65130 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations 

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 adding 

the following new airworthiness 

directive (AD): 

2015–19–51 Sikorsky Aircraft 

Corporation: Amendment 39–18300; Docket 

No. FAA–2015–3940; Directorate Identifier 

2015–SW–065–AD. 

(a) Applicability 

This AD applies to Model S–76A, S–76B, 

S–76C, and S–76D helicopters with main 

rotor (M/R) servo input control pushrod 

(pushrod) assembly part number (P/N) 

76400–00034–059 or tail rotor (T/R) pushrod 

assembly P/N 76400–00014–071 installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

loose jamnut. This condition could result in 

failure of a pushrod assembly, loss of M/R or 

T/R flight control, and subsequent loss of 

control of the helicopter. 

(c) Effective Date 

This AD becomes effective November 10, 

2015 to all persons except those persons to 

whom it was made immediately effective by 

Emergency AD 2015–19–51, issued on 

September 14, 2015, which contains the 

requirements of this AD. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

Within five hours time-in-service: 

(1) Inspect each pushrod end to determine 

whether a 0.020 inch diameter lockwire can 

pass through the inspection hole. 

(i) If the lockwire passes through the 

inspection hole, replace the pushrod 

assembly. 

(ii) If the lockwire does not pass through 

the inspection hole, inspect the jamnut to 

determine whether it is seated against the 

pushrod and whether it can be turned with 

finger pressure. If the jamnut is not seated 

against the pushrod or can be turned with 

finger pressure, replace the pushrod 

assembly. 

(2) Apply two slippage marks across each 

pushrod tube and jamnut as follows: 

(i) Clean the area where a slippage mark is 

to be applied. 

(ii) Apply two slippage marks across the 

pushrod tube and jamnut, parallel and on 

opposite sides of each other. Each slippage 

mark must extend at least 0.5 inch onto the 

pushrod tube and must not cover the 

inspection hole. Figures 2 and 4 of Sikorsky 

Alert Service Bulletin No. 76–67–57, Basic 

Issue, dated September 10, 2015, illustrate 

slippage marks across a pushrod tube and 

jamnut. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Boston Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Blaine Williams, Aerospace Engineer, Boston 

Aircraft Certification Office, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, Massachusetts 

01803; telephone (781) 238–7161; email 

blaine.williams@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. 

(g) Additional Information 

Sikorsky Alert Service Bulletin No. 76–67– 

57, Basic Issue, dated September 10, 2015, 

which is not incorporated by reference, 

contains additional information about the 

subject of this AD. For service information 

identified in this AD, contact Sikorsky 

Aircraft Corporation, Customer Service 

Engineering, 124 Quarry Road, Trumbull, CT 

06611; telephone 1–800–Winged–S or 203– 

416–4299; email sikorskywcs@sikorsky.com. 

You may review a copy of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 10101 

Hillwood Pkwy, Room 6N–321, Fort Worth, 

TX 76177. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2700, Flight Control System. 

Issued in Fort Worth, Texas, on October 9, 

2015. 

Lance T. Gant, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2015–26949 Filed 10–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4208; Directorate 

Identifier 2015–NM–152–AD; Amendment 

39–18303; AD 2015–21–10] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2015–19– 

03 for all The Boeing Company Model 

737–600, –700, –700C, –800, –900, and 

–900ER series airplanes. AD 2015–19– 

03 required revising the maintenance or 

inspection program to include new 

airworthiness limitations. This AD 

continues to require a maintenance or 

inspection program revision, but with 

revised language. This AD was 

prompted by a determination that 

certain language in the airworthiness 

limitation was not accurate in AD 2015– 

19–03. We are issuing this AD to detect 

and correct latent failures of the fuel 

shutoff valve to the engine, which could 

result in the inability to shut off fuel to 

the engine and, in case of certain engine 

fires, an uncontrollable fire that could 

lead to wing failure. 

DATES: This AD is effective October 28, 

2015. 

We must receive any comments on 

this AD by December 10, 2015. 

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: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

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– 

4208; 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 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: 

Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6509; fax: 


asabaliauskas on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations 65131 

425–917–6590; email: rebel.nichols@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On September 7, 2015, we issued AD 

2015–19–03, Amendment 39–18266 (80 

FR 55527, September 16, 2015), for all 

The Boeing Company Model 737–600, 

–700, –700C, –800, –900, and –900ER 

series airplanes. AD 2015–19–03 

required revising the maintenance or 

inspection program to include new 

airworthiness limitations. AD 2015–19– 

03 resulted from reports of latently 

failed fuel shutoff valves discovered 

during fuel filter replacement. We 

issued AD 2015–19–03 to detect and 

correct latent failures of the fuel shutoff 

valve to the engine, which could result 

in the inability to shut off fuel to the 

engine and, in case of certain engine 

fires, an uncontrollable fire that could 

lead to wing failure. 

Actions Since AD 2015–19–03, 

Amendment 39–18266 (80 FR 55527, 

September 16, 2015), Was Issued 

Since we issued AD 2015–19–03, 

Amendment 39–18266 (80 FR 55527, 

September 16, 2015), we have 

determined that certain language in the 

airworthiness limitation was not 

accurate. In paragraph D. of the 

‘‘Description’’ column of figure 1 to 

paragraph (g) of AD 2015–19–03, the 

‘‘START LEVER’’ is identified as a 

‘‘FUEL CONTROL switch’’ in four 

locations. In addition, in two locations 

in paragraph D. of the ‘‘Description’’ 

column of figure 1 to paragraph (g) of 

AD 2015–19–03, it specifies that fuel 

spar valve actuators are located in the 

‘‘rear spar,’’ but the correct location is 

the ‘‘front spar.’’ Also, in two locations 

in paragraph D. of the ‘‘Description’’ 

column of figure 1 to paragraph (g) of 

AD 2015–19–03, the term ‘‘quadrant’’ is 

used to describe the control stand, but 

the correct terminology is ‘‘CONTROL 

STAND.’’ We have determined that the 

language must be corrected to avoid any 

confusion in the paragraphs of the 

airworthiness limitation. We are issuing 

this AD to detect and correct latent 

failures of the fuel shutoff valve to the 

engine, which could result in the 

inability to shut off fuel to the engine 

and, in case of certain engine fires, an 

uncontrollable fire that could lead to 

wing failure. 

FAA’s Determination 

We are issuing 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. 

AD Requirements 

This AD requires revising the 

maintenance or inspection program to 

include new airworthiness limitations. 

Interim Action 

We consider this AD interim action. 

The manufacturer is currently 

developing a modification that will 

address the unsafe condition identified 

in this AD. Once this modification is 

developed, approved, and available, we 

might consider additional rulemaking. 

FAA’s Justification and Determination 

of the Effective Date 

We are superseding AD 2015–19–03, 

Amendment 39–18266 (80 FR 55527, 

September 16, 2015), to correct 

inaccurate terminology in paragraph D. 

of the ‘‘Description’’ column of figure 1 

to paragraph (g) of AD 2015–19–03. We 

have made no other changes to the 

requirements published in AD 2015–19– 

03. We have determined that the 

changes impose no additional burden 

on any operator. Therefore, we find that 

notice and opportunity for prior public 

comment are unnecessary and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the Docket Number 

FAA–2015–4208 and Directorate 

Identifier 2015–NM–152–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 1,244 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Incorporating Airworthiness Limitation ............ 1 work-hour × $85 per hour = $85 ................. $0 $85 $105,740 

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 

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 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 


asabaliauskas on DSK5VPTVN1PROD with RULES
65132 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations 

(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 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 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2015–19–03, Amendment 39–18266 (80 

FR 55527, September 16, 2015), and 

adding the following new AD: 

2015–21–10 The Boeing Company: 

Amendment 39–18303; Docket No. 

FAA–2015–4208; Directorate Identifier 

2015–NM–152–AD. 

(a) Effective Date 

This AD is effective October 28, 2015. 

(b) Affected ADs 

This AD replaces AD 2015–19–03, 

Amendment 39–18266 (80 FR 55527, 

September 16, 2015). 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 2823, Fuel Selector/Shutoff 

Valve. 

(e) Unsafe Condition 

This AD was prompted by reports of 

latently failed fuel shutoff valves discovered 

during fuel filter replacement. We are issuing 

this AD to detect and correct latent failures 

of the fuel shutoff valve to the engine, which 

could result in the inability to shut off fuel 

to the engine and, in case of certain engine 

fires, an uncontrollable fire that could lead to 

wing failure. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision of Maintenance or Inspection 

Program 

Within 30 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to add airworthiness 

limitation number 28–AWL–MOV, ‘‘Engine 

Fuel Shutoff Valve (Fuel Spar Valve) Position 

Indication Operational Check,’’ by 

incorporating the information specified in 

figure 1 to paragraph (g) of this AD into the 

Airworthiness Limitations Section of the 

Instructions for Continued Airworthiness. 

The initial compliance time for 

accomplishing the actions specified in 28– 

AWL–MOV is within 10 days after 

accomplishing the maintenance or inspection 

program revision required by this paragraph. 

FIGURE 1 TO PARAGRAPH (g) OF THIS AD—ENGINE FUEL SHUTOFF VALVE (FUEL SPAR VALVE) POSITION INDICATION

OPERATIONAL CHECK

AWL No. Task Interval Applicability Description 

28–AWL–MOV ........................ ALI DAILY ............................ 737–600, –700, –700C, 

–800, –900, and 

–900ER series airplanes.

Engine Fuel Shutoff Valve (Fuel Spar Valve) Position Indication Operational Check. 

INTERVAL NOTE: The 

operational check is 

not required on days 

when the airplane is 

not used in revenue 

service.

The check must be 

done before further 

flight once the airplane is returned to 

revenue service.

APPLICABILITY NOTE: 

Only applies to airplanes with a fuel 

spar valve actuator 

having part number 

MA20A2027 

(S343T003–56) or 

MA30A1001 

(S343T003–66) installed at the engine 

fuel spar valve positions.

Concern: The fuel spar valve actuator design 

can result in airplanes operating with a failed 

fuel spar valve actuator that is not reported. A 

latently failed fuel spar valve actuator could 

prevent fuel shutoff to an engine. In the event 

of certain engine fires, the potential exists for 

an engine fire to be uncontrollable. 

Perform one of the following checks of the engine fuel spar valve position (unless checked 

by the flightcrew in a manner approved by the 

principal operations inspector): 

A. Operational Check during engine shutdown. 

1. Do an operational check of the left engine fuel 

spar valve actuator. 

a. As the ENG 1 START LEVER on the CONTROL STAND is moved to the CUTOFF position, verify the SPAR VALVE CLOSED indication light on the OVERHEAD PANEL for No.1 

Engine changes from OFF to BRIGHT then 

DIM. 

b. If the test fails (bright light fails to illuminate), 

before further flight, repair faults as required 

(refer to Boeing Aircraft Maintenance Manual 

(AMM) 28–22–11). 

2. Do an operational check of the right engine 

fuel spar valve actuator. 

a. As the ENG 2 START LEVER on the CONTROL STAND is moved to the CUTOFF position, verify the SPAR VALVE CLOSED indication light on the OVERHEAD PANEL for No. 2 

Engine changes from OFF to BRIGHT then 

DIM. 


asabaliauskas on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations 65133 

FIGURE 1 TO PARAGRAPH (g) OF THIS AD—ENGINE FUEL SHUTOFF VALVE (FUEL SPAR VALVE) POSITION INDICATION

OPERATIONAL CHECK—Continued 

AWL No. Task Interval Applicability Description 

b. If the test fails (bright light fails to illuminate), 

before further flight, repair faults as required 

(refer to Boeing AMM 28–22–11). 

B. Operational check during engine start. 

1. Do an operational check of the left engine fuel 

spar valve actuator. 

a. As the ENG 1 START LEVER on the CONTROL STAND is moved to the IDLE position, 

verify the SPAR VALVE CLOSED indication 

light on the OVERHEAD PANEL for No. 1 Engine changes from DIM to BRIGHT then OFF. 

b. If the test fails (bright light fails to illuminate), 

before further flight, repair faults as required 

(refer to Boeing AMM 28–22–11). 

2. Do an operational check of the right engine 

fuel spar valve actuator. 

a. As the ENG 2 START LEVER on the CONTROL STAND is moved to the IDLE position, 

verify the SPAR VALVE CLOSED indication 

light on the OVERHEAD PANEL for No. 2 Engine changes from DIM to BRIGHT then OFF. 

b. If the test fails (bright light fails to illuminate), 

before further flight, repair faults as required 

(refer to Boeing AMM 28–22–11). 

C. Operational check without engine operation. 

1. Supply electrical power to airplane using 

standard practices. 

2. Make sure No. 1 and No. 2 Engine FIRE 

switches on the Aft Electronic Panel are in the 

NORMAL (IN) position. 

3. Make sure No. 1 and No. 2 Engine Start 

Switches on the Forward Overhead Panel are 

in the OFF or AUTO position. 

4. Do an operational check to the left engine fuel 

spar valve actuator. 

a. Move ENG 1 START LEVER on the CONTROL STAND to the IDLE position and wait 

approximately 10 seconds. 

NOTE: It is normal under this test condition for 

the ENG VALVE CLOSED indication light on 

the OVERHEAD PANEL to transition from DIM 

to BRIGHT and stay BRIGHT. 

b. Move ENG 1 START LEVER on the CONTROL STAND to the CUTOFF position. 

c. Verify the SPAR VALVE CLOSED indication 

light on the OVERHEAD PANEL for No. 1 Engine changes from OFF to BRIGHT then DIM. 

d. If the test fails (bright light fails to illuminate), 

before further flight, repair faults as required 

(refer to Boeing AMM 28–22–11). 

5. Do an operational check of the right engine 

fuel spar valve actuator. 

a. Move ENG 2 START LEVER on the CONTROL STAND to the IDLE position and wait 

approximately 10 seconds. 

NOTE: It is normal under this test condition for 

the ENG VALVE CLOSED indication light on 

the OVERHEAD PANEL to transition from DIM 

to BRIGHT and stay BRIGHT. 

b. Move ENG 2 START LEVER on the CONTROL STAND to the CUTOFF position. 

c. Verify the SPAR VALVE CLOSED indication 

light on the OVERHEAD PANEL for No.2 Engine changes from OFF to BRIGHT then DIM. 

d. If the test fails (bright light fails to illuminate), 

before further flight, repair faults as required 

(refer to Boeing AMM 28–22–11). 

D. Perform an inspection of the engine fuel spar 

valve actuator position. 


asabaliauskas on DSK5VPTVN1PROD with RULES
65134 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations 

FIGURE 1 TO PARAGRAPH (g) OF THIS AD—ENGINE FUEL SHUTOFF VALVE (FUEL SPAR VALVE) POSITION INDICATION

OPERATIONAL CHECK—Continued 

AWL No. Task Interval Applicability Description 

NOTE: This inspection may be used whenever 

the SPAR VALVE light does not function properly. 

1. Make sure the ENG 1 START LEVER on the 

CONTROL STAND is in the CUTOFF position. 

NOTE: It is not necessary to cycle the START 

LEVER to do this inspection. 

2. Inspect the left engine fuel spar valve actuator 

located in the left front spar. 

NOTE: The left engine fuel spar valve actuator is 

on the left wing front spar outboard of the engine strut. Access is through access panel 

521BB on the left wing leading edge. 

a. Verify the manual override handle on the engine fuel spar valve actuator is in the CLOSED 

position. 

b. Repair or replace any engine fuel spar valve 

actuator that is not in the CLOSED position 

(refer to Boeing AMM 28–22–11). 

3. Make sure the ENG 2 START LEVER on the 

CONTROL STAND is in the CUTOFF position. 

NOTE: It is not necessary to cycle the START 

LEVER to do this inspection. 

4. Inspect the right engine fuel spar valve actuator located in the right front spar. 

NOTE: The right engine fuel spar valve actuator 

is on the right wing front spar outboard of the 

engine strut. Access is through access panel 

621BB on the right wing leading edge. 

a. Verify the manual override handle on the engine fuel spar valve actuator is in the CLOSED 

position. 

b. Repair or replace any engine fuel spar valve 

actuator that is not in the CLOSED position 

(refer to Boeing AMM 28–22–11). 

(h) No Alternative Actions or Intervals 

After accomplishment of the maintenance 

or inspection program revision required by 

paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (i)(1) of 

this AD. 

(i) 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 (j) 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. 

(j) Related Information 

For more information about this AD, 

contact Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6509; fax: 425–917–6590; 

email: rebel.nichols@faa.gov. 

(k) Material Incorporated by Reference 

None. 

Issued in Renton, Washington, on October 

16, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26992 Filed 10–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

U.S. Customs and Border Protection 

DEPARTMENT OF THE TREASURY 

19 CFR Parts 4, 7, 10, 12, 18, 19, 24, 

54, 102, 113, 123, 125, 128, 132, 134, 

141, 142, 143, 144, 145, 146, 148, 151, 

152, 158, 163, 174, 181, and 191 

[CBP Dec. No. 15–14; USCBP–2015–0045] 

RIN 1515–AE03 

Automated Commercial Environment 

(ACE) Filings for Electronic Entry/Entry 

Summary (Cargo Release and Related 

Entry); Correction 

AGENCY: U.S. Customs and Border 

Protection, Department of Homeland 

Security; Department of the Treasury. 

ACTION: Interim final rule; correction. 

SUMMARY: U.S. Customs and Border 

Protection (CBP) published an Interim 

Final Rule (CBP Dec. 15–14) on October 

13, 2015, in the Federal Register, which 

amends the CBP regulations to reflect 


asabaliauskas on DSK5VPTVN1PROD with RULES