This section of the FEDERAL REGISTER

contains regulatory documents having general

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are keyed to and codified in the Code of

Federal Regulations, which is published under

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REGISTER issue of each week.

Rules and Regulations Federal Register

26097 

Vol. 81, No. 84 

Monday, May 2, 2016 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–1363; Directorate 

Identifier 2015–CE–040–AD; Amendment 

39–18496; AD 2016–08–19] 

RIN 2120–AA64 

Airworthiness Directives; Mitsubishi 

Heavy Industries, Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting 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 AD results from 

mandatory continuing airworthiness 

information (MCAI) issued 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 AD to require 

actions to address the unsafe condition 

on these products. 

DATES: This AD is effective June 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 6, 2016. 

ADDRESSES: 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 Document 

Management Facility, U.S. Department 

of Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

For service information identified in 

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://mu2aircraft.com. 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. It is also available on the Internet 

at http://www.regulations.gov by 

searching for Docket No. FAA–2016– 

1363. 

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: 

andrew.mcanaul@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Mitsubishi Heavy 

Industries, Ltd. Models MU–2B–30, 

MU–2B–35, MU–2B–36, MU–2B–36A, 

and MU–2B–60 airplanes. The NPRM 

was published in the Federal Register 

on January 26, 2016 (81 FR 4217). The 

NPRM proposed to correct an unsafe 

condition for the specified products and 

was based on mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country. 

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/

#!docketDetail;D=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 airplanes, 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (81 

FR 4217, January 26, 2016) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (81 FR 4217, 

January 26, 2016) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (81 FR 4217, 

January 26, 2016). 

Related Service Information Under 1 

CFR Part 51 

We reviewed Mitsubishi Heavy 

Industries, Ltd. MU–2 Service Bulletin 

No. 243, dated June 30, 2015, and MU– 

2 Service Bulletin No. 105/32–017, 

dated September 29, 2015. The service 

information describes 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. We also 

reviewed 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 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. 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 the AD. 

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26098 Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 

Differences Between This 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 incorporating that 

requirement through the rulemaking 

process. 

Costs of Compliance 

We estimate that this AD will affect 

95 products of U.S. registry. We also 

estimate that it will take about 5 workhours per product to comply with the 

visual inspection requirement of this 

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 AD on U.S. 

operators to be $40,375, or $425 per 

product. 

We also estimate that it will take 

about 3 work-hours per product to 

comply with the ultrasound inspection 

requirements of this 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 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 will take 

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 will 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 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 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. 

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 the NPRM, 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. 

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 

■ 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 AD: 

2016–08–19 Mitsubishi Heavy Industries, 

Ltd.: Amendment 39–18496; Docket No. 

FAA–2016–1363; Directorate Identifier 

2015–CE–040–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective June 6, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Mitsubishi Heavy 

Industries, Ltd. Models MU–2B–30, MU–2B– 

35, and 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 upper attach fittings of 

the main landing gear oleo strut. We are 

issuing this 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-inservice (TIS) after June 6, 2016 (the effective 

date of this AD) or within the next 6 months 

after June 6, 2016 (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 

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Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 26099 

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 June 6, 2016 (the 

effective date of this AD) or within the next 

6 months after June 6, 2016 (the effective date 

of this AD), whichever occurs first. 

Repetitively thereafter ultrasound inspect the 

attach fittings 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) and lubrication requirements 

of paragraph (f)(4) 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: 

andrew.mcanaul@faa.gov. 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. 

(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/#!docketDetail;D=FAA2016-1363. 

(i) 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 the AD specifies otherwise. 

(i) Mitsubishi Heavy Industries, Ltd. MU– 

2 Service Bulletin No. 105/32–017, dated 

September 29, 2015. 

(ii) Mitsubishi Heavy Industries, Ltd. MU– 

2 Service Bulletin No. 243, dated June 30, 

2015. 

(iii) Mitsubishi Heavy Industries, Ltd. MU– 

2 Service News JCAB T.C.: No. 176, FAA 

T.C.: No. 128/32–013, dated July 18, 2013. 

(iv) 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) For Mitsubishi Heavy Industries, Ltd 

service information identified in 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://mu2aircraft.com. 

(4) You may view this 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. In 

addition, you can access this service 

information on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2016–1363. 

(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: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Kansas City, Missouri, on April 

14, 2016. 

Robert P. Busto, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–09239 Filed 4–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0657; Directorate 

Identifier 2014–NM–058–AD; Amendment 

39–18501; AD 2016–09–03] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Dassault Aviation Model FALCON 2000, 

FALCON 2000EX, MYSTERE–FALCON 

900, and FALCON 900EX airplanes. 

This AD was prompted by reports of a 

co-pilot sliding aft on his seat during 

take-off at rotation. This AD requires 

replacement of certain springs installed 

on the pilot and co-pilot seats. We are 

issuing this AD to prevent fatigue wear, 

which, if not corrected, could cause the 

seat to slide and the pilot or co-pilot to 

lose contact with the controls, leading to 

an inadvertent input on the flight 

control commands during take-off or 

climb, possibly resulting in loss of 

control of the airplane. 

DATES: This AD becomes effective June 

6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 6, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Dassault Falcon Jet Corporation, 

Teterboro Airport, P.O. Box 2000, South 

Hackensack, NJ 07606; telephone 201– 

440–6700; Internet http://

www.dassaultfalcon.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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0657. 

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– 

0657; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

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