[Federal Register Volume 81, Number 16 (Tuesday, January 26, 2016)]
[Proposed Rules]
[Pages 4217-4220]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-01381]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-1363; Directorate Identifier 2015-CE-040-AD]
RIN 2120-AA64


Airworthiness Directives; Mitsubishi Heavy Industries, Ltd. 
Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Mitsubishi Heavy Industries, Ltd. Models MU-2B-30, MU-2B-35, 
MU-2B-36, MU-2B-36A, and MU-2B-60 airplanes. This proposed AD results 
from mandatory continuing airworthiness information (MCAI) originated 
by an aviation authority of another country to identify and correct an 
unsafe condition on an aviation product. The MCAI describes the unsafe 
condition as reports of cracks found in the attach fittings of the main 
landing gear oleo strut. We are issuing this proposed AD to require 
actions to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by March 11, 2016.

[[Page 4218]]


ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. 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 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Mitsubishi Heavy Industries America, Inc., c/o Turbine Aircraft 
Services, Inc., 4550 Jimmy Doolittle Drive, Addison, Texas 75001; 
telephone: (972) 248-3108, ext. 209; fax: (972) 248-3321; Internet: 
http://mu-2aircraft.com. You may review this referenced service 
information at the FAA, Small Airplane Directorate, 901 Locust, Kansas 
City, Missouri 64106. For information on the availability of this 
material at the FAA, call (816) 329-4148.

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-
1363; 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 
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:  Andrew McAnaul, Aerospace Engineer, 
FAA, ASW-143 (c/o San Antonio MIDO), 10100 Reunion Place, Suite 650, 
San Antonio, Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370; 
email: <a href="/cdn-cgi/l/email-protection#a5c4cbc1d7c0d28bc8c6c4cbc4d0c9e5c3c4c48bc2cad3"><span class="__cf_email__" data-cfemail="73121d170116045d1e10121d12061f331512125d141c05">[email protected]</span></a>.

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-2016-1363; 
Directorate Identifier 2015-CE-040-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 because of those comments.
    We will post all comments we receive, without change, to http://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 Japan Civil Aviation Bureau (JCAB), which is the aviation 
authority for Japan, has issued AD No. TCD-8595-2015, dated July 1, 
2015 (referred to after this as ``the MCAI''), to correct an unsafe 
condition for certain Mitsubishi Heavy Industries, Ltd. (MHI) Models 
MU-2B-30, MU-2B-35, and MU-2B-36 airplanes. You may examine the MCAI on 
the Internet at http://www.regulations.gov by searching for and 
locating it in Docket No. FAA-2016-1363.
    We have received reports of seven failures of the main landing gear 
oleo strut attach fitting on certain MHI Models MU-2B-30, MU-2B-35, MU-
2B-36, MU-2B-36A, and MU-2B-60 airplanes. Investigation revealed that 
the failures resulted from improper lubrication and/or hard landings, 
which caused cracks to develop in the main landing gear oleo strut 
attach fitting.
    Japan is the State of Design for MHI Models MU-2B-30, MU-2B-35, and 
MU-2B-36, which the MCAI AD applies to, and the United States is the 
State of Design for MHI Models MU-2B-36A and MU-2B-60 airplanes.

Related Service Information Under 1 CFR Part 51

    Mitsubishi Heavy Industries, Ltd. has issued MU-2 Service Bulletin 
No. 243, dated June 30, 2015, and MU-2 Service Bulletin No. 105/32-017, 
dated September 29, 2015. These service bulletins describe procedures 
for visually inspecting the lugs of the oleo attach fittings on both 
sides for cracks, and if any visible cracks are found, replacing with a 
new fitting. Mitsubishi Heavy Industries, Ltd. has also issued MU-2 
Service News JCAB T.C.: No. 171, FAA T.C.: No. 124/32-011, dated April 
27, 2012, and MU-2 Service News JCAB T.C.: No. 176, FAA T.C.: No. 128/
32-013, dated July 18, 2013. This service information specifies doing 
repetitive ultrasound inspections of the main landing gear oleo upper 
attach fittings for cracks and ensuring proper lubrication of the main 
landing gear oleo fitting. All the related 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 of this NPRM.

FAA's Determination and Requirements of the 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 this State of Design Authority, they 
have notified us of the unsafe condition described in the MCAI and 
service information referenced above. We are proposing this AD because 
we evaluated all information and determined the unsafe condition exists 
and is likely to exist or develop on other products of the same type 
design.

Differences Between This Proposed AD and the MCAI

    We have determined that the repetitive visual inspections specified 
in the MCAI are not adequate for detecting cracks in the main landing 
gear oleo strut attach fitting. Repetitive ultrasonic inspections of 
the main landing gear oleo strut attach fitting have been added into 
the maintenance requirement manual for these airplanes, which is not 
considered mandatory in the FAA's airworthiness regulatory system. 
Therefore, we are proposing to incorporate that requirement through the 
rulemaking process.

Costs of Compliance

    We estimate that this proposed AD will affect 95 products of U.S. 
registry. We also estimate that it would take about 5 work-hours per 
product to comply with the visual inspection requirement of this 
proposed AD. The average labor rate is $85 per work-hour.
    Based on these figures, we estimate the cost of the visual 
inspection requirements of this proposed AD on U.S. operators to be 
$40,375, or $425 per product.
    We also estimate that it would take about 3 work-hours per product 
to comply with the ultrasound inspection requirements of this proposed 
AD. The average labor rate is $85 per work-hour.
    Based on these figures, we estimate the cost of the ultrasound 
inspection requirements of this proposed AD on U.S. operators to be 
$24,225, or $255 per product.
    Owner/operators have the option to do an ultrasound inspection in 
lieu of the required visual inspection.
    In addition, we estimate that any necessary follow-on actions would 
take

[[Page 4219]]

about 24 work-hours and require parts costing $5,220, for a cost of 
$7,260 per product to replace the left-hand main landing gear oleo 
strut. We have no way of determining the number of products that may 
need this action.
    In addition, we also estimate that any necessary follow-on actions 
would take about 45 work-hours and require parts costing $5,220, for a 
cost of $9,045 per product to replace the right-hand main landing gear 
oleo strut. We have no way of determining the number of products that 
may need this action.

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 AD:

Mitsubishi Heavy Industries, Ltd.: Docket No. FAA-2016-1363; 
Directorate Identifier 2015-CE-040-AD.

(a) Comments Due Date

    We must receive comments by March 11, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Mitsubishi Heavy Industries, Ltd. Models MU-
2B-30, MU-2B-35, MU-2B-36 airplanes, serial numbers 502 through 696, 
except 652 and 661, and Models MU-2B-36A and MU-2B-60 airplanes, 
serial numbers 661SA, and 697SA through 1569SA, certificated in any 
category.

(d) Subject

    Air Transport Association of America (ATA) Code 32: Landing 
Gear.

(e) Reason

    This AD was prompted by mandatory continuing airworthiness 
information (MCAI) originated by an aviation authority of another 
country to identify and correct an unsafe condition on an aviation 
product. The MCAI describes the unsafe condition as reports of 
cracks found in the fittings of the main landing gear oleo strut. We 
are issuing this proposed AD to prevent failure of the main landing 
gear oleo strut attach fitting, which could cause the landing gear 
to fail and result in loss of control.

(f) Actions and Compliance

    Unless already done, do the following actions:
    (1) Within the next 100 hours time-in-service (TIS) after the 
effective date of this AD or within the next 6 months after the 
effective date of this AD, whichever occurs first, do a visual 
inspection of the main landing gear oleo upper attach fittings for 
cracks. Do the inspection following the INSTRUCTIONS section in 
Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletin No. 243, 
dated June 30, 2015, and the INSTRUCTIONS section in Mitsubishi 
Heavy Industries, Ltd. MU-2 Service Bulletin No. 105/32-017, dated 
September 29, 2015, as applicable.
    (2) Before further flight after the inspection required in 
paragraph (f)(1) of this AD, if no signs of cracks are found, 
lubricate the pin assembly attached to the main landing gear oleo 
attach fitting as specified in Mitsubishi Heavy Industries, Ltd. MU-
2 Service News JCAB T.C.: No. 171, FAA T.C.: No. 124/32-011, dated 
April 27, 2012.
    (3) Within the next 100 hours TIS after doing the initial visual 
inspection required in paragraph (f)(1) of this AD or within the 
next 12 months after doing the initial visual inspection required in 
paragraph (f)(1) of this AD, whichever occurs first, do an 
ultrasound inspection of the main landing gear oleo upper attach 
fittings for cracks as specified in Mitsubishi Heavy Industries, 
Ltd. MU-2 Service News JCAB T.C.: No. 176, FAA T.C.: No. 128/32-013, 
dated July 18, 2013. This ultrasound inspection may also be done in 
place of the visual inspection required in paragraph (f)(1) of this 
AD if done within the next 100 hours TIS after the effective date of 
this AD or within the next 6 months after the effective date of this 
AD, whichever occurs first. Repetitively thereafter inspect every 
600 hours TIS or 36 months, whichever occurs first, and any time a 
hard landing or overweight landing occurs.
    (4) Before further flight after any inspection required in 
paragraph (f)(3) of this AD, if no signs of cracks are found, 
lubricate the pin assembly attached to the main landing gear oleo 
attach fitting as specified in Mitsubishi Heavy Industries, Ltd. MU-
2 Service News JCAB T.C.: No. 171, FAA T.C.: No. 124/32-011, dated 
April 27, 2012, and Mitsubishi Heavy Industries, Ltd. MU-2 Service 
News JCAB T.C.: No. 176, FAA T.C.: No. 128/32-013, dated July 18, 
2013.
    (5) Before further flight after any inspection required in 
paragraph (f)(1) and (f)(3) of this AD where cracks are found, 
replace the main landing gear oleo upper attach fittings following 
the INSTRUCTIONS section in Mitsubishi Heavy Industries, Ltd. MU-2 
Service Bulletin No. 243, dated June 30, 2015, and the INSTRUCTIONS 
sections in Mitsubishi Heavy Industries, Ltd. MU-2 Service Bulletin 
No. 105/32-017, dated September 29, 2015, as applicable. After 
replacement, continue with the repetitive ultrasound inspection 
requirements of paragraph (f)(3) of this AD.

(g) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Office, FAA, has the authority to approve AMOCs for this 
AD, if requested using the procedures found in 14 CFR 39.19. Send 
information to ATTN: Andrew McAnaul, Aerospace Engineer, FAA, ASW-
143 (c/o San Antonio MIDO), 10100 Reunion Place, Suite 650, San 
Antonio, Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370; 
email: <a href="/cdn-cgi/l/email-protection#f899969c8a9d8fd6959b9996998d94b89e9999d69f978e"><span class="__cf_email__" data-cfemail="a3c2cdc7d1c6d48dcec0c2cdc2d6cfe3c5c2c28dc4ccd5">[email protected]</span></a>. Before using any approved AMOC on any 
airplane to which the AMOC applies, notify your appropriate 
principal inspector (PI) in the FAA Flight Standards District Office 
(FSDO), or lacking a PI, your local FSDO.

[[Page 4220]]

    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(h) Related Information

    Refer to MCAI Japan Civil Aviation Bureau (JCAB) AD No. TCD-
8585-2015, dated July 1, 2015, for related information. You may 
examine the MCAI on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2016-1363. For service 
information related to this AD, contact Mitsubishi Heavy Industries 
America, Inc., c/o Turbine Aircraft Services, Inc., 4550 Jimmy 
Doolittle Drive, Addison, Texas 75001; telephone: (972) 248-3108, 
ext. 209; fax: (972) 248-3321; Internet: http://mu-2aircraft.com. 
You may review this referenced service information at the FAA, Small 
Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call 
(816) 329-4148.

    Issued in Kansas City, Missouri, on January 16, 2016.
Melvin Johnson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. 2016-01381 Filed 1-25-16; 8:45 am]
 BILLING CODE 4910-13-P


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