81_FR_4893 81 FR 4875 - Airworthiness Directives; Airbus Airplanes

81 FR 4875 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 18 (January 28, 2016)

Page Range4875-4878
FR Document2016-00611

We are superseding Airworthiness Directive (AD) 98-20-27 for all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 98-20-27 required repetitive inspections to detect fatigue cracking of the wing top skin at the front spar joint; and a follow-on eddy current inspection and repair, if necessary. This new AD reduces the inspection compliance time and intervals, and expands the inspection area of the wing top skin at the front spar joint. This AD was prompted by reports of cracking of the wing top skin in an area not required for inspection by AD 98-20-27. We are issuing this AD to detect and correct fatigue cracking of the wing top skin at the front spar joint; such fatigue cracking could result in reduced structural integrity of the airplane.

Federal Register, Volume 81 Issue 18 (Thursday, January 28, 2016) 
[Federal Register Volume 81, Number 18 (Thursday, January 28, 2016)]
[Rules and Regulations]
[Pages 4875-4878]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-00611]



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Federal Register / Vol. 81, No. 18 / Thursday, January 28, 2016 / 
Rules and Regulations

[[Page 4875]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0824; Directorate Identifier 2013-NM-191-AD; 
Amendment 39-18378; AD 2016-01-18]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 98-20-27 for 
all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, 
and Model A300 C4-605R Variant F airplanes (collectively called Model 
A300-600 series airplanes). AD 98-20-27 required repetitive inspections 
to detect fatigue cracking of the wing top skin at the front spar 
joint; and a follow-on eddy current inspection and repair, if 
necessary. This new AD reduces the inspection compliance time and 
intervals, and expands the inspection area of the wing top skin at the 
front spar joint. This AD was prompted by reports of cracking of the 
wing top skin in an area not required for inspection by AD 98-20-27. We 
are issuing this AD to detect and correct fatigue cracking of the wing 
top skin at the front spar joint; such fatigue cracking could result in 
reduced structural integrity of the airplane.

DATES: This AD becomes effective March 3, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 3, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of October 
29, 1998 (63 FR 50981, September 24, 1998).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0824; or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    For service information identified in this AD, contact Airbus SAS, 
Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; 
email account.airworth-eas@airbus.com; Internet http://www.airbus.com. 
You may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-0824.

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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 98-20-27, Amendment 39-10793 (63 FR 50981, 
September 24, 1998). AD 98-20-27 applied to all Airbus Model A300 B4-
600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R 
Variant F airplanes (collectively called Model A300-600 series 
airplanes). The NPRM published in the Federal Register on April 14, 
2015 (80 FR 19892). The NPRM was prompted by reports of cracking of the 
wing top skin in an area not required for inspection by AD 98-20-27. 
The NPRM proposed to continue to require repetitive inspections to 
detect fatigue cracking of the wing top skin at the front spar joint; 
and a follow-on eddy current inspection and repair, if necessary. The 
NPRM also proposed to reduce the inspection compliance time and 
intervals, and expand the inspection area of the wing top skin at the 
front spar joint. We are issuing this AD to detect and correct fatigue 
cracking of the wing top skin at the front spar joint; such fatigue 
cracking could result in reduced structural integrity of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0232R1, dated October 2, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition.
    The MCAI states:

    During full-scale fatigue testing conducted in the early 1990's, 
cracks were found on the top skin of the wing between Ribs 1 and 7, 
starting at the front spar fastener holes.
    This condition, if not detected and corrected, could adversely 
affect the structural integrity of the wing.
    Consequently, Airbus issued Service Bulletin (SB) A300-57-6045 
and DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France issued AD 97-374-238 [http://ad.easa.europa.eu/blob/19973740tb_superseded.pdf/AD_F-1997-374-238_2] for A300-600 
aeroplanes and AD 1999-008-020 [http://ad.easa.europa.eu/blob/19980080tb_superseded.pdf/AD_F-1999-008-020_2] for A300-600ST 
aeroplanes to require repetitive detailed inspections of the wing 
top skin and, in case of findings, an Eddy Current (EC) inspection, 
and, depending on the size of the cracks, repair.
    After those [DGAC] ADs were issued, further cracks to the wing 
top skin were reported by operators, within an area not covered by 
the existing [DGAC] ADs. To address this potential unsafe condition, 
Airbus revised SB A300-57-6045 to extend the area to be inspected.
    In addition, a fleet survey and updated Fatigue and Damage 
Tolerance analyses were performed in order to substantiate the 
second A300-600 Extended Service Goal (ESG2) exercise. The results 
of these analyses have determined that the inspection thresholds and 
intervals must be reduced to allow timely detection of these cracks 
and the accomplishment of applicable corrective action(s).
    As the ESG2 exercise is only applicable to A300-600 aeroplanes, 
A300-600ST aeroplanes are now addressed through new Airbus SB A300-
57-9026.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 97-374-238(B) [http://ad.easa.europa.eu/blob/19973740tb_superseded.pdf/AD_F-1997-374-238_2] [which corresponds to FAA AD 98-

[[Page 4876]]

20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998)] and 
[DGAC] AD 1999-008-020(B) [http://ad.easa.europa.eu/blob/19980080tb_superseded.pdf/AD_F-1999-008-020_2], which are 
superseded, but requires those actions, for A300-600 aeroplanes 
only, within reduced thresholds and intervals.

* * * * *
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-0824-0003.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (80 
FR 19892, April 14, 2015) and the FAA's response to each comment.

Support for the NPRM (80 FR 19892, April 14, 2015)

    United Parcel Service (UPS) stated that the proposed changes 
maintain the fleet airworthiness using the service experience and 
current certification maintenance programs for all airplanes in 
service.

Request To Extend the Repetitive Inspection Interval

    UPS requested that we extend the interval for the repetitive 
inspections proposed in paragraph (j)(2) of the proposed AD (80 FR 
19892, April 14, 2015). UPS stated that its Model A300 fleet and 
associated maintenance program is not certified to the ESG-2 
limitations; therefore, the repetitive inspection interval should be 
based on the airplane certification design service goal (DSG). UPS 
explained that the repetitive interval extension request is due to the 
additional 12,000-flight-cycle service life to ensure any crack 
development is detected after an airplane operates beyond the 30,000-
flight-cycle DSG. UPS stated that, with an extension of airplane 
operational life, more frequent inspections would be necessary for 
airplanes operating beyond the original DSG that are not necessary for 
an airplane operating to the airplane DSG values.
    We disagree with UPS's request. UPS did not provide any data to 
substantiate that the changed compliance time for the repetitive 
inspection interval provides an equivalent level of safety. Under the 
provisions of paragraph (o)(1) of this AD, we will consider requests 
for approval of an alternative method of compliance (AMOC) if 
sufficient data are submitted to substantiate that a revised inspection 
interval would provide an equivalent level of safety. We have not 
changed this AD in this regard.

Request To Include Corrective Actions for Repetitive Inspections

    UPS requested that we correct the inadvertent omission of the 
corrective actions for the repetitive inspections in paragraph (j) of 
the proposed AD (80 FR 19892, April 14, 2015) by including a reference 
to paragraph (j) of the proposed AD in paragraphs (k)(1) and (k)(2) of 
the proposed AD, which specify the corrective actions.
    We agree with UPS to correct the inadvertent omission. We have 
revised paragraphs (k)(1) and (k)(2) of this AD accordingly.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 19892, April 14, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 19892, April 14, 2015).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-57-6045, Revision 10, dated 
November 13, 2013. The service information describes inspection 
procedures for fatigue cracking of the wing top skin at the front spar 
joint between ribs 1 and 7. 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.

Costs of Compliance

    We estimate that this AD affects 130 airplanes of U.S. registry.
    The actions that are required by AD 98-20-27, Amendment 39-10793 
(63 FR 50981, September 24, 1998), and retained in this AD take about 2 
work-hours per product, at an average labor rate of $85 per work-hour. 
Based on these figures, the estimated cost of the actions that are 
required by AD 98-20-27 is $170 per product.
    We also estimate that it will take about 2 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $22,100, or $170 per product.
    We have received no definitive data that will enable us to provide 
cost estimates for the on-condition actions specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0824; or in person at the 
Docket Management Facility between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal

[[Page 4877]]

holidays. The AD docket contains this 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
98-20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998), and 
adding the following new AD:

2016-01-18 Airbus: Amendment 39-18378. Docket No. FAA-2015-0824; 
Directorate Identifier 2013-NM-191-AD.

(a) Effective Date

    This AD becomes effective March 3, 2016.

(b) Affected ADs

    This AD replaces AD 98-20-27, Amendment 39-10793 (63 FR 50981, 
September 24, 1998).

(c) Applicability

    This AD applies to the Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1) through (c)(4) of this AD, 
all manufacturer serial numbers.
    (1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes.
    (2) Airbus Model A300 B4-605R and B4-622R airplanes.
    (3) Airbus Model A300 F4-605R and F4-622R airplanes.
    (4) Airbus Model A300 C4-605R Variant F airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracking of wing top skin in 
an area not required for inspection by AD 98-20-27, Amendment 39-
10793 (63 FR 50981, September 24, 1998). We are issuing this AD to 
detect and correct fatigue cracking of the wing top skin at the 
front spar joint; such fatigue cracking could result in reduced 
structural integrity of the airplane.

(f) Compliance

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

(g) Retained Repetitive Inspections, With Revised Service Information

    This paragraph restates the requirements of paragraph (a) of AD 
98-20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998), with 
revised service information. Prior to the accumulation of 22,000 
total flight cycles, or within 2,000 flight cycles after October 29, 
1998 (the effective date of AD 98-20-27), whichever occurs later: 
Perform a detailed visual inspection to detect fatigue cracking of 
the wing top skin at the front spar joint, in accordance with Airbus 
Service Bulletin A300-57-6045, Revision 1, dated August 3, 1994, 
including Appendix 1, Revision 1, dated August 3, 1994; Airbus 
Service Bulletin A300-57-6045, Revision 02, dated April 21, 1998, 
including Appendix 1, Revision 02, dated April 21, 1998; or Airbus 
Service Bulletin A300-57-6045, Revision 10, dated November 13, 2013. 
Repeat the detailed visual inspection thereafter at intervals not to 
exceed 8,000 flight cycles.

(h) Retained Inspection and Repair, With Revised Service Information

    This paragraph restates the requirements of paragraph (b) of AD 
98-20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998), with 
revised service information. If any cracking is suspected or 
detected during any inspection required by paragraph (g) of this AD: 
Prior to further flight, perform an eddy current inspection to 
confirm the findings of the visual inspection, in accordance with 
Airbus Service Bulletin A300-57-6045, Revision 1, dated August 3, 
1994, including Appendix 1, Revision 1, dated August 3, 1994; Airbus 
Service Bulletin A300-57-6045, Revision 02, dated April 21, 1998, 
including Appendix 1, Revision 02, dated April 21, 1998; or Airbus 
Service Bulletin A300-57-6045, Revision 10, dated November 13, 2013. 
If any cracking is detected during any eddy current inspection, 
prior to further flight, repair using a method approved by the 
Manager, International Branch, ANM-116, FAA, Transport Airplane 
Directorate; or the Direction G[eacute]n[eacute]rale de l'Aviation 
Civile (or its delegated agent).

(i) New Requirement of This AD: Initial Inspection

    At the applicable time specified in paragraph (i)(1) or (i)(2) 
of this AD: Do a detailed inspection of the wing top skin between 
ribs 1 and 7 for cracking, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-6045, Revision 10, 
dated November 13, 2013. Accomplishment of the initial inspection 
required by this paragraph terminates the requirements of paragraph 
(g) of this AD.
    (1) For Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; 
Model A300 B4-605R and B4-622R airplanes; and Model A300 C4-605R 
Variant F airplanes: At the later of the times specified in 
paragraphs (i)(1)(i) and (i)(1)(ii) of this AD.
    (i) Before the accumulation of 17,100 total flight cycles or 
38,400 total flight hours, whichever occurs first.
    (ii) Within 1,000 flight cycles or 2,200 flight hours, whichever 
occurs first after the effective date of this AD.
    (2) For Model A300 F4-605R and F4-622R airplanes: At the later 
of the times specified in paragraphs (i)(2)(i) and (i)(2)(ii) of 
this AD.
    (i) Before the accumulation of 22,000 total flight cycles or 
49,500 total flight hours, whichever occurs first.
    (ii) Within 1,300 flight cycles or 2,800 flight hours, whichever 
occurs first after the effective date of this AD.

(j) New Requirement of This AD: Repetitive Inspections

    Repeat the inspection required by paragraph (i) of this AD 
thereafter at the applicable time and intervals specified in 
paragraphs (j)(1) and (j)(2) of this AD.
    (1) For Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; 
Model A300 B4-605R and B4-622R airplanes; and Model A300 C4-605R 
Variant F airplanes: Repeat the inspection at the applicable time 
specified in paragraph (j)(1)(i) or (j)(1)(ii) of this AD.
    (i) For airplanes that have an average flight time (AFT) that is 
equal to or more than one and one-half hours: Repeat the inspection 
at intervals not to exceed 5,100 flight cycles or 11,000 flight 
hours, whichever occurs first.
    (ii) For airplanes that have an AFT that is less than one and 
one-half hours: Repeat the inspection at intervals not to exceed 
5,500 flight cycles or 8,300 flight hours, whichever occurs first.
    (2) For Model A300 F4-605R and F4-622R airplanes: Repeat the 
inspection at the applicable time specified in paragraph (j)(2)(i) 
or (j)(2)(ii) of this AD.
    (i) For airplanes that have an AFT that is equal to or more than 
one and one-half hours: Repeat the inspection at intervals not to 
exceed 6,500 flight cycles or 14,100 flight hours, whichever occurs 
first.
    (ii) For airplanes that have an AFT that is less than one and 
one-half hours: Repeat the inspection at intervals not to exceed 
7,000 flight cycles or 10,600 flight hours, whichever occurs first.

(k) New Requirement of This AD: Repair of Cracking

    (1) If any crack in the top skin in the area forward of the 
front spar attachment is found during any inspection required by 
paragraph (i) or (j) of this AD: 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).
    (2) If any crack or sign of a crack is found in the top skin at 
or aft of the spar attachment during any inspection required by 
paragraph (i) or (j) of this AD: Before further flight, do an eddy 
current inspection of the cracks or of the signs of cracking to 
confirm the findings of the detailed inspection, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A300-57-
6045, Revision 10, dated November 13,

[[Page 4878]]

2013. If there is any crack at or aft of the spar attachment, before 
further flight, repair using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
EASA; or Airbus's EASA DOA.

(l) No Terminating Action

    Accomplishment of any repair required by paragraph (k) this AD 
does not constitute terminating action for the repetitive 
inspections required by paragraph (j) of this AD.

(m) No Reporting Required

    Although Airbus Service Bulletin A300-57-6045, Revision 10, 
dated November 13, 2013, specifies to submit certain information to 
the manufacturer, this AD does not include that requirement.

(n) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (i), (j) and (k) of this AD, if those actions were 
performed before the effective date of this AD using the Airbus 
service bulletins specified in paragraphs (n)(1) through (n)(8) of 
this AD, which are not incorporated by reference in this AD.
    (1) Airbus Service Bulletin A300-57-6045, dated March 18, 1993.
    (2) Airbus Service Bulletin A300-57-6045, Revision 03, dated 
October 25, 1999.
    (3) Airbus Service Bulletin A300-57-6045, Revision 04, dated 
January 13, 2002.
    (4) Airbus Service Bulletin A300-57-6045, Revision 05, dated 
June 13, 2003.
    (5) Airbus Service Bulletin A300-57-6045, Revision 06, dated 
January 13, 2005.
    (6) Airbus Service Bulletin A300-57-6045, Revision 07, dated 
August 14, 2008.
    (7) Airbus Service Bulletin A300-57-6045, Revision 08, dated 
June 6, 2011.
    (8) Airbus Service Bulletin A300-57-6045, Revision 09, dated May 
21, 2013.

(o) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (i) 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.
    (ii) AMOCs approved previously for AD 98-20-27, Amendment 39-
10793 (63 FR 50981, September 24, 1998), are approved as AMOCs for 
the corresponding provisions of this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, 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.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0232R1, dated October 2, 
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-2015-0824.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (q)(5) and (q)(6) of this AD.

(q) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
March 3, 2016.
    (i) Airbus Service Bulletin A300-57-6045, Revision 10, dated 
November 13, 2013.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
October 29, 1998 (63 FR 50981, September 24, 1998).
    (i) Airbus Service Bulletin A300-57-6045, Revision 1, dated 
August 3, 1994, including Appendix 1, Revision 1, dated August 3, 
1994, which contains the following list of effective pages: Page 
numbers 1 through 10, Revision 1, dated August 3, 1994; Appendix 1, 
pages 1 and 2, Revision 1, dated August 3, 1994; and Appendix 1, 
pages 3 through 6, dated March 18, 1993.
    (ii) Airbus Service Bulletin A300-57-6045, Revision 02, dated 
April 21, 1998, including Appendix 1, Revision 02, dated April 21, 
1998.
    (5) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (6) 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on January 6, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-00611 Filed 1-27-16; 8:45 am]
 BILLING CODE 4910-13-P

4875 Rules and Regulations Federal Register Vol. 81, No. 18 Thursday, January 28, 2016 This section of the FEDERAL REGISTER of certain other publications listed in proposed to reduce the inspection contains regulatory documents having general this AD as of October 29, 1998 (63 FR compliance time and intervals, and applicability and legal effect, most of which 50981, September 24, 1998). expand the inspection area of the wing are keyed to and codified in the Code of top skin at the front spar joint. We are ADDRESSES: You may examine the AD Federal Regulations, which is published under issuing this AD to detect and correct 50 titles pursuant to 44 U.S.C. 1510. docket on the Internet at http:// www.regulations.gov/ fatigue cracking of the wing top skin at The Code of Federal Regulations is sold by #!docketDetail;D=FAA-2015-0824; or in the front spar joint; such fatigue the Superintendent of Documents. Prices of person at the Docket Management cracking could result in reduced new books are listed in the first FEDERAL Facility, U.S. Department of structural integrity of the airplane. REGISTER issue of each week. Transportation, Docket Operations, The European Aviation Safety Agency M–30, West Building Ground Floor, (EASA), which is the Technical Agent Room W12–140, 1200 New Jersey for the Member States of the European DEPARTMENT OF TRANSPORTATION Avenue SE., Washington, DC. Union, has issued EASA Airworthiness For service information identified in Directive 2013–0232R1, dated October Federal Aviation Administration this AD, contact Airbus SAS, 2, 2013 (referred to after this as the Airworthiness Office—EAW, 1 Rond Mandatory Continuing Airworthiness 14 CFR Part 39 Point Maurice Bellonte, 31707 Blagnac Information, or ‘‘the MCAI’’), to correct [Docket No. FAA–2015–0824; Directorate Cedex, France; telephone +33 5 61 93 36 an unsafe condition. Identifier 2013–NM–191–AD; Amendment 96; fax +33 5 61 93 44 51; email The MCAI states: 39–18378; AD 2016–01–18] account.airworth-eas@airbus.com; During full-scale fatigue testing conducted RIN 2120–AA64 Internet http://www.airbus.com. You in the early 1990’s, cracks were found on the may view this referenced service top skin of the wing between Ribs 1 and 7, Airworthiness Directives; Airbus information at the FAA, Transport starting at the front spar fastener holes. Airplanes Airplane Directorate, 1601 Lind Avenue This condition, if not detected and SW., Renton, WA. For information on corrected, could adversely affect the AGENCY: Federal Aviation the availability of this material at the structural integrity of the wing. Administration (FAA), Department of Consequently, Airbus issued Service FAA, call 425–227–1221. It is also Bulletin (SB) A300–57–6045 and DGAC Transportation (DOT). available on the Internet at http:// [Direction Générale de l’Aviation Civile] ACTION: Final rule. www.regulations.gov by searching for France issued AD 97–374–238 [http:// and locating Docket No. FAA–2015– ad.easa.europa.eu/blob/ SUMMARY: We are superseding 0824. 19973740tb_superseded.pdf/AD_F-1997-374- Airworthiness Directive (AD) 98–20–27 238_2] for A300–600 aeroplanes and AD FOR FURTHER INFORMATION CONTACT: Dan for all Airbus Model A300 B4–600, B4– 1999–008–020 [http://ad.easa.europa.eu/ Rodina, Aerospace Engineer, blob/19980080tb_superseded.pdf/AD_F- 600R, and F4–600R series airplanes, and International Branch, ANM–116, 1999-008-020_2] for A300–600ST aeroplanes Model A300 C4–605R Variant F Transport Airplane Directorate, FAA, to require repetitive detailed inspections of airplanes (collectively called Model 1601 Lind Avenue SW., Renton, WA the wing top skin and, in case of findings, an A300–600 series airplanes). AD 98–20– 98057–3356; telephone 425–227–2125; Eddy Current (EC) inspection, and, 27 required repetitive inspections to depending on the size of the cracks, repair. fax 425–227–1149. detect fatigue cracking of the wing top After those [DGAC] ADs were issued, SUPPLEMENTARY INFORMATION: skin at the front spar joint; and a follow- further cracks to the wing top skin were on eddy current inspection and repair, Discussion reported by operators, within an area not if necessary. This new AD reduces the covered by the existing [DGAC] ADs. To We issued a notice of proposed address this potential unsafe condition, inspection compliance time and rulemaking (NPRM) to amend 14 CFR intervals, and expands the inspection Airbus revised SB A300–57–6045 to extend part 39 to supersede AD 98–20–27, the area to be inspected. area of the wing top skin at the front Amendment 39–10793 (63 FR 50981, In addition, a fleet survey and updated spar joint. This AD was prompted by September 24, 1998). AD 98–20–27 Fatigue and Damage Tolerance analyses were reports of cracking of the wing top skin applied to all Airbus Model A300 B4– performed in order to substantiate the second in an area not required for inspection by 600, B4–600R, and F4–600R series A300–600 Extended Service Goal (ESG2) AD 98–20–27. We are issuing this AD to airplanes, and Model A300 C4–605R exercise. The results of these analyses have detect and correct fatigue cracking of the determined that the inspection thresholds Variant F airplanes (collectively called and intervals must be reduced to allow wing top skin at the front spar joint; Model A300–600 series airplanes). The such fatigue cracking could result in timely detection of these cracks and the NPRM published in the Federal accomplishment of applicable corrective reduced structural integrity of the Register on April 14, 2015 (80 FR action(s). airplane. 19892). The NPRM was prompted by As the ESG2 exercise is only applicable to DATES: This AD becomes effective reports of cracking of the wing top skin A300–600 aeroplanes, A300–600ST March 3, 2016. in an area not required for inspection by aeroplanes are now addressed through new wgreen on DSK2VPTVN1PROD with RULES The Director of the Federal Register AD 98–20–27. The NPRM proposed to Airbus SB A300–57–9026. For the reasons described above, this approved the incorporation by reference continue to require repetitive [EASA] AD retains the requirements of DGAC of a certain publication listed in this AD inspections to detect fatigue cracking of France AD 97–374–238(B) [http:// as of March 3, 2016. the wing top skin at the front spar joint; ad.easa.europa.eu/blob/ The Director of the Federal Register and a follow-on eddy current inspection 19973740tb_superseded.pdf/AD_F-1997-374- approved the incorporation by reference and repair, if necessary. The NPRM also 238_2] [which corresponds to FAA AD 98– VerDate Sep<11>2014 13:11 Jan 27, 2016 Jkt 238001 PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 E:\FR\FM\28JAR1.SGM 28JAR1

4876 Federal Register / Vol. 81, No. 18 / Thursday, January 28, 2016 / Rules and Regulations 20–27, Amendment 39–10793 (63 FR 50981, We have not changed this AD in this comply with the basic requirements of September 24, 1998)] and [DGAC] AD 1999– regard. this AD. The average labor rate is $85 008–020(B) [http://ad.easa.europa.eu/blob/ per work-hour. Based on these figures, 19980080tb_superseded.pdf/AD_F-1999-008- Request To Include Corrective Actions we estimate the cost of this AD on U.S. 020_2], which are superseded, but requires for Repetitive Inspections those actions, for A300–600 aeroplanes only, operators to be $22,100, or $170 per within reduced thresholds and intervals. UPS requested that we correct the product. inadvertent omission of the corrective We have received no definitive data * * * * * actions for the repetitive inspections in that will enable us to provide cost You may examine the MCAI in the paragraph (j) of the proposed AD (80 FR estimates for the on-condition actions AD docket on the Internet at http:// 19892, April 14, 2015) by including a specified in this AD. www.regulations.gov/ reference to paragraph (j) of the proposed AD in paragraphs (k)(1) and Authority for This Rulemaking #!documentDetail;D=FAA-2015-0824- 0003. (k)(2) of the proposed AD, which specify Title 49 of the United States Code the corrective actions. specifies the FAA’s authority to issue Comments We agree with UPS to correct the rules on aviation safety. Subtitle I, We gave the public the opportunity to inadvertent omission. We have revised section 106, describes the authority of participate in developing this AD. The paragraphs (k)(1) and (k)(2) of this AD the FAA Administrator. ‘‘Subtitle VII: following presents the comments accordingly. Aviation Programs,’’ describes in more received on the NPRM (80 FR 19892, detail the scope of the Agency’s Conclusion April 14, 2015) and the FAA’s response authority. to each comment. We reviewed the available data, We are issuing this rulemaking under including the comments received, and the authority described in ‘‘Subtitle VII, Support for the NPRM (80 FR 19892, determined that air safety and the Part A, Subpart III, Section 44701: April 14, 2015) public interest require adopting this AD General requirements.’’ Under that United Parcel Service (UPS) stated with the changes described previously section, Congress charges the FAA with that the proposed changes maintain the and minor editorial changes. We have promoting safe flight of civil aircraft in fleet airworthiness using the service determined that these changes: air commerce by prescribing regulations experience and current certification • Are consistent with the intent that for practices, methods, and procedures maintenance programs for all airplanes was proposed in the NPRM (80 FR the Administrator finds necessary for in service. 19892, April 14, 2015) for correcting the safety in air commerce. This regulation unsafe condition; and is within the scope of that authority Request To Extend the Repetitive • Do not add any additional burden because it addresses an unsafe condition Inspection Interval upon the public than was already that is likely to exist or develop on proposed in the NPRM (80 FR 19892, products identified in this rulemaking UPS requested that we extend the April 14, 2015). action. interval for the repetitive inspections We also determined that these proposed in paragraph (j)(2) of the Regulatory Findings changes will not increase the economic proposed AD (80 FR 19892, April 14, burden on any operator or increase the We determined that this AD will not 2015). UPS stated that its Model A300 scope of this AD. have federalism implications under fleet and associated maintenance Executive Order 13132. This AD will program is not certified to the ESG–2 Related Service Information Under 1 not have a substantial direct effect on limitations; therefore, the repetitive CFR Part 51 the States, on the relationship between inspection interval should be based on Airbus has issued Service Bulletin the national government and the States, the airplane certification design service A300–57–6045, Revision 10, dated or on the distribution of power and goal (DSG). UPS explained that the November 13, 2013. The service responsibilities among the various repetitive interval extension request is information describes inspection levels of government. due to the additional 12,000-flight-cycle procedures for fatigue cracking of the For the reasons discussed above, I service life to ensure any crack wing top skin at the front spar joint certify that this AD: development is detected after an between ribs 1 and 7. This service 1. Is not a ‘‘significant regulatory airplane operates beyond the 30,000- information is reasonably available action’’ under Executive Order 12866; flight-cycle DSG. UPS stated that, with because the interested parties have 2. Is not a ‘‘significant rule’’ under the an extension of airplane operational life, access to it through their normal course DOT Regulatory Policies and Procedures more frequent inspections would be of business or by the means identified (44 FR 11034, February 26, 1979); necessary for airplanes operating in the ADDRESSES section. 3. Will not affect intrastate aviation in beyond the original DSG that are not Alaska; and necessary for an airplane operating to Costs of Compliance 4. Will not have a significant the airplane DSG values. We estimate that this AD affects 130 economic impact, positive or negative, We disagree with UPS’s request. UPS airplanes of U.S. registry. on a substantial number of small entities did not provide any data to substantiate The actions that are required by AD under the criteria of the Regulatory that the changed compliance time for 98–20–27, Amendment 39–10793 (63 Flexibility Act. the repetitive inspection interval FR 50981, September 24, 1998), and provides an equivalent level of safety. retained in this AD take about 2 work- Examining the AD Docket Under the provisions of paragraph (o)(1) hours per product, at an average labor You may examine the AD docket on wgreen on DSK2VPTVN1PROD with RULES of this AD, we will consider requests for rate of $85 per work-hour. Based on the Internet at http:// approval of an alternative method of these figures, the estimated cost of the www.regulations.gov/ compliance (AMOC) if sufficient data actions that are required by AD 98–20– #!docketDetail;D=FAA-2015-0824; or in are submitted to substantiate that a 27 is $170 per product. person at the Docket Management revised inspection interval would We also estimate that it will take Facility between 9 a.m. and 5 p.m., provide an equivalent level of safety. about 2 work-hours per product to Monday through Friday, except Federal VerDate Sep<11>2014 13:11 Jan 27, 2016 Jkt 238001 PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 E:\FR\FM\28JAR1.SGM 28JAR1

Federal Register / Vol. 81, No. 18 / Thursday, January 28, 2016 / Rules and Regulations 4877 holidays. The AD docket contains this (f) Compliance (i) Before the accumulation of 17,100 total AD, the regulatory evaluation, any Comply with this AD within the flight cycles or 38,400 total flight hours, comments received, and other compliance times specified, unless already whichever occurs first. (ii) Within 1,000 flight cycles or 2,200 information. The street address for the done. flight hours, whichever occurs first after the Docket Operations office (telephone (g) Retained Repetitive Inspections, With effective date of this AD. 800–647–5527) is in the ADDRESSES Revised Service Information (2) For Model A300 F4–605R and F4–622R section. airplanes: At the later of the times specified This paragraph restates the requirements of paragraph (a) of AD 98–20–27, Amendment in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD. List of Subjects in 14 CFR Part 39 39–10793 (63 FR 50981, September 24, 1998), (i) Before the accumulation of 22,000 total Air transportation, Aircraft, Aviation with revised service information. Prior to the flight cycles or 49,500 total flight hours, safety, Incorporation by reference, accumulation of 22,000 total flight cycles, or whichever occurs first. Safety. within 2,000 flight cycles after October 29, (ii) Within 1,300 flight cycles or 2,800 1998 (the effective date of AD 98–20–27), flight hours, whichever occurs first after the Adoption of the Amendment whichever occurs later: Perform a detailed effective date of this AD. Accordingly, under the authority visual inspection to detect fatigue cracking of (j) New Requirement of This AD: Repetitive the wing top skin at the front spar joint, in Inspections delegated to me by the Administrator, accordance with Airbus Service Bulletin the FAA amends 14 CFR part 39 as Repeat the inspection required by A300–57–6045, Revision 1, dated August 3, paragraph (i) of this AD thereafter at the follows: 1994, including Appendix 1, Revision 1, applicable time and intervals specified in dated August 3, 1994; Airbus Service paragraphs (j)(1) and (j)(2) of this AD. PART 39—AIRWORTHINESS Bulletin A300–57–6045, Revision 02, dated DIRECTIVES (1) For Model A300 B4–601, B4–603, B4– April 21, 1998, including Appendix 1, 620, and B4–622 airplanes; Model A300 B4– Revision 02, dated April 21, 1998; or Airbus 605R and B4–622R airplanes; and Model ■ 1. The authority citation for part 39 Service Bulletin A300–57–6045, Revision 10, A300 C4–605R Variant F airplanes: Repeat continues to read as follows: dated November 13, 2013. Repeat the the inspection at the applicable time Authority: 49 U.S.C. 106(g), 40113, 44701. detailed visual inspection thereafter at specified in paragraph (j)(1)(i) or (j)(1)(ii) of intervals not to exceed 8,000 flight cycles. this AD. § 39.13 [Amended] (h) Retained Inspection and Repair, With (i) For airplanes that have an average flight Revised Service Information time (AFT) that is equal to or more than one ■ 2. The FAA amends § 39.13 by and one-half hours: Repeat the inspection at removing Airworthiness Directive (AD) This paragraph restates the requirements of intervals not to exceed 5,100 flight cycles or 98–20–27, Amendment 39–10793 (63 paragraph (b) of AD 98–20–27, Amendment 11,000 flight hours, whichever occurs first. FR 50981, September 24, 1998), and 39–10793 (63 FR 50981, September 24, 1998), (ii) For airplanes that have an AFT that is adding the following new AD: with revised service information. If any less than one and one-half hours: Repeat the cracking is suspected or detected during any inspection at intervals not to exceed 5,500 2016–01–18 Airbus: Amendment 39–18378. inspection required by paragraph (g) of this flight cycles or 8,300 flight hours, whichever Docket No. FAA–2015–0824; Directorate AD: Prior to further flight, perform an eddy occurs first. Identifier 2013–NM–191–AD. current inspection to confirm the findings of (2) For Model A300 F4–605R and F4–622R (a) Effective Date the visual inspection, in accordance with airplanes: Repeat the inspection at the Airbus Service Bulletin A300–57–6045, applicable time specified in paragraph This AD becomes effective March 3, 2016. Revision 1, dated August 3, 1994, including (j)(2)(i) or (j)(2)(ii) of this AD. (b) Affected ADs Appendix 1, Revision 1, dated August 3, (i) For airplanes that have an AFT that is 1994; Airbus Service Bulletin A300–57–6045, equal to or more than one and one-half hours: This AD replaces AD 98–20–27, Revision 02, dated April 21, 1998, including Repeat the inspection at intervals not to Amendment 39–10793 (63 FR 50981, Appendix 1, Revision 02, dated April 21, exceed 6,500 flight cycles or 14,100 flight September 24, 1998). 1998; or Airbus Service Bulletin A300–57– hours, whichever occurs first. (c) Applicability 6045, Revision 10, dated November 13, 2013. (ii) For airplanes that have an AFT that is This AD applies to the Airbus airplanes, If any cracking is detected during any eddy less than one and one-half hours: Repeat the certificated in any category, identified in current inspection, prior to further flight, inspection at intervals not to exceed 7,000 paragraphs (c)(1) through (c)(4) of this AD, all repair using a method approved by the flight cycles or 10,600 flight hours, manufacturer serial numbers. Manager, International Branch, ANM–116, whichever occurs first. (1) Airbus Model A300 B4–601, B4–603, FAA, Transport Airplane Directorate; or the Direction Générale de l’Aviation Civile (or its (k) New Requirement of This AD: Repair of B4–620, and B4–622 airplanes. Cracking (2) Airbus Model A300 B4–605R and B4– delegated agent). 622R airplanes. (1) If any crack in the top skin in the area (i) New Requirement of This AD: Initial (3) Airbus Model A300 F4–605R and F4– forward of the front spar attachment is found Inspection 622R airplanes. during any inspection required by paragraph (4) Airbus Model A300 C4–605R Variant F At the applicable time specified in (i) or (j) of this AD: Before further flight, airplanes. paragraph (i)(1) or (i)(2) of this AD: Do a repair using a method approved by the detailed inspection of the wing top skin Manager, International Branch, ANM–116, (d) Subject between ribs 1 and 7 for cracking, in Transport Airplane Directorate, FAA; or the Air Transport Association (ATA) of accordance with the Accomplishment European Aviation Safety Agency (EASA); or America Code 57, Wings. Instructions of Airbus Service Bulletin A300– Airbus’s EASA Design Organization 57–6045, Revision 10, dated November 13, Approval (DOA). (e) Reason 2013. Accomplishment of the initial (2) If any crack or sign of a crack is found This AD was prompted by reports of inspection required by this paragraph in the top skin at or aft of the spar attachment cracking of wing top skin in an area not terminates the requirements of paragraph (g) during any inspection required by paragraph wgreen on DSK2VPTVN1PROD with RULES required for inspection by AD 98–20–27, of this AD. (i) or (j) of this AD: Before further flight, do Amendment 39–10793 (63 FR 50981, (1) For Model A300 B4–601, B4–603, B4– an eddy current inspection of the cracks or September 24, 1998). We are issuing this AD 620, and B4–622 airplanes; Model A300 B4– of the signs of cracking to confirm the to detect and correct fatigue cracking of the 605R and B4–622R airplanes; and Model findings of the detailed inspection, in wing top skin at the front spar joint; such A300 C4–605R Variant F airplanes: At the accordance with the Accomplishment fatigue cracking could result in reduced later of the times specified in paragraphs Instructions of Airbus Service Bulletin A300– structural integrity of the airplane. (i)(1)(i) and (i)(1)(ii) of this AD. 57–6045, Revision 10, dated November 13, VerDate Sep<11>2014 13:11 Jan 27, 2016 Jkt 238001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\28JAR1.SGM 28JAR1

4878 Federal Register / Vol. 81, No. 18 / Thursday, January 28, 2016 / Rules and Regulations 2013. If there is any crack at or aft of the spar AMOCs for the corresponding provisions of www.archives.gov/federal-register/cfr/ibr- attachment, before further flight, repair using this AD. locations.html. a method approved by the Manager, (2) Contacting the Manufacturer: As of the Issued in Renton, Washington, on January International Branch, ANM–116, Transport effective date of this AD, for any requirement 6, 2016. Airplane Directorate, FAA; EASA; or in this AD to obtain corrective actions from Airbus’s EASA DOA. a manufacturer, the action must be Victor Wicklund, accomplished using a method approved by Acting Manager, Transport Airplane (l) No Terminating Action Directorate, Aircraft Certification Service. the Manager, International Branch, ANM– Accomplishment of any repair required by 116, Transport Airplane Directorate, FAA; or [FR Doc. 2016–00611 Filed 1–27–16; 8:45 am] paragraph (k) this AD does not constitute EASA; or Airbus’s EASA DOA. If approved BILLING CODE 4910–13–P terminating action for the repetitive by the DOA, the approval must include the inspections required by paragraph (j) of this DOA-authorized signature. AD. (p) Related Information DEPARTMENT OF TRANSPORTATION (m) No Reporting Required (1) Refer to Mandatory Continuing Although Airbus Service Bulletin A300– Airworthiness Information (MCAI) EASA Federal Aviation Administration 57–6045, Revision 10, dated November 13, Airworthiness Directive 2013–0232R1, dated 2013, specifies to submit certain information October 2, 2013, for related information. This 14 CFR Part 39 to the manufacturer, this AD does not MCAI may be found in the AD docket on the include that requirement. [Docket No. FAA–2015–1427; Directorate Internet at http://www.regulations.gov by Identifier 2013–NM–203–AD; Amendment (n) Credit for Previous Actions searching for and locating Docket No. FAA– 39–18380; AD 2016–02–01] 2015–0824. This paragraph provides credit for actions (2) Service information identified in this RIN 2120–AA64 required by paragraphs (i), (j) and (k) of this AD that is not incorporated by reference is AD, if those actions were performed before available at the addresses specified in Airworthiness Directives; Airbus the effective date of this AD using the Airbus paragraphs (q)(5) and (q)(6) of this AD. Airplanes service bulletins specified in paragraphs (n)(1) through (n)(8) of this AD, which are not (q) Material Incorporated by Reference AGENCY: Federal Aviation incorporated by reference in this AD. (1) The Director of the Federal Register (1) Airbus Service Bulletin A300–57–6045, Administration (FAA), Department of approved the incorporation by reference Transportation (DOT). dated March 18, 1993. (IBR) of the service information listed in this (2) Airbus Service Bulletin A300–57–6045, ACTION: Final rule. paragraph under 5 U.S.C. 552(a) and 1 CFR Revision 03, dated October 25, 1999. part 51. (3) Airbus Service Bulletin A300–57–6045, SUMMARY: We are superseding (2) You must use this service information Revision 04, dated January 13, 2002. as applicable to do the actions required by Airworthiness Directive (AD) 96–18–06 (4) Airbus Service Bulletin A300–57–6045, for certain Airbus Model A320–211 and this AD, unless this AD specifies otherwise. Revision 05, dated June 13, 2003. –231 airplanes. AD 96–18–06 required (3) The following service information was (5) Airbus Service Bulletin A300–57–6045, visual inspections to detect cracks of the approved for IBR on March 3, 2016. Revision 06, dated January 13, 2005. (6) Airbus Service Bulletin A300–57–6045, (i) Airbus Service Bulletin A300–57–6045, pressurized floor fittings at frame 36, Revision 10, dated November 13, 2013. and renewal of the zone protective Revision 07, dated August 14, 2008. (ii) Reserved. finish or replacement of fittings with (7) Airbus Service Bulletin A300–57–6045, (4) The following service information was new fittings if necessary. Since we Revision 08, dated June 6, 2011. approved for IBR on October 29, 1998 (63 FR (8) Airbus Service Bulletin A300–57–6045, issued AD 96–18–06, an extended 50981, September 24, 1998). Revision 09, dated May 21, 2013. service goal analysis by the (i) Airbus Service Bulletin A300–57–6045, (o) Other FAA AD Provisions Revision 1, dated August 3, 1994, including manufacturer revealed that the Appendix 1, Revision 1, dated August 3, compliance times and repetitive The following provisions also apply to this AD: 1994, which contains the following list of inspection intervals should be reduced (1) Alternative Methods of Compliance effective pages: Page numbers 1 through 10, to meet the design service goal. This AD (AMOCs): The Manager, International Revision 1, dated August 3, 1994; Appendix retains the requirements of AD 96–18– Branch, ANM–116, Transport Airplane 1, pages 1 and 2, Revision 1, dated August 06, with reduced compliance times and Directorate, FAA, has the authority to 3, 1994; and Appendix 1, pages 3 through 6, repetitive inspection intervals. This AD approve AMOCs for this AD, if requested dated March 18, 1993. also adds Model A320–212 airplanes to using the procedures found in 14 CFR 39.19. (ii) Airbus Service Bulletin A300–57–6045, Revision 02, dated April 21, 1998, including the applicability. We are issuing this AD In accordance with 14 CFR 39.19, send your Appendix 1, Revision 02, dated April 21, to detect and correct fatigue cracking in request to your principal inspector or local Flight Standards District Office, as 1998. the pressurized floor fittings at frame 36, appropriate. If sending information directly (5) For service information identified in which could result in failure of a floor to the International Branch, send it to ATTN: this AD, contact Airbus SAS, Airworthiness fitting and subsequent depressurization Dan Rodina, Aerospace Engineer, Office—EAW, 1 Rond Point Maurice of the fuselage. International Branch, ANM–116, Transport Bellonte, 31707 Blagnac Cedex, France; DATES: This AD becomes effective Airplane Directorate, FAA, 1601 Lind telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth- March 3, 2016. Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. eas@airbus.com; Internet http:// The Director of the Federal Register Information may be emailed to: 9-ANM-116- www.airbus.com. approved the incorporation by reference AMOC-REQUESTS@faa.gov. (6) You may view this service information of certain publications listed in this AD (i) Before using any approved AMOC, at the FAA, Transport Airplane Directorate, as of March 3, 2016. notify your appropriate principal inspector, 1601 Lind Avenue SW., Renton, WA. For The Director of the Federal Register or lacking a principal inspector, the manager information on the availability of this approved the incorporation by reference wgreen on DSK2VPTVN1PROD with RULES of the local flight standards district office/ material at the FAA, call 425–227–1221. of a certain other publication listed in certificate holding district office. The AMOC (7) You may view this service information this AD as of October 10, 1996. approval letter must specifically reference that is incorporated by reference at the this AD. National Archives and Records ADDRESSES: You may examine the AD (ii) AMOCs approved previously for AD Administration (NARA). For information on docket on the Internet at http:// 98–20–27, Amendment 39–10793 (63 FR the availability of this material at NARA, call www.regulations.gov/ 50981, September 24, 1998), are approved as 202–741–6030, or go to: http:// #!docketDetail;D=FAA-2015-1427; or in VerDate Sep<11>2014 13:11 Jan 27, 2016 Jkt 238001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\28JAR1.SGM 28JAR1


Document Created: 2018-02-02 12:40:58
Document Modified: 2018-02-02 12:40:58
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal rule.
DatesThis AD becomes effective March 3, 2016.
ContactDan 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 Citation81 FR 4875 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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