified in
10599 has been incorporated: Figure A–FBGAA, Sheet 01, of Airbus ANM-116-AMOC-REQUESTS@faa.gov.
(1) No action is required by this AD; and Service Bulletin A300–57–6047, Revision 06, Before using any approved AMOC, notify
(2) As of the effective date of this AD, the dated October 17, 2011. your appropriate principal inspector, or
actions specified in AD 98–21–34 are no (B) Within 500 flight cycles or 1,050 flight lacking a principal inspector, the manager of
longer required. hours after the effective date of this AD, the local flight standards district office/
whichever occurs first, without exceeding the certificate holding district office. The AMOC
(h) Inspection and Corrective Actions approval letter must specifically reference
time specified in paragraph (i)(2)(ii)(A) of
Within 60 months since the airplane’s first this AD. this AD.
flight, or within 60 months since (2) Contacting the Manufacturer: For any
accomplishment of the last inspection (j) Exceptions to Service Bulletin requirement in this AD to obtain corrective
specified in Airbus Service Bulletin A300– Specifications actions from a manufacturer, the action must
57–0204 or A300–57–6047, whichever occurs (1) Where Airbus Service Bulletin A300– be accomplished using a method approved
later: Do a detailed inspection for corrosion 57–0204, Revision 01, dated April 2, 1999; or by the Manager, International Branch, ANM–
of the rib 1 external lower surface splice Airbus Service Bulletin A300–57–6047, 116, Transport Airplane Directorate, FAA; or
between frame (FR)40 and FR47, in Revision 06, dated October 17, 2011; the EASA; or Airbus’s EASA DOA. If
accordance with the Accomplishment specifies to contact Airbus for appropriate approved by the DOA, the approval must
Instructions of Airbus Service Bulletin A300– corrective action, this AD requires repair include the DOA-authorized signature.
57–0204, Revision 01, dated April 2, 1999; or before further flight using a method approved
Airbus Service Bulletin A300–57–6047, by the Manager, International Branch, ANM– (n) Related Information
Revision 06, dated October 17, 2011; as 116, Transport Airplane Directorate, FAA; or (1) Refer to Mandatory Continuing
applicable. Repeat the inspection thereafter EASA; or Airbus’s EASA DOA. Airworthiness Information (MCAI) EASA
at intervals not to exceed 60 months. (2) Where Airbus Service Bulletin A300– Airworthiness Directive 2013–0230, dated
Accomplishment of the initial inspection 57–6047, Revision 06, dated October 17, September 24, 2013, for related information.
required by this paragraph terminates the 2011, specifies to contact Airbus for the This MCAI may be found in the AD docket
requirements of AD 98–21–34 for Model appropriate threshold or repetitive interval, on the Internet at http://www.regulations.gov
A300 and A300–600 series airplanes. this AD requires that the compliance time be by searching for and locating Docket No.
(i) Corrective Actions for Corrosion determined using a method approved by the FAA–2016–5040.
Manager, International Branch, ANM–116, (2) For service information identified in
If any corrosion is found during any Transport Airplane Directorate, FAA; or this AD, contact Airbus SAS, Airworthiness
inspection required by paragraph (h) of this EASA; or Airbus’s EASA DOA.
AD, do the actions specified in paragraph Office—EAW, 1 Rond Point Maurice
(i)(1) and (i)(2) of this AD. (k) Calculating Average Flight Time (AFT) Bellonte, 31707 Blagnac Cedex, France;
(1) Before further flight, do all applicable telephone +33 5 61 93 36 96; fax +33 5 61
The accumulated flight hours (counted 93 44 51; email account.airworth-eas@
corrective actions in accordance with the from the takeoff up to the landing) divided
Accomplishment Instructions of Airbus airbus.com; Internet http://www.airbus.com.
by the number of accumulated flight cycles You may view this service information at the
Service Bulletin A300–57–0204, Revision 01, is the AFT per flight cycle.
dated April 2, 1999; or Airbus Service FAA, Transport Airplane Directorate, 1601
Bulletin A300–57–6047, Revision 06, dated (l) Credit for Previous Actions Lind Avenue SW., Renton, WA. For
October 17, 2011; as applicable; except as information on the availability of this
This paragraph provides credit for the
required by paragraph (j)(1) of this AD. material at the FAA, call 425–227–1221.
Lhorne on DSK5TPTVN1PROD with PROPOSALS

inspections and corrective actions required
(2) At the applicable time specified in by paragraphs (h) and (i) of this AD, if those Issued in Renton, Washington, on March
paragraph (i)(2)(i) or (i)(2)(ii) of this AD, actions were performed before the effective 24, 2016.
except as required by paragraph (j)(2) of this date of this AD using the applicable service Michael Kaszycki,
AD: Do fatigue inspections to detect cracks of information specified in paragraphs (l)(1)
Acting Manager, Transport Airplane
the fasteners and on the surface of the through (l)(3) of this AD.
Directorate, Aircraft Certification Service.
forward and aft lower surface panels, in (1) Airbus Service Bulletin A300–57–6047,
accordance with the Accomplishment Revision 02, dated April 2, 1999, which is [FR Doc. 2016–07575 Filed 4–4–16; 8:45 am]
Instructions of Airbus Service Bulletin A300– not incorporated by reference in this AD. BILLING CODE 4910–13–P

VerDate Sep<11>2014 13:17 Apr 04, 2016 Jkt 238001 PO 00000 Frm 00012 Fmt 4702 Sfmt 9990 E:\FR\FM\05APP1.SGM 05APP1
Document Created: 2018-02-07 13:53:50
Document Modified: 2018-02-07 13:53:50
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by May 20, 2016.
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.
FR Citation		81 FR 19509
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
81 FR 19509 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 81, Issue 65 (April 5, 2016)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
