
[Federal Register Volume 81, Number 128 (Tuesday, July 5, 2016)]
[Rules and Regulations]
[Pages 43472-43475]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-15356]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-8134; Directorate Identifier 2014-NM-256-AD; 
Amendment 39-18572; AD 2016-13-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
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 AD was 
prompted by a report of cracking of the lower tension bolt area at the 
rib one junction (both sides) of the lower wing. This AD requires 
repetitive inspections for cracking of the fasteners and of the fitting 
around the fastener holes at the frame (FR) 40 lower wing location, and 
corrective actions if necessary. We are issuing this AD to detect and 
correct crack initiation of the fittings of the FR40 lower wing 
locations, which could result in reduced structural integrity of the 
airplane.

DATES: This AD becomes effective August 9, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 9, 
2016.

ADDRESSES: For Airbus service information identified in this final 
rule, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 
96; fax +33 5 61 93 44 51; email 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-2015-8134.

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-2015-
8134; 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 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.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

[[Page 43473]]

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all 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). The NPRM published in the 
Federal Register on December 31, 2015 (80 FR 81786) (``the NPRM'').
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0272, dated December 12, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A300 
series airplanes; 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). The MCAI states:

    Following the A300-600 Extended Service Goal (ESG2) exercise, 
specific inspections for cracks were performed in fittings of frame 
(FR) 40, in areas not covered by any existing task.
    Findings were identified on an A300-600 aeroplane withdrawn from 
service in the lower tension bolt area at rib one junction (both 
sides).
    This condition, if not detected and corrected, could lead to 
crack initiation, affecting the structural integrity of the 
aeroplane.
    To address this potential unsafe condition, an inspection 
programme was developed for the fitting around the fastener holes 
located at FR40 lower wing junction, left-hand (LH) and right-hand 
(RH) sides.
    For the reasons described above, this [EASA] AD requires 
repetitive High Frequency Eddy Current (HFEC) inspections and 
rototest inspections of the fitting around the fastener holes 
located at FR40 lower wing junction and, depending on findings, 
accomplishment of a repair.

    The corrective actions include a repair using a method approved by 
the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the EASA; or Airbus's EASA Design Organization 
Approval (DOA).
    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-2015-
8134.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request To Clarify Corrective Actions

    FedEx asked that the corrective actions identified in paragraph (i) 
of the proposed AD be clarified. FedEx stated that paragraph (h)(1) of 
the proposed AD specifies ``If one or more of the hole diameters is 
outside the tolerance of the nominal diameter, and outside the 
tolerance of the first and second oversize: Do the applicable 
corrective actions required by paragraph (i) of this AD.'' FedEx added 
that paragraph (i) of the proposed AD specifies ``If, during any 
inspection required by this AD, any crack is found, or one or more of 
the hole diameters are outside the tolerance of the nominal diameter: 
Repair before further flight 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).'' FedEx noted that paragraph (i) should 
specify ``one or more of the hole diameters are outside the tolerance 
of the nominal diameter and outside the tolerance of the first and 
second oversize'' to match the language in paragraph (h)(1) of the 
proposed.
    We agree. We have confirmed that the language in paragraph (i) of 
this AD should match the language in paragraph (h)(1) of this AD. We 
have changed paragraph (i) of this AD accordingly.

Request To Revise Compliance Time

    United Parcel Service (UPS) asked that we revise the compliance 
time for the rototest inspections specified by paragraph (h) of the 
proposed AD to a threshold based on total service time, rather than 
calendar time alone. UPS stated that, based on reported findings to 
date, the crack growth rate is so slow it will not affect the immediate 
airworthiness of the airplane. UPS suggested that we add a threshold of 
11,900 total flight cycles.
    We do not agree with the commenter's request. The commenter 
provided no data to substantiate the proposed compliance time based on 
flight cycles. In developing an appropriate compliance time for this 
AD, we considered not only the urgency associated with the subject 
unsafe condition, but also the manufacturer's recommendations, EASA's 
recommendations, and the practical aspect of accomplishing the required 
inspections within a period of time that corresponds to the normal 
scheduled maintenance for most affected operators. After considering 
all the available information, we have determined that the compliance 
time, as proposed, represents an appropriate interval of time in which 
the required actions can be performed in a timely manner within the 
affected fleet, while still maintaining an adequate level of safety. 
However, affected operators may request an alternative method of 
compliance (AMOC) to request a change to the compliance time under the 
provisions of paragraph (j) of this AD by submitting data and analysis 
substantiating that the change would provide an acceptable level of 
safety. We have not changed this AD regarding this issue.

Request To Remove High Frequency Eddy Current (HFEC) Inspections

    UPS asked that the HFEC inspections specified by paragraph (g) of 
the proposed AD be removed. UPS stated that the HFEC inspection 
requirement does not enhance airplane safety because only substantial 
damage can be detected by this method, due to a restricted inspection 
area. UPS also stated that the smallest crack detectable by an HFEC 
inspection method is calculated to be 7.5 mm in length, not taking into 
account the inspection surface radius and the limited access to the 
inspection area. UPS added that fastener location and potential 
obstacles affect consistent probe movement, which increases the chance 
for inconsistent inspection readings.
    We do not agree with the commenter's request. The HFEC inspection 
required by paragraph (g) of this AD is a necessary interim measure 
intended to find cracking before the required compliance time for the 
rototest inspection in paragraph (h) of this AD. As the commenter 
acknowledged, a 7.5-mm crack may be detected during an HFEC inspection 
within 1,000 flight hours. That same 7.5-mm crack, undetected for 3 
years until the rototest inspection is done, could grow and result in 
reduced structural integrity of the airplane; therefore, the repetitive 
HFEC inspections must be retained in this AD. If no cracking is found, 
the HFEC inspection can be repeated, or terminated when the rototest 
inspection is accomplished. However, affected operators may request 
approval of an AMOC to do the rototest inspections only, under the 
provisions of paragraph (j) of this AD by submitting data and analysis, 
and a compliance schedule, substantiating that the change would provide 
an acceptable level of safety. We have not changed this AD regarding 
this issue.

[[Page 43474]]

Request To Correct Typographical Errors in Service Information

    FedEx asked that the typographical errors for the structural repair 
manual (SRM) references in Airbus Service Bulletin A300-57-6115, dated 
April 4, 2014, be corrected so FedEx can use them to comply with the 
NPRM requirements. FedEx stated that Airbus was informed of and 
acknowledged these typographical errors, but currently no changes have 
been made to the service information. FedEx noted that the service 
information listed SRM 51-40-13 for the application of special 
coatings, but the correct reference is SRM 51-23-20. FedEx also noted 
that the service information listed SRM 51-40-12 for the application of 
paint coatings, but the correct reference is SRM 51-23-10.
    We agree with the commenter's concerns. We have changed paragraph 
(g) of this AD to clarify the correct SRM references to be used.

Conclusion

    We reviewed the available data 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 
minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed the following service information.
     Airbus Service Bulletin A300-57-0257, excluding Appendix 
01 and including Appendix 02, dated April 4, 2014.
     Airbus Service Bulletin A300-57-6115, dated April 4, 2014.

The service information describes procedures for repetitive inspections 
for cracking of the fasteners and of the fitting around the fastener 
holes at the FR40 lower wing location. 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 166 airplanes of U.S. registry.
    We also estimate that it takes about 12 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 $169,320, or $1,020 per product.
    We have received no definitive data that would enable us to provide 
a cost estimate 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.

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 adding the following new airworthiness 
directive (AD):

2016-13-08 Airbus: Amendment 39-18572. Docket No. FAA-2015-8134; 
Directorate Identifier 2014-NM-256-AD.

(a) Effective Date

    This AD becomes effective August 9, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
    (2) Airbus 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 a report of cracking of the lower 
tension bolt area at rib one junction (both sides) of the lower 
wing. We are issuing this AD to detect and correct crack initiation 
of the fittings of the frame (FR) 40 lower wing locations, which 
could result in reduced structural integrity of the airplane.

(f) Compliance

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

(g) Repetitive High Frequency Eddy Current (HFEC) Inspections

    Within 1,000 flight hours after the effective date of this AD: 
Do an HFEC inspection for cracking of fasteners 1 through 3 at the 
left-hand and right-hand sides of the FR40 lower junction, and of 
the fitting around the fastener holes, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-0257, 
excluding Appendix 01 and including Appendix 02, dated April 4, 2014 
(for Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-
203 airplanes); or Airbus Service Bulletin A300-57-6115, dated April 
4, 2014 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, F4-622R, and C4-605R Variant F airplanes). If no 
cracking is found, repeat the HFEC inspection at intervals not to 
exceed 1,000 flight hours until a rototest inspection required by 
paragraph (h)(2) of this AD has been done. Where Airbus Service 
Bulletin

[[Page 43475]]

A300-57-6115, dated April 4, 2014, refers to Structural Repair 
Manual (SRM) 51-40-13 for applying special protection, the correct 
reference is SRM 51-23-20; and to SRM 51-40-12 for applying paint 
coatings, the correct reference is SRM 51-23-10.

(h) Repetitive Rototest Inspections

    Within 36 months after the effective date of this AD: Remove the 
fasteners and measure the diameter of the fastener holes; and, 
before further flight, do the applicable actions required by 
paragraph (h)(1) or (h)(2) of this AD, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-0257, 
excluding Appendix 01 and including Appendix 02, dated April 4, 2014 
(for Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-
203 airplanes); or Airbus Service Bulletin A300-57-6115, dated April 
4, 2014 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, F4-622R, and C4-605R Variant F airplanes).
    (1) If one or more of the hole diameters is outside the 
tolerance of the nominal diameter, and outside the tolerance of the 
first and second oversize: Do the applicable corrective actions 
required by paragraph (i) of this AD.
    (2) If all of the hole diameters are within the tolerance of the 
nominal diameter or the first or second oversize: Do detailed and 
rototest inspections for cracking of the fastener holes at the left-
hand and right-hand sides of the FR40 lower junction, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A300-57-0257, excluding Appendix 01 and including Appendix 02, dated 
April 4, 2014 (for Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, 
B4-103, and B4-203 airplanes); or Airbus Service Bulletin A300-57-
6115, dated April 4, 2014 (for Model A300 B4-601, B4-603, B4-620, 
B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F 
airplanes). If no cracking is found, before further flight, install 
new fasteners of the same diameter in special clearance fit for 
fasteners 1 through 3 of the FR40 lower junction, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletins A300-57-
0257, excluding Appendix 01 and including Appendix 02, dated April 
4, 2014; or Airbus Service Bulletin A300-57-6115, dated April 4, 
2014. Repeat the rototest inspection thereafter at intervals not to 
exceed 7,000 flight cycles. Accomplishment of a rototest inspection 
required by this paragraph terminates the repetitive HFEC 
inspections required by paragraph (g) of this AD.

(i) Corrective Actions

    If, during any inspection required by this AD, any crack is 
found, or one or more of the hole diameters is outside the tolerance 
of the nominal diameter, and outside the tolerance of the first and 
second oversize: Repair before further flight in accordance with a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the European Aviation Safety 
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).

(j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (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.
    (3) Required for Compliance (RC): Except as required by 
paragraph (i) of this AD: If any service information contains 
procedures or tests that are identified as RC, those procedures and 
tests must be done to comply with this AD; any procedures or tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operator's maintenance or 
inspection program without obtaining approval of an AMOC, provided 
the procedures and tests identified as RC can be done and the 
airplane can be put back in an airworthy condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.

(k) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA Airworthiness Directive 2014-0272, dated December 12, 2014, 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-2015-8134.

(l) 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.
    (i) Airbus Service Bulletin A300-57-0257, excluding Appendix 01 
and including Appendix 02, dated April 4, 2014.
    (ii) Airbus Service Bulletin A300-57-6115, dated April 4, 2014.
    (3) For Airbus service information identified in this final 
rule, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 
36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (4) 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.
    (5) 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 June 21, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-15356 Filed 7-1-16; 8:45 am]
 BILLING CODE 4910-13-P


