Federal Register / Vol. 81, No. 149 / Wednesday, August 3, 2016 / Rules and Regulations 51097 

deployment as a result of wear and tear, 

or inertial loads resulting from in-flight 

or ground maneuvers (including gusts 

and hard landings), and other operating 

and environmental conditions 

(vibrations, moisture, etc.) likely to 

occur in service. 

3. Deployment of the leg-flail airbag 

system must not introduce injury 

mechanisms to the seated occupant, or 

result in injuries that could impede 

rapid egress. 

4. Inadvertent deployment of the legflail airbag system, during the most 

critical part of the flight, must either 

meet the requirement of § 25.1309(b), or 

not cause a hazard to the airplane or its 

occupants. This also includes 

preventing inadvertent airbag 

deployment from a static discharge. 

5. The leg-flail airbag system must not 

impede rapid egress of occupants from 

the airplane 10 seconds after airbag 

deployment. 

6. The leg-flail airbag system must be 

protected from lightning and highintensity radiated fields (HIRF). The 

threats to the airplane specified in 

existing regulations regarding lightning 

(§ 25.1316) and HIRF (§ 25.1317) are 

incorporated by reference for the 

purpose of measuring lightning and 

HIRF protection. 

7. The leg-flail airbag system must 

function properly after loss of normal 

airplane electrical power, and after a 

transverse separation of the fuselage at 

the most critical location. A separation 

at the location of the leg-flail airbag 

system does not have to be considered. 

8. The leg-flail airbag system must not 

release hazardous quantities of gas, 

sharp injurious metal fragments, or 

particulate matter into the cabin. 

9. The leg-flail airbag system 

installation must be protected from the 

effects of fire such that no hazard to 

occupants will result. 

10. A means must be available to 

verify the integrity of the leg-flail airbag 

system’s activation system prior to each 

flight, or the leg-flail airbag system’s 

activation system must reliably operate 

between inspection intervals. The FAA 

considers that the loss of the leg-flail 

airbag system’s deployment function 

alone (i.e., independent of the 

conditional event that requires the legflail airbag system’s deployment) is a 

major-failure condition. 

11. The airbag inflatable material may 

not have an average burn rate of greater 

than 2.5 inches per minute when tested 

using the horizontal flammability test 

defined in part 25, appendix F, part I, 

paragraph (b)(5). 

12. The leg-flail airbag system, once 

deployed, must not adversely affect the 

emergency-lighting system (i.e., block 

floor-proximity lights to the extent that 

the lights no longer meet their intended 

function). 

Issued in Renton, Washington, on July 26, 

2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–18398 Filed 8–2–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3983; Directorate 

Identifier 2015–NM–009–AD; Amendment 

39–18582; AD 2016–14–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting an 

airworthiness directive (AD) that 

published in the Federal Register. That 

AD applies to certain Airbus Model 

A330–200 Freighter series airplanes; 

Model A330–200 and A330–300 series 

airplanes; Model A340–200 and A340– 

300 series airplanes; Model A340–500 

series airplanes; and Model A340–600 

series airplanes. Table 1 to paragraph (j) 

of the regulatory text contains 

typographical errors regarding certain 

part numbers (P/Ns). This document 

corrects those errors. In all other 

respects, the original document remains 

the same. 

DATES: This final rule is effective August 

16, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 16, 2016 (81 FR 44983, July 

12, 2016). 

ADDRESSES: For Airbus service 

information identified in this final rule, 

contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

61 93 45 80; email airworthiness.A330- 

A340@airbus.com; Internet http://

www.airbus.com. 

For Hamilton Sundstrand service 

information identified in this final rule, 

contact Hamilton Sundstrand, Technical 

Publications, Mail Stop 302–9, 4747 

Harrison Avenue, P.O. Box 7002, 

Rockford, IL 61125–7002; telephone 

860–654–3575; fax 860–998–4564; email 

tech.solutions@hs.utc.com; Internet 

http://www.hamiltonsundstrand.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–2016– 

3983. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

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 FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Airworthiness Directive 2016–14–01, 

Amendment 39–18582 (81 FR 44983, 

July 12, 2016) (‘‘AD 2016–14–01’’), 

currently requires identification of the 

manufacturer, part number, and serial 

number of the ram air turbine (RAT), 

and re-identification and modification 

of the RAT if necessary, for certain 

Airbus Model A330–200 Freighter series 

airplanes; Model A330–200 and A330– 

300 series airplanes; Model A340–200 

and A340–300 series airplanes; Model 

A340–500 series airplanes; and Model 

A340–600 series airplanes. 

Need for the Correction 

As published, table 1 to paragraph (j) 

of the regulatory text contains 

typographical errors in two part 

numbers. Table 1 to paragraph (j) of the 

AD incorrectly refers to RAT P/Ns 

1720934C and 1720934D. Those part 

numbers should have been 1702934C 

and 1702934D. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information, which describes 

procedures for identifying the supplier, 

part number, and serial number of the 


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51098 Federal Register / Vol. 81, No. 149 / Wednesday, August 3, 2016 / Rules and Regulations 

installed RAT actuator; modifying the 

RAT; and re-identifying the RAT 

actuator and RAT. 

• Service Bulletin A330–29–3126, 

dated June 12, 2014. 

• Service Bulletin A340–29–4097, 

dated June 12, 2014. 

• Service Bulletin A340–29–5025, 

dated June 16, 2014. 

Hamilton Sundstrand has issued 

Service Bulletins ERPS06M–29–21, 

Revision 1, dated April 14, 2015; and 

ERPS33T–29–7, dated June 6, 2014. 

This service information describes 

procedures for identifying the affected 

RAT actuator and RAT part numbers 

and serial numbers, modifying affected 

actuators, and re-identifying affected 

RAT actuators and RATs. 

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. 

Correction of Publication 

This document corrects an error and 

correctly adds the AD as an amendment 

to 14 CFR 39.13. Although no other part 

of the preamble or regulatory 

information has been corrected, we are 

publishing the entire rule in the Federal 

Register. 

The effective date of this AD remains 

August 16, 2016. 

Since this action only corrects 

typographical errors, it has no adverse 

economic impact and imposes no 

additional burden on any person. 

Therefore, we have determined that 

notice and public procedures are 

unnecessary. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Correction 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration amends part 39 of the 

Federal Aviation Regulations (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 [Corrected] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2016–14–01 Airbus: Amendment 39–18582; 

Docket No. FAA–2016–3983; Directorate 

Identifier 2015–NM–009–AD. 

(a) Effective Date 

This AD becomes effective on August 16, 

2016. 

(b) Affected ADs 

This AD affects the ADs specified in 

paragraphs (b)(1), (b)(2), and (b)(3) of this AD. 

(1) AD 2012–21–19, Amendment 39–17235 

(77 FR 65812, October 31, 2012) (‘‘AD 2012– 

21–19’’). 

(2) AD 2012–21–20, Amendment 39–17236 

(77 FR 65799, October 31, 2012) (‘‘AD 2012– 

21–20’’). 

(3) AD 2016–04–01, Amendment 39–18395 

(81 FR 8134, February 18, 2016) (‘‘AD 2016– 

04–01’’). 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) through (c)(7) of this AD, 

certificated in any category. 

(1) Airbus Model A330–223F and –243F 

airplanes, all manufacturer serial numbers; 

except those on which Airbus Modification 

204067 has been embodied in production. 

(2) Airbus Model A330–201, –202, –203, 

–223, and –243 airplanes, all manufacturer 

serial numbers; except those on which 

Airbus Modification 204067 has been 

embodied in production. 

(3) Airbus Model A330–301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes, all manufacturer serial numbers; 

except those on which Airbus Modification 

204067 has been embodied in production. 

(4) Airbus Model A340–211, –212, and 

–213, airplanes, all manufacturer serial 

numbers. 

(5) Airbus Model A340–311, –312, and 

–313 airplanes, all manufacturer serial 

numbers. 

(6) Airbus Model A340–541 airplanes, all 

manufacturer serial numbers. 

(7) Airbus Model A340–642 airplanes, all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 29, Hydraulic Power. 

(e) Reason 

This AD was prompted by a report 

indicating that, during an operational test of 

a ram air turbine (RAT), the RAT did not 

deploy in automatic mode. We are issuing 

this AD to prevent non-deployment of the 

RAT, which, if preceded by a total engine 

flame-out, or during a total loss of normal 

electrical power generation, could result in 

reduced control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Identification and Replacement for 

Certain Airbus Model A330, and A340–200 

and –300 Airplanes 

For Airbus Model A330–200 Freighter 

series airplanes, Model A330–200 and –300 

series airplanes, and Model A340–200 and 

–300 series airplanes: Within 30 months after 

the effective date of this AD, identify the 

supplier, part number, and serial number of 

the installed RAT actuator, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–29–3126, 

dated June 12, 2014; or Airbus Service 

Bulletin A340–29–4097, dated June 12, 2014; 

as applicable. 

(1) If the supplier identified is Arkwin 

Industries, and the identified RAT actuator 

part number and serial number are listed in 

Hamilton Sundstrand Service Bulletin 

ERPS06M–29–21, Revision 1, dated April 14, 

2015, and the serial number is included in 

table 2 of Hamilton Sundstrand Service 

Bulletin ERPS06M–29–21, Revision 1, dated 

April 14, 2015, with a description of 

‘‘correctly shimmed’’: Within 30 months after 

the effective date of this AD, re-identify the 

actuator and the RAT, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–29–3126, dated June 

12, 2014; or Airbus Service Bulletin A340– 

29–4097, dated June 12, 2014; as applicable. 

(2) If the supplier identified is Arkwin 

Industries, and the identified actuator RAT 

part number and serial number are listed in 

Hamilton Sundstrand Service Bulletin 

ERPS06M–29–21, Revision 1, dated April 14, 

2015, and the serial number is included in 

table 2 of Hamilton Sundstrand Service 

Bulletin ERPS06M–29–21, Revision 1, dated 

April 14, 2015, with a description of 

‘‘incorrectly shimmed’’: Within 30 months 

after the effective date of this AD, remove the 

actuator from the RAT, install a modified 

actuator, and re-identify the RAT, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

29–3126, dated June 12, 2014; or Airbus 

Service Bulletin A340–29–4097, dated June 

12, 2014; as applicable. 

(3) If the supplier identified is Arkwin 

Industries, and the identification plate for the 

RAT actuator is missing, or the part number 

and serial number are not listed in Hamilton 

Sundstrand Service Bulletin ERPS06M–29– 

21, Revision 1, dated April 14, 2015: Within 

30 months after the effective date of this AD, 

remove the actuator from the RAT, install a 

modified actuator, and re-identify the RAT, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

29–3126, dated June 12, 2014; or Airbus 

Service Bulletin A340–29–4097, dated June 

12, 2014; as applicable. 

(h) Identification and Replacement for 

Certain Airbus Model A340–500 and –600 

Airplanes 

For Airbus Model A340–500 and –600 

airplanes: Within 30 months after the 

effective date of this AD, identify the part 

number and serial number of the installed 

RAT actuator, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A340–29–5025, dated June 

16, 2014. 

(1) If the identified RAT actuator part 

number and serial number are listed in 

Hamilton Sundstrand Service Bulletin 

ERPS33T–29–7, dated June 6, 2014, and the 

serial number is included in table 2 of 

Hamilton Sundstrand Service Bulletin 

ERPS33T–29–7, dated June 6, 2014, with a 

description of ‘‘correctly shimmed’’: Within 

30 months after the effective date of this AD, 

re-identify the actuator and the RAT, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A340– 

29–5025, dated June 16, 2014. 


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(2) If the identified RAT actuator part 

number and serial number are listed in 

Hamilton Sundstrand Service Bulletin 

ERPS33T–29–7, dated June 6, 2014, and the 

serial number is included in table 2 of 

Hamilton Sundstrand Service Bulletin 

ERPS33T–29–7, dated June 6, 2014, with a 

description of ‘‘incorrectly shimmed’’: 

Within 30 months after the effective date of 

this AD, remove the actuator from the RAT, 

install a modified actuator, and re-identify 

the RAT, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A340–29–5025, dated June 

16, 2014. 

(3) If the identification plate for the RAT 

actuator is missing, or the part number and 

serial number are not listed in Hamilton 

Sundstrand Service Bulletin ERPS33T–29–7, 

dated June 6, 2014: Within 30 months after 

the effective date of this AD, remove the 

actuator from the RAT, install a modified 

actuator, and re-identify the RAT, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A340– 

29–5025, dated June 16, 2014. 

(i) Terminating Action for Certain 

Requirements of Other ADs 

(1) For Airbus Model A330–200 Freighter, 

A330–200, and A330–300 series airplanes; 

and Model A340–200 and –300 series 

airplanes: Accomplishment of the actions 

required by paragraph (g)(1), (g)(2), or (g)(3) 

of this AD constitutes compliance with the 

requirements of paragraph (g)(1) of AD 2012– 

21–19, paragraph (g) of AD 2012–21–20, and 

paragraphs (g), (h), and (i) of AD 2016–04– 

01, for that airplane only. 

(2) For Airbus Model A340–500 and –600 

series airplanes: Accomplishment of the 

actions required by paragraphs (h)(1), (h)(2), 

and (h)(3) of this AD constitutes compliance 

with the requirements of paragraphs (h)(1) 

and (h)(2) of AD 2012–21–20, and paragraph 

(j) of 2016–04–01, for that airplane only. 

(j) Parts Installation Limitations 

As of the effective date of this AD, no 

person may install any RAT actuator or any 

RAT having a part number identified in table 

1 to paragraph (j) of this AD on any airplane, 

unless it meets the conditions specified in 

paragraph (j)(1) or (j)(2) of this AD, as 

applicable. 

TABLE 1 TO PARAGRAPH (j) OF THIS AD—AFFECTED PART NUMBERS

Affected Airbus airplane models RAT part No. RAT actuator 

part No. 

Model A330–200 and –300 series airplanes.1702934C, 1702934D, 766351A, 768084A, 770379A, 770952C, 770952D, 

770952E.

5912958, 5915768 

Model A330–200 Freighter series airplanes.1702934C, 1702934D, 766351A, 768084A, 770379A, 770952C, 770952D, 

770952E.

5912958, 5915768 

Model A340–200 and –300 series airplanes.1702934C, 1702934D, 766351A, 768084A, 770379A, 770952C, 770952D, 

770952E.

5912958, 5915768 

Model A340–500 and –600 series airplanes.772722H, 772722J, 772722L ................................................................................ 5912536, 5915769 

(1) For Airbus Model A330–200 Freighter 

series airplanes; Model A330–200, and 

A330–300 series airplanes; and Model A340– 

200 and –300 series airplanes: The RAT 

actuator or RAT has a serial number listed as 

affected and modified in Hamilton 

Sundstrand Service Bulletin ERPS06M–29– 

21, Revision 1, dated April 14, 2015, and the 

RAT has been re-identified in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–29–3126, 

dated June 12, 2014; or Airbus Service 

Bulletin A340–29–4097, dated June 12, 2014. 

(2) For Airbus Model A340–500 and –600 

series airplanes: The RAT actuator or the 

RAT has a serial number listed as affected 

and modified in Hamilton Sundstrand 

Service Bulletin ERPS33T–29–7, dated June 

6, 2014, and the RAT has been re-identified 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A340– 

29–5025, dated June 16, 2014. 

(k) Credit for Previous Actions 

(1) This paragraph provides credit for the 

RAT and RAT actuator identification 

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

(g)(3) of this AD if that identification was 

performed before the effective date of this AD 

using Hamilton Sundstrand Service Bulletin 

ERPS06M–29–21, dated May 27, 2014, which 

is not incorporated by reference in this AD. 

(2) This paragraph provides credit for the 

RAT or RAT actuator identification and 

modification specified in paragraph (j)(1) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Hamilton Sundstrand Service Bulletin 

ERPS06M–29–21, dated May 27, 2014, which 

is not incorporated by reference in this AD. 

(l) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; 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 

Airbus 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. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0008, dated 

January 15, 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–2016–3983. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(n) 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 August 16, 2016 (81 FR 

44983, July 12, 2016). 


rmajette on DSK2TPTVN1PROD with RULES
51100 Federal Register / Vol. 81, No. 149 / Wednesday, August 3, 2016 / Rules and Regulations 

1Electronic Tariff Filings, Order No. 714, FERC 

Stats. & Regs. ¶ 31,276, 73 FR 57515 (2008) (Order 

No. 714). 

(i) Airbus Service Bulletin A330–29–3126, 

dated June 12, 2014. 

(ii) Airbus Service Bulletin A340–29–4097, 

dated June 12, 2014. 

(iii) Airbus Service Bulletin A340–29– 

5025, dated June 16, 2014. 

(iv) Hamilton Sundstrand Service Bulletin 

ERPS06M–29–21, Revision 1, dated April 14, 

2015. 

(v) Hamilton Sundstrand Service Bulletin 

ERPS33T–29–7, dated June 6, 2014. 

(4) For Airbus service information 

identified in this AD, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

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

5 61 93 45 80; email airworthiness.A330- 

A340@airbus.com; Internet http://

www.airbus.com. 

(5) For Hamilton Sundstrand service 

information identified in this AD, contact 

Hamilton Sundstrand, Technical 

Publications, Mail Stop 302–9, 4747 Harrison 

Avenue, P.O. Box 7002, Rockford, IL 61125– 

7002; telephone 860–654–3575; fax 860–998– 

4564; email tech.solutions@hs.utc.com; 

Internet http://

www.hamiltonsundstrand.com. 

(6) 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. 

(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 Renton, Washington, on July 25, 

2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–18174 Filed 8–2–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Part 154 

[Docket No. RM01–5–000] 

Electronic Tariff Filings 

AGENCY: Federal Energy Regulatory 

Commission, DOE. 

ACTION: Correcting amendment. 

SUMMARY: This document contains 

corrections to the final regulations that 

became effective November 3, 2008 

(with implementation of the 

requirements beginning April 1, 2010), 

as published in the subsequent editions 

of the Code of Federal Regulations, 

including the 2015 edition. 

DATES: Effective date: August 3, 2016. 

FOR FURTHER INFORMATION CONTACT: 

Richard Wartchow, Office of the General 

Counsel, Federal Energy Regulatory 

Commission, 888 First Street NE., 

Washington, DC 20426, Telephone: 

202–502–6000. 

SUPPLEMENTARY INFORMATION: The 

Commission amended 18 CFR 

154.112(a), addressing the filing of 

‘‘special rate schedules,’’ reflecting 

special operating arrangements 

previously certificated pursuant to part 

157 of the Commission’s regulations 

(such as for the exchange of natural 

gas).1

As published in the 2015 edition of 

the Code of Federal Regulations, the 

final regulations (effective November 3, 

2008) contained an error. Order No. 714 

revised the fourth, fifth and sixth 

sentences to reflect new filing 

requirements. However, the published 

version of 18 CFR 154.112(a) incorrectly 

retained language from the earlier 

version that should have been 

superseded. The Commission did not 

intend to retain the superseded 

sentences. This correcting amendment 

removes the incorrectly-retained 

language. This correction does not affect 

18 CFR 154.112(b) which remains 

unchanged. 

List of Subjects in 18 CFR Part 154 

Natural gas, Pipelines, Reporting and 

record-keeping requirements, Natural 

gas companies, Rate schedules and 

tariffs. 

Accordingly, 18 CFR part 154 is 

corrected by making the following 

correcting amendments: 

PART 154—RATE SCHEDULES AND 

TARIFFS 

■ 1. The authority citation for part 154 

continues to read as follows: 

Authority: 15 U.S.C. 717–717w; 31 U.S.C. 

9701; 42 U.S.C. 7102–7352. 

■ 2. Section 154.112 is corrected by 

revising paragraph (a) to read as follows: 

§ 154.112 Exception to form and 

composition of tariff. 

(a) The Commission may permit a 

special rate schedule to be filed in the 

form of an agreement in the case of a 

special operating arrangement, 

previously certificated pursuant to part 

157 of this chapter, such as for the 

exchange of natural gas. The special rate 

schedule must contain a title page 

showing the parties to the agreement, 

the date of the agreement, a brief 

description of services to be rendered, 

and the designation: ‘‘Rate Schedule X- 

[number].’’ Special rate schedules may 

not contain any supplements. 

Modifications must be made by 

inserting revised sheets, sections or the 

entire document as appropriate. Special 

rate schedules must be included in a 

separate volume of the tariff. Each such 

separate volume must contain a table of 

contents which is incorporated as a 

sheet or section in the open access 

transmission tariff. 

* * * * * 

Dated: July 28, 2016. 

Kimberly D. Bose, 

Secretary. 

[FR Doc. 2016–18360 Filed 8–2–16; 8:45 am] 

BILLING CODE 6717–01–P 

SOCIAL SECURITY ADMINISTRATION 

20 CFR Part 404 

[Docket No. SSA–2016–0023] 

RIN 0960–AI03 

Extension of Expiration Dates for Four 

Body System Listings 

AGENCY: Social Security Administration. 

ACTION: Final rule. 

SUMMARY: We are extending the 

expiration dates of the following body 

systems in the Listing of Impairments 

(listings) in our regulations: 

Musculoskeletal System, Cardiovascular 

System, Digestive System, and Skin 

Disorders. We are making no other 

revisions to these body systems in this 

final rule. This extension ensures that 

we will continue to have the criteria we 

need to evaluate impairments in the 

affected body systems at step three of 

the sequential evaluation processes for 

initial claims and continuing disability 

reviews. 

DATES: This final rule is effective on 

August 3, 2016. 

FOR FURTHER INFORMATION CONTACT: 

Cheryl A. Williams, Director, Office of 

Medical Policy, 6401 Security 

Boulevard, Baltimore, MD 21235–6401, 

(410) 965–1020. For information on 

eligibility or filing for benefits, call our 

national toll-free number, 1–800–772– 

1213, or TTY 1–800–325–0778, or visit 

our Internet site, Social Security Online, 

at http://www.socialsecurity.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

We use the listings in appendix 1 to 

subpart P of part 404 of 20 CFR at the 

third step of the sequential evaluation 


rmajette on DSK2TPTVN1PROD with RULES