4214 Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Proposed Rules 

participation in and compliance with 

USDA programs; and to improve current 

regulations to help USDA agencies 

advance the USDA mission. USDA is 

particularly interested in public 

comments that speak to areas in which 

we can reduce costs and reporting 

burdens on the public, through 

technological advances or other 

modernization efforts, and comments on 

regulatory flexibility. 

III. Regulatory Flexibility 

USDA is also seeking public input on 

measures that can be taken to reduce 

burdens and increase flexibility and 

freedom of choice for the public. 

Regulatory flexibility includes a variety 

of regulatory techniques that can help 

avoid unnecessary costs on regulated 

entities and avoid negative impacts. 

Regulatory flexibility techniques could 

include: 

• Pilot projects, which can be used to 

test regulatory approaches; 

• Safe harbors, which are streamlined 

modes of regulatory compliance and can 

serve to reduce compliance costs; 

• Sunset provisions, which terminate 

a rule after a certain date; 

• Trigger provisions, which specify 

one or more threshold indicators that 

the rule is designed to address; 

• Phase-ins, which allow the rule to 

be phased-in for different groups at 

different times; 

• Streamlined requirements, which 

provide exemptions or other 

streamlined requirements if a particular 

entity (for example, a small business) 

may otherwise experience 

disproportionate burden from a rule; 

• State flexibilities, which provide 

greater flexibility to States or other 

regulatory partners, for example, giving 

them freedom to implement alternative 

regulatory approaches; and 

• Exceptions, which allow exceptions 

to part of the rule, or the entire rule in 

cases where there is a potential or 

suspected unintended consequence. 

IV. Existing USDA Regulations 

In addition to retrospective review 

actions and other regulatory reforms 

identified in USDA’s 2015 Fall 

Regulatory Agenda, we welcome 

comments from the public on any of 

USDA’s existing regulations and ways to 

improve them to help USDA agencies 

advance the mission of the Department 

consistent with the Executive Order. 

USDA notes that this RFI is issued 

solely for information and programplanning purposes. While responses to 

this RFI do not bind USDA to any 

further actions, all submissions will be 

reviewed by the appropriate program 

office, and made publicly available on 

http://www.regulations.gov. 

Dated: January 7, 2016. 

Thomas J. Vilsack, 

Secretary. 

[FR Doc. 2016–00693 Filed 1–25–16; 8:45 am] 

BILLING CODE 3410–90–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0338; Directorate 

Identifier 2014–CE–010–AD] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain Piper Aircraft, Inc. Model 

PA–31–350 airplanes. The NPRM 

proposed to require inspecting the fuel 

hose assembly and the turbocharger 

support assembly for proper clearance 

between them, inspecting each assembly 

for any sign of damage, and making any 

necessary repairs or replacements. The 

NPRM was prompted by a report of an 

engine fire caused by a leak in the fuel 

pump inlet hose. This action revises the 

NPRM by requiring the use of revised 

procedures in a new service bulletin. 

We are proposing this supplemental 

NPRM (SNPRM) to correct the unsafe 

condition on these products. Since these 

actions impose an additional burden 

over that proposed in the NPRM, we are 

reopening the comment period to allow 

the public the chance to comment on 

these proposed changes. 

DATES: We must receive comments on 

this SNPRM by March 11, 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 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Piper 

Aircraft, Inc., 2926 Piper Drive, Vero 

Beach, Florida 32960; telephone: (772) 

567–4361; fax: (772) 978–6573; Internet: 

www.piper.com/home/pages/

Publications.cfm. You may view 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–2014– 

0338; 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 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Gary 

Wechsler, Aerospace Engineer, FAA, 

Atlanta Aircraft Certification Office, 

1701 Columbia Avenue, College Park, 

Georgia 30337; telephone: (404) 474– 

5575; fax: (404) 474–5606; email: 

gary.wechsler@faa.gov. 

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–2014–0338; Directorate Identifier 

2014–CE–010–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://

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. 

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Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Proposed Rules 4215 

Discussion 

We issued an NPRM to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Piper Aircraft, Inc. 

Model PA–31–350 airplanes. The NPRM 

published in the Federal Register on 

June 3, 2014 (79 FR 31888). The NPRM 

proposed to require inspecting the fuel 

hose assembly and the turbocharger 

support assembly for proper clearance 

between them, inspecting each assembly 

for any sign of damage, and making any 

necessary repairs or replacements. 

Actions Since Previous NPRM Was 

Issued 

Since we issued the NPRM (79 FR 

31888, June 3, 2014), Piper Aircraft, Inc. 

has revised the related service 

information to clarify which engines are 

part of the airplane applicability and to 

revise the accomplishment instructions 

for inspecting for proper clearance 

between the fuel hose assembly and the 

turbocharger support assembly, 

inspecting the fuel hose assembly and 

the turbocharger support assembly for 

any signs of damage, and taking all 

necessary corrective actions. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (79 FR 31888, 

June 3, 2014) and the FAA’s response to 

the comment. 

Request To Change the Applicability of 

the AD 

Joe Miller of Werbelow’s Air 

Ventures, Inc., requested that the 

Applicability section of the AD be 

changed so that it applies only to Piper 

Aircraft, Inc. Model PA–31–350 

airplanes with TIO–540–J2B engine 

configurations. 

The commenter stated that Model 

PA–31–350 airplanes configured with 

TIO–540–J2B engines have fuel pumps 

orientated such that their inlet fuel hose 

assemblies can adversely contact a 

nearby turbocharger support assembly. 

The commenter also stated that the 

other type certificated engine 

configurations of applicable Model PA– 

31–350 airplanes have engine fuel 

pumps orientated such that their inlet 

fuel hose assemblies cannot adversely 

contact the nearby turbocharger support 

assembly. 

The commenter requested that the AD 

exclude Model PA–31–350 airplanes 

that have the fuel pump installed on a 

Lycoming (L)TIO–540–J2BD engine. 

We partially agree with the 

commenter. We agree that there is more 

than one orientation for the engine fuel 

pump in the applicable Model PA–31– 

350 airplanes with (L)TIO–540 series 

engines because this is shown in the 

Lycoming parts catalog for the TIO, 

LTIO–540–J2B, and –J2BD engines, 

which were type certificated on the 

Model PA–31–350 airplane. 

We disagree with the commenter’s 

request to change the actions of the AD 

so that they apply only to the inlet hose 

assembly for the engine fuel pump of 

the TIO–540–J2B engine configuration 

of applicable Model PA–31–350 

airplanes. We reviewed the Lycoming 

parts catalog for the TIO, LTIO–540–J2B, 

and –J2BD engines and applicable 

Model PA–31–350 airplanes with 

(L)TIO–540–J2BD engines and found 

that the TIO and LTIO–540–J2B and 

–J2BD engines each have a fuel pump 

with one fuel hose assembly (either and 

inlet or exit) that can be incorrectly 

installed so that it is in contact with the 

nearby turbocharger support assembly. 

Related Service Information Under 

1 CFR Part 51 

We reviewed Piper Aircraft, Inc. 

Service Bulletin No. 1257A, dated 

August 4, 2015. The service information 

describes procedures for the following. 

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 SNPRM. 

—Inspecting for a minimum 3/16-inch 

clearance between the fuel hose 

assembly and the turbocharger 

support assembly and making any 

necessary adjustments. 

—Inspecting the fuel hose assembly for 

any signs of damage and, if necessary, 

replacing with a serviceable part. 

—Inspecting the turbocharger support 

assembly for any signs of damage and, 

if necessary, repairing or replacing 

with a serviceable part. 

—Performing an engine run-up to check 

for any leaks. 

FAA’s Determination 

We are proposing this SNPRM 

because we evaluated all the relevant 

information and determined the unsafe 

condition described previously is likely 

to exist or develop in other products of 

the same type design. Certain changes 

described above expand the scope of the 

NPRM (79 FR 31888, June 3, 2014). As 

a result, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 

the public to comment on this SNPRM. 

Proposed Requirements of This SNPRM 

This SNPRM would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between this Proposed AD 

and the Service Information.’’ 

Differences Between This SNPRM and 

the Service Information 

There are differences between the 

compliance times for the corrective 

actions in this proposed AD and those 

in the related service information. 

We based the compliance times in 

this proposed AD on risk analysis and 

cost impact to operators. There has only 

been one event of the reported incident 

in the operational history of Piper 

Model PA–31–350 airplanes. Cost was 

also a strong consideration due to the 

age of the fleet and the number of 

airplanes still in service. 

The one-time inspection required in 

this proposed AD is very inexpensive 

and requires minimal time to 

accomplish. It is expected that almost 

all airplanes in service can be cleared 

with a single inspection, and no 

additional actions or costs would be 

incurred by the vast majority of the 

fleet. 

We determined that a single 

inspection with any necessary 

corrective actions is an adequate 

terminating action for the unsafe 

condition. The risk related to future 

maintenance on the fuel line would be 

mitigated by the related service 

information and awareness from this 

proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 773 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspect for proper clearance between the fuel hose assembly and the turbocharger support assembly..5 work-hour × $85 per hour = 

$85.

N/A $42.50 $32,852.50 

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4216 Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Proposed Rules 

ESTIMATED COSTS—Continued 

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspect the fuel hose assembly for evidence of leaking, 

cracking, chafing, and any other sign of damage.

.5 work-hour × $85 per hour = 

$42.50.

N/A 42.50 32,852.50 

Inspect the turbocharger support assembly for evidence of 

chafing and any other sign of damage.

.5 work-hour × $85 per hour = 

$42.50.

N/A 42.50 32,852.50 

Engine run-up/leak check ........................................................ 1 work-hour × $85 = $85 (.5 

work hour per engine).

N/A 85.00 65,705.00 

We estimate the following costs to do 

any necessary follow-on actions that 

will be required based on the results of 

the inspection. We have no way of 

determining the number of airplanes 

that might need these corrective actions. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Adjust routing of fuel hose assembly for proper clearance between the 

fuel hose assembly and the turbocharger support assembly.

5.5 work-hours × $85 per hour = 

$467.50.

N/A $467.50 

Replace Piper fuel pump inlet hose assembly, part number 39995–34 (2 

per airplane).

1 work-hour × $85 per hour = $85 .. $1,068 1,153.00 

Replace Lycoming turbocharger support assembly, part number LW– 

18302 (2 per airplane).

24 work-hours × $85 per hour = 

$2,040.

12,874 14,914.00 

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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Piper Aircraft, Inc.: FAA–2014–0338; 

Directorate Identifier 2014–CE–010–AD. 

(a) Comments Due Date 

We must receive comments by March 11, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Piper Aircraft, Inc. 

Model PA–31–350 airplanes, serial numbers 

31–5001 through 31–5004, 31–7305005 

through 31–8452024, and 31–8253001 

through 31–8553002, certificated in any 

category, that are equipped with the 

following engines and fuel pump hose 

assemblies: 

TABLE 1 TO PARAGRAPH (C) OF THIS AD—APPLICABLE ENGINES AND FUEL PUMP HOSE ASSEMBLIES

Engine Manufacturer’s hose name Manufacturer’s part No. (P/N) Hose description 

TIO–540–J2B (right wing) .............. Hose Assembly—Fuel .................. Piper 39995–034 .......................... Inlet fuel hose to engine fuel 

pump. 

LTIO–540–J2B (left wing) .............. Hose, Fuel pump to Injector ......... Lycoming LW–12877–6S142 ....... Exit fuel hose from engine fuel 

pump. 

TIO540–J2BD (right wing) ............. Hose, Fuel pump to Injector ......... Lycoming LW–12877–6S142 ....... Exit fuel hose from engine fuel 

pump. 

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Federal Register / Vol. 81, No. 16 / Tuesday, January 26, 2016 / Proposed Rules 4217 

TABLE 1 TO PARAGRAPH (C) OF THIS AD—APPLICABLE ENGINES AND FUEL PUMP HOSE ASSEMBLIES—Continued 

Engine Manufacturer’s hose name Manufacturer’s part No. (P/N) Hose description 

LTIO–540–J2BD (left wing) ........... Hose Assembly—Fuel .................. Piper 39995–034 .......................... Inlet fuel hose to engine fuel 

pump. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 73: Engine Fuel and Control. 

(e) Unsafe Condition 

This AD was prompted by a report of an 

engine fire caused by a leak in the fuel pump 

inlet hose. We are issuing this AD to correct 

the unsafe condition on these products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified in paragraphs 

(g)(1) through (j)(2) of this AD, unless already 

done. 

(g) Ensure Proper Clearance Between the 

Fuel Hose Assembly and the Turbocharger 

Support Assembly 

(1) Within the next 60 hours time-inservice (TIS) after the effective date of this 

AD or within the next 6 months after the 

effective date of this AD, whichever occurs 

first, inspect to determine the clearance 

between the inlet and exit fuel hose 

assemblies listed in table 1 to paragraph (c) 

of this AD, and each turbocharger support 

assembly, Lycoming P/N LW–18302. There 

should be a minimum 3⁄16-inch clearance. Do 

the inspection following the INSTRUCTIONS 

section of Piper Aircraft, Inc. Service Bulletin 

No. 1257A, dated August 4, 2015. 

(2) Before further flight after the inspection 

required in paragraph (g)(1) of this AD, if the 

measured clearance is less than 3⁄16-inch, 

make all necessary adjustments to make the 

clearance a minimum of 3⁄16-inch between 

the inlet and exit fuel hose assemblies listed 

in table 1 to paragraph (c) of this AD and 

each turbocharger support assembly, 

Lycoming P/N LW–18302, following the 

INSTRUCTIONS section of Piper Aircraft, 

Inc. Service Bulletin No. 1257A, dated 

August 4, 2015. 

(h) Visually Inspect the Fuel Hose Assembly 

and Replace if Necessary 

(1) Within the next 60 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, visually inspect the 

inlet and exit fuel hose assemblies listed in 

table 1 to paragraph (c) of this AD for 

evidence of leaking, cracking, chafing, and 

any other sign of damage. Do the inspection 

following the INSTRUCTIONS section of 

Piper Aircraft, Inc. Service Bulletin No. 

1257A, dated August 4, 2015. 

(2) Before further flight after the inspection 

required in paragraph (h)(1) of this AD, if any 

evidence of leaking, cracking, chafing, or any 

other sign of damage is found in any inlet or 

exit fuel host assembly listed in table 1 to 

paragraph (c) of this AD, replace the fuel 

hose assembly with a serviceable part. Do the 

replacement following the INSTRUCTIONS 

section of Piper Aircraft, Inc. Service Bulletin 

No. 1257A, dated August 4, 2015. 

(i) Visually Inspect the Turbocharger 

Support Assembly and Replace if Necessary 

(1) Within the next 60 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, visually inspect each 

turbocharger support assembly, Lycoming P/ 

N LW–18302, for evidence of chafing and any 

other signs of damage. Do the inspection 

following the INSTRUCTIONS section of 

Piper Aircraft, Inc. Service Bulletin No. 

1257A, dated August 4, 2015. 

(2) Before further flight after the inspection 

required in paragraph (i)(1) of this AD, if any 

evidence of chafing or any other sign of 

damage is found on any turbocharger support 

assembly, replace Lycoming 

P/N LW–18302 with a serviceable part. Do 

the replacement following the 

INSTRUCTIONS section of Piper Aircraft, 

Inc. Service Bulletin No. 1257A, dated 

August 4, 2015. 

(j) Engine Run-Up 

(1) If any fuel line component was adjusted 

or replaced during any actions required in 

paragraphs (g)(1) through (i)(2) of this AD, 

before further flight, perform an engine runup on the ground to check for leaks. Do the 

engine run-up following the INSTRUCTIONS 

section of Piper Aircraft, Inc. Service Bulletin 

No. 1257A, dated August 4, 2015. 

(2) If any leaks found during the engine 

run-up required in paragraph (j)(1) of this AD 

emanate from any fuel line component 

adjusted, repaired, or replaced during any 

actions required in paragraphs (g)(1) through 

(i)(2) of this AD, before further flight, take all 

necessary corrective actions following the 

INSTRUCTIONS section of Piper Aircraft, 

Inc. Service Bulletin No. 1257A, dated 

August 4, 2015. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) 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. 

(l) Related Information 

(1) For more information about this AD, 

contact Gary Wechsler, Aerospace Engineer, 

FAA, Atlanta ACO, 1701 Columbia Avenue, 

College Park, Georgia 30337; telephone: (404) 

474–5575; fax: (404) 474–5606; email: 

gary.wechsler@faa.gov. 

(2) For service information identified in 

this AD, contact Piper Aircraft, Inc., 926 

Piper Drive, Vero Beach, Florida 32960; 

telephone: (772) 567–4361; fax: (772) 978– 

6573; Internet: www.piper.com/home/pages/

Publications.cfm. You may review copies of 

the 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. 2016–01380 Filed 1–25–16; 8:45 am] 

BILLING CODE 4910–13–P 

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). 

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. 

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