79384 Federal Register / Vol. 81, No. 219 / Monday, November 14, 2016 / Rules and Regulations 

(n) New Requirement of This AD: 

Terminating Action 

For airplanes on which any incorrectly 

oriented fastener, and no fractured or missing 

fastener, was detected during any inspection 

required by paragraph (g), (h)(2), (i), and (j)(1) 

of this AD: Within 24 months after the 

effective date of this AD, replace all forward 

and aft fasteners, regardless of condition or 

orientation, at WS 76.50 and WS 127.25, on 

affected wings, in accordance with the 

Accomplishment Instructions of the 

applicable service information specified in 

paragraphs (k)(1) and (k)(2) of this AD, except 

as provided by paragraph (m) of this AD. 

Doing the replacements specified in this 

paragraph terminates the requirements of this 

AD. Doing the replacements specified in this 

paragraph terminates the requirements of 

paragraphs (g) and (j) of AD 2014–03–17, 

only for the airplane on which the 

replacement was done. 

(o) Credit for Previous Actions 

This paragraph restates the provisions of 

paragraph (n) of AD 2015–02–23, with new 

credit for paragraph (n) of this AD. This 

paragraph provides credit for actions 

required by paragraphs (g), (h), (i), and (n) of 

this AD, if those actions were performed 

before the effective date of this AD using the 

applicable service information identified in 

paragraphs (o)(1) through (o)(4) of this AD. 

(1) Bombardier Alert Service Bulletin 

A600–0763, including Appendixes 1 and 2, 

dated September 26, 2013, which was 

previously incorporated by reference on 

March 6, 2014 (79 FR 9389, February 19, 

2014). 

(2) Bombardier Alert Service Bulletin 

A600–0763, Revision 01, dated February 26, 

2014, including Appendixes 1 and 2, dated 

September 26, 2013, which is not 

incorporated by reference in this AD. 

(3) Bombardier Alert Service Bulletin 

A601–0627, including Appendixes 1 and 2, 

dated September 26, 2013, which was 

previously incorporated by reference on 

March 6, 2014 (79 FR 9389, February 19, 

2014). 

(4) Bombardier Alert Service Bulletin 

A601–0627, Revision 01, dated February 26, 

2014, including Appendixes 1 and 2, dated 

September 26, 2013, which is not 

incorporated by reference in this AD. 

(p) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. In 

accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone: 

516–228–7300; fax: 516–794–5531. 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. 

(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, New York ACO, ANE–170, 

FAA; or TCCA; or Bombardier, Inc.’s TCCA 

DAO. If approved by the DAO, the approval 

must include the DAO-authorized signature. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Emergency AD CF–2013–39R2, dated 

December 12, 2014, 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–2016–5593. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(r) 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 February 18, 2015 (80 

FR 5670, February 3, 2015). 

(i) Bombardier Alert Service Bulletin 

A600–0763, Revision 02, dated December 9, 

2014, including Appendixes 1 and 2, dated 

September 26, 2013. 

(ii) Bombardier Alert Service Bulletin 

A601–0627, Revision 02, dated December 9, 

2014, including Appendixes 1 and 2, dated 

September 26, 2013. 

(4) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; Widebody Customer Response 

Center North America toll-free telephone: 1– 

866–538–1247 or direct-dial telephone: 1– 

514–855–2999; fax 514–855–7401; email: 

ac.yul@aero.bombardier.com; Internet: 

http://www.bombardier.com. 

(5) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(6) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

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

Issued in Renton, Washington, on October 

7, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–25009 Filed 11–10–16; 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; Amendment 

39–18686; AD 2016–21–05] 

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 777–200, 

–200LR, –300, and –300ER series 

airplanes. 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. This AD requires 

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 AD also requires 

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 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. 

DATES: This AD is effective December 

19, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 19, 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 


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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 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: 

Brendan Shanley, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; telephone: 425–917– 

6492; fax: 425–917–6590; email: 

brendan.shanley@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 777–200, –200LR, –300, and 

–300ER series airplanes. The NPRM 

published in the Federal Register on 

December 23, 2015 (80 FR 79754) (‘‘the 

NPRM’’). The NPRM 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. The NPRM proposed to 

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. The NPRM 

also proposed to require an inspection 

to identify the part number of the 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 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. 

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. Boeing 

stated that it has reviewed the NPRM 

and concurs with the contents of the 

NPRM. 

Request To Reduce the Compliance 

Time 

One commenter, Geoffrey Barrance, 

requested that we reduce the 

compliance time in paragraph (g) of the 

proposed AD. Mr. Barrance stated he is 

concerned that the timescale proposed 

for implementing the required 

modification, 60 months after the 

effective date of the AD, is too long. Mr. 

Barrance commented that the unsafe 

condition is a common failure affecting 

the continued operation of both engines, 

and therefore is critical to the safe flight 

and landing of any airplane. 

We disagree with the commenter’s 

request. It is important to note that 

while the commenter has indicated 

there is currently a common mode 

failure affecting the continued operation 

of both engines, it is more accurate to 

say that certain airplanes are currently 

in a configuration that makes them 

vulnerable to a single event causing a 

common mode failure. However, there 

have been no reports of any events 

causing this condition. This AD is 

intended to eliminate that condition. 

The compliance time is determined to 

be appropriate in consideration of the 

risk and the safety implications, the 

average utilization rate of the affected 

fleet, the practical aspects of an orderly 

modification of the fleet during regular 

maintenance periods, and the 

availability of required modification 

parts. In addition to our own criteria, we 

have also considered the manufacturer’s 

safety assessment and recommendation 

for the compliance time. The 

compliance time accounts for the risk to 

the fleet, availability of parts, and other 

factors. Therefore, we have determined 

that the compliance time is acceptable. 

We have not changed this AD in this 

regard. 

Request To Remove the Concurrent 

Requirements 

All Nippon Airways (ANA), Japan 

Airlines (JAL), and United Airlines 

(UAL) requested that we remove the 

concurrent requirement for 

accomplishing Boeing Service Bulletin 

777–28A0034, Revision 3, dated 

September 25, 2015. JAL and ANA 

stated that there was no relationship 

between the wiring change and the 

actuator replacement. ANA, JAL, and 

UAL commented that Boeing Service 

Bulletin 777–28A0034, Revision 3, 

dated September 25, 2015, is already 

mandated by AD 2013–05–03, 

Amendment 39–17375 (78 FR 17290, 

March 21, 2013) (‘‘AD 2013–05–03’’), 

and it addressed MOV actuator part 

number (P/N) MA20A1001–1; therefore, 

it should not be a concurrent 

requirement. ANA also added that 

because the MOV actuator has been 

addressed, paragraphs (i)(2) and (i)(3) of 

the proposed AD should not be 

included. 

We partially agree with the 

commenters. We agree that the actions 

in Boeing Service Bulletin 777– 

28A0034, Revision 3, dated September 

25, 2015, are the same actions that are 

required by AD 2013–05–03 in 

accordance with Boeing Service Bulletin 

777–28A0034, Revision 2, dated 

September 20, 2010, with a compliance 

date of April 25, 2018. Because of the 

overlap in compliance times, the action 

required by AD 2013–05–03 may not be 

fully completed by the time the 

requirements of this AD become 

effective. To ensure that the actuator 

change, in accordance with Boeing 

Service Bulletin 777–28A0034, Revision 

3, dated September 25, 2015, is done 

prior to the wiring change in accordance 

with Boeing Special Attention Service 

Bulletin 777–28–0061, Revision 2, dated 

May 4, 2015, we have required Boeing 

Service Bulletin 777–28A0034, Revision 

3, dated September 25, 2015, as a 

concurrent requirement in this AD. 

Without this concurrent requirement, it 

is possible that this AD could approve 

certain configurations that are not 

compliant and safe. The concurrent 

requirement eliminates this possibility. 

The requirements of Boeing Service 

Bulletin 777–28A0034, Revision 3, 

dated September 25, 2015, and related 

credit for previous actions, will remain 

as stated. We have not changed this AD 

in this regard. 

Request To Use Boeing Information 

Notice for Completing the Requirements 

in the AD 

ANA requested that we include 

Boeing Service Bulletin Information 

Notice 777–28–0061, IN 03, dated 

November 16, 2015, to this AD to allow 

the operators to complete the proposed 

requirements of the NPRM. 

We partially agree with the 

commenter’s request. We cannot 

include Boeing Service Bulletin 

Information Notice 777–28–0061, IN 03, 

dated November 16, 2015, as an 


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appropriate source of service 

information in this AD because it is not 

an FAA-approved document. However, 

we acknowledge that for certain 

airplanes, Figure 22, Sheet 9, of Boeing 

Special Attention Service Bulletin 777– 

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

includes an editorial error, which shows 

incorrect wire routing. Boeing Service 

Bulletin Information Notice 777–28– 

0061, IN 03, dated November 16, 2015, 

allows for a modification of Group 2 

airplanes that meets the requirements of 

the AD without an additional burden to 

operators. We have included a corrected 

figure in paragraph (h) of this AD to 

address this issue. 

In addition, Figure 11, Sheet 1, of 

Boeing Special Attention Service 

Bulletin 777–28–0061, Revision 2, dated 

May 4, 2015, is incorrect in that it 

shows the cap and stow of an existing 

wire, W4255–1002–20, which is 

terminated at splice SP41201. The 

correct wire number to be capped and 

stowed is W6251–1002–20, which is 

terminated at splice SP41201. We have 

clarified this information in paragraph 

(h)(2) of this AD. 

Request To Clarify the Terminating 

Action 

JAL and UAL requested that we 

clarify the terminating action specified 

in the proposed rule. JAL asked that 

Boeing Service Bulletin 777–28A0034 

be used as a terminating action for the 

requirements of the proposed rule. UAL 

stated that since AD 2013–05–03 

already addressed MOV actuator P/N 

MA20A2027 and P/N MA30A1001, it 

contradicts airworthiness limitations 

(AWL) 28–AWL–MOV, which was 

mandated in AD 2015–19–01, 

Amendment 39–18264 (80 FR 55521, 

dated September 16, 2015) (‘‘AD 2015– 

19–01’’). 

We agree that clarification is 

necessary. We agree that certain 

configurations in Boeing Service 

Bulletin 777–28A0034, Revision 3, 

dated September 25, 2015, in 

conjunction with previous airplane 

configurations, alleviate the need to do 

the AWL task implemented by AD 

2013–05–03 because the configurations 

are outside the applicability of that 

AWL. However, we disagree with using 

Boeing Service Bulletin 777–28A0034, 

Revision 3, dated September 25, 2015, 

as a terminating action because the 

requirement of AD 2015–19–01 is to 

implement the airworthiness limitations 

items (ALI) into an operator’s 

maintenance program, and this must be 

done regardless of the configuration of 

the airplane. Further, certain MOV 

actuator part numbers can be installed 

that will place an airplane in the 

applicability of AWL 28–AWL–MOV, 

thus requiring periodic inspections to 

ensure safe operation. Each operator has 

the option to select a configuration best 

for its circumstances and can evaluate 

its configurations and determine if AWL 

28–AWL–MOV is applicable to their 

fleet configuration. We have not 

changed this AD in this regard. 

Request To Review the Design and 

Certification Process 

Geoffrey Barrance requested that we 

review the design and certification 

process that allowed for the unsafe 

condition to exist, as well as a review 

of designs in other airplanes with 

similar unsafe conditions. Mr. Barrance 

commented that the unsafe condition 

indicated a failure has occurred in the 

design and certification process for the 

airplane type. Mr. Barrance also 

commented that a review of the airplane 

design is required to prevent the 

implementation of common mode fault 

exposures for redundant systems. 

We acknowledge the commenter’s 

concerns. We continuously evaluate our 

certification system and procedures and 

improve them when problems are 

found. If the FAA is made aware of 

potential design deficiencies occurring 

on a certificated product, we conduct an 

investigation, evaluate the 

manufacturer’s root-cause analysis, and 

make a determination whether or not an 

unsafe condition exists. We then take 

appropriate action to mitigate the unsafe 

condition and to identify and 

incorporate certification system process 

improvements for future designs. 

Furthermore, the manufacturer performs 

a cross model evaluation to determine if 

the condition exists on other models. 

We agree with the manufacturer’s 

actions in this regard. We have not 

changed this AD regarding this issue. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and 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. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

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 

(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. 

Costs of Compliance 

We estimate that this AD affects 133 

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 

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. 


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We estimate the following costs to do 

any necessary replacements and 

bonding resistance measurements that 

would be required based on the results 

of the 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 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 

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. 

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): 

2016–21–05 The Boeing Company: 

Amendment 39–18686; Docket No. 

FAA–2015–7527; Directorate Identifier 

2015–NM–094–AD. 

(a) Effective Date 

This AD is effective December 19, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to 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) Modification 

Within 60 months after the effective date 

of this AD, modify the wiring and install new 

relay brackets in new locations to allow 

installation of new relays for 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, 

except as required by paragraph (h) of this 

AD. 

(h) Exceptions to the Service Information 

(1) Where Boeing Special Attention Service 

Bulletin 777–28–0061, Revision 2, dated May 

4, 2015, specifies to use Figure 22, Sheet 9, 

for the wiring installation of the right engine 

fuel spar valve, this AD requires using figure 

1 to paragraph (h) of this AD. 

(2) Boeing Special Attention Service 

Bulletin 777–28–0061, Revision 2, dated May 

4, 2015, specifies to use Figure 11, Sheet 1, 

for the wiring change at E2–6—Shelf to 

Disconnect Panel and Splice Area. The figure 

shows the capping and stowing of an existing 

wire, W4255–1002–20, which is terminated 

at splice SP41201. The wire number is 

incorrect. The correct wire number to cap 

and stow is W6251–1002–20, which is 

terminated at splice SP41201. 

BILLING CODE 4910–13–P 


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BILLING CODE 4910–13–C 

(i) 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 

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 (i)(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 an MOV actuator that meets 

the criteria specified in paragraphs (i)(2)(i) 

and (i)(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 


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Federal Register / Vol. 81, No. 219 / Monday, November 14, 2016 / Rules and Regulations 79389 

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. 

(j) 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. These documents are not 

incorporated by reference in this AD. 

(2) This paragraph provides credit for the 

requirements of paragraph (i) 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), ‘‘AD 2013–05–03’’), 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 (j)(2)(i) or (j)(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. Boeing 

Service Bulletin 777–28A0034, Revision 2, 

dated September 20, 2010, is incorporated by 

reference in AD 2013–05–03. 

(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 

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

(3) This paragraph provides credit for the 

requirements of paragraph (i) 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. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 (l)(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 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. 

(l) Related Information 

(1) For more information about this AD, 

contact Brendan Shanley, Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone: 425– 

917–6492; fax: 425–917–6590; email: 

brendan.shanley@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 777–28–0061, Revision 2, dated May 

4, 2015. 

(ii) Boeing Service Bulletin 777–28A0034, 

Revision 3, dated September 25, 2015. 

(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 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 October 

7, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–25491 Filed 11–10–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF JUSTICE 

Drug Enforcement Administration 

21 CFR Part 1308 

[Docket No. DEA–440] 

Schedules of Controlled Substances: 

Temporary Placement of U–47700 Into 

Schedule I 

AGENCY: Drug Enforcement 

Administration, Department of Justice. 

ACTION: Final order. 

SUMMARY: The Administrator of the Drug 

Enforcement Administration is issuing 

this final order to temporarily schedule 

the synthetic opioid, 3,4-dichloro-N-[2- 

(dimethylamino)cyclohexyl]-Nmethylbenzamide (also known as 

U–47700), and its isomers, esters, 

ethers, salts and salts of isomers, esters 

and ethers, into schedule I pursuant to 

the temporary scheduling provisions of 

the Controlled Substances Act. This 

action is based on a finding by the 

Administrator that the placement of 

U–47700 into schedule I of the 

Controlled Substances Act is necessary 

to avoid an imminent hazard to the 

public safety. As a result of this order, 

the regulatory controls and 

administrative, civil, and criminal 

sanctions applicable to schedule I 

controlled substances will be imposed 

on persons who handle (manufacture, 

distribute, reverse distribute, import, 

export, engage in research, conduct 

instructional activities or chemical 

analysis, or possess), or propose to 

handle, 

U–47700. 

DATES: This final order is effective on 

November 14, 2016. 

FOR FURTHER INFORMATION CONTACT: 

Michael J. Lewis, Diversion Control 

Division, Drug Enforcement 

Administration; Mailing Address: 8701 

Morrissette Drive, Springfield, Virginia 

22152; Telephone: (202) 598–6812. 

SUPPLEMENTARY INFORMATION: 

Legal Authority 

The Drug Enforcement 

Administration (DEA) implements and 

enforces titles II and III of the 

Comprehensive Drug Abuse Prevention 

and Control Act of 1970, as amended. 21 

U.S.C. 801–971. Titles II and III are 

referred to as the ‘‘Controlled 

Substances Act’’ and the ‘‘Controlled 

Substances Import and Export Act,’’ 

respectively, and are collectively 

referred to as the ‘‘Controlled 

Substances Act’’ or the ‘‘CSA’’ for the 

purpose of this action. The DEA 

publishes the implementing regulations 


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