Airworthiness Directives; Airbus Airplanes

[Federal Register Volume 82, Number 146 (Tuesday, August 1, 2017)]
[Rules and Regulations]
[Pages 35644-35647]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-15808]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9055; Directorate Identifier 2016-NM-071-AD; 
Amendment 39-18977; AD 2017-15-17]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A300 B4-600R series airplanes, Model A300 C4-605R Variant 
F airplanes, and Model A300 F4-600R series airplanes. This AD was 
prompted by the results of a full stress analysis of the lower area of 
a certain frame that revealed that a crack could occur in this area 
after a certain number of flight cycles. This AD requires an inspection 
of the lower area of a certain frame radius for cracking, and 
corrective action if necessary. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective September 5, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 5, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email [email protected]; Internet 
http://www.airbus.com. You may view this 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-2016-
9055.

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-
9055; 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 Office (telephone 
800-647-5527) is 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 20590.

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 supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 by adding an AD that would apply to certain Airbus 
Model A300 B4-600R series airplanes, Model A300 C4-605R Variant F 
airplanes, and Model A300 F4-600R series airplanes. The SNPRM published 
in the Federal Register on March 2, 2017 (82 FR 12314) (``the SNPRM''). 
We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that 
published in the Federal Register on September 8, 2016 (81 FR 62026) 
(``the NPRM''). The NPRM proposed to require an inspection of the lower 
area of a certain frame radius for cracking, and corrective action if 
necessary. The NPRM was prompted by the results of a full stress 
analysis of the lower area of a certain frame that revealed a crack 
could occur in the forward fitting lower radius of a certain frame 
after a certain number of flight cycles. The SNPRM proposed to require 
extending the area to be inspected for cracking and adding an 
inspection for previously inspected airplanes. We are issuing this AD 
to detect and correct cracking in the forward fitting lower radius of a 
certain frame. Such cracking could reduce the structural integrity of 
the fuselage.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0179, dated September 12, 2016 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the

[[Page 35645]]

MCAI''), which superseded EASA AD 2016-0085, dated April 28, 2016. EASA 
AD 2016-0085 was the MCAI referred to in the NPRM.
    The MCAI was issued to correct an unsafe condition for certain 
Airbus Model A300 B4-600R series airplanes, Model A300 C4-605R Variant 
F airplanes, and Model A300 F4-600R series airplanes. The MCAI states:

    Following a full stress analysis of the Frame (FR) 40 lower 
area, supported by a Finite Element Model (FEM), of the post-mod 
10221 configuration, it was demonstrated that, for the FR40 forward 
fitting lower radius, a crack could occur after a certain amount of 
flight cycles (FC).
    This condition, if not detected and corrected, could reduce the 
structural integrity of the fuselage.
    To address this potential unsafe condition, Airbus established 
that crack detection could be achieved through a special detailed 
inspection (SDI) using a high frequency eddy current (HFEC) method, 
and issued Alert Operators Transmission (AOT) A57W009-16 to provide 
those inspection instructions.
    Consequently, EASA issued AD 2016-0085 to require a one-time SDI 
of the FR40 lower area and, depending on findings, accomplishment of 
applicable corrective action(s).
    Since that [EASA] AD was issued, further cracks were detected, 
originating from the fastener hole, and, based on these findings, it 
was determined that inspection area must be enlarged, and Airbus AOT 
A57W009-16 Revision (Rev.) 01 was issued accordingly.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2016-0085, which is superseded, extends the 
area of inspection, and requires an additional inspection for 
aeroplanes previously inspected.
    The one-time SDI for high cycle aeroplanes is intended to 
mitigate the highest risks within the fleet. Airbus is currently 
developing instructions for repetitive inspections that are likely 
to be the subject of further [EASA] AD action.

    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-
9055.

Comments

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

Requests To Refer to New Service Information

    FedEx and United Parcel Service (UPS) requested that the SNPRM be 
revised to refer to a service bulletin that Airbus plans to release to 
replace Airbus Alert Operators Transmission (AOT) A57W009-16, Rev 01, 
including Appendices 1 and 2, dated July 13, 2016 (``AOT A57W009-16, 
Rev 01''). AOT A57W009-16, Rev 01, was identified as the service 
information to be used to accomplish the actions specified in the 
SNPRM. UPS noted that the service bulletin would include information 
based on in-service reports from operators who had accomplished the 
inspection identified in AOT A57W009-16, Rev 01, and based on the 
results of a full stress analysis of the frame (FR) 40 lower area. 
Based on this information Airbus changed the initial inspection 
compliance time from what was specified in AOT A57W009-16, Rev 01, and 
established repetitive inspection intervals. FedEx and UPS both 
mentioned that to reduce the number of alternative method of compliance 
(AMOC) requests, the SNPRM should be revised to include the service 
bulletin. UPS also noted that including the service information would 
benefit the FAA because the FAA could avoid future rulemaking regarding 
this issue.
    We partially agree with the commenters' requests. After the SNPRM 
was published, Airbus issued Service Bulletin A300-57-6120, dated April 
28, 2017. However, instead of removing the reference to AOT A57W009-16, 
Rev 01, in this AD, we have added paragraph (j) to this AD to allow 
operators to do the required actions in accordance with the 
Accomplishment Instructions of Service Bulletin A300-57-6120, dated 
April 28, 2017. We have redesignated the subsequent paragraphs 
accordingly.

Request To Revise Reporting Method

    FedEx requested that paragraph (j) of the proposed AD (in the 
SNPRM) be revised to provide flexibility regarding the method of 
reporting inspection results to Airbus. FedEx stated that to utilize 
the Airbus online reporting system would require substantial updates to 
its information technology systems and personnel training; therefore, 
it is not prepared to utilize the online reporting system at this time. 
FedEx suggested that the older method of reporting be allowed until it 
has the computer and personnel resources in place to utilize online 
reporting.
    We agree with the commenter's request. We have determined that 
operators may use either the online or older reporting method. We have 
revised paragraph (k) of this AD (paragraph (j) of the proposed AD (in 
the SNPRM)) to allow operators to report inspection findings using the 
online reporting system or submit the results to Airbus in accordance 
with the instructions of Airbus Service Bulletin A300-57-6120, dated 
April 28, 2017.

Conclusion

    We reviewed the relevant data, considered 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 minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
SNPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the SNPRM.
    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

    We reviewed Airbus AOT A57W009-16, Rev 01, including Appendices 1 
and 2, dated July 13, 2016. This service information describes 
procedures for a one-time inspection of the forward fitting lower 
radius of FR 40 for cracking, and corrective action.
    We have also reviewed Airbus Service Bulletin A300-57-6120, dated 
April 28, 2017. This service information describes procedures for 
repetitive inspections of the forward fitting lower radius of FR 40 for 
cracking, and corrective action.
    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 94 airplanes of U.S. registry.

[[Page 35646]]

    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.........................  3 work-hours x $85 per hour              $0            $255         $23,970
                                      = $255.
Report.............................  1 work-hour x $85 per hour                0              85           7,990
                                      = $85.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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):

2017-15-17 Airbus: Amendment 39-18977; Docket No. FAA-2016-9055; 
Directorate Identifier 2016-NM-071-AD.

(a) Effective Date

    This AD is effective September 5, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of 
this AD, on which Airbus Modification 10221 was embodied in 
production.
    (1) Airbus Model A300 B4-605R and B4-622R airplanes.
    (2) Airbus Model A300 C4-605R Variant F airplanes.
    (3) Airbus Model A300 F4-605R and F4-622R airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by the detection of cracking that 
originated from the fastener holes in the forward fitting lower 
radius of frame (FR) 40. We are issuing this AD to detect and 
correct cracking in the forward fitting lower radius of FR 40. Such 
cracking could reduce the structural integrity of the fuselage.

(f) Compliance

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

(g) Inspection

    At the later of the compliance times specified in paragraphs 
(g)(1) and (g)(2) of this AD, do a high frequency eddy current 
(HFEC) inspection of the lower area of the FR 40 radius for 
cracking, in accordance with paragraph 4.2.2 in Airbus Alert 
Operators Transmission (AOT) A57W009-16, Rev 01, including 
Appendices 1 and 2, dated July 13, 2016.
    (1) Prior to exceeding 19,000 total flight cycles or 41,000 
total flight hours since the airplane's first flight, whichever 
occurs first.
    (2) Within 300 flight cycles or 630 flight hours after the 
effective date of this AD, whichever occurs first.

(h) Additional Inspection for Previously Inspected Airplanes

    For airplanes on which the HFEC inspection required by paragraph 
(g) of this AD was accomplished before the effective date of this AD 
using the procedures in Airbus AOT A57W009-16, Rev 00, including 
Appendices 1 and 2, dated February 25, 2016: Within 300 flight 
cycles or 630 flight hours after the effective date of this AD, 
whichever occurs first, do a one-time additional HFEC inspection of 
the lower area of the FR 40 radius for cracking, in accordance with 
paragraph 4.2.2 in Airbus

[[Page 35647]]

AOT A57W009-16, Rev 01, including Appendices 1 and 2, dated July 13, 
2016.

(i) Corrective Action

    If any crack is found during the inspection required by 
paragraph (g) or (h) of this AD: Before further flight, do the 
applicable corrective actions in accordance with the procedures in 
Airbus AOT A57W009-16, Rev 01, including Appendices 1 and 2, dated 
July 13, 2016. Where AOT A57W009-16, Rev 01, including Appendices 1 
and 2, dated July 13, 2016, specifies to contact Airbus for 
appropriate action, accomplish the corrective actions in accordance 
with the procedures specified in paragraph (m)(2) of this AD.

(j) Optional Service Information for Accomplishing Required Actions

    Accomplishment of the actions required by paragraphs (g), (h), 
and (i) of this AD, in accordance with, and at the compliance times 
specified in, the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-6120, dated April 28, 2017, is acceptable for 
compliance with the requirements of those paragraphs.

(k) Reporting Requirement

    Submit a report of all findings (both positive and negative) 
from the inspection required by paragraph (g) of this AD to Airbus 
Customer Services through TechRequest on Airbus World (https://w3.airbus.com/) by selecting Engineering Domain and ATA 57-10; or 
submit the results to Airbus in accordance with the procedures in 
Airbus Service Bulletin A300-57-6120, dated April 28, 2017.
    (1) For airplanes on which the inspection specified in paragraph 
(g) of this AD is accomplished on or after the effective date of 
this AD: Submit the report within 30 days after performing the 
inspection.
    (2) For airplanes on which the inspection specified in paragraph 
(g) of this AD is accomplished before the effective date of this AD: 
Submit the report within 30 days after the effective date of this 
AD.

(l) Credit for Previous Actions

    This paragraph provides credit for the action required by 
paragraph (g) of this AD, if that action was done before the 
effective date of this AD using Airbus AOT A57W009-16, Rev 00, 
including Appendices 1 and 2, dated February 25, 2016, provided the 
inspection required by paragraph (h) of this AD is accomplished.

(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, 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 the attention of the person identified in 
paragraph (n)(2) of this AD. Information may be emailed to: [email protected].
    (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 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0179, dated September 12, 2016, 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-2016-9055.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, FAA, 1601 Lind 
Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-
227-1149.

(o) 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 Alert Operators Transmission A57W009-16, Rev 01, 
including Appendices 1 and 2, dated July 13, 2016.
    (ii) Airbus Service Bulletin A300-57-6120, dated April 28, 2017.
    (3) 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.
    (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 July 19, 2017.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-15808 Filed 7-31-17; 8:45 am]
 BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T02:19:57.562802+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

54c8320d5b178689d7787e7b87398b0a878fc4c8c86362b6b0d12777a71a0ae9

Text SHA-256

4c17b19ebe014f4feef4bf427e84e9a040755628d3cf95ac2ff0cbf91298f6c1