
[Federal Register Volume 81, Number 81 (Wednesday, April 27, 2016)]
[Proposed Rules]
[Pages 24745-24748]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-09641]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5596; Directorate Identifier 2015-NM-121-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2014-12-
06, for certain Airbus 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); and Airbus Model A310 series 
airplanes. AD 2014-12-06 currently requires inspections of the external 
area of the aft cargo door sill beam for cracking, and repair if 
necessary. Since we issued AD 2014-12-06, we have determined it is 
necessary to require that high frequency eddy current (HFEC) 
inspections be performed repetitively. This proposed AD would mandate 
the previously optional terminating HFEC inspection, and require that 
it be done repetitively. We are proposing this AD to detect and correct 
fatigue cracking of the cargo door sill beam, lock fitting, and torsion 
box plate. Failure of one or more of these components could result in 
the loss of the door locking function and, subsequently, complete loss 
of the cargo door in flight with the risk of rapid decompression.

DATES: We must receive comments on this proposed AD by June 13, 2016.

ADDRESSES: You may send comments 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-
5596; 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-2016-5596; 
Directorate Identifier 2015-NM-121-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

    On June 4, 2014, we issued AD 2014-12-06, Amendment 39-17867 (79 FR 
34403, June 17, 2014) (``AD 2014-12-06''). AD 2014-12-06 requires 
actions intended to address an unsafe condition on certain Airbus 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); and Airbus Model A310 series airplanes.
    Since we issued AD 2014-12-06, we have determined it is necessary 
to require that the HFEC inspections be performed repetitively.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0150, dated July 23, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus 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); and Airbus Model A310 series airplanes. The MCAI states:

    During accomplishment of Maintenance Review Board Report (MRBR) 
task 531625-01-1 on an A300-600 aeroplane having accumulated more 
than 25,000 flight cycles (FC) since aeroplane first flight, 
multiple fatigue cracks were found on the following parts:

--Aft cargo door sill beam Part Number (P/N) A53973085210
--Lock fitting P/N A53978239002
--Torsion box plate P/N A53973318206.

    Prompted by these findings, a stress analysis was performed 
during which it was discovered that there is no dedicated scheduled 
maintenance task to inspect the affected area for fatigue damage.
    This condition, if not detected and corrected, could lead to 
failure of multiple lock fittings, possibly resulting in loss of the 
cargo door in flight and consequent explosive decompression of the 
aeroplane.
    To address this unsafe condition, Airbus issued Alert Operators 
Transmission (AOT) A53W005-14 providing instructions for inspection 
of the affected area.
    Consequently, EASA issued Emergency AD 2014-0097-E [FAA AD 2014-
12-06, Amendment 39-17867 (79 FR 34403, June 17, 2014)] to require 
repetitive ultrasonic (US) inspections or detailed inspections (DET) 
of the aft cargo door sill beam external area, and/or a one-time 
High Frequency Eddy Current (HFEC) inspection of the aft cargo door 
sill beam internal structure and, depending on findings, 
accomplishment of corrective action(s).
    Since that [EASA] AD was issued, the results of further analysis 
have indicated that repetitive HFEC inspections need to be 
introduced.

[[Page 24746]]

    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0097-E, which is superseded, and 
requires repetitive HFEC inspections of the concerned areas. The 
first HFEC inspection terminates the repetitive US/DET inspections.

    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-
5596.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-53-6179, dated December 12, 
2014; and Service Bulletin A310-53-2139, dated December 12, 2014. The 
service information describes procedures for repetitive HFEC 
inspections of the cargo door sill beam, lock fitting, and torsion box 
plate.
    Airbus has also issued AOT A53W005-14, Revision 01, dated April 29, 
2014. The service information describes procedures for doing an 
ultrasonic inspection or detailed inspection of the aft cargo door sill 
beam external area for cracking.
    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 75 airplanes of U.S. 
registry.
    The actions required by AD 2014-12-06, and retained in this 
proposed AD, take about 12 work-hours per product, at an average labor 
rate of $85 per work-hour. Based on these figures, the estimated cost 
of the actions that are required by AD 2014-12-06 and retained in this 
AD is $1,020 per product.
    We also estimate that it would take about 1 work-hour per product 
to comply with the reporting 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 $6,374, 
or $85 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.

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 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 removing AD 2014-12-06, Amendment 39-
17867 (79 FR 34403, June 17, 2014), and adding the following new AD:

Airbus: Docket No. FAA-2016-5596; Directorate Identifier 2015-NM-
121-AD.

(a) Comments Due Date

    We must receive comments by June 13, 2016.

(b) Affected ADs

    This AD replaces AD 2014-12-06, Amendment 39-17867 (79 FR 34403, 
June 17, 2014) (``AD 2014-12-06'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), (c)(3), (c)(4), and (c)(5) of this AD, certificated 
in any category, all manufacturer serial numbers on which Airbus 
Modification 05438 has been embodied in production, except those on 
which Airbus Modification 12046 has been embodied in production.
    (1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes.
    (2) Airbus Model A300 B4-605R and B4-622R airplanes.
    (3) Airbus Model A300 F4-605R and F4-622R airplanes.
    (4) Airbus Model A300 C4-605R Variant F airplanes.
    (5) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes.

[[Page 24747]]

(d) Subject

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

(e) Reason

    This AD was prompted by reports of fatigue cracks on the cargo 
door sill beam, lock fitting, and torsion box plate. We are issuing 
this AD to detect and correct fatigue cracking of the cargo door 
sill beam, lock fitting, and torsion box plate, which could result 
in the loss of the door locking function and subsequently, complete 
loss of the cargo door in flight with the risk of rapid 
decompression.

(f) Compliance

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

(g) Retained Inspection With Revised Service Information

    This paragraph restates the requirements of paragraph (g)(1) of 
AD 2014-12-06 with revised service information: Within the 
compliance time identified in paragraph (g)(1), (g)(2), or (g)(3) of 
this AD, as applicable, do an ultrasonic inspection or detailed 
inspection of the aft cargo door sill beam external area for 
cracking, in accordance with Airbus Alert Operators Transmission 
(AOT) A53W005-14, dated April 22, 2014; or Airbus AOT A53W005-14, 
Revision 01, dated April 29, 2014. Repeat the inspection thereafter 
at intervals not to exceed 275 flight cycles. As of the effective 
date of this AD, only Airbus AOT A53W005-14, Revision 01, dated 
April 29, 2014, may be used to comply with the requirements of this 
paragraph.
    (1) For airplanes that have accumulated 30,000 flight cycles or 
more since the airplane's first flight as of July 2, 2014 (the 
effective date of AD 2014-12-06): Within 50 flight cycles after July 
2, 2014.
    (2) For airplanes that have accumulated 18,000 flight cycles or 
more, but fewer than 30,000 flight cycles since the airplane's first 
flight as of July 2, 2014 (the effective date of AD 2014-12-06): 
Within 275 flight cycles after July 2, 2014.
    (3) For airplanes that have accumulated fewer than 18,000 flight 
cycles since the airplane's first flight as of July 2, 2014 (the 
effective date of AD 2014-12-06): Before exceeding 18,275 flight 
cycles since the airplane's first flight.

(h) Retained Optional Terminating Action, With Revised Service 
Information

    This paragraph restates the provisions of paragraph (h) of AD 
2014-12-06, with revised service information. Accomplishment of high 
frequency eddy current (HFEC) inspection for cracking, in accordance 
with Airbus AOT A53W005-14, dated April 22, 2014; or Airbus AOT 
A53W005-14, Revision 01, dated April 29, 2014, terminates the 
repetitive inspections required by paragraph (g) of this AD for that 
airplane. If any cracking is found during the HFEC inspection, 
before further flight, repair 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) Retained Reporting Requirement, With Revised Service Information

    This paragraph restates the provisions of paragraph (i) of AD 
2014-12-06, with revised service information. Submit a report of the 
findings (both positive and negative) of the inspection required by 
paragraph (g) of this AD to Airbus, as specified in paragraph 
7.,''Reporting,'' of Airbus AOT A53W005-14, dated April 22, 2014; or 
Airbus AOT A53W005-14, Revision 01, dated April 29, 2014, at the 
applicable time specified in paragraph (i)(1) or (i)(2) of this AD. 
The report must include inspection results, including no findings.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(j) Definition of Airplane Groups

    Paragraphs (k)(1), (k)(2), and (k)(3) of this AD refer to 
airplane groups, as identified in paragraphs (j)(1), (j)(2), and 
(j)(3) of this AD.
    (1) Airplanes on which a HFEC inspection was accomplished as 
specified in Airbus AOT A53W005-14.
    (2) Airplanes on which no HFEC inspection was accomplished as 
specified in Airbus AOT A53W005-14, and that have accumulated more 
than 18,000 total flight cycles as of the effective date of this AD.
    (3) Airplanes on which no HFEC inspection accomplished as 
specified in Airbus AOT A53W005-14, that have accumulated 18,000 
total flight cycles or fewer as of the effective date of this AD.

(k) New Repetitive HFEC Inspections and Repair

    At the applicable time specified in paragraph (k)(1), (k)(2), or 
(k)(3) of this AD, do an HFEC inspection for fatigue cracking of the 
cargo door sill beam, lock fitting, and torsion box plate, in 
accordance with Airbus Service Bulletin A300-53-6179, dated December 
12, 2014; or Airbus Service Bulletin A310-53-2139, dated December 
12, 2014, as applicable. Repeat the HFEC inspection thereafter at 
intervals not to exceed 4,600 flight cycles.
    (1) For airplanes identified in paragraph (j)(1) of this AD: 
Inspect within 4,600 flight cycles after the most recent HFEC 
inspection specified in Airbus AOT A53W005-14.
    (2) For airplanes identified in paragraph (j)(2) of this AD: 
Inspect within 2,000 flight cycles after the effective date of this 
AD.
    (3) For airplanes identified in paragraph (j)(3) of this AD: 
Inspect before exceeding 13,000 total flight cycles since the 
airplane's first flight, or within 2,000 flight cycles after the 
effective date of this AD, whichever occurs later.

(l) Corrective Action

    If any crack is found during any inspection required by 
paragraph (g) or (k) of this AD: Before further flight, repair using 
a method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA 
DOA.

(m) Terminating Action for HFEC Inspections

    For any airplane identified in paragraphs (j)(2) and (j)(3) of 
this AD, accomplishment of the initial inspection required by 
paragraph (k) of this AD terminates the repetitive inspections 
required by paragraph (g) of this AD.

(n) 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: As of the effective date of 
this AD, 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) 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.
    (4) Required for Compliance (RC): Except as required by 
paragraph (l) of this AD: If any service information contains 
procedures or tests that are identified as RC, those

[[Page 24748]]

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.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency (EASA) Airworthiness 
Directive 2015-0150, dated July 23, 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-
2016-5596.
    (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 April 15, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-09641 Filed 4-26-16; 8:45 am]
BILLING CODE 4910-13-P


