This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

27718 

Vol. 83, No. 115 

Thursday, June 14, 2018 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0510; Product 

Identifier 2017–NM–115–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2016–04– 

16, which applies to all The Boeing 

Company Model DC–10–10, DC–10– 

10F, DC–10–15, DC–10–30, DC–10–30F 

(KC–10A and KDC–10), DC–10–40, DC– 

10–40F, MD–10–10F, MD–10–30F, MD– 

11, and MD–11F airplanes. AD 2016– 

04–16 requires adding design features to 

detect electrical faults and to detect a 

pump running in an empty fuel tank. 

Since we issued AD 2016–04–16, we 

have received new service information 

that would eliminate the need for 

certain provisions of AD 2016–04–16. 

This proposed AD would provide 

optional terminating action for certain 

requirements. We are proposing this AD 

to address the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by July 30, 2018. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, 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–2018– 

0510. 

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–2018– 

0510; 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 NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for Docket Operations 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Serj 

Harutunian, Aerospace Engineer, 

Propulsion Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5254; fax: 562–627– 

5210; email: serj.harutunian@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2018–0510; Product Identifier 2017– 

NM–115–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM 

because of those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We issued AD 2016–04–16, 

Amendment 39–18410 (81 FR 12806, 

March 11, 2016) (‘‘AD 2016–04–16’’), for 

all The Boeing Company Model DC–10– 

10, DC–10–10F, DC–10–15, DC–10–30, 

DC–10–30F (KC–10A and KDC–10), DC– 

10–40, DC–10–40F, MD–10–10F, MD– 

10–30F, MD–11, and MD–11F airplanes. 

AD 2016–04–16 requires adding design 

features to detect electrical faults and to 

detect a pump running in an empty fuel 

tank. AD 2016–04–16 resulted from a 

determination that it is necessary to 

clarify the requirements for the design 

features and to remove a terminating 

action for certain inspections. We issued 

AD 2016–04–16 to reduce the potential 

of ignition sources inside fuel tanks, 

which, in combination with flammable 

fuel vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. 

Actions Since AD 2016–04–16 Was 

Issued 

Since we issued AD 2016–04–16, we 

have received new service information 

that would eliminate the need for 

certain provisions of AD 2016–04–16. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following Boeing 

service information. 

• Boeing Alert Service Bulletin 

DC10–28A253, dated June 5, 2014; and 

Boeing Alert Service Bulletin MD11– 

28A133, dated June 5, 2014. This 

service information describes 

procedures for replacing the fuel pump 

control relays with fault current 

detectors and changing the fuel tank 

boost/transfer pump wire termination. 

These documents are distinct since they 

apply to different airplane models. 

• Boeing Service Bulletin DC10–28– 

256, dated June 24, 2014; and Boeing 

Service Bulletin MD11–28–137, dated 

June 24, 2014. This service information 

describes procedures for changing the 

fuel pump control and indication 

system wiring. These documents are 

distinct since they apply to different 

airplane models. 

• Boeing Trijet Special Compliance 

Item Report MDC–02K1003, Revision M, 


daltland on DSKBBV9HB2PROD with PROPOSALS
Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules 27719 

including Appendices A through D, 

dated July 25, 2014, which includes 

Critical Design Configuration Control 

Limitations (CDCCLs), Airworthiness 

Limitation Instructions (ALIs), and 

short-term extensions in Appendices B, 

C, and D, respectively. The service 

information describes fuel ALIs that 

address ignition sources. 

• Boeing Service Bulletin DC10–28– 

264, dated May 15, 2015, or Boeing 

Service Bulletin MD11–28–146, dated 

May 15, 2015. This service information 

describes procedures for replacement of 

the fuel pump housing electrical 

connector, associated wires, fuel tank 

feed-through components, and installing 

sealed terminal lugs on the fuel pump 

wiring, or replacement of the fuel pump 

housing, associated wires, fuel tank 

feed-through components, and installing 

sealed terminal lugs on the fuel pump. 

These documents are distinct since they 

apply to different airplane models. 

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. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. 

Proposed AD Requirements 

This proposed AD would retain all 

requirements of AD 2016–04–16. 

Specifically, this proposed AD would 

retain the repetitive inspections for 

proper operation of the fuel pump, and 

applicable corrective actions. 

This proposed AD would also 

eliminate the need for the provisions in 

paragraph (j) of this proposed AD by 

providing optional terminating action 

for the requirements of paragraph (a) of 

AD 2002–13–10, Amendment 39–12798 

(67 FR 45053, July 8, 2002); paragraph 

(a) of AD 2003–07–14, Amendment 39– 

13110 (68 FR 17544, April 10, 2003); 

and paragraph (j) of AD 2011–11–05, 

Amendment 39–16704 (76 FR 31462, 

June 1, 2011). 

This proposed AD specifies to revise 

certain operator maintenance 

documents to include new actions (e.g., 

inspections) and CDCCLs. Compliance 

with these actions and CDCCLs is 

required by 14 CFR 91.403(c). For 

airplanes that have been previously 

modified, altered, or repaired in the 

areas addressed by this proposed AD, 

the operator may not be able to 

accomplish the actions described in the 

revisions. In this situation, to comply 

with 14 CFR 91.403(c), the operator 

must request approval for an alternative 

method of compliance according to 

paragraph (l) of this proposed AD. The 

request should include a description of 

changes to the required actions and 

CDCCLs that will ensure the continued 

operational safety of the airplane. For 

information on the procedures and 

compliance times, see this service 

information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0510. 

Costs of Compliance 

We estimate that this proposed AD 

affects 341 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Installing design features using a method approved by the FAA (retained actions from 

AD 2016–04–16).

152 work-hours × $85 per hour = $12,920 .... $137,500 $150,420 $51,293,220 

Installing design features using service information (retained actions from AD 2016– 

04–16).

98 work-hours × $85 per hour = $8,330 ........ 109,000 117,330 40,009,530 

Inspection for proper operation (new proposed action).Up to 130 work-hours × $85 per hour = 

$11,050 per inspection cycle.

0 Up to $11,050 per inspection 

cycle. 

ESTIMATED COSTS FOR OPTIONAL TERMINATING ACTIONS

Action Labor cost Parts cost Cost per product 

Option 1: Replace connectors for Model DC–10 and MD–10 (122 airplanes).68 work-hours × $85 per hour = 

$5,780.

$54,842 ............ $60,622. 

Option 1: Replace connectors for Model MD–11 (124 airplanes) ......... 59 work-hours × $85 per hour = 

$5,015.

$67,031 ............ $72,046. 

Option 2: Replace fuel pump housings for Model DC–10 and MD–10 

(122 airplanes).

Up to 81 work-hours × $85 per 

hour = $6,885.

Up to $54,842 .. Up to $61,727. 

Option 2: Replace fuel pump housings for Model MD–11 (124 airplanes).Up to 77 work-hours × $85 per 

hour = $6,545.

Up to $67,031 .. Up to $73,576. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed 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. 


daltland on DSKBBV9HB2PROD with PROPOSALS
27720 Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules 

This proposed AD is issued in 

accordance with authority delegated by 

the Executive Director, Aircraft 

Certification Service, 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 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2016–04–16, Amendment 39–18410 (81 

FR 12806, March 11, 2016), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2018–0510; Product Identifier 2017– 

NM–115–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by July 30, 2018. 

(b) Affected ADs 

(1) This AD replaces AD 2016–04–16, 

Amendment 39–18410 (81 FR 12806, March 

11, 2016) (‘‘AD 2016–04–16’’). 

(2) This AD affects AD 2002–13–10, 

Amendment 39–12798 (67 FR 45053, July 8, 

2002) (‘‘AD 2002–13–10’’). 

(3) This AD affects AD 2003–07–14, 

Amendment 39–13110 (68 FR 17544, April 

10, 2003) (‘‘AD 2003–07–14’’). 

(4) This AD affects AD 2008–06–21 R1, 

Amendment 39–16100 (74 FR 61504, 

November 25, 2009) (‘‘AD 2008–06–21 R1’’). 

(5) This AD affects AD 2011–11–05, 

Amendment 39–16704 (76 FR 31462, June 1, 

2011) (‘‘AD 2011–11–05’’). 

(c) Applicability 

This AD applies to all The Boeing 

Company airplanes identified in paragraphs 

(c)(1) and (c)(2) of this AD, certificated in any 

category. 

(1) Model DC–10–10, DC–10–10F, DC–10– 

15, DC–10–30, DC–10–30F (KC–10A and 

KDC–10), DC–10–40, and DC–10–40F 

airplanes. 

(2) Model MD–10–10F, MD–10–30F, MD– 

11, and MD–11F airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by a fuel system 

review conducted by the manufacturer. We 

are issuing this AD to reduce the potential of 

ignition sources inside fuel tanks, which, in 

combination with flammable fuel vapors, 

could result in fuel tank explosions and 

consequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Restatement of Paragraph (g) of AD 2016– 

04–16, With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2016–04–16, with no 

changes. Except as provided by paragraph (h) 

of this AD: As of 48 months after April 15, 

2016 (the effective date of AD 2016–04–16), 

no person may operate any airplane affected 

by this AD unless an amended type 

certificate or supplemental type certificate 

that incorporates the design features and 

requirements described in paragraphs (g)(1) 

through (g)(4) of this AD has been approved 

by the Manager, Los Angeles ACO Branch, 

FAA, and those design features are installed 

on the airplane to meet the criteria specified 

in section 25.981(a) and (d) of the Federal 

Aviation Regulations (14 CFR 25.981(a) and 

(d), at Amendment 25–125 (http://rgl.faa.gov/ 

Regulatory_and_Guidance_Library/ 

rgFAR.nsf/0/339DAEE3E0A6379D86257

4CF00641951?OpenDocument)). For 

airplanes on which Boeing-installed auxiliary 

fuel tanks are removed, the actions specified 

in this AD for the auxiliary fuel tanks are not 

required. 

(1) For all airplanes: Each electrically 

powered alternating current (AC) fuel pump 

installed in any fuel tank that normally 

empties during flight and each pump that is 

partially covered by a lowering fuel level— 

such as main tanks, center wing tanks, 

auxiliary fuel tanks installed by the airplane 

manufacturer, and tail tanks—must have a 

protective device installed to detect electrical 

faults that can cause arcing and burn through 

of the fuel pump housing and pump 

electrical connector. The same device must 

shut off the pump by automatically removing 

electrical power from the pump when such 

faults are detected. When a fuel pump is shut 

off resulting from detection of an electrical 

fault, the device must stay latched off, until 

the fault is cleared through maintenance 

action and the pump is verified safe for 

operation. 

(2) For airplanes with a 2-person 

flightcrew: Additional design features, if not 

originally installed by the airplane 

manufacturer, must be installed to meet 3 

criteria: To detect a running fuel pump in a 

tank that is normally emptied during flight, 

to provide an indication to the flightcrew that 

the tank is empty, and to automatically shut 

off that fuel pump. The prospective pump 

indication and shutoff system must 

automatically shut off each pump in case the 

flightcrew does not shut off a pump running 

dry in an empty tank within 60 seconds after 

each fuel tank is emptied. An airplane flight 

manual supplement (AFMS) that includes 

flightcrew manual pump shutoff procedures 

in the Limitations section of the AFMS must 

be submitted to the Los Angeles ACO Branch, 

FAA, for approval. 

(3) For airplanes with a 3-person 

flightcrew: Additional design features, if not 

originally installed by the airplane 

manufacturer, must be installed to detect 

when a fuel pump in a tank that is normally 

emptied during flight is running in an empty 

fuel tank, and to provide an indication to the 

flightcrew that the tank is empty. The flight 

engineer must manually shut off each pump 

running dry in an empty tank within 60 

seconds after the tank is emptied. The AFMS 

Limitations section must be revised to 

specify that this pump shutoff must be done 

by the flight engineer. 

(4) For all airplanes with tanks that 

normally empty during flight: Separate 

means must be provided to detect and shut 

off a pump that was previously commanded 

to be shut off automatically or manually but 

remained running in an empty tank during 

flight. 

(h) Restatement of Paragraph (h) of AD 

2016–04–16, With No Changes 

This paragraph restates the provisions of 

paragraph (h) of AD 2016–04–16, with no 

changes. In lieu of doing the requirements of 

paragraph (g) of this AD, do the applicable 

actions specified in paragraphs (h)(1), (h)(2), 

and (h)(3) of this AD. 

(1) For MD–11 and MD–11F airplanes: Do 

the actions specified in paragraphs (h)(1)(i) 

and (h)(1)(ii) of this AD. 

(i) As of 48 months after April 15, 2016 

(the effective date of AD 2016–04–16), 

change the fuel pump control and indication 

system wiring, in accordance with the 


daltland on DSKBBV9HB2PROD with PROPOSALS
Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules 27721 

Accomplishment Instructions of Boeing 

Service Bulletin MD11–28–137, dated June 

24, 2014. 

(ii) Prior to or concurrently with 

accomplishing the actions specified in 

paragraph (h)(1)(i) of this AD: Replace the 

fuel pump control relays with fault current 

detectors, and change the fuel tank boost/ 

transfer pump wire termination, in 

accordance with Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD11–28A133, dated June 5, 2014. 

(2) For Model DC–10–10, DC–10–10F, DC– 

10–15, DC–10–30, DC–10–30F (KC–10A and 

KDC–10), DC–10–40, DC–10–40F, MD–10– 

10F, and MD–10–30F airplanes: Do the 

actions specified in paragraphs (h)(2)(i) and 

(h)(2)(ii) of this AD. 

(i) As of 48 months after April 15, 2016 

(the effective date of AD 2016–04–16), 

change the fuel pump control and indication 

system wiring, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC10–28–256, dated June 

24, 2014. 

(ii) Prior to or concurrently with 

accomplishing the actions specified in 

paragraph (h)(2)(i) of this AD: Replace the 

fuel pump control relays with fault current 

detectors, and change the fuel tank boost/ 

transfer pump wire termination, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

DC10–28A253, dated June 5, 2014. 

(3) For all airplanes: Within 30 days after 

accomplishing the actions required by 

paragraph (h)(1) or (h)(2) of this AD, or 

within 30 days after April 15, 2016 (the 

effective date of AD 2016–04–16), whichever 

occurs later, revise the maintenance or 

inspection program, as applicable, to 

incorporate the Critical Design Configuration 

Control Limitations (CDCCLs), Airworthiness 

Limitation Instructions (ALIs), and shortterm extensions specified in Appendices B, 

C, and D of Boeing Trijet Special Compliance 

Item (SCI) Report MDC–02K1003, Revision 

M, dated July 25, 2014. The initial 

compliance time for accomplishing the 

actions specified in the ALIs is at the later 

of the times specified in paragraphs (h)(3)(i) 

and (h)(3)(ii) of this AD. Revising the 

maintenance or inspection program required 

by this paragraph terminates the 

requirements in paragraphs (g) and (h) of AD 

2008–06–21 R1. 

(i) At the applicable time specified in 

Appendix C of Boeing Trijet SCI Report 

MDC–02K1003, Revision M, dated July 25, 

2014, except as provided by Appendix D of 

Boeing Trijet SCI Report MDC–02K1003, 

Revision M, dated July 25, 2014. 

(ii) Within 30 days after accomplishing the 

actions required by paragraph (h)(1) or (h)(2) 

of this AD, as applicable; or within 30 days 

after April 15, 2016 (the effective date of AD 

2016–04–16); whichever occurs later. 

(i) Restatement of Paragraph (i) of AD 2016– 

04–16, With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2016–04–16, with no 

changes. If the option in paragraph (h)(3) of 

this AD is accomplished: After the 

maintenance or inspection program has been 

revised as provided by paragraph (h)(3) of 

this AD, no alternative actions (e.g., 

inspections), intervals, or CDCCLs may be 

used unless the actions, intervals, or CDCCLs 

are approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (l) of this 

AD. 

(j) Restatement of Paragraph (j) of AD 2016– 

04–16, With Additional AD Reference and 

Clarification of Provisions 

This paragraph restates the provisions of 

paragraph (j) of AD 2016–04–16, with an 

additional AD reference and clarification of 

the provisions. Accomplishment of the 

actions specified in paragraphs (h)(1), (h)(2), 

and (h)(3) of this AD, as applicable, extends 

the 18-month interval for the repetitive 

inspections and tests required by paragraph 

(a) of AD 2002–13–10; the 18-month interval 

for the repetitive inspections required by 

paragraph (a) of AD 2003–07–14; and the 18- 

month interval for the repetitive inspections 

required by paragraph (j) of AD 2011–11–05; 

to 24-month intervals for pumps affected by 

those ADs, regardless if the pump is installed 

in a tank that normally empties, provided the 

remaining actions required by those three 

ADs have been accomplished. 

(k) New Provision of This AD: Optional 

Terminating Action 

Replacing the electrical connectors or fuel 

pump housing in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC10–28–264, dated May 

15, 2015; or Boeing Service Bulletin MD11– 

28–146, dated May 15, 2015, as applicable; 

terminates the repetitive inspections and 

tests required by paragraph (a) of AD 2002– 

13–10, paragraph (a) of AD 2003–07–14, and 

paragraph (j) of AD 2011–11–05. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (m)(1) of 

this AD. Information may be emailed to: 

9-ANM-LAACO-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, Los Angeles 

ACO Branch, 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 (l)(4)(i) and (l)(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. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. 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. 

(m) Related Information 

(1) For more information about this AD, 

contact Serj Harutunian, Aerospace Engineer, 

Propulsion Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5254; fax: 562–627–5210; email: 

serj.harutunian@faa.gov. 

(2) 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. You may view this 

referenced 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. 

Issued in Des Moines, Washington, on June 

6, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–12656 Filed 6–13–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0511; Product 

Identifier 2017–NM–145–AD] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all BAE 

Systems (Operations) Limited Model 

4101 airplanes. This proposed AD was 

prompted by a determination that 


daltland on DSKBBV9HB2PROD with PROPOSALS