Document ID: FAA-2016-6894-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2016-05-31T04:00Z

[Federal Register Volume 81, Number 104 (Tuesday, May 31, 2016)]
[Proposed Rules]
[Pages 34285-34287]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-12522]

 ========================================================================
 Proposed Rules
                                                 Federal Register
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 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.
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  Federal Register / Vol. 81, No. 104 / Tuesday, May 31, 2016 / 
Proposed Rules  

[[Page 34285]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6894; Directorate Identifier 2015-NM-120-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 F4-600R series airplanes. This proposed AD 
was prompted by a report of two adjacent frame forks that were found 
cracked on the aft lower deck cargo door (LDCD) of two Model A300-600F4 
airplanes during scheduled maintenance. This proposed AD would require 
repetitive high frequency eddy current (HFEC) inspections of the aft 
LDCD frame forks; a one-time check of the LDCD clearances; and a one-
time detailed visual inspection of hooks, eccentric bushes, and x-
stops; and corrective actions if necessary. We are proposing this AD to 
detect and correct cracked or ruptured aft LDCD frames, which could 
allow loads to be transferred to the remaining structural elements. 
This condition could lead to the rupture of one or more vertical aft 
LDCD frames, which could result in reduced structural integrity of the 
aft LDCD.

DATES: We must receive comments on this proposed AD by July 15, 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-
6894; 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-2016-6894; 
Directorate Identifier 2015-NM-120-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 
Airworthiness Directive 2015-0152, dated July 24, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A300 
F4-605R and A300 F4-622R. The MCAI states:

    During scheduled maintenance at frames (FR) 61 and FR61A on the 
aft lower deck cargo door (LDCD) of two A300-600F4 aeroplanes, two 
adjacent frame forks were found cracked.
    Subsequent analysis determined that, in case of cracked or 
ruptured aft cargo door frame(s), loads will be transferred to the 
remaining structural elements. However, these secondary load paths 
will be able to sustain the loads for a limited number of flight 
cycles only.
    This condition, if not detected and corrected, could lead to the 
rupture of one or more vertical aft cargo door frame(s), resulting 
in reduced structural integrity of the aft cargo door.
    To address this unsafe condition, Airbus issued Alert Operators 
Transmission (AOT) A52W011-15 to provide inspection instructions.
    For the reason described above, this [EASA] AD requires 
repetitive inspections [for cracking] of the aft LDCD frame forks 
and, depending on findings, the accomplishment of corrective 
action(s).
    This [EASA] AD is considered interim action and further [EASA] 
AD action may follow.

    Required actions include a one-time check of the LDCD clearances; 
and a one-time detailed visual inspection of hooks, eccentric bushes, 
x-stops; and corrective actions if necessary. 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-2016-6894.

[[Page 34286]]

Related Service Information Under 1 CFR Part 51

    Airbus has issued Alert Operators Transmission (AOT) A52W011-15, 
Revision 00, dated July 23, 2015. The service information describes 
procedures for repetitive HFEC inspections for cracking of the aft LDCD 
frame forks; a one-time check of the LDCD clearances; and a one-time 
detailed visual inspection of hooks, eccentric bushes, and x-stops; and 
corrective actions if necessary. 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 the same 
type design.

Costs of Compliance

    We estimate that this proposed AD affects 58 airplanes of U.S. 
registry. We also estimate that it would take about 4 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Required parts would cost 
about $0 per product. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be $19,720, or $340 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 15 work-hours and require parts costing $10,000, for a cost 
of $11,275 per product. We have no way of determining the number of 
aircraft that might need these actions.
    Also, we estimate that the reporting requirement would take about 1 
work-hour, for a cost of $85 per product.

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 proposed AD 
is 2120-0056. The paperwork cost associated with this proposed 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 proposed 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 adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2016-6894; Directorate Identifier 2015-NM-
120-AD.

(a) Comments Due Date

    We must receive comments by July 15, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300 F4-605R and A300 F4-622R 
airplanes, certificated in any category, on which Airbus 
Modification 12046 has been embodied in production. Modification 
12046 has been embodied in production on manufacturer serial numbers 
(MSNs) 0805 and above, except MSNs 0836, 0837, and 0838.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by a report of two adjacent frame forks 
that were found cracked on the aft lower deck cargo door (LDCD) of 
two Model A300-600F4 airplanes during scheduled maintenance. We are 
issuing this AD to detect and correct cracked or ruptured aft LDCD 
frames, which could allow loads to be transferred to the remaining 
structural elements. This condition could lead to the rupture of one 
or more vertical aft LDCD frames, which could result in reduced 
structural integrity of the aft LDCD.

(f) Compliance

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

(g) Inspection Requirements

    At the applicable time specified in paragraph (h) of this AD, do 
the actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of 
this AD, in accordance with Airbus Alert Operators Transmission 
(AOT) A52W011-15, Revision 00, dated July 23, 2015.
    (1) Do a one-time check of the aft LDCD clearances ``U'' and 
``V'' between the latching

[[Page 34287]]

hooks and the eccentric bush at FR60 through FR64A. If any value 
outside tolerance is found, adjust the latching hook before further 
flight.
    (2) Do a one-time detailed inspection to detect signs of wear of 
the hooks, eccentric bushes, and x-stops. If any wear is found, do 
all applicable corrective actions before further flight.
    (3) Do a high frequency eddy current (HFEC) inspection to detect 
cracking at all frame fork stations of the aft LDCD. If any crack is 
found, replace the cracked frame fork before further flight. Repeat 
the HFEC inspection thereafter at intervals not to exceed 600 flight 
cycles.

(h) Compliance Times

    At the later of the times specified in paragraphs (h)(1) and 
(h)(2) of this AD, do the actions required by paragraph (g) of this 
AD.
    (1) Before the accumulation of 4,500 total flight cycles.
    (2) At the applicable time specified by paragraph (h)(2)(i) or 
(h)(2)(ii) of this AD.
    (i) For airplanes that have accumulated 8,000 or more total 
flight cycles as of the effective date this AD: Within 100 flight 
cycles after the effective date of this AD.
    (ii) For airplanes that have accumulated fewer than 8,000 total 
flight cycles as of the effective date of this AD: Within 400 flight 
cycles after the effective date of this AD.

(i) Reporting

    At the applicable time specified in paragraph (i)(1) or (i)(2) 
of this AD, report the findings (both positive and negative) of the 
clearance check and detailed inspection required by paragraphs 
(g)(1) and (g)(2) of this AD, and each HFEC inspection required by 
paragraph (g)(3) of this AD. Send the report to Airbus in accordance 
with paragraph 7 of Airbus AOT A52W011-15, Revision 00, dated July 
23, 2015. The report must include the applicable information 
specified in Appendix 2 of Airbus AOT A52W011-15, Revision 00, dated 
July 23, 2015.
    (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) Post-Repair Provisions

    (1) Accomplishment of corrective actions required by this AD 
does not terminate the repetitive HFEC inspections required by 
paragraph (g)(3) of this AD.
    (2) If all frame forks are replaced at the same time on the aft 
LDCD of an airplane, the next HFEC inspection required by paragraph 
(g)(3) of this AD can be deferred up to 4,500 flight cycles after 
the frame fork replacement.

(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 425-227-2125; 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: 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

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Airworthiness Directive 2015-0152, dated July 24, 
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-2016-6894.
    (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 May 18, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-12522 Filed 5-27-16; 8:45 am]
 BILLING CODE 4910-13-P