[Federal Register Volume 82, Number 2 (Wednesday, January 4, 2017)]
[Rules and Regulations]
[Pages 712-716]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-30117]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0143; Directorate Identifier 2012-NM-113-AD; 
Amendment 39-18753; AD 2016-25-27]
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 B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, 
F4-622R, and C4-605R variant F airplanes. This AD was prompted by 
reports of cracks in the frame base fittings connecting the frame lower 
positions to the center wing box. This AD requires repetitive detailed 
inspections for cracking of the lower frame fittings of the frame foot, 
and replacement with a new frame foot if cracking is found. This AD 
also provides optional terminating action for the repetitive 
inspections. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective February 8, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 8, 
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-2014-0143.

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-2014-
0143; or in person at the Docket Management Facility between 9 a.m.

[[Page 713]]

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 all Airbus 
Model A300 B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, 
and C4-605R variant F airplanes. The SNPRM published in the Federal 
Register on July 7, 2016 (81 FR 44241) (``the SNPRM''). We preceded the 
SNPRM with a notice of proposed rulemaking (NPRM) that published in the 
Federal Register on March 19, 2014 (79 FR 15266) (``the NPRM''). The 
NPRM was prompted by reports of cracks in the frame base fittings 
connecting the frame lower positions to the center wing box. The NPRM 
proposed to require repetitive detailed inspections of the lower frame 
fittings, related investigative actions, and corrective actions if 
necessary. The SNPRM proposed to replace the proposed requirements in 
the NPRM with new repetitive detailed inspections for cracking of the 
lower frame fittings of the frame foot, and replacement with a new 
frame foot if cracking is found. The SNPRM also proposed to provide 
optional terminating action for the repetitive inspections. We are 
issuing this AD to detect and correct cracking of the lower frame 
fittings, which 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 AD 
2015-0217, dated October 30, 2015 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition on all Airbus Model A300 B4-603, B4-620, 
B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R variant F 
airplanes. The MCAI states:

    During accomplishment of Airbus Service Bulletin (SB) A300-53-
6111 (EASA AD 2012-0103), addressing detailed visual inspections of 
the lower frame fittings between Frame (FR) 41 and FR46, a crack was 
detected on one A300-600 aeroplane in the area 2 of the foot of FR46 
at junction radius level.
    This frame, previously repaired due to a crack finding in the 
frame foot area 1, was not due to be inspected before reaching the 
post-repair inspection threshold, i.e. 45,400 flight cycles since 
repair embodiment.
    Further investigation determined that the repairs specified in 
Airbus SB A300-53-6111 were of limited effect to prevent cracking in 
the frame foot area 2.
    This condition, if not detected and corrected, could affect the 
structural integrity of the fuselage of all aeroplanes operated up 
to the extended service goal (ESG).
    As a temporary action and until an improvement of the existing 
repairs was made available, EASA issued AD 2012-0229 [AD * * *] to 
require a one-time detailed inspection (DET) of the frame feet that 
were repaired in accordance with Airbus SB A300-53-6111, and the 
reporting of findings to Airbus.
    Since that [EASA] AD was issued, a detailed study was performed 
resulting in the development of a new inspection programme.
    Consequently, Airbus cancelled SB A300-53-6111 and replaced it 
with SB A300-53-6177, introducing repetitive DET of the lower frame 
fittings between FR41 and FR46 for the entire fleet. In addition to 
this new inspection programme, Airbus designed a new frame foot 
which can be installed on aeroplanes through Airbus SB A300-53-6176.
    For the reasons described above, this [EASA] AD supersedes EASA 
AD 2012-0103, not retaining its requirements, and instead requires 
the new inspection programme for the lower frame fittings. This 
[EASA] AD also introduces an optional terminating action for the 
repetitive inspections required by the [EASA] AD.

    Corrective actions include replacing any cracked lower frame 
fittings with a new frame foot. 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-2014-0143.

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.

Request To Extend Compliance Time for Reporting Requirement

    United Parcel Service (UPS) asked that the compliance time for 
submitting the inspection report specified in paragraph (h) of the 
proposed AD (in the SNPRM) be extended from 30 to 60 days. UPS stated 
that accomplishing the inspection may occur many days before the final 
task signoff (i.e., restoring access due to other work in the area), 
risking noncompliance with the 30-day requirement.
    We agree to extend the compliance time for the reporting 
requirement in this AD to 60 days, because we have determined that this 
longer compliance time does not affect continued operational safety. We 
have changed paragraph (i) of this AD accordingly.

Request for Clarification of Compliance Time

    Airbus asked that we clarify the compliance time for the 
inspections specified in paragraph (g) of the proposed AD (in the 
SNPRM). Airbus stated that unless Airbus Service Bulletin A300-53-6177, 
dated May 20, 2015, specifies differently, the inspection thresholds 
should be counted from the first flight of the airplane, not from the 
effective date of the AD. Airbus added that the compliance time 
provided in the proposed AD could be confusing to operators. Airbus 
also stated that for airplanes on which the inspections have not been 
done as of the effective date of the AD, no grace period is provided, 
which is a burden on operators.
    We agree that clarification is necessary.
    We agree that the compliance time identified in the ``Threshold'' 
column of paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin 
A300-53-6177, dated May 20, 2015, refers to accumulated flight cycles 
or flight hours on the airplane since its first flight, but only if 
Airbus Service Bulletin A300-53-6177, dated May 20, 2015, does not 
specify differently. We redesignated paragraph (h) in the SNPRM as 
paragraph (i) of this AD, and redesignated subsequent paragraphs 
accordingly. We added clarification of the compliance times for the 
thresholds in paragraph (h)(1) of this AD.
    We acknowledge that a grace period was not provided for all 
configurations. We removed the grace period exception language from 
paragraph (g) of the proposed AD (in the SNPRM) and moved it to 
paragraph (h)(2) of this AD. Paragraph (h)(2) of this AD explains that 
where grace periods specified in Airbus Service Bulletin A300-53-6177, 
dated May 20, 2015, refer to the issue date of certain service 
information, those compliance times are after the effective date of the 
AD. The exception in paragraph (h)(2) of this AD does not apply to 
compliance times specified as

[[Page 714]]

thresholds in Airbus Service Bulletin A300-53-6177, dated May 20, 2015.
    In addition, we have determined that the actions for Configuration 
004 airplanes identified in Airbus Service Bulletin A300-53-6177, dated 
May 20, 2015, must be clarified. For Configuration 004 airplanes 
identified in Airbus Service Bulletin A300-53-6177, dated May 20, 2015, 
the actions required by paragraph (g) of this AD cannot be accomplished 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6177, dated May 20, 2015. Paragraph 1.E., 
``Compliance,'' of Airbus Service Bulletin A300-53-6177, dated May 20, 
2015, specifies the action for Configuration 004 airplanes as 
contacting and reporting to Airbus. Therefore, we have added paragraph 
(h)(3) to this AD to require operators to contact 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), for corrective actions for Configuration 
004 airplanes.

Request for Clarification of Inspections for Airplanes With a 
Previously Replaced Frame Foot

    UPS asked for clarification of the inspection requirements 
specified in paragraph (g) of the proposed AD (in the SNPRM) for 
airplanes that previously replaced a frame foot per Airbus Service 
Bulletin A300-53-6111. UPS stated that if cracking was found during the 
inspections using that service information there were two options 
available: Installing a reinforcing doubler on the damaged fitting or 
replacing the fitting with a new part. UPS added that in Airbus Service 
Bulletin A300-53-6177, dated May 20, 2015, the inspection requirements 
are defined for airplanes previously inspected and found with no 
cracks, or fittings repaired per Airbus Service Bulletin A300-53-6111. 
UPS noted that it is not clear how to address airplanes on which the 
cracked fittings were replaced instead of installing a reinforcing 
repair. UPS asked that fittings replaced with a new part per Airbus 
Service Bulletin A300-53-6111 be treated as a previously inspected 
fitting with no crack findings, with repetitive inspections done per 
Airbus Service Bulletin A300-53-6177, dated May 20, 2015, using 
Configuration 001 instructions. UPS stated that this proposal is 
conservative and exceeds the inspection requirements in the proposed AD 
(in the SNPRM).
    We agree that clarification is necessary. Airbus Service Bulletin 
A300-53-6177, dated May 20, 2015, defines four configurations: 
Configuration 001 for a frame foot that was never repaired, 
Configuration 002 for a frame foot that was preventatively repaired, 
Configuration 003 for a frame foot repaired in Area 1 as specified in 
Airbus Service Bulletin A300-53-6111 or with certain other repairs, and 
Configuration 004 for any frame foot not addressed by Configurations 1 
through 3. If a new frame foot is installed on an airplane, it would be 
classified as Configuration 001. We have not changed this AD in this 
regard.

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:
     Are consistent with the intent that was proposed in the 
SNPRM for correcting the unsafe condition; and
     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

    Airbus has issued Service Bulletin A300-53-6177, dated May 20, 
2015. The service information describes procedures for repetitive 
detailed inspections for cracking of the lower frame fittings between 
FR41 and FR46. Airbus has also issued Service Bulletin A300-53-6176, 
dated May 20, 2015. The service information describes procedures for 
replacing all lower frame feet between frame FR41 and FR46 with new, 
improved frame feet. 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 123 airplanes of U.S. registry.
    We estimate that it takes about 541 work-hours per product to 
comply with the basic requirements of this AD, and 1 work-hour per 
product for reporting. 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 $5,666,610, or $46,070 per product.
    We estimate that the optional terminating modification will take 
about 529 work-hours and require parts costing $131,500, for a cost of 
$176,465.

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;

[[Page 715]]

    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):

2016-25-27 Airbus: Amendment 39-18753; Docket No. FAA-2014-0143; 
Directorate Identifier 2012-NM-113-AD.

(a) Effective Date

    This AD is effective February 8, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300 B4-603, B4-620, B4-622, B4-
605R, B4-622R, F4-605R, F4-622R, and C4-605R variant F airplanes; 
certificated in any category; all serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by reports of cracks in the frame base 
fittings connecting the frame lower positions to the center wing 
box. We are issuing this AD to detect and correct cracking of the 
lower frame fittings, 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 Inspections and Replacement

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Airbus Service Bulletin A300-53-6177, dated May 
20, 2015, except as required by paragraphs (h)(1) and (h)(2) of this 
AD: Perform a detailed inspection for cracking of the lower frame 
fittings between frame (FR) 41 and FR46 of the frame foot, and if 
any crack is found, before further flight, replace with a new frame 
foot, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A300-53-6177, dated May 20, 2015, except as 
required by paragraph (h)(3) of this AD. Repeat the inspection 
thereafter at the applicable intervals specified in paragraph 1.E., 
``Compliance,'' of Airbus Service Bulletin A300-53-6177, dated May 
20, 2015.

(h) Service Information Exceptions

    (1) Where the threshold identified in the ``Threshold'' column 
of paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A300-
53-6177, dated May 20, 2015, specifies flight cycles or flight hours 
without specifying from a repair, replacement, or last inspection, 
the specified compliance time is accumulated flight cycles or flight 
hours on the airplane since its first flight.
    (2) Where Airbus Service Bulletin A300-53-6177, dated May 20, 
2015, specifies a compliance time ``from issuance of revision 04 of 
Service Bulletin No. A300-53-6111,'' or ``from issuance of Service 
Bulletin No. A300-53-6177,'' this AD requires compliance within the 
specified compliance time after the effective date of this AD.
    (3) For Configuration 004 airplanes identified in Airbus Service 
Bulletin A300-53-6177, dated May 20, 2015: Within 6 months after the 
effective date of this AD, contact 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), for corrective actions and accomplish 
all applicable corrective actions using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or Airbus's EASA DOA.

(i) Reporting

    At the applicable time specified in paragraph (i)(1) or (i)(2) 
of this AD: Submit a report of the findings (both positive and 
negative) of each inspection required by paragraph (g) of this AD. 
Send the report to Airbus Service Bulletin Reporting Online 
Application on Airbus World (https://w3.airbus.com).
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 60 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 60 days after the effective date of 
this AD.

(j) Optional Terminating Action

    Replacement of all lower frame feet between FR41 and FR46, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6176, dated May 20, 2015, terminates the repetitive 
inspections required by paragraph (g) of this AD.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone: 425-227-1405; fax: 425-227-2125. Information may be 
emailed to: [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or 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.

(l) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA AD 2015-0217, dated October 30, 2015, 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-
2014-0143.

(m) 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.

[[Page 716]]

    (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 A300-53-6176, dated May 20, 2015.
    (ii) Airbus Service Bulletin A300-53-6177, dated May 20, 2015.
    (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 December 6, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-30117 Filed 1-3-17; 8:45 am]
 BILLING CODE 4910-13-P