67038 Federal Register / Vol. 83, No. 248 / Friday, December 28, 2018 / Rules and Regulations 

reset in response to the ECAM alert, which 

could lead to exposure of critical locations 

and the surrounding structure to heat stress, 

possibly resulting in reduced structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, EASA AD 2018–0246. 

(h) Exceptions to EASA AD 2018–0246 

(1) For purposes of determining 

compliance with the requirements of this AD: 

Where EASA AD 2018–0246 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) The ‘‘Remarks’’ section of EASA AD 

2018–0246 does not apply to this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards Branch, 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 Section, send it 

to the attention of the person identified in 

paragraph (j) of this AD. 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. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, International Section, 

Transport Standards Branch, FAA; or EASA; 

or Airbus SAS’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

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

service information referenced in EASA AD 

2018–0246 that contain RC procedures and 

tests: Except as required by paragraph (i)(2) 

of this AD, RC 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. 

(j) Related Information 

For more information about this AD, 

contact Kathleen Arrigotti, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3218. 

(k) 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. 

(i) EASA AD 2018–0246, dated November 

13, 2018. 

(ii) [Reserved] 

(3) For EASA AD 2018–0246, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 89990 

6017; email ADs@easa.europa.eu; Internet 

www.easa.europa.eu. You may find this 

EASA AD on the EASA website at https://

ad.easa.europa.eu. 

(4) You may view this EASA AD at the 

FAA, Transport Standards Branch, 2200 

South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

EASA AD 2018–0246 may be found in the 

AD docket on the internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2018–1062. 

(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 Des Moines, Washington, on 

December 14, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–28067 Filed 12–27–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–4219; Product 

Identifier 2015–NM–169–AD; Amendment 

39–19535; AD 2018–26–05] 

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 

airplanes. This AD was prompted by 

reports of latently failed engine fuel 

shutoff spar valves discovered during 

fuel filter replacement. This AD requires 

inspecting to determine the part 

numbers (P/Ns) of the motor-operated 

valve (MOV) actuators at the engine fuel 

shutoff spar valve positions, installing 

MOV actuators having a certain 

acceptable part number or software if 

necessary, and revising the maintenance 

or inspection program to add a new 

airworthiness limitation. We are issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective February 1, 

2019. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 1, 2019. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Blvd., MC 

110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; internet 

https://www.myboeingfleet.com. You 

may view this service information at the 

FAA, Transport Standards Branch, 2200 

South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available on the internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2016– 

4219. 

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–2016– 

4219; or in person at Docket Operations 

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

through Friday, except Federal holidays. 

The AD docket contains this final rule, 

the regulatory evaluation, any 

comments received, and other 

information. The address for Docket 

Operations (phone: 800–647–5527) is 

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: 

Kevin Nguyen, Aerospace Engineer, 

Propulsion Section, FAA, Seattle ACO 

Branch, 2200 South 216th St., Des 

Moines, WA 98198; phone and fax: 206– 

231–3555; email: Kevin.Nguyen@

faa.gov. 

SUPPLEMENTARY INFORMATION: 


amozie on DSK3GDR082PROD with RULES
Federal Register / Vol. 83, No. 248 / Friday, December 28, 2018 / Rules and Regulations 67039 

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 airplanes. The NPRM 

published in the Federal Register on 

March 8, 2016 (81 FR 12039). The 

NPRM was prompted by reports of 

latently failed engine fuel shutoff spar 

valves discovered during fuel filter 

replacement. The NPRM proposed to 

require replacing certain MOV actuators 

with MOV actuators having a certain 

acceptable part number on both airline 

information management system (AIMS) 

Version 1- and 2-equipped airplanes, or 

installing a newer software version on 

AIMS Version 2-equipped airplanes. 

We issued a SNPRM to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 777 airplanes. The SNPRM 

published in the Federal Register on 

August 21, 2017 (82 FR 39545). We 

issued the SNPRM to add a part number 

inspection, add an AWL, and specify 

new AIMS software. 

We are issuing this AD to address 

latent failure of the fuel shutoff spar 

valve to the engine, which could result 

in the inability to terminate fuel flow to 

the engine and, in the case of an engine 

fire, could lead to wing failure. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

The following presents the comments 

received on the SNPRM and the FAA’s 

response to each comment. 

Request To Omit Inspection 

Requirement 

American Airlines (American) 

requested that we revise paragraph (g) of 

the proposed AD (in the SNPRM) to 

omit the requirement to inspect for the 

MOV actuator part numbers, and to 

reflect only the essential compliance 

requirements as stated in paragraphs 

(g)(1) and (g)(2) of the proposed AD (in 

the SNPRM) (the conditional 

requirements that depend on the part 

number found). The commenter stated 

that the inspection is not necessary to 

accomplish any of the compliance 

options and adds no value to the 

process. 

We disagree with the request. The 

MOV actuator is a rotable part. Several 

previously approved and existing 

interchangeable MOV actuator part 

numbers may be installed at the engine 

fuel shutoff spar valve positions. The 

MOV actuator installed at the engine 

fuel shutoff spar valve positions at the 

time of airplane manufacture may have 

been later replaced by an MOV actuator 

of a different part number. Because an 

unsafe condition exists with certain part 

numbers, we have determined that it is 

necessary to control the method by 

which an operator may determine what 

part number is installed. In the absence 

of such a control, an operator might 

simply assume that the part number 

delivered with the airplane is still in 

place. The most positive method to 

verify the installed part number is to 

inspect the part. Alternatively, as stated 

in paragraph (g) of this AD, the FAA 

will accept verification through a 

maintenance records check if the 

records positively show the installed 

part number. We have not changed the 

AD regarding this issue. 

Request To Incorporate AWL After 

MOV Actuator Installation 

American requested that we revise 

paragraph (g)(1) of the proposed AD (in 

the SNPRM) to include incorporation of 

new airworthiness limitation (AWL) 28– 

AWL–MOVA, which is specified in 

paragraph (h) of the proposed AD (in the 

SNPRM). 

We disagree with the request. The 

commenter did not provide rationale for 

the requested change, but we infer their 

request was to have all required actions 

within paragraph (g) of this AD. We 

have determined that it is better to 

structure the AD by separating required 

actions that are discretely different into 

separate paragraphs. As such, all 

required actions associated with 

inspecting and replacing the affected 

MOV actuators are in paragraph (g) of 

this AD and all required actions 

associated with the AWL revisions are 

in paragraph (h) of this AD. Therefore, 

we find it unnecessary to change this 

AD regarding this issue. 

Request To Clarify Airplanes Subject to 

Inspection 

Cathay Pacific noted a discrepancy in 

Boeing Service Bulletin 777–28A0034, 

Revision 3, dated September 25, 2015. 

Some airplanes that subsequently 

installed AIMS–2 Block Point (BP) 

Version 17A software may no longer 

match the conditions for the service 

bulletin groups, and do not fit the 

criteria of either paragraph (g)(1) or 

(g)(2) of the proposed AD (in the 

SNPRM). Cathay Pacific therefore 

requested that we revise paragraph (g) of 

the proposed AD (in the SNPRM) to 

clarify that the inspection is required 

only on airplanes without AIMS–2 BP 

Version 17A software. The commenter 

reported that Boeing confirmed that the 

service bulletin will be revised to 

address this discrepancy. 

We agree with the request. We had 

intended to exclude the inspection 

requirement for airplanes with AIMS–2 

BP Version 17A software installed. We 

have therefore revised paragraph (g) of 

this AD to also state that no further 

action is required by paragraph (g) of 

this AD if AIMS–2 BP Version 17 or 

later software is installed, which also 

include AIMS–2 BP Versions 17.1 and 

17A. 

Request To Allow Alternative Service 

Information 

Delta Air Lines (Delta) requested that 

we revise paragraph (g)(2)(ii) of the 

proposed AD (in the SNPRM) to allow 

Boeing Service Bulletin 777–31–0275, 

dated June 8, 2017, as another method 

to use to install AIMS–2 BP Version 17A 

software or later-approved version. 

Delta explained that this service bulletin 

describes procedures for modifying the 

hardware and software related to 

converting from AIMS–1 to AIMS–2 

software, including AIMS–2 BP Version 

17A software. Delta added that Boeing 

Service Bulletin 777–31–0275 specifies 

installation of the same software as that 

specified in Boeing Service Bulletin 

777–31–0218, and provides an 

equivalent level of safety to that of the 

SNPRM. 

We partially agree with the request. 

We agree that installation of AIMS–2 BP 

Version 17A and later-approved 

software is an acceptable alternative to 

replacing the MOV actuator, because 

that software allows failure of any of the 

previously approved MOV actuator part 

numbers to be detected and annunciated 

by the airplane display system. 

However, we find it unnecessary to 

revise paragraph (g)(2)(ii) of this AD to 

add another acceptable method of 

compliance (Boeing Service Bulletin 

777–31–0275) for the installation of 

AIMS–2 BP Version 17A software 

during conversion of an airplane from 

AIMS–1 to AIMS–2 software. Instead, 

we have revised paragraph (g) of this AD 

to clarify that no further action is 

required by paragraph (g) of this AD if 

AIMS–2 BP Version 17 or later software 

is installed. 

Request To Provide Credit for AIMS–2 

BP Version 17A Software 

American and Delta requested that we 

revise paragraph (j) of the proposed AD 

(in the SNPRM) to provide credit for 

installation of AIMS–2 BP Version 17A 

software. Delta noted a conflict between 

the ‘‘Actions Since the NPRM was 

Issued’’ section of the SNPRM (which 

specified the proposed AD would 

require installing AIMS–2 BP Version 

17A software) and paragraph (j) of the 

proposed AD (in the SNPRM) (which 


amozie on DSK3GDR082PROD with RULES
67040 Federal Register / Vol. 83, No. 248 / Friday, December 28, 2018 / Rules and Regulations 

specified credit for paragraph (g)(2)(ii) 

when AIMS–2 BP Version 17 or 17.1 

software was installed before the 

effective date of this AD). 

We agree to clarify that we have 

achieved similar results to the 

commenters request since we have 

clarified the multiple references to 

AIMS–2 BP Version 17 software in this 

AD, and that we have revised this AD 

to exclude airplanes with AIMS–2 BP 

Version 17 or later software installed 

from the requirements of paragraph (g) 

of this AD. Therefore, we have not 

changed paragraph (j) and have 

determined that no further change to the 

AD is necessary regarding this issue. 

Request To Remove AWL Requirement 

Boeing requested that we revise 

paragraph (h) of the proposed AD (in the 

SNPRM) to remove the requirement to 

incorporate the new AWL. Boeing noted 

that paragraphs (g)(1) and (g)(2)(i) of the 

proposed AD (in the SNPRM) would 

require inspection of all affected 

airplanes and replacement of all MOV 

actuators at the engine fuel shutoff spar 

valve positions with MOV actuators 

having P/N MA30A1017 (Boeing P/N 

S343T003–76). Boeing asserted that 

those proposed requirements would 

therefore be redundant with the 

proposed requirement of paragraph (h) 

of the proposed AD (in the SNPRM), 

since the AWL prohibits installation of 

MA20A2027 (Boeing P/N S343T003–56) 

and P/N MA30A1001 (Boeing P/N 

S343T003–66) MOV actuators at the 

engine fuel shutoff spar valve positions. 

We disagree with the request. As 

previously explained in the SNPRM, the 

new AWL is necessary to prevent an 

airplane from being modified to a preAD condition. Although the AWL 

would prohibit installation of the MOV 

actuators at the engine fuel shutoff spar 

valve positions, these two MOV actuator 

part numbers may still be installed at 

other locations (as their failure in the 

other locations is of economic impact 

only), and could be inadvertently reinstalled at the engine fuel shutoff spar 

valve positions. To address this 

concern, we added paragraph (h) to the 

proposed AD (in the SNPRM) to specify 

the incorporation of the new AWL. We 

have not changed this AD regarding this 

issue. 

Request To Add Instructions for 

Maintenance Program Revision 

Delta recommended that we add 

details on how to conduct the 

maintenance or inspection program, 

such as inspection methods and 

repetitive intervals, in order to clarify 

the proposed requirements of paragraph 

(h) of the proposed AD (in the SNPRM). 

That proposed requirement would 

require revising the maintenance 

program to incorporate a new 

airworthiness limitation prohibiting the 

installation of certain MOV actuators, 

and to maintain this limitation in the 

operator’s fleet maintenance program. 

Delta inferred that the purpose of the 

proposed requirement is to ensure that 

P/Ns MA30A1001 and MA20A2027 are 

not installed in the two engine fuel 

shutoff spar valve positions once the 

requirements of paragraph (g) of the AD 

have been complied with. 

Delta stated that the requirement to 

incorporate a statement indicating that a 

part is prohibited is not a maintenance 

program. Delta stated that an aircraft 

maintenance program is not the 

appropriate way to do this, adding that 

a ‘‘parts prohibition’’ statement 

(including locations—left and right 

engine fuel shutoff spar valve positions, 

in this case) would be more appropriate 

to ensure that a specific part number is 

not installed in the future. Delta stated 

that similar parts prohibition statements 

are included in AD 2016–04–20, 

Amendment 39–18414 (81 FR 10460, 

March 1, 2016), and AD 2013–05–03, 

Amendment 39–17375 (78 FR 17290, 

March 21, 2013), such that operators 

could then add notes to the airplane 

illustrated parts catalog (IPC), aircraft 

maintenance manual (AMM), etc., to 

ensure that those parts are not installed 

at the specified location in the future. 

We disagree with the request. An 

AWL containing a parts prohibition 

statement for a maintenance or 

inspection program has been required 

by other ADs, and is appropriate in this 

case. Paragraph (h) of this AD requires 

only the incorporation of the AWL item 

into the operator’s fleet, not specific 

ways to accomplish the AWL task or 

comply with the restriction. Each 

operator is responsible for 

accomplishing the AWL task and 

maintaining the AWL restriction. 

Although a parts prohibition statement 

could be included in the AD, we chose 

to mandate this requirement via 

incorporation of an AWL to be 

consistent with the requirements of AD 

2015–19–01, Amendment 39–18264 (80 

FR 55521, September 16, 2015) (‘‘AD 

2015–19–01’’). AD 2015–19–01 required 

revising the existing maintenance or 

inspection program to include a new 

AWL that required certain actions for 

The Boeing Company Model 777 

airplanes with MOV actuators having P/ 

N MA20A2027 or P/N MA30A1001 

installed at the engine fuel shutoff spar 

valve positions. The prohibited MOV 

actuator part numbers at the engine fuel 

shutoff spar valve positions are still 

physically interchangeable with the 

acceptable part numbers and may be 

used in other valve locations, and they 

are expected to remain in operators’ 

parts stores for a long period of time. We 

have not changed this AD regarding this 

issue. 

Request To Revise Compliance Time to 

Incorporate AWL 

Delta requested that we clarify the 

compliance time for incorporating the 

new AWL into the maintenance 

program, as specified in paragraph (h) of 

the proposed AD (in the SNPRM): 24 

months after the effective date of the 

AD, and after accomplishing the actions 

required by (g). Delta recommended that 

the compliance time be changed to 

within 24 months after the effective date 

of the AD or after accomplishment of 

the actions required by paragraph (g)(1) 

or (g)(2)(i) of the AD, whichever occurs 

first. Delta also asked that we remove 

the condition ‘‘after accomplishing the 

actions required by paragraph (g) of this 

AD on all airplanes in an operator’s 

fleet.’’ Delta stated that the current 

wording is unclear and appears to 

indicate operators must wait until the 

actions of paragraph (g) of the AD are 

complete on their Model 777 fleets 

before they can insert 28–AWL–MOVA 

into the maintenance program. Delta 

believes the FAA’s intent is to put in 

place a part prohibition for MOV 

actuators at the engine fuel shutoff spar 

valve positions on applicable airplanes 

without AIMS–2 BP Version 17 software 

or later version, and that when the 

requirements of paragraph (g)(2)(ii) of 

the AD are completed, this AWL would 

no longer be applicable. 

We agree with the request. We have 

revised the compliance time in 

paragraph (h) of this AD to ‘‘within 24 

months after the effective date of the 

AD.’’ This allows operators to 

incorporate the new AWL into their 

maintenance program at any time 

within that 24-month period, without 

waiting until all required actions on all 

affected airplanes in the fleet are 

completed. This would also allow 

continued operation of an airplane if 

another airplane having the pre-AD 

configuration is introduced into an 

operator’s fleet before the end of the 

compliance time, even if this were to 

occur after the accomplishment of the 

required actions on all other airplanes 

in the fleet. 

Request To Exclude Model 777F Series 

Airplanes 

FedEx requested that we exclude 

Model 777F series airplanes from the 

proposed requirements of paragraphs 

(g), (h), and (i) of the proposed AD (in 

the SNPRM). The service information, 


amozie on DSK3GDR082PROD with RULES
Federal Register / Vol. 83, No. 248 / Friday, December 28, 2018 / Rules and Regulations 67041 

Boeing Service Bulletin 777–28A0034, 

Revision 3, dated September 25, 2015, 

specifies that no work is necessary for 

airplanes in Group 7, which includes 

Model 777F series airplanes. 

We disagree with the request. Even 

though the commenter is correct in that 

Boeing Service Bulletin 777–28A0034, 

Revision 3, dated September 25, 2015, 

specifies that no work is necessary for 

airplanes in Group 7, which includes 

Model 777F series airplanes, the intent 

of this AD is to ensure that all airplanes 

identified in paragraph (c) of this AD, 

which includes Model 777F series 

airplanes and other Group 7 airplanes, 

address the unsafe condition through 

compliance with the requirements of the 

AD. Compliance with the requirements 

of paragraph (g) of this AD may be 

accomplished by installing a certain 

MOV actuator in accordance with 

Boeing Service Bulletin 777–28A0034, 

Revision 3, dated September 25, 2015, 

or installing certain AIMS–2 BP Version 

17 or later software in accordance with 

Boeing Service Bulletin 777–31–0218, 

dated September 8, 2016 (depending on 

configuration). 

We have clarified the options 

available for some of the affected 

airplanes, i.e., Group 7 airplanes with 

AIMS–2 BP Version 16 or earlier 

software. Specifically, if the actions 

specified in paragraph (g)(2)(i) of this 

AD are done, Figures 35 and 37 of 

Boeing Service Bulletin 777–28A0034, 

Revision 3, dated September 25, 2015, 

can be used for compliance regarding 

installation of the MOV actuator. 

Operators may also install AIMS–2 BP 

Version 17A software in accordance 

with paragraph (g)(2)(ii) of this AD. It is 

also necessary for operators of affected 

Boeing Model 777F airplanes to 

incorporate the AWL requirements 

specified in paragraph (h) of this AD. 

Additional Changes to AD 

The effectivity of Boeing Service 

Bulletin 777–28A0034, Revision 3, 

dated September 25, 2015, incorrectly 

categorizes airplanes in Group 4 as only 

those with AIMS–1 software installed. 

We have confirmed with Boeing that 

Group 4 airplanes includes airplanes 

with AIMS–1 software or AIMS–2 BP 

Version 16 or earlier software; or AIMS– 

2 BP Version 17 or later software. The 

airplane variable number listing in the 

service information does include the 

AIMS–2 equipped airplanes. We have 

therefore clarified for the purposes of 

the requirements in paragraph (g)(2) of 

this AD to state that Group 4, as 

identified in Boeing Service Bulletin 

777–28A0034, Revision 3, dated 

September 25, 2015, includes airplanes 

with AIMS–1 software or AIMS–2 BP 

Version 16 or earlier software installed. 

We have revised paragraph (i) in this 

AD to clarify that the requirements of 

AD 2015–19–01 may be terminated only 

when the requirements of paragraph (g) 

and (h) of this AD have been done on 

‘‘all affected airplanes in an operator’s 

fleet.’’ 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 

final rule 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 SNPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this final rule. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Service Bulletin 

777–28A0034, Revision 3, dated 

September 25, 2015. This service 

information describes procedures for, 

among other things, inspection and 

replacement of the MOV actuators at the 

engine fuel shutoff spar valve positions. 

We also reviewed Boeing Service 

Bulletin 777–31–0218, dated September 

8, 2016. This service information 

describes procedures for installing the 

AIMS–2 BP Version 17A software 

upgrade. 

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 154 

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 

Inspection .................................................... 1 work-hour × $85 per hour = $85 ............. $0 $85 $13,090. 

Replacement of two MOV actuators without fuel tank access.5 work-hours × $85 per hour = $425 ......... 12,000 12,425 Up to $422,450. 

Installation of AIMS–2 BP Version 17A 

software.

7 work-hours × $85 per hour = $595 ......... 0 595 Up to 71,400. 

We have determined that revising the 

maintenance or inspection program 

takes an average of 90 work-hours per 

operator, although we recognize that 

this number may vary from operator to 

operator. In the past, we have estimated 

that this action takes 1 work-hour per 

airplane. Since operators incorporate 

maintenance or inspection program 

changes for their affected fleets, we have 

determined that a per-operator estimate 

is more accurate than a per-airplane 

estimate. Therefore, we estimate the 

total cost per operator to be $7,650 (90 

work-hours × $85 per work-hour). 

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. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 


amozie on DSK3GDR082PROD with RULES
67042 Federal Register / Vol. 83, No. 248 / Friday, December 28, 2018 / Rules and Regulations 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to transport category 

airplanes and associated appliances to 

the Director of the System Oversight 

Division. 

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): 

2018–26–05 The Boeing Company: 

Amendment 39–19535; Docket No. 

FAA–2016–4219; Product Identifier 

2015–NM–169–AD. 

(a) Effective Date 

This AD is effective February 1, 2019. 

(b) Affected ADs 

This AD affects AD 2015–19–01, 

Amendment 39–18264 (80 FR 55521, 

September 16, 2015) (‘‘AD 2015–19–01’’). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200, 777–200LR, 777–300, 777– 

300ER, and 777F series airplanes, certificated 

in any category, excluding line numbers 1165 

and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by reports of 

latently failed engine fuel shutoff spar valves 

discovered during fuel filter replacement. We 

are issuing this AD to address latent failure 

of the fuel shutoff spar valve to the engine, 

which could result in the inability to 

terminate fuel flow to the engine and, in the 

case of an engine fire, could lead to wing 

failure. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Replacement 

Within 24 months after the effective date 

of this AD: Do an inspection to determine the 

part numbers (P/Ns) of the motor-operated 

valve (MOV) actuators at the fuel shutoff spar 

valve positions for the left and right engines, 

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 numbers can be 

conclusively determined from that review. If 

it can be definitively determined, by visual 

inspection or airplane maintenance records 

review, that P/N MA30A1017 (Boeing P/N 

S343T003–76) is installed, or that airplane 

information management system (AIMS) 2 

Block Point (BP) Version 17 or later software 

is installed, no further action is required by 

paragraph (g) of this AD. 

(1) For any MOV actuator with a P/N other 

than P/N MA30A1017 (Boeing P/N 

S343T003–76) on an airplane having AIMS– 

1 installed: Within 24 months after the 

effective date of this AD, install MOV 

actuators having part number (P/N) 

MA30A1017 at the engine fuel shutoff spar 

positions, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–28A0034, Revision 3, 

dated September 25, 2015. 

(2) For any MOV actuator with a P/N other 

than P/N MA30A1017 (Boeing P/N 

S343T003–76) on an airplane having AIMS– 

2 BP Version 16 software or earlier version, 

installed: Within 24 months after the 

effective date of this AD, do the actions 

specified in paragraph (g)(2)(i) or (g)(2)(ii) of 

this AD. For purposes of this AD, airplanes 

identified as Group 4 in Boeing Service 

Bulletin 777–28A0034, Revision 3, dated 

September 25, 2015, also include airplanes 

with AIMS–2 BP Version 16 or earlier 

software installed. 

(i) Install MOV actuators having P/N 

MA30A1017 at the engine fuel shutoff spar 

valve positions, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–28A0034, Revision 3, 

dated September 25, 2015. For airplanes 

identified as Group 7 in Boeing Service 

Bulletin 777–28A0034, Revision 3, dated 

September 25, 2015, with AIMS–2 BP 

Version 16 or earlier software, the 

instructions for installing P/N MA30A1017 

(Boeing P/N S343T003–76) are in Figures 35 

and 37 of Boeing Service Bulletin 777– 

28A0034, Revision 3, dated September 25, 

2015. 

(ii) Install AIMS–2 BP Version 17A 

software or later-approved version, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 777– 

31–0218, dated September 8, 2016. Laterapproved versions of the software are only 

those Boeing software versions that are 

approved as a replacement for AIMS–2 BP 

Version 17A software, and approved as part 

of the type design by the FAA after issuance 

of Boeing Service Bulletin 777–31–0218, 

dated September 8, 2016. 

(h) Revision of Maintenance or Inspection 

Program 

Within 24 months after the effective date 

of this AD, revise the maintenance or 

inspection program, as applicable, to add 

Airworthiness Limitation (AWL) 28–AWL– 

MOVA by incorporating the information 

specified in figure 1 to paragraph (h) of this 

AD into the Airworthiness Limitations 

Section of the Instructions for Continued 

Airworthiness. 


amozie on DSK3GDR082PROD with RULES
Federal Register / Vol. 83, No. 248 / Friday, December 28, 2018 / Rules and Regulations 67043 

(i) Terminating Action for AD 2015–19–01 

Accomplishment of the actions required by 

paragraphs (g) and (h) of this AD on all 

affected airplanes in an operator’s fleet 

terminates all requirements of AD 2015–19– 

01. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO Branch, 

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 

certification office, send it to the attention of 

the person identified in paragraph (k) of this 

AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

Branch, FAA, 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. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (j)(4)(i) and (j)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled 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 RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(k) Related Information 

For more information about this AD, 

contact Kevin Nguyen, Aerospace Engineer, 

Propulsion Section, FAA, Seattle ACO 

Branch, 2200 South 216th St., Des Moines, 

WA 98198; phone and fax: 206–231–3555; 

email: Kevin.Nguyen@faa.gov. 

(l) 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 Service Bulletin 777–28A0034, 

Revision 3, dated September 25, 2015. 

(ii) Boeing Service Bulletin 777–31–0218, 

dated September 8, 2016. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; internet https://

www.myboeingfleet.com. 

(4) You may view this service information 

at the FAA, Transport Standards Branch, 

2200 South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

(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 Des Moines, Washington, on 

December 18, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–28075 Filed 12–27–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0393; Product 

Identifier 2018–NM–010–AD; Amendment 

39–19536; AD 2018–26–06] 

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 all The 

Boeing Company Model 737–600, –700, 

–700C, –800, –900, and –900ER series 

airplanes. This AD was prompted by 

reports of loose, worn, or missing 

attachment bolts for the main landing 

gear (MLG) center door assemblies. This 

AD requires repetitive detailed 

inspections of the forward and aft MLG 

center door assembly attachments for 

loose, missing, damaged, or bottomedout attachment bolts, and any wear to 

the retention clip assemblies as 

applicable; and applicable on-condition 

actions. This AD also provides an 


amozie on DSK3GDR082PROD with RULESER28DE18.009</GPH>