Federal Register / Vol. 80, No. 102 / Thursday, May 28, 2015 / Rules and Regulations 30349 

(a) Effective Date 

This AD is effective June 12, 2015. 

(b) Affected ADs 

This AD supersedes AD 2014–01–01, 

Amendment 39–17724 (79 FR 3481, January 

22, 2014). 

(c) Applicability 

This AD applies to all Turbomeca S.A. 

Arrius 2F turboshaft engines. 

(d) Unsafe Condition 

This AD was prompted by the 

determination that additional lubricating 

devices, identifiable by serial number (S/N), 

may have an incorrect bonding of the nozzle 

on the ejector assembly. We are issuing this 

AD to prevent failure of the ejector assembly 

nozzle, which could lead to an in-flight 

shutdown of the engine, damage to the 

engine, and damage to the helicopter. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For engines equipped with a lubricating 

device having an S/N listed in Figure 1 to 

paragraph (e) of this AD, within 30 days after 

the effective date of this AD, inspect the 

ejector assembly nozzle and the tightening 

torque. Use paragraphs 4.4.2.1 through 

4.4.2.3.4.2 of Turbomeca Mandatory Service 

Bulletin (MSB) No. 319 79 4835, Version B, 

dated February 12, 2015, to do the 

inspection. 

(2) For any part that fails the inspection 

required by paragraph (e)(1) of this AD, 

before further flight, remove and replace the 

failed part with a part eligible for installation. 

FIGURE 1 TO PARAGRAPH (e)—S/N’S OF AFFECTED LUBRICATING DEVICES

100 140M 185M 247 436M 

105M 141M 190M 255M 443M 

106 142B 191M 266M 445M 

107B 146M 195M 278M 451M 

109M 147M 198M 292M 467M 

112B 156M 202M 304M 477M 

112M 159M 204M 330M 479M 

114B 164M 207M 334M 483M 

124B 178 210M 369M 484M 

125M 178M 213M 384M 512M 

129M 180 218M 391M 526M 

135B 180M 222M 392M 563M 

135M 181M 244M 417M 

(f) Credit for Previous Actions 

If you inspected the ejector assembly 

nozzle of any lubricating device having an S/ 

N listed in Figure 1 to paragraph (e) of this 

AD before the effective date of this AD, using 

the instructions of Turbomeca S.A. MSB No. 

319 79 4835, Version A, dated May 22, 2013, 

you met the requirements of paragraph (e) of 

this AD for that S/N lubricating device. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

return to service any engine having a 

lubricating device with an S/N listed in 

Figure 1 to paragraph (e) of this AD, unless 

the engine has been inspected per the 

requirements of paragraph (e) of this AD. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(i) Related Information 

(1) For more information about this AD, 

contact Philip Haberlen, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7770; fax: 781–238–7199; 

email: philip.haberlen@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2015–0057, dated April 1, 

2015, for more information. You may 

examine the MCAI in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2013–1003. 

(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. 

(3) The following service information was 

approved for IBR on June 12, 2015. 

(i) Turbomeca S.A. Mandatory Service 

Bulletin (MSB) No. 319 79 4835, Version B, 

dated February 12, 2015. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on February 6, 2014 (79 FR 

3481, January 22, 2014). 

(i) Turbomeca S.A. MSB No. 319 79 4835, 

Version A, dated May 22, 2013. 

(ii) Reserved. 

(5) For Turbomeca S.A. service information 

identified in this AD, contact Turbomeca 

S.A., 40220 Tarnos, France; phone: 33 (0)5 59 

74 40 00; telex: 570 042; fax: 33 (0)5 59 74 

45 15. 

(6) You may view this service information 

at FAA, Engine & Propeller Directorate, 12 

New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(7) You may view this service information 

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 Burlington, Massachusetts, on 

May 13, 2015. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–12654 Filed 5–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1282; Directorate 

Identifier 2015–NM–007–AD; Amendment 

39–18157; AD 2015–10–02] 

RIN 2120–AA64 

Airworthiness Directives; Zodiac Seats 

France (Formerly Sicma Aero Seat) 

Passenger Seat Assemblies 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2014–20– 

11, for Zodiac Seats France 9140, 9166, 

9173, 9174, 9184, 9188, 9196, 91B7, 

91B8, 91C0, 91C2, 91C4, 91C5, 91C9, 

9301, and 9501 series passenger seat 

assemblies. AD 2014–20–11 required a 

general visual inspection for cracking of 


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backrest links; replacement with new 

links if cracking is found; and eventual 

replacement of all links with new links. 

This AD was prompted by a 

determination that a model designation 

specified in paragraph (c)(1) of that AD 

was incorrect. This new AD identifies 

the correct model designation. We are 

issuing this AD to detect and correct 

cracks in the backrest links, which 

could affect the structural integrity of 

seat backrests. Failure of the backrest 

links could result in injury to an 

occupant during emergency landing 

conditions. 

DATES: This AD becomes effective June 

12, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 22, 2014 (79 FR 60322, 

October 7, 2014). 

We must receive comments on this 

AD by July 13, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Zodiac Seats France, 7, 

Rue Lucien Coupet, 36100 ISSOUDUN, 

France; telephone +33 (0) 2 54 03 39 39; 

fax +33 (0) 2 54 03 39 00; email 

customerservices@sicma.zodiac.com; 

Internet http://

www.sicma.zodiacaerospace.com/en/. 

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. 

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– 

1282; 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 regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Ian 

Lucas, Aerospace Engineer, Boston 

Aircraft Certification Office (ACO) 

ANE–150, FAA, Engine and Propeller 

Directorate, 12 New England Executive 

Park, Burlington, MA 01803; phone: 

781–238–7757; fax: 781–238–7170; 

email: ian.lucas@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On September 23, 2014, we issued AD 

2014–20–11, Amendment 39–17984 (79 

FR 60322, October 7, 2014), to 

supersede AD 2011–07–05, Amendment 

39–16642 (76 FR 18020, April 1, 2011). 

AD 2014–20–11 applied to certain 

Zodiac Seats France 9140, 9166, 9173, 

9174, 9184, 9188, 9196, 91B7, 91B8, 

91C0, 91C2, 91C4, 91C5, 91C9, 9301, 

and 9501 series passenger seat 

assemblies; identified in Annex 1, Issue 

3, dated January 25, 2012, of Sicma Aero 

Seat Service Bulletin 90–25–012, Issue 

6, dated January 25, 2012. AD 2014–20– 

11 was prompted by a report that new 

seat backrest links could be affected by 

cracks similar to those identified on the 

backrest links with the previous design. 

AD 2014–20–11 required a general 

visual inspection for cracking of 

backrest links, which includes new seat 

backrest links; replacement with new 

links if cracking is found; and eventual 

replacement of all links with new links. 

We issued AD 2014–20–11 to detect and 

correct cracking of backrest links, which 

could affect the structural integrity of 

seat backrests. Failure of the backrest 

links could result in injury to an 

occupant during emergency landing 

conditions. 

AD 2014–20–11, Amendment 39– 

17984 (79 FR 60322, October 7, 2014), 

corresponds to Mandatory Continuing 

Airworthiness Information (MCAI) 

European Aviation Safety Agency 

Airworthiness Directive 2012–0038, 

dated March 12, 2012. You may 

examine the MCAI on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

1282. 

Since we issued AD 2014–20–11, 

Amendment 39–17984 (79 FR 60322, 

October 7, 2014), we have determined 

that, in paragraph (c)(1) of AD 2014–20– 

11, a model designation incorrectly 

specified ‘‘A320–300’’ instead of 

‘‘A330–300’’ as one of the models that 

the affected passenger seats might be 

installed on. Therefore, we have 

determined that paragraph (c)(1) of this 

AD should read as follows: Airbus 

Model A330–200, A330–200 Freighter, 

and A330–300 series airplanes. 

We have also re-designated paragraph 

(l) of AD 2014–20–11, Amendment 39– 

17984 (79 FR 60322, October 7, 2014), 

as paragraph (l)(1) of this AD. We also 

added a new paragraph (l)(2) to this AD 

to provide information on the 

availability of service information that is 

not incorporated by reference in this 

AD. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of airplanes that are equipped 

with this product, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2015–1282; 

Directorate Identifier 2015–NM–007– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 

Costs of Compliance 

We estimate that this AD affects 0 seat 

assemblies installed on, but not limited 

to, transport airplanes of U.S. registry. 


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Federal Register / Vol. 80, No. 102 / Thursday, May 28, 2015 / Rules and Regulations 30351 

The actions required by AD 2014–20– 

11, Amendment 39–17984 (79 FR 

60322, October 7, 2014), and retained in 

this AD take about 1 work-hour per 

product, at an average labor rate of $85 

per work-hour. Required parts cost 

about $227 per product. Based on these 

figures, the estimated cost of the actions 

that were required by AD 2014–20–11 is 

$312 per product. 

Since this AD only clarifies airplane 

models on which the affected passenger 

seat assemblies might be installed, this 

AD adds no additional economic 

burden. 

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 that 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. 

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 airworthiness directive (AD) 

2014–20–11, Amendment 39–17984 (79 

FR 60322, October 7, 2014), and adding 

the following new AD: 

2015–10–02 Zodiac Seats France (formerly 

Sicma Aero Seat): Amendment 39– 

18157. Docket No. FAA–2015–1282; 

Directorate Identifier 2015–NM–007–AD. 

(a) Effective Date 

This AD becomes effective June 12, 2015. 

(b) Affected ADs 

This AD replaces AD 2014–20–11, 

Amendment 39–17984 (79 FR 60322, October 

7, 2014). 

(c) Applicability 

This AD applies to Zodiac Seats France 

9140, 9166, 9173, 9174, 9184, 9188, 9196, 

91B7, 91B8, 91C0, 91C2, 91C4, 91C5, 91C9, 

9301, and 9501 series passenger seat 

assemblies; identified in Annex 1, Issue 3, 

dated January 25, 2012, of Sicma Aero Seat 

Service Bulletin 90–25–012, Issue 6, dated 

January 25, 2012. These passenger seat 

assemblies are installed on, but not limited 

to, the airplanes identified in paragraphs 

(c)(1), (c)(2), and (c)(3) of this AD, certificated 

in any category. 

(1) Airbus Model A330–200, A330–200 

Freighter, and A330–300 series airplanes. 

(2) Airbus Model A340–200, A340–300, 

A340–500, and A340–600 series airplanes. 

(3) The Boeing Company Model 777–200, 

777–200LR, 777–300, 777–300ER, and 777F 

series airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings. 

(e) Reason 

This AD was prompted by a report of 

cracks in the backrest links on certain seats 

and also by a determination that a model 

designation specified in paragraph (c)(1) of 

AD 2014–20–11, Amendment 39–17984 (79 

FR 60322, October 7, 2014) was incorrect. We 

are issuing this AD to detect and correct 

cracks in the backrest links, which could 

affect the structural integrity of seat 

backrests. Failure of the backrest links could 

result in injury to an occupant during 

emergency landing conditions. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Inspections, With No 

Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2014–20–11, 

Amendment 39–17984 (79 FR 60322, October 

7, 2014), with no changes. At the later of the 

times specified in paragraphs (g)(1) and (g)(2) 

of this AD: Do a general visual inspection for 

cracking of seat backrest links having part 

number (P/N) 90–000200–104–1, P/N 90– 

000200–104–2, P/N 90–000202–104–1, and 

P/N 90–000202–104–2, in accordance with 

the ‘‘PART ONE: GENERAL INTERMEDIATE 

CHECKING PROCEDURE’’ of the 

Accomplishment Instructions of Sicma Aero 

Seat Service Bulletin 90–25–012, Issue 6, 

dated January 25, 2012, including Annex 1, 

Issue 3, dated January 25, 2012. If no 

cracking is found on any link, repeat the 

inspection thereafter at intervals not to 

exceed 900 flight hours on the seat or 5 

months since the most recent inspection, 

whichever occurs later, until the replacement 

specified in paragraph (i) of this AD is done. 

(1) Within 6,000 flight hours on the seat or 

2 years, whichever occurs later after the seat 

manufacturing date or after the backrest link 

replacement. 

(2) Within 900 flight hours on the seat after 

October 22, 2014 (the effective date AD 

2014–20–11, Amendment 39–17984 (79 FR 

60322, October 7, 2014)), but no later than 5 

months after October 22, 2014. 

(h) Retained Corrective Actions, With No 

Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2014–20–11, 

Amendment 39–17984 (79 FR 60322, October 

7, 2014), with no changes. 

(1) If, during any inspection required by 

paragraph (g) of this AD, any cracking is 

found on the link and no crack length 

exceeds the lock-out pin-hole as specified in 

Figure 2 or 4, as applicable, of Sicma Aero 

Seat Service Bulletin 90–25–012, Issue 6, 

dated January 25, 2012, including Annex 1, 

Issue 3, dated January 25, 2012: Within 600 

flight hours on the seat or 3 months, 

whichever occurs later after crack 

identification, replace the cracked link with 

a new link, in accordance with ‘‘PART TWO: 

ROUTINE REPLACEMENT PROCEDURE 

(EXCEPT FOR SERIES 91B7, 91B8 & 91C5)’’ 

or ‘‘PART THREE: ROUTINE 

REPLACEMENT PROCEDURE (FOR SERIES 

91B7, 91B8 & 91C5)’’ of the Accomplishment 

Instructions of Sicma Aero Seat Service 

Bulletin 90–25–012, Issue 6, dated January 

25, 2012, including Annex 1, Issue 3, dated 

January 25, 2012. 

(2) If, during any inspection required by 

paragraph (g) of this AD, any cracking is 

found on the link and any crack length 

exceeds the lock-out pin-hole as specified in 

Figure 2 or 4, as applicable, of Sicma Aero 

Seat Service Bulletin 90–25–012, Issue 6, 

dated January 25, 2012, including Annex 1, 

Issue 3, dated January 25, 2012: Before 


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further flight, replace the cracked link with 

a new link, in accordance with ‘‘PART TWO: 

ROUTINE REPLACEMENT PROCEDURE 

(EXCEPT FOR SERIES 91B7, 91B8 & 91C5)’’ 

or ‘‘PART THREE: ROUTINE 

REPLACEMENT PROCEDURE (FOR SERIES 

91B7, 91B8 & 91C5)’’ of the Accomplishment 

Instructions of Sicma Aero Seat Service 

Bulletin 90–25–012, Issue 6, dated January 

25, 2012, including Annex 1, Issue 3, dated 

January 25, 2012. 

(i) Retained Replacement, With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2014–20–11, Amendment 

39–17984 (79 FR 60322, October 7, 2014), 

with no changes. At the later of the times 

specified in paragraphs (i)(1) and (i)(2) of this 

AD: Replace all seat backrest links, having P/ 

N 90–000200–104–1, P/N 90–000200–104–2, 

P/N 90–000202–104–1, and P/N 90–000202– 

104–2, with new links, in accordance with 

‘‘PART TWO: ROUTINE REPLACEMENT 

PROCEDURE (EXCEPT FOR SERIES 91B7, 

91B8 & 91C5)’’ or ‘‘PART THREE: ROUTINE 

REPLACEMENT PROCEDURE (FOR SERIES 

91B7, 91B8 & 91C5)’’ of the Accomplishment 

Instructions of Sicma Aero Seat Service 

Bulletin 90–25–012, Issue 6, dated January 

25, 2012, including Annex 1, Issue 3, dated 

January 25, 2012. 

(1) Within 12,000 flight hours on the seat 

or 4 years, whichever occurs later after the 

seat manufacturing date or after the backrest 

link replacement. 

(2) Within 3,500 flight hours on the seat 

after October 22, 2014 (the effective date AD 

2014–20–11, Amendment 39–17984 (79 FR 

60322, October 7, 2014), but no later than 18 

months after October 22, 2014. 

(j) Retained Credit for Previous Actions, 

With No Changes 

This paragraph restates the credit provided 

in paragraph (j) of AD 2014–20–11, 

Amendment 39–17984 (79 FR 60322, October 

7, 2014), with no changes. This paragraph 

provides credit for actions required by 

paragraphs (g), (h), and (i) of this AD, if those 

actions were performed before October 22, 

2014 (the effective date AD 2014–20–11, 

Amendment 39–17984 (79 FR 60322, October 

7, 2014), using the service information 

specified in paragraph (j)(1), (j)(2), or (j)(3) of 

this AD. 

(1) Sicma Aero Seat Service Bulletin 90– 

25–012, Issue 3, dated October 3, 2001, 

which is not incorporated by reference in this 

AD. 

(2) Sicma Aero Seat Service Bulletin 90– 

25–012, Issue 4, dated December 19, 2001, 

which is not incorporated by reference in this 

AD. 

(3) Sicma Aero Seat Service Bulletin 90– 

25–012, Issue 5, dated March 19, 2004, 

including Annex 1, Issue 2, dated March 19, 

2004, which was incorporated by reference in 

AD 2011–07–05, Amendment 39–16642 (76 

FR 18020, April 1, 2011). 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Boston 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 ACO, send it to ATTN: Ian Lucas, 

Aerospace Engineer, Boston ACO, ANE–150, 

FAA, Engine and Propeller Directorate, 12 

New England Executive Park, Burlington, 

MA 01803; phone: 781–238–7757; fax: 781– 

238–7170; email: ian.lucas@faa.gov. 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. The AMOC approval 

letter must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, Boston ACO, FAA; or the 

European Aviation Safety Agency (EASA). 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2012–0038, dated 

March 12, 2012, for related information. You 

may examine the MCAI on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2015–1282. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(4) and (m)(5) of this AD. 

(m) 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 this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on October 22, 2014 (79 FR 

60322, October 7, 2014). 

(i) Sicma Aero Seat Service Bulletin 90– 

25–012, Issue 6, dated January 25, 2012, 

including Annex 1, Issue 3, dated January 25, 

2012. 

(ii) Reserved. 

(4) For service information identified in 

this AD, contact Zodiac Seats France, 7, Rue 

Lucien Coupet, 36100 ISSOUDUN, France; 

telephone +33 (0) 2 54 03 39 39; fax +33 (0) 

2 54 03 39 00; email customerservices@

sicma.zodiac.com; Internet http://

www.sicma.zodiacaerospace.com/en/. 

(5) 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. 

(6) 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 May 4, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–11392 Filed 5–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

NATIONAL AERONAUTICS AND 

SPACE ADMINISTRATION 

14 CFR Part 1216 

RIN 2700–AE20 

[Docket No. NASA–2015–0002] 

Removal of Obsolete Regulations 

AGENCY: National Aeronautics and 

Space Administration. 

ACTION: Direct final rule. 

SUMMARY: This direct final rule makes 

non-substantive changes by removing 

regulations that are captured in NASA 

internal requirements. The revisions to 

this rule are part of NASA’s 

retrospective plan completed in August 

2011 under Executive Order (E.O.) 

13563. NASA’s full plan can be 

accessed on the Agency’s open 

Government Web site at http://

www.nasa.gov/open/. 

DATES: This direct final rule is effective 

on July 27, 2015. Comments due on or 

before June 29, 2015. If adverse 

comments are received, NASA will 

publish a timely withdrawal of the rule 

in the Federal Register. 

ADDRESSES: Comments must be 

identified with RIN 2700–AE20 and 

may be sent to NASA via the Federal ERulemaking Portal: http://

www.regulations.gov. Follow the online 

instructions for submitting comments. 

Please note that NASA will post all 

comments on the Internet with changes, 

including any personal information 

provided. 

FOR FURTHER INFORMATION CONTACT: 

Nanette Jennings, 202–358–0819. 

SUPPLEMENTARY INFORMATION: 

Direct Final Rule Adverse Comments 

NASA has determined this 

rulemaking meets the criteria for a 

direct final rule because it involves nonsubstantive changes to remove a section 

from 14 CFR part 1216 that is captured 

in internal NASA requirements. No 

opposition to the changes and no 

significant adverse comments are 

expected. However, if the Agency 

receives a significant adverse comment, 

it will withdraw this direct final rule by 

publishing a notice in the Federal 

Register. A significant adverse comment 


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