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[Federal Register Volume 81, Number 32 (Thursday, February 18, 2016)]
[Proposed Rules]
[Pages 8155-8157]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-03135]

========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / 
Proposed Rules

[[Page 8155]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-0466; Directorate Identifier 2014-NM-188-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt 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 proposed AD was prompted 
by a report of a crack found on door frame (FR) 73A between stringers 
24 and 25. This proposed AD would require inspections around the rivet 
heads of the seal retainer run-out holes at certain frames and 
corrective actions if necessary. We are proposing this AD to detect and 
correct cracking of the door frame, which could result in reduced 
structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by April 4, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this NPRM, 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.

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 proposed 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. 
Comments will be available in the AD docket shortly after receipt.

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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-0466; 
Directorate Identifier 2014-NM-188-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    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 France had issued AD 1999-013-276R1 [http://ad.easa.europa.eu/ad/F-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.

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

[[Page 8156]]

information describes procedures to do 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.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 24 airplanes of U.S. 
registry.
    We also estimate that it would take about 11 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $22,440, or $935 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

Airbus: Docket No. FAA-2016-0466; Directorate Identifier 2014-NM-
188-AD.

(a) Comments Due Date

    We must receive comments by April 4, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300B4-603, A300B4-605R, A300B4-
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 MSN 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, which could reduce the structural 
integrity of the airplane.

(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 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. The 
AMOC approval letter must specifically reference this AD.

[[Page 8157]]

    (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) 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

    (1) 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.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet http://www.airbus.com. You may view this 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.

    Issued in Renton, Washington, on February 6, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-03135 Filed 2-17-16; 8:45 am]
 BILLING CODE 4910-13-P
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