AD 2015-06-10

[Federal Register Volume 80, Number 75 (Monday, April 20, 2015)]
[Rules and Regulations]
[Pages 21639-21645]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2015-07162]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0497; Directorate Identifier 2012-NM-192-AD; 
Amendment 39-18128; AD 2015-06-10]
RIN 2120-AA64


Airworthiness Directives; ATR-GIE Avions de Transport 
R[eacute]gional Airplanes

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

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
ATR-GIE Avions de Transport R[eacute]gional Model ATR72-212A airplanes. 
This AD requires inspection of the shock mount pick-up fittings and 
cone bolts, and replacement of certain shock mount pick-up fittings if 
necessary. This AD was prompted by reports of several cases of engine 
shock mount pick-up fittings with cracks or failure on the engine left-
hand (LH) aft side attachment. We are issuing this AD to detect and 
correct an aft side attachment

[[Page 21640]]

pick-up fitting failure associated with a cone bolt failure that could 
reduce the structural integrity of the concerned engine nacelle, and 
possibly result in detachment of the engine and consequent reduced 
control of the airplane.

DATES: This AD becomes effective May 5, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of May 5, 2015.
    We must receive comments on this AD by June 4, 2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 ATR-GIE 
Avions de Transport R[eacute]gional, 1, All[eacute]e Pierre Nadot, 
31712 Blagnac Cedex, France; telephone +33 (0) 5 62 21 62 21; fax +33 
(0) 5 62 21 67 18; email <a href="/cdn-cgi/l/email-protection#b4d7dbdac0dddac1d1d09ad5ddc6c3dbc6c0dcdddad1c7c7f4d5c0c69ad2c6"><span class="__cf_email__" data-cfemail="83e0ecedf7eaedf6e6e7ade2eaf1f4ecf1f7ebeaede6f0f0c3e2f7f1ade5f1">[email&#160;protected]</span></a>; Internet 
<a href="http://www.aerochain.com">http://www.aerochain.com</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating 
Docket No. FAA-2015-0497.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2015-
0497; 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: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1137; 
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 Union, has issued EASA 
Airworthiness Directive 2012-0192, dated September 21, 2012 (corrected 
September 24, 2012) (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain ATR-GIE Avions de Transport R[eacute]gional Model 
ATR72-212A airplanes. The MCAI states:

    Several cases of engine shock mount pick-up fitting with crack 
or failure have been reported, always on engine Left Hand (LH) aft 
side attachment. Prompted by those reports, improved Part Number (P/
N) S54210394200 (Barry Control P/N 94423-05) fittings (machined 
radius modification) have been introduced in production, having 
serial number (s/n) 2451 and higher. No crack has been reported on 
aeroplanes equipped with those improved fittings.
    Two recent cases of failed cone bolt have been reported on ATR 
72-212A aeroplanes, both on engine Right Hand (RH) aft side 
isolator.
    An aft side attachment pick-up fitting failure associated to a 
cone bolt failure, if not detected and corrected, could reduce the 
structural integrity of the concerned engine nacelle, possibly 
resulting in detachment of the engine and consequent reduced control 
of the aeroplane.
    For the reasons described above, this [EASA] AD requires a one-
time [detailed] inspection [for cracks] of the shock mount pick-up 
fittings and cone bolts and, depending on findings, accomplishment 
of applicable repair. This AD also requires replacement of all LH 
shock mount pick-up fitting P/N S54210394200 having a s/n lower than 
2451.
* * * * *

    You may examine the MCAI on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2015-
0497.

Related Service Information Under 1 CFR Part 51

    ATR-GIE Avions de Transport R[eacute]gional (ATR) has issued the 
following service information. The service information describes 
procedures for a detailed visual inspection of the engine shock mounts. 
The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.
    <bullet> ATR ATR72 airplane maintenance manual (AMM) Job 
Instruction Card 54-11-61 DVI 10000, Detailed Visual Inspection of 
Forward Engine Mount, dated March 1, 2012.
    <bullet> ATR ATR72 AMM Job Instruction Card 71-20-00 DVI 10000, 
Detailled (sic) Visual Inspec[tion] of Engine Shockmounts, dated March 
1, 2012.
    This service information is reasonably available; see ADDRESSES for 
ways to access this service information.

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 the same 
type design.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this product, 
notice and opportunity for public comment before issuing this AD are 
unnecessary.

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-2015-0497; Directorate 
Identifier 2012-NM-192-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 <a href="http://www.regulations.gov">http://www.regulations.gov</a>, 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

    Currently, there are no affected airplanes on the U.S. Register. 
However,

[[Page 21641]]

if an affected airplane is imported and placed on the U.S. Register in 
the future, we estimate that it will take about 3 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 $255 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 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):

2015-06-10 ATR-GIE Avions de Transport R[eacute]gional: Amendment 
39-18128. Docket No. FAA-2015-0497; Directorate Identifier 2012-NM-
192-AD.

(a) Effective Date

    This AD becomes effective May 5, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to ATR-GIE Avions de Transport R[eacute]gional 
Model ATR72-212A airplanes, certificated in any category, 
manufacturer serial numbers 468 through 719 inclusive, 723, 776, 
777, 779, 821, and 837.

(d) Subject

    Air Transport Association (ATA) of America 54, Nacelles/Pylons.

(e) Reason

    This AD was prompted by reports of several cases of engine shock 
mount pick-up fittings with cracks or failure on the engine left-
hand (LH) aft side attachment. We are issuing this AD to detect and 
correct an aft side attachment pick up fitting failure associated 
with a cone bolt failure that could reduce the structural integrity 
of the concerned engine nacelle, and possibly result in detachment 
of the engine and consequent reduced control of the airplane.

(f) Compliance

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

(g) Engine Shock Mount Pick-up Fittings Inspection

    Within 6 months after the effective date of this AD, accomplish 
the actions specified by paragraphs (g)(1), (g)(2), and (g)(3) of 
this AD concurrently.
    (1) Identify the serial number (S/N) of the part number (P/N) 
S54210394200 (Barry Control P/N 94423-05) LH and right-hand (RH) 
shock mount pick-up fittings installed on both engine nacelles. 
Figure 1 to paragraph (g)(1) of this AD identifies the fitting part 
number and serial number locations.

BILLING CODE 4910-13-C

[[Page 21642]]

[GRAPHIC] [TIFF OMITTED] TR20AP15.002

    (2) Do a detailed inspection of both LH and RH aft side isolator 
pick-up fittings on both engines to detect cracks, in accordance 
with paragraph 004.1 of ATR ATR72 Aircraft Maintenance Manual (AMM) 
Job Instruction Card (JIC) 54-11-61 DVI 10000, dated March 1, 2012. 
Refer to figure 2 to paragraph (g)(2) of this AD for potential crack 
location.

[[Page 21643]]

[GRAPHIC] [TIFF OMITTED] TR20AP15.003

    (3) Do a detailed inspection of both LH and RH aft shock mount 
cone bolts on both engines to detect cracks, in accordance with 
paragraph 006.3.A. of ATR ATR72 AMM JIC 71-20-00 DVI 10000. Refer to 
figure 3 to paragraph (g)(3) of this AD for potential crack 
location.

[[Page 21644]]

[GRAPHIC] [TIFF OMITTED] TR20AP15.004

(h) Corrective Actions

    (1) If any crack is found during any inspection required by 
paragraphs (g)(2) and (g)(3) of this AD: Before further flight, 
repair in accordance with a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or ATR's EASA Design Organization Approval (DOA).
    (2) If the serial number of the LH shock mount pick-up fitting, 
identified during any inspection required by paragraph (g)(1) of 
this AD, is lower than 2451 or is unreadable, and no crack has been 
found during any

[[Page 21645]]

inspection required by paragraphs (g)(2) and (g)(3) of this AD: 
Within 6 months after the inspection required by paragraph (g)(2) of 
this AD, replace the LH shock mount pick-up fitting P/N S54210394200 
with a serviceable LH shock mount pick-up fitting having a serial 
number equal to or higher than 2451, in accordance with a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or ATR--GIE Avions de Transport 
R[eacute]gional's EASA DOA.

(i) Parts Installation Limitation

    As of the effective date of this AD, do not install on any 
airplane a LH shock mount pick-up fitting P/N S54210394200, unless 
it is serviceable and has been determined to have an S/N equal to or 
higher than 2451, in accordance with the requirements of paragraph 
(g)(1) of this AD.

(j) Reporting Requirement

    Submit a report of the findings (both positive and negative) of 
the inspections required by paragraphs (g)(1), (g)(2), and (g)(3) of 
this AD to ATR at <a href="/cdn-cgi/l/email-protection#364253555e5253455d76574244185044"><span class="__cf_email__" data-cfemail="691d0c0a010d0c1a0229081d1b470f1b">[email&#160;protected]</span></a> and <a href="/cdn-cgi/l/email-protection#74171b1a001d1a0111105a151d06031b06001c1d1a110707341500065a1206"><span class="__cf_email__" data-cfemail="b9dad6d7cdd0d7ccdcdd97d8d0cbced6cbcdd1d0d7dccacaf9d8cdcb97dfcb">[email&#160;protected]</span></a> 
at the applicable time specified in paragraph (j)(1) or (j)(2) of 
this AD. The report must include the airplane serial number, 
registration, inspection date, inspection results, and engine pick-
up serial numbers.
    (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.

(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, 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: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1137; 
fax 425-227-1149. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#97aebad6d9dabaa6a6a1bad6dad8d4bac5d2c6c2d2c4c3c4d7f1f6f6b9f0f8e1"><span class="__cf_email__" data-cfemail="645d49252a29495555524925292b27493621353121373037240205054a030b12">[email&#160;protected]</span></a>. 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 EASA; or 
ATR-GIE Avions de Transport R[eacute]gional'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.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2012-0192, dated September 21, 
2012 (corrected September 24, 2012), for related information. You 
may examine the MCAI on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> 
by searching for and locating Docket No. FAA-2015-0497.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(m) 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) ATR ATR72 Airplane Maintenance Manual (AMM) Job Instruction 
Card 54-11-61 DVI 10000, Detailed Visual Inspection of Forward 
Engine Mount, dated March 1, 2012.
    (ii) ATR ATR72 AMM Job Instruction Card 71-20-00 DVI 10000, 
Detailled (sic) Visual Inspec[tion] of Engine Shockmounts, dated 
March 1, 2012.
    (3) For service information identified in this AD, contact ATR--
GIE Avions de Transport R[eacute]gional, 1, All[eacute]e Pierre 
Nadot, 31712 Blagnac Cedex, France; telephone +33 (0) 5 62 21 62 21; 
fax +33 (0) 5 62 21 67 18; email <a href="/cdn-cgi/l/email-protection#adcec2c3d9c4c3d8c8c983ccc4dfdac2dfd9c5c4c3c8dedeedccd9df83cbdf"><span class="__cf_email__" data-cfemail="a7c4c8c9d3cec9d2c2c389c6ced5d0c8d5d3cfcec9c2d4d4e7c6d3d589c1d5">[email&#160;protected]</span></a>; 
Internet <a href="http://www.aerochain.com">http://www.aerochain.com</a>.
    (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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on March 19, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-07162 Filed 4-17-15; 8:45 am]
 BILLING CODE 4910-13-P