79754 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules 

information identified in paragraph (i)(1)(i) 

through (i)(1)(xxvi) of this AD. This service 

information is not incorporated by reference 

in this AD. 

(i) Airbus Service Bulletin A320–34–1170, 

Revision 04, dated May 24, 2000. 

(ii) Airbus Service Bulletin A320–34–1170, 

Revision 05, dated September 11, 2000. 

(iii) Airbus Service Bulletin A320–34– 

1170, Revision 06, dated October 18, 2001. 

(iv) Airbus Service Bulletin A320–34– 

1170, Revision 07, dated December 4, 2001. 

(v) Airbus Service Bulletin A320–34–1170, 

Revision 08, dated January 15, 2003. 

(vi) Airbus Service Bulletin A320–34– 

1170, Revision 09, dated February 17, 2003. 

(vii) Airbus Service Bulletin A320–34– 

1170, Revision 10, dated November 21, 2003. 

(viii) Airbus Service Bulletin A320–34– 

1170, Revision 11, dated August 18, 2004. 

(ix) Airbus Service Bulletin A320–34– 

1170, Revision 12, dated December 2, 2004. 

(x) Airbus Service Bulletin A320–34–1170, 

Revision 13, dated January 18, 2005. 

(xi) Airbus Service Bulletin A320–34– 

1170, Revision 14, dated April 21, 2005. 

(xii) Airbus Service Bulletin A320–34– 

1170, Revision 15, dated July 19, 2005. 

(xiii) Airbus Service Bulletin A320–34– 

1170, Revision 16, dated November 23, 2006. 

(xiv) Airbus Service Bulletin A320–34– 

1170, Revision 17, dated February 14, 2007. 

(xv) Airbus Service Bulletin A320–34– 

1170, Revision 18, dated October 9, 2009. 

(xvi) Airbus Service Bulletin A320–34– 

1170, Revision 19, dated November 9, 2009. 

(xvii) Airbus Service Bulletin A320–34– 

1170, Revision 20, dated December 1, 2010. 

(xviii) Airbus Service Bulletin A320–34– 

1170, Revision 21, dated March 24, 2011. 

(xix) Airbus Service Bulletin A320–34– 

1170, Revision 22, dated July 19, 2011. 

(xx) Airbus Service Bulletin A320–34– 

1170, Revision 23, dated February 3, 2012. 

(xxi) Airbus Service Bulletin A320–34– 

1170, Revision 24, dated April 12, 2012. 

(xxii) Airbus Service Bulletin A320–34– 

1170, Revision 25, dated September 4, 2012. 

(xxiii) Airbus Service Bulletin A320–34– 

1170, Revision 26, dated September 16, 2013. 

(xxiv) Airbus Service Bulletin A320–34– 

1170, Revision 27, dated March 18, 2014. 

(xxv) Airbus Service Bulletin A320–34– 

1170, Revision 28, dated September 1, 2014. 

(xxvi) Airbus Service Bulletin A320–34– 

1170, Revision 29, dated February 16, 2015. 

(2) This paragraph provides credit for the 

replacement of pitot probes on the captain 

and standby sides specified in paragraph 

(h)(1) of this AD, if the replacement was 

performed before the effective date of this AD 

using Airbus Service Bulletin A320–34–1456, 

dated December 2, 2009, which is not 

incorporated by reference in this AD. 

(3) This paragraph provides credit for the 

replacement of pitot probes on the first 

officer side as specified in paragraph (h)(1) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A320–34–1463, 

dated March 9, 2010, which is not 

incorporated by reference in this AD. 

(j) Parts Installation Limitations 

(1) At the applicable time specified in 

paragraph (j)(1)(i) or (j)(1)(ii) of this AD: No 

person may install on any airplane a Thales 

pitot probe having P/N C16195AA or P/N 

C16195BA. 

(i) For airplanes with a Thales pitot probe 

having P/N C16195AA or P/N C16195BA 

installed: After accomplishing the 

replacement required by paragraph (g) of this 

AD. 

(ii) For airplanes without a Thales pitot 

probe having P/N C16195AA or P/N 

C16195BA installed: As of the effective date 

of this AD. 

(2) As of the effective date of this AD, no 

person may install on any airplane a Thales 

pitot probe having part number P/N 50620– 

10. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@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, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(l) Related Information 

(1) Refer to EASA Airworthiness Directive 

2015–0205, dated October 9, 2015, for related 

information. This MCAI may be found in the 

AD docket on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2015–0250. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

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. 

Issued in Renton, Washington, on 

November 25, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–30821 Filed 12–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–7527; Directorate 

Identifier 2015–NM–094–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777–200, 

–200LR, –300, and –300ER series 

airplanes. This proposed AD was 

prompted by a report indicating that the 

manufacturer discovered locations 

where the control components and 

wiring of the left and right engine fuel 

spar valves do not have adequate 

physical separation to meet the 

redundant system separation 

requirements. This proposed AD would 

require modifying the wiring, and 

installing a new relay bracket and new 

location for the relay on the left and 

right engine fuel spar valves. This 

proposed AD would also require an 

inspection to identify the part number 

of the motor operated valve (MOV) 

actuators for the left and right engine 

fuel spar valves; replacement of 

specified MOV actuators with new MOV 

actuators; certain bonding resistance 

measurements; and applicable 

corrective actions. We are proposing 

this AD to prevent loss of control of 

both the left and right engine fuel spar 

valves during a single event, such as 


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local wire bundle damage or a wire 

bundle fire, which could cause both 

engines to shut down or result in the 

inability to control an engine fire. 

DATES: We must receive comments on 

this proposed AD by February 8, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.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–2015– 

7527. 

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– 

7527; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Georgios Roussos, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; telephone: 425–917– 

6482; fax: 425–917–6590; email: 

georgios.roussos@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–7527; Directorate Identifier 2015– 

NM–094–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We have received a report indicating 

that the manufacturer discovered 

locations where the control components 

and wiring of the left and right engine 

fuel spar valve do not have adequate 

physical separation to meet the 

redundant system separation 

requirements. The control relays for 

both the left and right engine fuel spar 

valves are located in the same panel, 

and the left and right fuel spar valve 

control wiring is routed in common 

wire bundles and share the same 

electrical connectors. This condition, if 

not corrected, could result in loss of 

control of both the left and right engine 

fuel spar valves during a single event, 

such as local wire bundle damage or a 

wire bundle fire, which could cause 

both engines to shut down or result in 

the inability to control an engine fire. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Special 

Attention Service Bulletin 777–28– 

0061, Revision 2, dated May 4, 2015. 

The service information describes 

procedures for modifying the wiring, 

and installing a new relay bracket and 

new location for the relay on the left 

and right engine fuel spar valves. 

We have also reviewed Boeing Service 

Bulletin 777–28A0034, Revision 3, 

dated September 25, 2015. The service 

information describes procedures for an 

inspection of the MOV actuators of the 

left and right engine fuel spar valves for 

part number (P/N) MA20A1001–1, 

replacement of MOV actuators, 

measurement of the electrical resistance 

of the bond from the adapter plate to the 

airplane structure, and applicable 

corrective actions. 

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 NPRM. 

Other Relevant Rulemaking 

AD 2013–05–03, Amendment 39– 

17375 (78 FR 17290, March 21, 2013), 

was issued for certain Model 777–200, 

–200LR, –300, and –300ER series 

airplanes. AD 2013–05–03 requires an 

inspection to identify the part number 

of the MOV actuators of the main and 

center fuel tanks; replacing certain MOV 

actuators with new MOV actuators; and 

measuring the electrical resistance of 

the bond from the adaptor plate to the 

airplane structure, and doing corrective 

actions if necessary. AD 2013–05–03 

refers to Boeing Service Bulletin 777– 

28A0034, Revision 2, dated September 

20, 2010, as the appropriate source of 

service information for accomplishing 

the required actions. 

In addition, AD 2015–19–01, 

Amendment 39–18264 (80 FR 55521, 

September 16, 2015), requires revising 

the maintenance or inspection program 

to add a new airworthiness limitation 

for a repetitive inspection of the fuel 

spar valve. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 133 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


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ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Installation and modification.119 work-hours × $85 per 

hour = $10,115.

Up to $3,780 depending 

on airplane configuration.

Up to $13,895 depending 

on airplane configuration.

Up to $1,848,035 depending on airplane configuration. 

Inspection of MOV Actuators [concurrent requirements].1 work-hour × $85 per 

hour = $85.

$0 ...................................... $85 .................................... $11,305. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Replacement of MOV actuators for the left and 

right engine fuel spar valves.

Up to 105 work-hours × $85 per hour =$8,925 ... Up to $10,954 ....... Up to $19,879. 

Bonding resistance measurements ....................... 1 work-hour × $85 per hour = $85 ....................... $0 .......................... $85. 

We have received no definitive data 

on the costs of the corrective actions for 

the bonding resistance measurement in 

this proposed AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2015–7527; Directorate Identifier 2015– 

NM–094–AD. 

(a) Comments Due Date 

We must receive comments by February 8, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

The Boeing Company Model 777–200, 

–200LR, –300, and –300ER series airplanes, 

certificated in any category, as identified in 

Boeing Special Attention Service Bulletin 

777–28–0061, Revision 2, dated May 4, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 2822, Fuel Boost Pump. 

(e) Unsafe Condition 

This AD was prompted by a report 

indicating that the manufacturer discovered 

locations where the control components and 

wiring of the left and right engine fuel spar 

valves do not have adequate physical 

separation to meet the redundant system 

separation requirements. We are issuing this 

AD to prevent loss of control of both the left 

and right engine fuel spar valves during a 

single event, such as local wire bundle 

damage or a wire bundle fire, which could 

cause both engines to shut down or result in 

the inability to control an engine fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation and Modification 

Within 60 months after the effective date 

of this AD, modify the wiring and install a 

new relay bracket and new location for the 

relay on the left and right engine fuel spar 

valves, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–28– 

0061, Revision 2, dated May 4, 2015. 

(h) Concurrent Requirements 

(1) Prior to or concurrently with 

accomplishing the requirements of paragraph 

(g) of this AD: Do an inspection of the motor 

operated valve (MOV) actuators of the left 

and right engine fuel spar valves for part 

number (P/N) MA20A1001–1, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 777–28A0034, 

Revision 3, dated September 25, 2015. A 


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review of airplane maintenance records is 

acceptable in lieu of this inspection if the 

part number can be conclusively determined 

from that review. 

(2) If any MOV actuator having P/N 

MA20A1001–1 is found during the 

inspection required by paragraph (h)(1) of 

this AD, prior to or concurrently with 

accomplishing the requirements of paragraph 

(g) of this AD, replace the MOV actuator with 

either a new or serviceable MOV actuator 

having P/N MA30A1001, MA30A1017, 

MA20A2027, or with an MOV actuator that 

meets the criteria specified in paragraphs 

(h)(2)(i) and (h)(2)(ii) of this AD; and, as 

applicable, measure the electrical resistance 

of the bond from the adapter plate to the 

airplane structure and, before further flight, 

do all applicable corrective actions. All 

actions specified in this paragraph for the left 

and right engine fuel spar valves must be 

done in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–28A0034, Revision 3, 

dated September 25, 2015. 

(i) The replacement MOV actuator must be 

a Boeing part that is approved after the 

issuance of Boeing Service Bulletin 777– 

28A0034, Revision 3, dated September 25, 

2015, by the Manager, Seattle Aircraft 

Certification Office (ACO), FAA; or the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to approve the part. 

(ii) The replacement MOV actuator must be 

fully interchangeable with the part specified 

in Boeing Service Bulletin 777–28A0034, 

Revision 3, dated September 25, 2015. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for the 

requirements of paragraph (g) of this AD, if 

those actions were performed before the 

effective date of this AD using Boeing Special 

Attention Service Bulletin 777–28–0061, 

dated October 25, 2010; or Boeing Special 

Attention Service Bulletin 777–28–0061, 

Revision 1, dated January 26, 2012; as 

applicable; which are not incorporated by 

reference in this AD. 

(2) This paragraph provides credit for the 

requirements of paragraph (h) of this AD, if 

those actions were performed before April 

25, 2013 (the effective date of AD 2013–05– 

03, Amendment 39–17375 (78 FR 17290, 

March 21, 2013), using Boeing Alert Service 

Bulletin 777–28A0034, dated August 2, 2007; 

or Boeing Alert Service Bulletin 777– 

28A0034, Revision 1, dated May 20, 2010; 

except that the replacement of MOV 

actuators of the left and right engine fuel spar 

valves must also include cap sealing the 

bonding jumper, as described in Boeing 

Service Bulletin 777–28A0034, Revision 2, 

dated September 20, 2010; and provided that 

the replacement is an MOV actuator 

identified in paragraph (i)(2)(i) or (i)(2)(ii) of 

this AD. Boeing Alert Service Bulletin 777– 

28A0034, dated August 2, 2007; and Boeing 

Alert Service Bulletin 777–28A0034, 

Revision 1, dated May 20, 2010; are not 

incorporated by reference in this AD. 

(i) An MOV actuator that has P/N 

MA30A1001, MA30A1017, or MA20A2027. 

(ii) An MOV actuator that has a part 

number other than P/N MA20A1001–1 and 

meets the criteria specified in paragraphs 

(h)(2)(i) and (h)(2)(ii) of this AD. 

(3) This paragraph provides credit for the 

requirements of paragraph (h) of this AD, if 

those actions were performed before the 

effective date of this AD using Boeing Service 

Bulletin 777–28A0034, Revision 2, dated 

September 20, 2010, which was incorporated 

by reference in AD 2013–05–03, Amendment 

39–17375 (78 FR 17290, March 21, 2013). 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (k)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane and the 

approval must specifically refer to this AD. 

(k) Related Information 

(1) For more information about this AD, 

contact Georgios Roussos, Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone: 425– 

917–6482; fax: 425–917–6590; email: 

georgios.roussos@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.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. 

Issued in Renton, Washington, on 

December 11, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–32081 Filed 12–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

SECURITIES AND EXCHANGE 

COMMISSION 

17 CFR Part 240 

[Release No. 34–76624; File No. S7–26–15] 

RIN 3235–AL72 

Establishing the Form and Manner with 

which Security-Based Swap Data 

Repositories Must Make SecurityBased Swap Data Available to the 

Commission 

AGENCY: Securities and Exchange 

Commission. 

ACTION: Proposed rule. 

SUMMARY: The Securities and Exchange 

Commission (‘‘SEC’’ or ‘‘Commission’’) 

is publishing for comment a proposed 

amendment to specify the form and 

manner with which security-based swap 

data repositories (‘‘SDRs’’) will be 

required to make security-based swap 

(‘‘SBS’’) data available to the 

Commission under Exchange Act Rule 

13n–4(b)(5). The Commission is 

proposing to require SDRs to make these 

data available according to schemas that 

will be published on the Commission’s 

Web site and that will reference the 

international industry standards 

Financial products Markup Language 

(‘‘FpML’’) and Financial Information 

eXchange Markup Language (‘‘FIXML’’). 

DATES: Comments should be received on 

or before February 22, 2016. 

ADDRESSES: Comments may be 

submitted by any of the following 

methods: 

Electronic Comments 

• Use the Commission’s Internet 

comment form (http://www.sec.gov/

rules/proposed.shtml); or 

• Send an email to rule-comments@

sec.gov. Please include File Number S7– 

26–25 on the subject line; or 

• Use the Federal eRulemaking Portal 

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

instructions for submitting comments. 

Paper Comments 

• Send paper comments to Secretary, 

Securities and Exchange Commission, 

100 F Street NE., Washington, DC 

20549–1090. 

All submissions should refer to File 

Number S7–26–15. This file number 

should be included on the subject line 

if email is used. To help us process and 

review your comments more efficiently, 

please use only one method. The 

Commission will post all comments on 

the Commission’s Internet Web site 

(http://www.sec.gov/rules/

proposed.shtml). Comments are also 

available for Web site viewing and 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS