36452 Federal Register / Vol. 81, No. 109 / Tuesday, June 7, 2016 / Rules and Regulations 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(l) Related Information 

(1) For more information about this AD, 

contact Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6501; fax: 425– 

917–6590; email: kevin.nguyen@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(3) and (m)(4) 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 the AD specifies otherwise. 

(i) Boeing Special Attention Service 

Bulletin 777–54–0028, Revision 1, dated 

December 10, 2013. 

(ii) Boeing Special Attention Service 

Bulletin 777–71–0055, Revision 1, dated 

April 15, 2015. 

(iii) Airworthiness Limitation 54–AWL–01, 

‘‘Forward Strut Drain Line,’’ as specified in 

Section D.4, Pratt and Whitney Forward Strut 

Drain Line, dated March 2014, of the Boeing 

777 Maintenance Planning Data Document 

Section 9, Airworthiness Limitations and 

Certification Maintenance Requirements, 

D622W001–9, dated October 2014. 

(3) For Boeing 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. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on May 20, 

2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–12599 Filed 6–6–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3987; Directorate 

Identifier 2015–NM–066–AD; Amendment 

39–18544; AD 2016–11–17] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 787–8 

airplanes. This AD was prompted by a 

report of wire chafing caused by a left 

wing spoiler actuator wire not having 

enough separation from a certain 

bracket when the spoiler is in the 

deployed position. This AD requires 

measuring the separation between a 

certain electro-mechanical actuator wire 

of the left wing, spoiler 4, and the 

support bracket of the flap variable 

camber trim unit; and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct wire chafing. Such 

chafing could result in an electrical 

short and potential fire in a flammable 

fluid leakage zone and possible loss of 

several functions essential for safe 

flight. 

DATES: This AD is effective July 12, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 12, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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– 

3987. 

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– 

3987; 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: 

Sean J. Schauer, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office (ACO), 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425– 

917–6479; fax: 425–917–6590; email: 

sean.schauer@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 787–8 airplanes. The NPRM 

published in the Federal Register on 

October 19, 2015 (80 FR 63132) (‘‘the 

NPRM’’). The NPRM was prompted by 

a report of insufficient clearance and 

wire chafing between the wiring to the 

number 4 spoiler electro-mechanical 

actuator and a bracket of the flap 

variable camber trim unit with the 

spoiler fully deployed. The NPRM 

proposed to require measuring the 

separation between a certain electromechanical actuator wire of the left 

wing, spoiler 4, and the support bracket 

of the flap variable camber trim unit, 

and related investigative and corrective 

actions if necessary. We are issuing this 

AD to detect and correct wire chafing. 

Such chafing could result in an 

electrical short and potential fire in a 

flammable fluid leakage zone and 

possible loss of several functions 

essential for safe flight. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Support for the NPRM 

United Airlines stated that it agrees 

with the NPRM, has completed the 

actions specified in Boeing Alert Service 

Bulletin B787–81205–SB270024–00, 

Issue 001, dated September 24, 2014, 

and has no technical findings/issues to 

report. 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 109 / Tuesday, June 7, 2016 / Rules and Regulations 36453 

We acknowledge United Airlines’ 

comment. 

An anonymous commenter stated that 

it is in the airplane manufacturer’s best 

interest to address the faulty wire as 

soon as possible as this safety issue may 

have an impact on profits because of the 

impact to the company’s image. 

We agree with the commenter in so 

much as the identified unsafe condition 

needs to be addressed on the affected 

airplanes. No change to this final rule 

was requested. 

Request To Clarify the Issue That 

Prompted the NPRM 

Boeing requested that we revise the 

Discussion section of the NPRM to 

clarify that the safety issue was 

prompted by a report of wire chafing 

caused by insufficient clearance 

between the wiring to the number 4 

spoiler electro-mechanical actuator and 

a bracket of the flap variable camber 

trim unit with the spoiler fully 

deployed. 

We agree with Boeing’s statement 

regarding the action that prompted this 

AD. We have revised the Discussion 

section of this final rule accordingly. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin B787–81205–SB270024–00, 

Issue 001, dated September 24, 2014. 

The service information describes 

procedures for accomplishing the 

following actions. 

• Measuring the separation between 

the electro-mechanical actuator wire 

W801182 of the left wing, spoiler 4, and 

the support bracket of the flap variable 

camber trim unit. 

• Related investigative actions and 

corrective actions such as doing a 

general visual inspection for chafing of 

the electro-mechanical actuator wire 

W801182 of the left wing, spoiler 4; 

adjusting the electro-mechanical 

actuator wire W801182 of the left wing, 

spoiler 4; and replacing the electromechanical actuator wire W801182 of 

the left wing, spoiler 4. 

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. 

Costs of Compliance 

We estimate that this AD affects 12 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Cost per 

product 

Cost on U.S. 

operators 

Measurement ................................................................ 6 work-hours × $85 per hour = $510 ........................... $510 $6,120 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Related investigative and corrective actions ................ 2 work-hours × $85 per hour = $170 ........................... $24 $194 

According to the manufacturer, all of 

the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all the available costs in 

our cost estimate. 

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), 

(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. 


jstallworth on DSK7TPTVN1PROD with RULES
36454 Federal Register / Vol. 81, No. 109 / Tuesday, June 7, 2016 / Rules and Regulations 

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 adding 

the following new airworthiness 

directive (AD): 

2016–11–17 The Boeing Company: 

Amendment 39–18544 ; Docket No. 

FAA–2015–3987; Directorate Identifier 

2015–NM–066–AD. 

(a) Effective Date 

This AD is effective July 12, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to certain The Boeing 

Company Model 787–8 airplanes, certificated 

in any category, as identified in Boeing Alert 

Service Bulletin B787–81205–SB270024–00, 

Issue 001, dated September 24, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical power. 

(e) Unsafe Condition 

This AD was prompted by a report of wire 

chafing caused by a left wing spoiler actuator 

wire not having enough separation from a 

certain bracket when the spoiler is in the 

deployed position. We are issuing this AD to 

detect and correct wire chafing; such chafing 

could result in an electrical short and 

potential fire in a flammable fluid leakage 

zone and possible loss of several functions 

essential for safe flight. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Wire Separation Measurement, Related 

Investigative Actions, and Corrective 

Actions 

Within 24 months after the effective date 

of this AD: Measure the separation between 

the electro-mechanical actuator wire 

W801182 of the left wing, spoiler 4, and the 

support bracket of the flap variable camber 

trim unit, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

B787–81205–SB270024–00, Issue 001, dated 

September 24, 2014. Do all applicable related 

investigative and corrective actions before 

further flight. 

(h) 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 (i) 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 

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. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(i) Related Information 

For more information about this AD, 

contact Sean J. Schauer, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle ACO, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6479; fax: 425–917–6590; email: 

sean.schauer@faa.gov. 

(j) 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. 

(i) Boeing Alert Service Bulletin B787– 

81205–SB270024–00, Issue 001, dated 

September 24, 2014. 

(ii) Reserved. 

(3) For Boeing 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. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on May 20, 

2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–12842 Filed 6–6–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Office of the Secretary 

15 CFR Part 6 

[Docket No. 160523449–6449–01] 

RIN 0605–AA44 

Civil Monetary Penalty Adjustments for 

Inflation 

AGENCY: Office of the Chief Financial 

Officer and Assistant Secretary for 

Administration, Department of 

Commerce. 

ACTION: Interim final rule with request 

for comments. 

SUMMARY: This interim final rule is 

being issued to adjust for inflation each 

civil monetary penalty (CMP) provided 

by law within the jurisdiction of the 

Department of Commerce (Commerce 

Department). The Federal Civil 

Penalties Inflation Adjustment Act of 

1990, as amended by the Debt 

Collection Improvement Act of 1996 

and the Federal Civil Penalties Inflation 

Adjustment Act Improvements Act of 

2015, requires the head of each agency 

to adjust for inflation its CMP levels in 

effect as of November 2, 2015, under a 

revised methodology effective for 2016 

which provides for initial catch up 

adjustments for inflation in 2016, and 

under a revised methodology for each 

year thereafter. The revised 

methodologies provide for the 

improvement of the effectiveness of 

CMPs and to maintain their deterrent 

effect. The initial catch up adjustment 

for inflation of a CMP in 2016 shall not 

exceed 150 percent of the amount of the 

CMP on the date of enactment of the 

Federal Civil Penalties Inflation 

Adjustment Act Improvements Act of 

2015 (November 2, 2015). The initial 

catch up adjustments for inflation to 

CMPs are required to be published 

through an interim final rule not later 

than July 1, 2016, and the adjustments 

for inflation shall take effect not later 

than August 1, 2016. For each year 

thereafter, the adjustments for inflation 

to CMPs shall take effect not later than 

January 15. These adjustments for 

inflation apply only to CMPs with a 

dollar amount, and will not apply to 

CMPs written as functions of violations. 


jstallworth on DSK7TPTVN1PROD with RULES