Airworthiness Directives; Airbus Airplanes, 34403-34405 [2014-13832]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 79, Number 116 (Tuesday, June 17, 2014)]
[Rules and Regulations]
[Pages 34403-34405]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-13832]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

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


Federal Register / Vol. 79, No. 116 / Tuesday, June 17, 2014 / Rules 
and Regulations

[[Page 34403]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0340; Directorate Identifier 2014-NM-084-AD; 
Amendment 39-17867; AD 2014-12-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) 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. This AD 
requires inspections of the external area of the aft cargo door sill 
beam for cracking, and repair if necessary. 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.

DATES: This AD becomes effective July 2, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 2, 
2014.
    We must receive comments on this AD by August 1, 2014.

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 https://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 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 https://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 https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0340; or in person at the Docket Operations office 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 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: 

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Emergency Airworthiness Directive 2014-0097-E, dated April 23, 2014 
(referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for 
certain Airbus Model A300 B4-600, 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.
    The loss of more than one lock fitting could lead to loss of the 
door locking function and, subsequently, complete loss of the cargo 
door in flight with associated risk of rapid decompression.
    To address this unsafe condition, Airbus issued Alert Operators 
Transmission (AOT) A53W005-14 providing instructions for inspection 
of the affected area.
    For the reason described above, this [EASA] AD requires 
repetitive ultrasonic inspections or detailed inspections (DET) for 
cracking of the aft cargo door sill beam external area, or a one-
time High Frequency Eddy Current (HFEC) inspection [for cracking] of 
the aft cargo door sill beam internal structure and, depending on 
findings, accomplishment of corrective action(s) [e.g. repair].
    This [EASA] AD is considered an interim measure and further AD 
action may follow.

You may examine the MCAI on the Internet at https://www.regulations.gov 
by searching for and locating Docket No. FAA-2014-0340.

Relevant Service Information

    Airbus has issued Alert Operators Transmission A53W005-14, dated 
April 22, 2014. The actions described in this service information are 
intended to correct the unsafe condition identified in the MCAI.

[[Page 34404]]

FAA's Determination and Requirements of This 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Interim Action

    We consider this AD interim action. If final action is later 
identified, we might consider further rulemaking then.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
fatigue cracking of the cargo door sill beam, lock fitting, and torsion 
box plate 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. Therefore, we determined that notice and 
opportunity for public comment before issuing this AD are impracticable 
and that good cause exists for making this amendment effective in fewer 
than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2014-0340; Directorate 
Identifier 2014-NM-084-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD based on 
those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 170 airplanes of U.S. registry.
    We also estimate that it will take about 11 work-hours per product 
to comply with the basic requirements of this AD. 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 $158,950, 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 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 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):

2014-12-06 Airbus: Amendment 39-17867. Docket No. FAA-2014-0340; 
Directorate Identifier 2014-NM-084-AD.

(a) Effective Date

    This AD becomes effective July 2, 2014.

(b) Affected ADs

    None.

(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 certified models, all manufacturer serial 
numbers on which Airbus Modification 05438 has been embodied in 
production, except those on which 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.

[[Page 34405]]

    (4) Airbus Model A300 C4-605R Variant F airplanes.
    (5) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes.

(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) Inspection and Repair

    (1) Within the compliance time identified in paragraph 
(g)(1)(i), (g)(1)(ii), or (g)(1)(iii) 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. 
Repeat the inspection thereafter at intervals not to exceed 275 
flight cycles.
    (i) For airplanes that have accumulated 30,000 flight cycles or 
more since the airplane's first flight as of the effective date of 
this AD: Within 50 flight cycles after the effective date of this 
AD.
    (ii) For airplanes that have accumulated 18,000 flight cycles or 
more, but less than 30,000 flight cycles since the airplane's first 
flight as of the effective date of this AD: Within 275 flight cycles 
after the effective date of this AD.
    (iii) For airplanes that have accumulated less than 18,000 
flight cycles since the airplane's first flight as of the effective 
date of this AD: Before exceeding 18,275 flight cycles since the 
airplane's first flight.
    (2) If any crack is found during any inspection required by 
paragraph (g)(1) of this AD: 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 its delegated agent, or the Design Approval Holder 
(DAH) with EASA design organization approval).

(h) Optional Terminating Action

    Accomplishment of the high frequency eddy current (HFEC) 
inspection for cracking in accordance with Airbus AOT A53W005-14, 
dated April 22, 2014, terminates the repetitive inspections required 
by paragraph (g)(1) 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 EASA (or its 
delegated agent, or the DAH with EASA design organization approval).

(i) Reporting Requirement

    Submit a report of the findings (both positive and negative) of 
the inspection required by paragraph (g)(1) of this AD to Airbus as 
specified in paragraph 7., ``Reporting'' of the Airbus AOT A53W005-
14, dated April 22, 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) 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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer, use these actions if they 
are FAA-approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or the DAH with a State of Design Authority's 
design organization approval, as applicable). You are required to 
ensure the product is airworthy before it is returned to service.
    (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.

(k) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA Emergency Airworthiness Directive 2014-0097-E, dated April 23, 
2014, for related information. You may examine the MCAI on the 
Internet at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2014-0340.

(l) 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 Alert Operators Transmission A53W005-14, dated April 
22, 2014.
    (ii) Reserved.
    (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 https://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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.


    Issued in Renton, Washington, on: June 4, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-13832 Filed 6-16-14; 8:45 am]
BILLING CODE 4910-13-P