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[Federal Register Volume 81, Number 150 (Thursday, August 4, 2016)]
[Rules and Regulations]
[Pages 51320-51322]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-18254]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-0466; Directorate Identifier 2014-NM-188-AD; 
Amendment 39-18604; AD 2016-16-06]
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 certain 
Airbus Model A300 B4-603, B4-605R, and B4-622R airplanes; and Model 
A310-304, -324, and -325 airplanes. This AD was prompted by a report of 
a crack found on door frame (FR) 73A between stringers 24 and 25. This 
AD requires inspections around the rivet heads of the seal retainer 
run-out holes at certain frames and corrective actions if necessary. We 
are issuing this AD to detect and correct cracking of the door frame, 
which could result in reduced structural integrity of the airplane.

DATES: This AD is effective September 8, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 8, 
2016.

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 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-2016-
0466.

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-
0466; 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.

[[Page 51321]]

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 by adding an AD that would apply to certain Airbus Model A300 
B4-603, B4-605R, and B4-622R airplanes; and Model A310-304, -324, and -
325 airplanes. The NPRM published in the Federal Register on February 
18, 2016 (81 FR 8155) (``the NPRM''). The NPRM was prompted by a report 
of a crack found on door FR 73A between stringers 24 and 25. The NPRM 
proposed to require inspections around the rivet heads of the seal 
retainer run-out holes at certain frames and corrective actions if 
necessary. We are issuing this AD to detect and correct cracking of the 
door frame, 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 
2014-0202R1, dated September 19, 2014 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus Model A300 B4-603, B4-
605R, and B4-622R airplanes; and Model A310-304, -324, and -325 
airplanes The MCAI states:

    During the preparation phase for conversion of an A300-600 
aeroplane from passenger to freighter configuration, a crack was 
detected on door frame (FR) 73A, between stringer (STRG) 24 and STRG 
25.
    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France had issued AD 1999-013-276R1 to require inspections at FR 73A 
in accordance with the instructions of Airbus Service Bulletin (SB) 
A310-53-2107 or SB A300-53-6116, as applicable. However, the new 
crack was found in an area not covered by the existing inspection 
and is therefore addressed by this new [EASA] AD. (DGAC France AD 
1999-013-276R1 remains in place).
    Further investigations identified that, on A300-600 aeroplanes, 
the areas at FR 56A and FR 57A have the same design and material as 
at FR 73A.
    This condition, if not detected and corrected, could affect the 
structural integrity of the airframe.
    For the reasons described above, this [EASA] AD requires 
repetitive [high frequency eddy current (HFEC)] inspections of the 
rivet heads of the seal retainer run out holes to detect cracks and, 
depending on findings, accomplishment of corrective actions 
[repair].
    Even though no crack has been identified at FR 56A and FR 57A, 
as a preventive measure, the inspection is extended to these areas. 
On A310 aeroplanes, only the area at FR 73A needs to be inspected.
    This [EASA] AD is revised to reduce the applicability to 
aeroplanes in post-MOD 06924 configuration.

    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-
0466.

Comments

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

Request To Reduce Compliance Time

    An anonymous commenter asked why the NPRM has not yet been enacted. 
The commenter stated that they do not want to be on a plane that lacks 
structural integrity because of cracks on the door frame.
    ADs are federal regulations that have the force and effect of law. 
In simple terms, the Administrative Procedure Act (APA), Title 5 of the 
United States Code (5 U.S.C.) Sec.  553, requires all regulatory 
agencies such as the FAA to provide the public with notice and time for 
comment prior to issuing a regulation. ADs are issued in accordance 
with the public rulemaking procedures of the APA, FAA procedures in 14 
CFR part 11, and several other relevant regulations. For this AD, we 
did not substantiate that a critical, immediate safety of flight 
problem exists that would warrant issuing a rule without prior notice 
or opportunity for public comment. We have not changed this AD in this 
regard.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed except for 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

    Airbus has issued Service Bulletins A300-53-6175 and A310-53-2138, 
both dated May 28, 2014. The service information describes procedures 
for doing HFEC inspections around the rivet heads of the seal retainer 
run-out holes at certain frame locations on the left-hand and right-
hand sides. 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 24 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                    Labor cost         Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection......................  11 work-hours x $85              $0   $935 per inspection  $22,440 per
                                   per hour = $935                       cycle.               inspection cycle.
                                   per inspection
                                   cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would 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

[[Page 51322]]

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):

2016-16-06 Airbus: Amendment 39-18604; Docket No. FAA-2016-0466; 
Directorate Identifier 2014-NM-188-AD.

(a) Effective Date

    This AD is effective September 8, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300 B4-603, A300 B4-605R, A300 
B4-622R, A310-304, A310-324, and A310-325 airplanes; certificated in 
any category; all manufacturer serial numbers (MSNs) in post-
modification (MOD) 06924 configuration, except MSNs 464, 477, 479, 
481, 482, 483, 484, and 488.
    Note 1 to paragraph (c) of this AD: MSNs 464, 477, 479, 481, 
482, 483, 484 and 488 partially embodied MOD 06924 by means of 
modification proposal D05902.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of a crack found on door frame 
(FR) 73A between stringers 24 and 25. We are issuing this AD to 
detect and correct cracking of the door frame, 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) Inspections for Cracking

    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 for any crack around the rivet heads of the seal 
retainer run-out holes at FR 56A, FR 57A, and FR 73A, left-hand (LH) 
and right-hand (RH) sides on Model A300-600 airplanes; and at FR 
73A, LH and RH sides on Model A310 airplanes; in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-53-2138, 
dated May 28, 2014; or Airbus Service Bulletin A300-53-6175, dated 
May 28, 2014; as applicable. Repeat the HFEC inspection thereafter 
at intervals not to exceed 7,500 flight cycles.
    (1) Before the accumulation of 32,000 total flight cycles.
    (2) Within 36 months after the effective date of this AD, or 
before the accumulation of 36,000 total flight cycles, whichever 
occurs first.

(h) Corrective Actions

    If any crack is found during any inspection required by 
paragraph (g) of this AD, 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).

(i) 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.
    (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; 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 (h) 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.

(j) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA AD 2014-0202R1, dated September 19, 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-2016-0466.

(k) 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 A300-53-6175, dated May 28, 2014.
    (ii) Airbus Service Bulletin A310-53-2138, dated May 28, 2014.
    (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 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 July 21, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-18254 Filed 8-3-16; 8:45 am]
BILLING CODE 4910-13-P
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