51456 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations 

(e) Required Actions 

(1) Within 165 hours time-in-service (TIS), 

visually inspect the swashplate assembly to 

determine whether a ferrule is installed on 

the rotating star. If the ferrule is not visible, 

use a magnetic retriever positioned in Area 

(X) as shown in the pictures under paragraph 

3.B.2.b., Accomplishment Instructions, of 

Airbus Helicopters Alert Service Bulletin 

(ASB) No. EC130 62A010, ASB No. AS350 

62.00.34, or ASB No. AS355 62.00.33, all 

Revision 0, and all dated April 28, 2014, 

whichever is applicable to your helicopter, to 

determine whether the ferrule is installed. 

The magnetic retriever will be magnetized if 

a ferrule is installed. 

(2) If a ferrule is not installed, no further 

action is needed. 

(3) If a ferrule is installed on the rotating 

star, before further flight, dye-penetrant 

inspect the rotating star for a crack in areas 

‘‘Z’’ depicted in Figure 1 of Airbus 

Helicopters ASB No. EC130 62A010, ASB 

No. AS350 62.00.34, or ASB No. AS355 

62.00.33, all Revision 0, and all dated April 

28, 2014, as applicable to your model 

helicopter. 

(i) If the rotating star has a crack, before 

further flight, remove from service the 

rotating star; ferrule; and the screws, washers 

and nuts used to attach the pitch change 

rods, compass, and the rotating star deflector. 

(ii) If the rotating star does not have a 

crack, within 160 hours TIS, remove from 

service the rotating star; ferrule; and the 

screws, washers and nuts used to attach the 

pitch change rods, compass, and the rotating 

star deflector. 

(4) Do not install a rotating star P/N 

350A371003–04, 350A371003–05, 

350A371003–06, 350A371003–07, or 

350A371003–08 with a ferrule. 

(f) Special Flight Permits 

Special flight permits are prohibited. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 10101 Hillwood Pkwy., Fort 

Worth, Texas 76177; telephone (817) 222– 

5110; email asw-ftw-amoc@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

The subject of this AD is addressed in the 

European Aviation Safety Agency (EASA) AD 

No. 2014–0132R1, dated June 2, 2014. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA–2015–0673. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6200, Main Rotor System. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Airbus Helicopters Alert Service 

Bulletin (ASB) No. EC130 62A010, Revision 

0, dated April 28, 2014. 

(ii) Airbus Helicopters ASB No. AS350 

62.00.34, Revision 0, dated April 28, 2014. 

(iii) Airbus Helicopters ASB No. AS355 

62.00.33, Revision 0, dated April 28, 2014. 

(3) For Airbus Helicopters service 

information identified in this AD, contact 

Airbus Helicopters, Inc., 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. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, Texas 76177. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on August 13, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–20587 Filed 8–24–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2047; Directorate 

Identifier 2015–CE–013–AD; Amendment 

39–18243; AD 2015–17–10] 

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) 2007–04– 

13 for certain SOCATA Model TBM 700 

airplaness (type certificate previously 

held by EADS SOCATA). 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 cracks found on the main 

landing gear cylinders. We are issuing 

this AD to require actions to address the 

unsafe condition on these products. 

DATES: This AD is effective September 

29, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 29, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of March 23, 2007 (72 FR 

7576, February 16, 2007). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

2047; 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; 

telephone: 33 (0)5 62.41.73.00; fax: 33 

(0)5 62.41.76.54; or SOCATA North 

America, North Perry Airport, 7501 S 

Airport Rd., Pembroke Pines, Florida 

33023, telephone: (954) 893–1400; fax: 

(954) 964–4141; Internet: http://

www.socata.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–2015– 

2047. 

FOR FURTHER INFORMATION CONTACT: 

Albert J. 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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to make 

changes to an NPRM (80 FR 8821, 

February 19, 2015), which would amend 

14 CFR part 39 to add an AD that would 

apply to certain SOCATA Model TBM 

700 airplaness (type certificate 

previously held by EADS SOCATA). 

That SNPRM was published in the 

Federal Register on June 11, 2015 (80 

FR 33208), and proposed to supersede 


Lhorne on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations 51457 

AD 2007–04–13, Amendment 39–14945, 

(72 FR 7576, February 16, 2007) (‘‘AD 

2007–04–13’’). 

Since we issued AD 2007–04–13, it 

has been determined that the time 

between repetitive inspections should 

be extended and an optional terminating 

action for the repetitive inspections is 

now available. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No. 2006– 

0085R2, dated January 16, 2015 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

Cracks on several main landing gear (MLG) 

cylinders have been reported in service. 

This condition, if not to detected and 

corrected, could lead to fatigue cracks in the 

shock strut cylinder of the MLG, which could 

result in a collapsed MLG during take-off or 

landing runs, and possibly reduce the 

structural integrity of the aeroplane. 

To address this unsafe condition, EASA 

issued AD 2006–0085 to require repetitive 

special detailed inspections (SDI) for cracks 

of the MLG shock strut cylinder and, 

depending on findings, relevant investigative 

and corrective actions. 

After that AD was issued, SOCATA 

performed an analysis to demonstrate that 

the inspection interval could be extended, 

and developed a reinforced MLG less prone 

to fatigue, which is embodied in production 

through SOCATA modification (MOD) 70– 

0190–32 and can be introduced in service 

through SOCATA Service Bulletin (SB) 70– 

130–32 at Revision 03. 

Prompted by these developments, EASA 

issued AD 2006–0085R1 to increase the 

inspection interval and to introduce the 

installation of a reinforced MLG on the right 

hand (RH) side and left hand (LH) side as an 

optional terminating action for the repetitive 

SDI required by this AD. 

Since that AD was issued, it was found that 

aeroplanes MSN 639 to 683 (inclusive) are 

not affected by this AD. The applicability has 

therefore been revised to remove those MSN. 

The MCAI can be found in the AD 

docket on the Internet at: http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-2047- 

0002. 

In addition, we have determined that 

airplanes with MLG with forging body 

that had not reached 1,750 landings as 

of March 23, 2007 (the effective date of 

AD 2007–04–13) were not affected by 

the AD. This is not the intent and allows 

airplanes to fly indefinitely with the 

unsafe condition. This AD includes 

those airplanes with MLG with forging 

body either at or under 1,750 landings 

as of March 23, 2007, and extends the 

time between the repetitive inspections 

until a reinforced landing gear is 

installed, which terminates the 

repetitive inspections. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received one supportive comment to the 

NPRM (80 FR 8821, February 19, 2015) 

and no comments on the SNPRM (80 FR 

33208, June 11, 2015) 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 SNPRM (80 FR 

33208, June 11, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (80 FR 33208, 

June 11, 2015). 

Related Service Information Under 1 

CFR Part 51 

EADS SOCATA has issued TBM 

Aircraft Mandatory Service Bulletin SB 

70–130, ATA No. 32, dated January 

2006, and SOCATA has issued DAHER– 

SOCATA TBM Aircraft Mandatory 

Service Bulletin SB 70–130, Revision 3, 

dated December 2014. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. The DAHER– 

SOCATA TBM Aircraft Mandatory 

Service Bulletin SB 70–130, Revision 3, 

dated December 2014, incorporates 

procedures for replacing cracked MLG 

with a reinforced MLG as a terminating 

action for the repetitive inspections. 

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 AD. 

Costs of Compliance 

We estimate that this AD will affect 

431 products of U.S. registry. We also 

estimate that it will take about 3 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD on U.S. operators to be 

$109,905, or $255 per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 4 work-hours and require parts 

costing $6,000, for a cost of $6,340 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–2015– 

2047; 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 SNPRM, 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. 


Lhorne on DSK5TPTVN1PROD with RULES
51458 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations 

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 39–14945 (72 FR 

7576, February 16, 2007), and adding 

the following new AD: 

2015–17–10 SOCATA (type certificate 

previously held by EADS SOCATA): 

Amendment 39–18243; Docket No. 

FAA–2015–2047; Directorate Identifier 

2015–CE–013–AD. 

(a) Effective Date 

This AD becomes effective September 29, 

2015. 

(b) Affected ADs 

This AD supersedes AD 2007–04–13, 

Amendment 39–14945, (72 FR 7576, 

February 16, 2007) (‘‘AD 2007–04–13’’). 

(c) Applicability 

This AD applies to SOCATA Model TBM 

700 airplanes, serial numbers 1 through 638 

and 687, that: 

(1) are not equipped with a left-hand main 

landing gear (MLG) body part number (P/N) 

D68161 or D68161–1 and a right-hand MLG 

body P/N D68162 or D68162–1; and 

(2) are certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 32: Landing gear. 

(e) Reason 

This AD was prompted 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 cracks 

found on the main landing gear cylinders. In 

addition, the FAA determined that airplanes 

with MLG with forging body that had not 

reached 1,750 landings as of March 23, 2007 

(the effective date of AD 2007–04–13) were 

not affected by AD 2007–04–13. This is not 

the intent and allows airplanes to fly 

indefinitely with the unsafe condition. This 

AD increases the scope of the affected 

airplanes by including those airplanes with 

MLG with forging body either at or under 

1,750 landings as of March 23, 2007, 

increases the time between the repetitive 

inspections, and incorporates a modification 

to terminate the required repetitive 

inspections. We are issuing this AD to detect 

and correct cracks in the shock strut cylinder 

of the MLG, which could cause the MLG to 

fail. Failure of the shock strut cylinder of the 

MLG could result in a collapsed MLG during 

takeoff or landing and possible reduced 

structural integrity of the airplane. 

(f) Actions and Compliance for Airplanes 

Not Previously Affected by AD 2007–04–13 

Unless already done, do the actions in 

paragraphs (f)(1), (f)(2), and (h) of this AD: 

(1) For MLG with forging body that were 

either at or under 1,750 landings as of March 

23, 2007 (the effective date of (AD 2007–04– 

13): Upon or before accumulating 1,750 

landings on the MLG with forging body since 

new or within the next 100 landings after 

September 29, 2015 (the effective date of this 

AD), whichever occurs later, inspect the 

forging body for cracks. Do the inspection 

following the Accomplishment Instructions 

of EADS SOCATA TBM Aircraft Mandatory 

Service Bulletin SB 70–130, dated January 

2006, or DAHER–SOCATA TBM Aircraft 

Mandatory Service Bulletin SB 70–130, 

Revision 3, dated December 2014. 

(2) If no cracks are detected during the 

inspection required in paragraph (f)(1) of this 

AD, repetitively thereafter inspect at intervals 

not to exceed 240 landings until a reinforced 

landing gear specified in paragraph E. 

Terminating Solution of the Accomplishment 

Instructions in DAHER–SOCATA TBM 

Aircraft Mandatory Service Bulletin SB 70– 

130, Revision 3, dated December 2014, is 

installed. 

(g) Actions and Compliance for Airplanes 

Previously Affected by AD 2007–04–13 

Unless already done, do the actions in 

paragraphs (g)(1), (g)(2), and (h) of this AD, 

including all subparagraphs: 

(1) As of March 23, 2007 (the effective date 

retained from AD 2007–04–13), for MLG with 

forging body totaling more than 1,750 

landings but less than 3,501 landings since 

new: 

(i) Inspect the forging body for cracks 

within 100 landings after March 23, 2007 (the 

effective date retained from AD 2007–04–13), 

following the Accomplishment Instructions 

of EADS SOCATA TBM Aircraft Mandatory 

Service Bulletin SB 70–130, dated January 

2006, or DAHER–SOCATA TBM Aircraft 

Mandatory Service Bulletin SB 70–130, 

Revision 3, dated December 2014. 

(ii) If no cracks are detected during the 

inspection required in paragraph (g)(1)(i) of 

this AD, repetitively thereafter inspect at 

intervals not to exceed 240 landings until a 

reinforced landing gear specified in 

paragraph E. Terminating Solution of the 

Accomplishment Instructions in DAHER– 

SOCATA TBM Aircraft Mandatory Service 

Bulletin SB 70–130, Revision 3, dated 

December 2014, is installed. 

(2) As of March 23, 2007 (the effective date 

retained from AD 2007–04–13), for MLG with 

forging body totaling more than 3,500 

landings since new: 

(i) Inspect the forging body for cracks 

within 25 landings after March 23, 2007 (the 

effective date retained from AD 2007–04–13), 

following the Accomplishment Instructions 

of EADS SOCATA TBM Aircraft Mandatory 

Service Bulletin SB 70–130, dated January 

2006, or DAHER–SOCATA TBM Aircraft 

Mandatory Service Bulletin SB 70–130, 

Revision 3, dated December 2014. 

(ii) If no cracks are detected during the 

inspection required in paragraph (g)(2)(i) of 

this AD, repetitively thereafter inspect at 

intervals not to exceed 240 landings until a 

reinforced landing gear specified in 

paragraph E. Terminating Solution of the 

Accomplishment Instructions in DAHER– 

SOCATA TBM Aircraft Mandatory Service 

Bulletin SB 70–130, Revision 3, dated 

December 2014, is installed. 

(h) Actions and Compliance for All Affected 

Airplanes 

If any cracks are detected during any 

inspection required in paragraphs (f)(1) 

through (g)(2) of this AD, including all 

subparagraphs: 

(1) Before further flight, remove the 

affected landing gear leg and confirm the 

presence of the crack with dye penetrant 

inspection or fluorescent penetrant 

inspection. 

(2) If the crack is confirmed, before further 

flight, contact SOCATA at the address in 

paragraph (l)(5) of this AD to coordinate the 

FAA-approved landing gear repair/

replacement and implement any FAAapproved repair/replacement instructions 

obtained from SOCATA, or replace the 

cracked landing gear with a reinforced 

landing gear specified in paragraph E. 

Terminating Solution of the Accomplishment 

Instructions in DAHER–SOCATA TBM 

Aircraft Mandatory Service Bulletin SB 70– 

130, Revision 3, dated December 2014. This 

replacement terminates the repetitive 

inspections required by this AD. 

(i) Calculating Unknown Number of 

Landings for Compliance 

The compliance times of this AD are 

presented in landings instead of hours timein-service (TIS). If the number of landings is 

unknown, hours TIS may be used by dividing 

the number of hours TIS by 1.35. 

(j) 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 J. 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 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. 


Lhorne on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations 51459 

(k) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No. 2006–0085R2, dated 

January 16, 2015, for related information. 

You may examine the MCAI on the Internet 

at http://www.regulations.gov/

#!documentDetail;D=FAA-2015-2047-0002. 

(l) 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. 

(3) The following service information was 

approved for IBR on September 29, 2015. 

(i) DAHER–SOCATA TBM Aircraft 

Mandatory Service Bulletin SB 70–130, 

Revision 3, dated December 2014. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on March 23, 2007 (72 FR 

7576, February 16, 2007). 

(i) EADS SOCATA TBM Aircraft 

Mandatory Service Bulletin SB 70–130, dated 

January 2006. 

(ii) Reserved. 

(5) For SOCATA service information 

identified in this AD, contact SOCATA, 

Direction des Services, 65921 Tarbes Cedex 

9, France; telephone: 33 (0)5 62.41.73.00; fax: 

33 (0)5 62.41.76.54; or SOCATA North 

America, North Perry Airport, 7501 S Airport 

Rd., Pembroke Pines, Florida 33023, 

telephone: (954) 893–1400; fax: (954) 964– 

4141; Internet: http://www.socata.com. 

(6) You may view this service information 

at 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–2015–2047. 

(7) 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 August 

14, 2015. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2015–20588 Filed 8–24–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1050; Directorate 

Identifier 2014–NM–123–AD; Amendment 

39–18241; AD 2015–17–08] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–400 

series airplanes. This AD was prompted 

by an in-service report of an 

uncommanded and unannunciated nose 

wheel steering during airplane 

pushback from the gate. This AD 

requires installing new cable assemblies 

with a pull-down resistor. We are 

issuing this AD to prevent an 

uncommanded nose wheel steering 

during takeoff or landing in the event of 

an open circuit in the steering system, 

and possible consequent runway 

excursion. 

DATES: This AD becomes effective 

September 29, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 29, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-1050 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. 

For service information identified in 

this AD, contact Bombardier, Inc., QSeries Technical Help Desk, 123 Garratt 

Boulevard, Toronto, Ontario M3K 1Y5, 

Canada; telephone 416–375–4000; fax 

416–375–4539; email thd.qseries@

aero.bombardier.com; Internet http://

www.bombardier.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– 

1050. 

FOR FURTHER INFORMATION CONTACT: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Services Branch, ANE– 

172, FAA, New York Aircraft 

Certification Office (ACO), 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone (516) 228–7301; fax 

(516) 794–5531. 

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 Bombardier, Inc. Model 

DHC–8–400 series airplanes. The NPRM 

published in the Federal Register on 

January 23, 2015 (80 FR 3504). 

The Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2013–38, 

dated November 28, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model 

DHC–8–400, –401, and –402 series 

airplanes. The MCAI states: 

There has been one in-service report of an 

un-commanded and un-annunciated nose 

wheel steering during aeroplane push-back 

from the gate. The investigation revealed that 

a design deficiency exists within the steering 

control unit (SCU) where an open circuit may 

not be adequately detected and annunciated 

to the flight crew. A sustained open circuit 

could result in an un-commanded and unannunciated nose wheel steering input. 

Un-commanded nose wheel steering 

during takeoff or landing may lead to a 

runway excursion. 

This [Canadian] AD mandates the 

installation of new cable assemblies, with a 

pull-down resistor, to ensure that the nose 

wheel steering system reverts to fail-safe free 

castor mode in the event of an open circuit 

in the steering system. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-1050- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (80 FR 3504, 

January 23, 2015) and the FAA’s 

response to each comment. 

Request To Remove Certain Service 

Information Procedures 

Horizon Air requested that we amend 

paragraph (g) of the proposed AD (80 FR 

3504, January 23, 2015) to exclude Part 

A, ‘‘Job Set-up,’’ and Part C ‘‘Close Out,’’ 

sections of the Accomplishment 

Instructions in Bombardier Service 


Lhorne on DSK5TPTVN1PROD with RULES