[Federal Register Volume 81, Number 180 (Friday, September 16, 2016)]
[Proposed Rules]
[Pages 63725-63728]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-22182]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9139; Directorate Identifier 2016-CE-023-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-10, MU-2B-15, 
MU-2B-20, MU-2B-25, MU-2B-26, MU-2B-26A, MU-2B-30, MU-2B-35, MU-2B-36, 
MU-2B-36A, MU-2B-40, 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 wing spacer plates. We are 
issuing this proposed AD to require actions to detect and correct 
cracks in the wing spacer plates, which could result in reduced 
structural integrity of the wings and loss of control.

DATES: We must receive comments on this proposed AD by October 31, 
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 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-
9139; 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

[[Page 63726]]

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: [email protected].

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-2016-9139; 
Directorate Identifier 2016-CE-023-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-8783-2016, dated June 28, 
2016 (referred to after this as ``the MCAI''), to correct an unsafe 
condition for certain Mitsubishi Heavy Industries, Ltd. (MHI) Models 
MU-2B-20, MU-2B-25, MU-2B-26, 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-
2016-9139.
    As part of the MHI MU-2B aging aircraft program, one-piece and 
three-piece main wings were subjected to detailed teardown inspections, 
and cracks were found in the wing spacer plates attached to the forward 
lower spar area at wing station 580. It was determined that the cracks 
resulted from fatigue caused by flight loads.
    Japan is the State of Design for MHI Models MU-2B-20, MU-2B-25, MU-
2B-26, MU-2B-30, MU-2B-35, and MU-2B-36 airplanes, which the MCAI AD 
applies to, and the United States is the State of Design for MHI Models 
MU-2B-26A, MU-2B-36A, MU-2B-40, and MU-2B-60 airplanes.

Related Service Information Under 1 CFR Part 51

    Mitsubishi Heavy Industries, Ltd. has issued MU-2 Service Bulletin 
No. 245, dated April 21, 2016, and MU-2 Service Bulletin No. 107/57-
005, dated May 3, 2016. These service bulletins describe procedures for 
doing a fluorescent penetrant inspection of the wing spacer plates for 
cracks and replacing cracked wing spacer plates with an improved part. 
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 of this NPRM.

FAA's Determination and Requirements of This Proposed AD

    The Models MU-2B-20, MU-2B-25, MU-2B-26, MU-2B-30, MU-2B-35, and 
MU-2B-36 airplanes have been approved by the aviation authority of 
another country, and are 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.
    The procedures described in this proposed AD meet the FAA's 
expectations for flight with known cracks described in Chapter 6 in FAA 
Advisory Circular (AC) 23-13A Fatigue, Fail-Safe and Damage Tolerance 
Evaluation of Metallic Structure for Normal, Utility, Acrobatic, and 
Commuter Category Airplanes.
    In addition, we are including the Models MU-2B-26A, MU-2B-36A, MU-
2B-40, and MU-2B-60 airplanes for which the United States is the State 
of Design and the unsafe condition exists and is likely to exist or 
develop in other products of the same type design.
    The Models MU-2B-10 and MU-2B-15 are not included in Japan Civil 
Aviation Bureau (JCAB) AD No. TCD-8783-2016, dated June 28, 2016, or 
any of the service bulletins referenced in this proposed AD. The FAA 
does not believe there are any of these airplanes currently in 
operation, but are including them as a part of this proposed AD.

Costs of Compliance

    We estimate that this proposed AD will affect 209 products of U.S. 
registry. We also estimate that it would take about 8 work-hours per 
product to comply with the fluorescent penetrant 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 fluorescent 
penetrant inspection requirement of this proposed AD on U.S. operators 
to be $142,120, or $680 per product.
    In addition, we estimate the following to do any necessary follow-
on actions:
    It would take about 200 work-hours and require parts costing $500, 
for a cost of $17,500, per product to replace a cracked wing spacer 
plate on one side of the airplane.
    It would take about 250 work-hours and require parts costing 
$1,000, for a cost of $22,250, per product to replace a cracked wing 
spacer plate on both sides of the airplane.
    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:

[[Page 63727]]

    (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-2016-9139; 
Directorate Identifier 2016-CE-023-AD.

(a) Comments Due Date

    We must receive comments by October 31, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the following Mitsubishi Heavy Industries, 
Ltd. (MHI) models airplanes that are certificated in any category:
    (1) MU-2B-10 and MU-2B-15: Serial Numbers (S/Ns) 101 and 103 
through 120.

    Note 1 to paragraph (c)(1) of this AD: The Models MU-2B-10 and 
MU-2B-15 are not included in Japan Civil Aviation Bureau (JCAB) AD 
No. TCD-8783-2016, dated June 28, 2016, or any of the service 
bulletins referenced in this AD. The FAA does not believe there are 
any of these airplanes currently in operation, but are including 
them as a part of this AD.

    (2) MU-2B-20, MU-2B-25, and MU-2B-26: S/Ns 102 and 121 through 
347, except 313 and 321;
    (3) MU-2B-25, MU-2B-26, MU-2B-26A, and MU-2B-40: S/Ns 313SA, 
321SA, and 348SA through 459SA;
    (4) MU-2B-30, MU-2B-35, and MU-2B-36: S/Ns 502 through 696, 
except 652 and 661; and
    (5) MU-2B-36A and MU-2B-60 airplanes: S/Ns 661SA, and 697SA 
through 1569SA.

(d) Subject

    Air Transport Association of America (ATA) Code 57: Wings.

(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 wing spacer plates. We are issuing this AD to 
detect and correct cracks in the wing spacer plates, which could 
result in reduced structural integrity of the wings and loss of 
control.

(f) Compliance

    Comply with paragraphs (g)(1) through (3) of this AD using the 
following service bulletins within the compliance times specified 
below, unless already done. The Models MU-2B-10 and MU-2B-15 
currently do not have service bulletins associated with them. The 
FAA does not believe any of these airplanes are currently in 
operation. If they do become operational, an alternative method of 
compliance must be obtained to comply with this AD.
    (1) For Models MU-2B-20, MU-2B-25, and MU-2B-26: S/Ns 102 and 
121 through 347, except 313 and 321, and MU-2B-30, MU-2B-35, and MU-
2B-36: S/Ns 502 through 696, except 652 and 661: Use Mitsubishi 
Heavy Industries, Ltd. (MHI) MU-2 Service Bulletin No. 245, dated 
April 21, 2016.
    (2) Models MU-2B-25, MU-2B-26, MU-2B-26A, and MU-2B-40: S/Ns 
313SA, 321SA, and 348SA through 459SA, and MU-2B-36A and MU-2B-60 
airplanes: S/Ns 661SA, and 697SA through 1569SA: Use MHI MU-2 
Service Bulletin No. 107/57-005, dated May 3, 2016.

(g) Actions

    (1) Do an initial fluorescent penetrant inspection of the wing 
spacer plates at whichever of the following compliance times that 
occurs later, and repetitively inspect thereafter at intervals not 
to exceed 2,000 hours time-in-service (TIS). Do the inspections 
following the Instructions section of the service bulletins 
identified in paragraph (f) of this AD, including all subparagraphs, 
as applicable.
    (i) At or before accumulating 7,500 hours TIS; or
    (ii) Within the next 200 hours TIS after the effective date of 
this AD or within the next 12 months after the effective date of 
this AD, whichever occurs first.
    (2) During any inspection required in paragraph (g)(1) of this 
AD, including all subparagraphs, if any crack is found that is 0.6-
inch or more in length, before further flight after the inspection 
in which the crack is found, replace the cracked wing spacer plate 
with an improved wing spacer plate, part number (P/N) 017A-11102-13 
or 017A-11102-14. Do the replacement following the Instructions 
section of the service bulletins identified in paragraph (f) of this 
AD, including all subparagraphs, as applicable. Installing the 
improved wing spacer plates terminates the repetitive inspections 
required in paragraph (g)(1) of this AD.
    (3) During any inspection required in paragraph (g)(1) of this 
AD, including all subparagraphs, if any crack is found that is less 
than 0.6-inch in length, repetitively fluorescent penetrant inspect 
for crack growth every 600 hours TIS after the inspection in which 
the crack was found. Do the inspections following the Instructions 
section of the service bulletins identified in paragraph (f) of this 
AD, including all subparagraphs, as applicable. If it is found 
during any required inspection that the crack has grown to0.6-inch 
in length or more, before further flight, replace the wing spacer 
plate as specified in paragraph (g)(2) of this AD.
    (4) Installing improved wing spacer plates, part number (P/N) 
017A-11102-13 or 017A-11102-14, terminates the repetitive 
inspections required in paragraph (g)(1) of this AD. You may install 
the improved wing spacer plates at any time to terminate the 
repetitive inspection requirement of this AD.

(h) 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: [email protected]. 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.
    (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.

(i) Related Information

    Refer to MCAI JCAB AD No. TCD-8783-2016, dated June 28, 2016, 
for related information. You may examine the MCAI on the Internet at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2016-9139. 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. Youmay 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.


[[Page 63728]]


    Issued in Kansas City, Missouri, on September 8, 2016.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-22182 Filed 9-15-16; 8:45 am]
 BILLING CODE 4910-13-P