Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 21711 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(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: http://

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

Issued in Renton, Washington, on March 

31, 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–08346 Filed 4–12–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–0068; Directorate 

Identifier 2015–CE–037–AD; Amendment 

39–18484; AD 2016–08–08] 

RIN 2120–AA64 

Airworthiness Directives; SOCATA 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 92–06–10 

for SOCATA Models MS 880B, MS 885, 

MS 892A–150, MS 892E–150, MS 893A, 

MS 893E, MS 894A, MS 894E, Rallye 

100S, Rallye 150ST, Rallye 150T, Rallye 

235E, and Rallye 235C 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 fatigue failure of the nose 

landing gear wheel axle. We are issuing 

this AD to require actions to address the 

unsafe condition on these products. 

DATES: This AD is effective May 18, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 18, 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– 

0068; or in person at the Docket 

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 SOCATA, Direction des 

services, 65921 Tarbes Cedex 9, France; 

phone: +33 (0) 5 62 41 73 00; fax: +33 

(0) 5 62 41 76 54; email: info@

socata.daher.com; Internet: http://

www.tbm.aero/. For the United States, 

contact SOCATA NORTH AMERICA, 

North Perry Airport, 601 NE 10 Street, 

Pompano Beach, Florida 33060; phone: 

(954) 366–3331; Internet: http://

www.socatanorthamerica.com/

default.htm. 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– 

0068. 

FOR FURTHER INFORMATION CONTACT: 

Albert Mercado, Aerospace Engineer, 

901 Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4119; fax: (816) 329–4090; email: 

albert.mercado@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 SOCATA Models MS 880B, MS 

885, MS 894A, MS 893A, MS 892A–150, 

MS 892E–150, MS 893E, MS 894E, 

Rallye 100S, Rallye 150T, Rallye 150ST, 

Rallye 235E, and Rallye 235C airplanes. 

That NPRM was published in the 

Federal Register on January 15, 2016 

(81 FR 2134), and proposed to 

supersede AD 92–06–10, Amendment 

39–8190 (57 FR 8063; March 6, 1992) 

(‘‘92–06–10’’). 

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 MCAI 

states that: 

A nose landing gear (NLG) wheel axle 

rupture occurred in service. The results of 

the technical investigation revealed that this 

failure was due to premature wear. 

This condition, if not detected and 

corrected, could lead to cracks in the axle 

and detachment of axle and wheel, possibly 

resulting in failure of the NLG with 

consequent damage to the aeroplane and 

injury to occupants. 

To address this potential unsafe condition, 

DGAC France issued AD 91–163(A) (later 

revised twice) to require repetitive detailed 

inspections (DET) of the NLG wheel axle and 

replacement of the NLG wheel axle 

attachment screws in accordance with the 

instructions of SOCATA Service Bulletin 

(SB) 150–32. 

Since DGAC France AD 91–163(A)R2 was 

issued, new findings led to an adjustment of 

the inspection interval. Consequently, 

SOCATA issued SB 150–32, now at Revision 

3. 

The MCAI can be found in the AD 

docket on the Internet at: http://

www.regulations.gov/

#!documentDetail;D=FAA-2016-0068- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (81 

FR 2134, January 15, 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 2134, 

January 15, 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 2134, 

January 15, 2016). 

Related Service Information Under 1 

CFR Part 51 

We reviewed Daher-Socata Mandatory 

Service Bulletin SB 150–32, Revision 3, 

dated September 2015. The service 

bulletin describes procedures for 

inspection of the nose gear wheel axle. 

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. 

Costs of Compliance 

We estimate that this AD will affect 

77 products of U.S. registry. We also 

estimate that it would take about 10 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about $500 

per product. 

Based on these figures, we estimate 

the cost of the AD on U.S. operators to 

be $103,950, or $1,350 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 


jstallworth on DSK7TPTVN1PROD with RULES
21712 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 

about 3 work-hours and require parts 

costing $1,450, for a cost of $1,705 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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– 

0068; 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 

removing Amendment 39–8190 (57 FR 

8063; March 6, 1992) and adding the 

following new AD: 

2016–08–08 SOCATA: Amendment 39– 

18484; Docket No. FAA–2016–0068; 

Directorate Identifier 2015–CE–037–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective May 18, 2016. 

(b) Affected ADs 

This AD supersedes AD 92–06–10 

Amendment 39–8190 (57 FR 8063; March 6, 

1992) (‘‘AD 92–06–10’’). 

(c) Applicability 

This AD applies to SOCATA Models MS 

880B, MS 885, MS 892A–150, MS 892E–150, 

MS 893A, MS 893E, MS 894A, MS 894E, 

Rallye 100S, Rallye 150ST, Rallye 150T, 

Rallye 235E, and Rallye 235C airplanes, all 

serial numbers, 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 fatigue 

failure of the nose landing gear wheel axle. 

We are issuing this AD to detect and correct 

chafing and cracking of the nose gear wheel 

axle, which could lead to failure of the nose 

landing gear with consequent damage to the 

airplane and/or occupants. 

(f) Actions and Compliance 

Do the actions in paragraphs (f)(1) through 

(f)(5) of this AD, including all subparagraphs. 

If the initial actions of paragraphs (f)(1), 

(f)(2), (f)(3), and (f)(4) of this AD have already 

been done before the effective date of this 

AD, then do the repetitive actions of these 

paragraphs at the specified times. 

(1) Do a detailed visual inspection of the 

intersection between the axle radius and the 

nose landing gear fork area for chafing at 

whichever occurs later in paragraph (f)(1)(i) 

or (f)(1)(ii) of this AD and repetitively 

thereafter at intervals not to exceed 200 hours 

time-in-service (TIS) following Daher-Socata 

Mandatory Service Bulletin SB 150–32, 

Revision 3, dated September 2015: 

(i) Upon accumulating 200 hours TIS since 

the airplane’s first flight or 200 hours TIS 

since the last inspection required by AD 92– 

06–10; or 

(ii) Within the next 50 hours TIS after May 

18, 2016 (the effective date of this AD) or 

within 500 hours TIS since the last 

inspection required by AD 92–06–10, 

whichever occurs first. 

(2) Do a dye penetrant inspection on the 

nose wheel axle for cracks, distortion, and 

nicks or wear at whichever occurs later in 

paragraph (f)(2)(i) or (f)(2)(ii) of this AD and 

repetitively thereafter at intervals not to 

exceed 200 hours time-in-service (TIS) 

following Daher-Socata Mandatory Service 

Bulletin SB 150–32, Revision 3, dated 

September 2015: 

(i) Upon accumulating 200 hours TIS since 

the airplane’s first flight or 200 hours TIS 

since the last inspection required by AD 92– 

06–10; or 

(ii) Within the next 50 hours TIS after May 

18, 2016 (the effective date of this AD) or 

within 500 hours TIS since the last 

inspection required by AD 92–06–10, 

whichever occurs first. 

(3) If any cracks or damage is found in any 

inspection required by paragraphs (f)(1) or 

(f)(2) in this AD, contact SOCATA for FAAapproved repair or replacement instructions 

approved specifically for this AD and, before 

further flight, implement those instructions. 

Use the contact information found in 

paragraph (j) of this AD to contact SOCATA. 

(4) Replace the nose landing gear wheel 

axle attachment screws with new screws at 

whichever occurs later in paragraph (f)(4)(i) 

or (f)(4)(ii) of this AD following Daher-Socata 

Mandatory Service Bulletin SB 150–32, 

Revision 3, dated September 2015: 

(i) Upon accumulating 2,000 hours TIS 

since airplane’s first flight or 2,000 hours TIS 

since last nose landing gear wheel 

attachment screw replacement with new 

screws; or 

(ii) Within 50 hours TIS since April 17, 

1992 (the effective date retained from AD 92– 

06–10). 

(5) After May 18, 2016 (the effective date 

of this AD), a used nose landing gear or a 

used nose landing gear wheel axle may be 

installed provided it has been inspected and 

found free of cracks and/or damage and the 

nose landing gear wheel axle attachment 

screws have been replaced with new screws 

as specified in paragraphs (f)(1), (f)(2), and 

(f)(4) of this AD. 

(g) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

This AD allows credit for the inspections 

required in paragraph (f)(1) and (f)(2) of this 

AD, if done before May 18, 2016 (the 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 21713 

effective date of this AD), following DaherSocata Mandatory Service Bulletin SB 150– 

32, Revision 2, dated January 1994. 

(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: Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4119; fax: (816) 329– 

4090; email: albert.mercado@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 FAAapproved 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 European Aviation Safety 

Agency (EASA) AD 2015–0203, dated 

October 7, 2015; and Daher-Socata 

Mandatory Service Bulletin SB 150–32, 

Revision 2, dated January 1994, for related 

information. The MCAI can be found in the 

AD docket on the Internet at: http://

www.regulations.gov/#!documentDetail;

D=FAA-2016-0068-0002. 

(j) 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) Daher-Socata Mandatory Service 

Bulletin SB 150–32, Revision 3, dated 

September 2015. 

(ii) Reserved. 

(3) For SOCATA service information 

identified in this AD, contact SOCATA, 

Direction des services, 65921 Tarbes Cedex 9, 

France; phone: +33 (0) 5 62 41 73 00; fax: +33 

(0) 5 62 41 76 54; email: info@

socata.daher.com; Internet: http://

www.tbm.aero/. For the United States, 

contact SOCATA NORTH AMERICA, North 

Perry Airport, 601 NE 10 Street, Pompano 

Beach, Florida 33060; phone: (954) 366– 

3331; Internet: http://

www.socatanorthamerica.com/default.htm. 

(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–2016–0068. 

(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 

4, 2016. 

Pat Mullen, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–08262 Filed 4–12–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–5914; Directorate 

Identifier 2014–SW–056–AD; Amendment 

39–18472; AD 2016–07–27] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (formerly Eurocopter 

France) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model SA341G and SA342J 

helicopters. This AD requires repetitive 

inspections of a certain part-numbered 

main rotor hub torsion bar (torsion bar). 

This AD was prompted by several cases 

of corrosion in the metal strands of the 

torsion bar. The actions of this AD are 

intended to detect corrosion and 

prevent failure of the torsion bar, loss of 

a main rotor blade, and subsequent loss 

of control of the helicopter. 

DATES: This AD is effective May 18, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of May 18, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http:// 

www.airbushelicopters.com/techpub. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy, Room 6N–321, 

Fort Worth, TX 76177. It is also on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–5914. 

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–2015– 

5914; 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 European Aviation 

Safety Agency (EASA) AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 10101 

Hillwood Pkwy, Fort Worth, Texas 

76177; telephone (817) 222–5110; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On November 19, 2015, at 80 FR 

72390, the Federal Register published 

our notice of proposed rulemaking 

(NPRM), which proposed to amend 14 

CFR part 39 by adding an AD that 

would apply to Model SA341G and 

SA342J helicopters with a torsion bar 

part number 704A33633274 installed. 

The NPRM proposed to require 

removing and performing repetitive 

inspections of each torsion bar for a 

crack in the polyurethane (PU) coating, 

the dimension of the angle between the 

bushings, corrosion on the inside 

diameter of each bushing, the thickness 

of each bushing, the size of the inside 

diameter of each bushing, and missing 

varnish on the two faces of each 

bushing. The NPRM also proposed to 

require replacing the torsion bar before 

further flight if there is a crack in the PU 

coating of a torsion bar that matches or 

exceeds the damage criteria, if the angle 

of the torsion bar is 7 degrees or more, 

if any corrosion on a bushing cannot be 

removed by rubbing it with an abrasive 

pad, if the thickness of a bushing is less 

than 37.520 mm (1.477 in), or if the 

diameter of a bushing is larger than 

21,040 mm (.828 in). If varnish is 

missing from more than 15 percent of 

the surface area from a face of a bushing, 

the NPRM proposed to require removing 

all varnish, finishing with an abrasive 

pad, and applying a coat of paint to the 

face of the bushing. The proposed 

requirements were intended to detect 

corrosion and prevent failure of the 


jstallworth on DSK7TPTVN1PROD with RULES