46666 Federal Register / Vol. 83, No. 179 / Friday, September 14, 2018 / Proposed Rules 

(e) Unsafe Condition 

This AD was prompted by a report of two 

fan disks found with surface rollovers in the 

dovetail slot area. We are issuing this AD to 

prevent uncontained failure of the fan disks. 

The unsafe condition, if not addressed, could 

result in uncontained fan disk release, 

damage to the engine, and damage to the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Remove the affected fan disk using the 

following criteria: 

(1) Remove fan disks with 9,000 cyclessince-new (CSN) or more as of the effective 

date of this AD, within 100 cycles-in-service 

(CIS), or at the next engine shop visit, or at 

next access, whichever occurs first, after the 

effective date of this AD. 

(2) Remove fan disks with between 8,000 

and 8,999 CSN, inclusive, as of the effective 

date of this AD, within 9,100 CSN or within 

1,000 CIS, or at the next engine shop visit, 

or at next access, whichever occurs first, after 

the effective date of this AD. 

(3) Remove fan disks with fewer than 8,000 

CSN as of the effective date of this AD, before 

exceeding 9,000 CSN, or at the next engine 

shop visit, or at next access, whichever 

occurs first, after the effective date of this 

AD. 

(4) Replace any removed fan disk with a 

part eligible for installation. 

(h) Installation Prohibition 

Do not install an affected fan disk, P/N 

3060267–2, unless ‘‘T43374’’ is marked 

adjacent to the engine P/N or S/N. 

(i) Definitions 

(1) For the purposes of this AD, an ‘‘engine 

shop visit’’ is defined as the removal of the 

tie-shaft nut from the engine. 

(2) For the purposes of this AD, ‘‘access’’ 

is defined as the removal of the fan rotor 

assembly from the engine. 

(3) For the purposes of this AD, a ‘‘part 

eligible for installation’’ is: 

(i) a fan disk not listed in the 

Accomplishment Instructions, Table 9, in 

Honeywell SB TFE731–72–5256, Revision 0, 

dated October 7, 2016; or 

(ii) a fan disk listed in Table 9, in 

Honeywell SB TFE731–72–5256, Revision 0, 

dated October 7, 2016, that has been 

inspected, reworked, and marked with 

‘‘T43374’’ adjacent to the P/N or S/N. 

Guidance on returning affected parts to 

Honeywell for inspection and rework is 

found in the Accomplishment Instructions, 

paragraph 3.D., of Honeywell SB TFE731– 

72–5256, Revision 0, dated October 7, 2016. 

(j) Alternative Methods of Compliance 

(AMOCs) 

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

this AD. 

(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. 

(k) Related Information 

(1) For more information about this AD, 

contact Joseph Costa, Los Angeles ACO 

Branch, FAA, 3960 Paramount Boulevard, 

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

627–5246; fax: 562–627–5210; email: 

joseph.costa@faa.gov. 

(2) For service information identified in 

this AD, contact Honeywell International 

Inc., 111 S. 34th Street, Phoenix, AZ, 85034– 

2802; phone: 800–601–3099 (Toll Free 

U.S.A./Canada); phone: 602–365–3099 

(International Direct); website: 

www.myaerospace.com; email: 

engine.reliability@honeywell.com. You may 

view this referenced service information at 

the FAA, Engine and Propeller Standards 

Branch, 1200 District Avenue, Burlington, 

MA, 01803. For information on the 

availability of this material at the FAA, call 

781–238–7759. 

Issued in Burlington, Massachusetts, on 

September 6, 2018. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2018–19798 Filed 9–13–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9189; Product 

Identifier 2016–NM–114–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (SNPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposal for certain The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series 

airplanes. This action revises the notice 

of proposed rulemaking (NPRM) by 

adding airplanes to the applicability and 

adding a measurement of the distance 

between the hooks of the torsion spring 

of the lanyard assembly. We are 

proposing this airworthiness directive 

(AD) to address the unsafe condition on 

these products. Since these actions 

would impose an additional burden 

over those in the NPRM, we are 

reopening the comment period to allow 

the public the chance to comment on 

these changes. 

DATES: The comment period for the 

NPRM published in the Federal 

Register on October 13, 2016 (81 FR 

70647), is reopened. 

We must receive comments on this 

SNPRM by October 29, 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: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590, 

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

through Friday, except Federal holidays. 

For service information identified in 

this SNPRM, 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– 

9189. 

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– 

9189; 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 SNPRM, 

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: 

Scott Craig, Aerospace Engineer, Cabin 


daltland on DSKBBV9HB2PROD with PROPOSALS
Federal Register / Vol. 83, No. 179 / Friday, September 14, 2018 / Proposed Rules 46667 

Safety and Environmental Systems 

Section, FAA, Seattle ACO Branch, 2200 

South 216th St., Des Moines, WA 98198; 

phone and fax: 206–231–3566; email: 

michael.s.craig@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– 

2016–9189; Product Identifier 2016– 

NM–114–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this SNPRM. We will 

consider all comments received by the 

closing date and may amend this 

SNPRM 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 SNPRM. 

Discussion 

We issued an NPRM to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 737–600, –700, –700C, –800, 

–900, and –900ER series airplanes. The 

NPRM published in the Federal 

Register on October 13, 2016 (81 FR 

70647). The NPRM was prompted by 

reports of passenger service units (PSUs) 

becoming detached from the supporting 

airplane structure in several Model 737 

airplanes during survivable accidents. 

The NPRM proposed to require 

modifying the PSUs and life vest panels 

by replacing the existing inboard 

lanyard and installing two new lanyards 

on the outboard edge of the PSUs and 

life vest panels. 

Actions Since the NPRM Was Issued 

Since we issued the NPRM, we have 

determined that additional airplanes are 

subject to the unsafe condition. In 

addition, we have determined that the 

torsion spring of a certain lanyard 

assembly may be manufactured 

incorrectly and have an inadequate 

distance between the hooks of the 

torsion spring. Since the discrepant 

torsion springs may have been installed 

in production, as well as on airplanes 

modified in accordance with Boeing 

Service Bulletin 737–25–1707, dated 

September 24, 2015, we have 

determined that it is necessary to 

measure the distance between the hooks 

of the torsion spring of the lanyard 

assembly and replace discrepant 

lanyard assemblies. 

Comments 

We gave the public the opportunity to 

comment on the NPRM. The following 

presents the comments received on the 

NPRM and the FAA’s response to each 

comment. 

Support for the NPRM 

The National Transportation Safety 

Board (NTSB) and commenter London 

Smith expressed their support for the 

NPRM. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

the installation of winglets per 

Supplemental Type Certificate (STC) 

ST00830SE does not affect the 

accomplishment of the manufacturer’s 

service instructions. 

We agree with the commenter that 

STC ST00830SE does not affect the 

accomplishment of the manufacturer’s 

service instructions. Therefore, the 

installation of STC ST00830SE does not 

affect the ability to accomplish the 

actions that would be required by this 

SNPRM. We have not changed this 

SNPRM in this regard. 

Request To Extend the Compliance 

Time 

Japan Airlines (JAL) and American 

Airlines (AA) requested that the 

compliance time in paragraph (g) of the 

proposed AD be extended from 60 

months to 84 months. JAL suggested 

that, due to Boeing’s manufacturing 

schedule for the kits, Boeing might not 

manufacture an adequate number of kits 

within the proposed compliance time. 

AA stated that extending the 

compliance time would allow operators 

to perform the modification during 

regularly scheduled heavy maintenance 

checks, thereby reducing the financial 

burden on operators. 

We disagree with the requests. In 

developing an appropriate compliance 

time for this action, we considered the 

urgency of the unsafe condition along 

with the practical aspect of 

accomplishing the required 

modification at a time corresponding to 

the normal scheduled maintenance for 

most operators. According to the 

manufacturer, an adequate number of 

modification kits will be available to 

modify the affected fleet within the 

proposed compliance time. However, 

under the provisions of paragraph (i) of 

this SNPRM, we will consider requests 

for approval of an extension of the 

compliance time if sufficient data are 

submitted to substantiate that the new 

compliance time would provide an 

acceptable level of safety. We have not 

changed this SNPRM in this regard. 

Request To Clarify Service Information 

Requirements 

AA requested that we clarify that data 

notes (b) and (d) to Figure 1 of Boeing 

Service Bulletin 737–25–1707, dated 

September 24, 2015, can be complied 

with in accordance with an operator’s 

procedures. AA noted paragraph 

3.B.1.b. of the Accomplishment 

Instructions of Boeing Service Bulletin 

737–25–1707, dated September 24, 

2015, which requires the installation of 

new lanyards in accordance with Figure 

1 of the service information, is a 

Required for Compliance (RC) step. AA 

added that data notes (b) and (d) to 

Figure 1 of Boeing Service Bulletin 737– 

25–1707, dated September 24, 2015, 

provide latitude when the operator has 

an accepted alternative procedure by 

using the term ‘‘refer to.’’ 

We agree to clarify that the operator 

is allowed latitude in accomplishing 

work steps that use the term ‘‘refer to.’’ 

If a step is marked RC and a procedure 

or document may be followed to 

accomplish an action (e.g., the design 

approval holder’s procedure or 

document may be used, but an FAAaccepted procedure could also be used), 

the appropriate terminology to use to 

cite the procedure or document is ‘‘refer 

to . . . as an accepted procedure.’’ We 

have not changed this SNPRM in this 

regard. 

Request To Add Airplanes to the 

Applicability 

United Airlines (UAL) noted that the 

proposed AD did not refer to the PSUs 

on Model 757–200 and –300 airplanes, 

which can have the same part numbers 

as the airplanes addressed by the 

proposed AD. UAL stated that operators 

who operate both of these fleet types 

need to review the risk of having both 

pre- and post-AD parts in their 

inventory. UAL added that they will 

mitigate the risk of potential parts 

intermingling by modifying their Model 

757–200 and –300 airplanes with the 

same PSU modification. 

We infer that UAL requests that 

Model 757–200 and –300 series 

airplanes should be included in the 

applicability of this proposed AD. We 

agree to investigate whether a similar 

unsafe condition exists on Model 757– 

200 and –300 series airplanes. We will 

take appropriate action based on the 

result of that investigation. However, 

delaying this SNPRM in order to 

determine if Model 757 airplanes 

should be added to the applicability 

would be inappropriate given that we 


daltland on DSKBBV9HB2PROD with PROPOSALS
46668 Federal Register / Vol. 83, No. 179 / Friday, September 14, 2018 / Proposed Rules 

have determined that an unsafe 

condition exists and that the 

modifications must be done to ensure 

continued safety. We have not changed 

this SNPRM in this regard. 

Request To Change Text To Match the 

Service Information 

Boeing requested that we change 

wording in the proposed AD that 

discusses ‘‘. . . removing the existing 

lanyard and installing two new 

lanyards. . .’’ to instead read ‘‘. . . 

replacing the existing lanyard and 

installing two new lanyards. . . .’’ 

Boeing stated that the proposed text 

more accurately describes the 

modification required by the service 

bulletin. 

We agree with the request. We have 

updated the wording of the applicable 

sentence in the Discussion and Related 

Service Information under 1 CFR part 51 

sections of this SNPRM. 

Request To Clarify Language Describing 

What Prompted the AD 

Boeing requested that the word 

‘‘incidents’’ be changed to ‘‘accidents’’ 

in language describing what prompted 

the proposed AD. Boeing noted that the 

events in which PSUs became detached 

were accidents, not incidents, as 

defined by the NTSB and International 

Civil Aviation Organization (ICAO) 

Annex 13. 

We agree to make this change, which 

will more accurately define these events 

according to industry standards. We 

have updated the Discussion section 

and paragraph (e) of this SNPRM to 

reflect this change. 

Request To Refer to New Service 

Information 

Boeing requested that we update the 

proposed AD to refer to Boeing Service 

Bulletin 737–25–1707, Revision 1, dated 

May 18, 2018, which was recently 

released. Boeing stated that the service 

bulletin would be revised to include the 

737NG Boeing Business Jet (BBJ) aircraft 

effectivity blocks, which were omitted 

in the original revision of the service 

bulletin. 

We agree with the commenter’s 

request. Boeing Service Bulletin 737– 

25–1707, Revision 1, dated May 18, 

2018, adds airplanes to the effectivity, 

adds a new measurement of the torsion 

spring of the lanyard assembly, and 

clarifies the instructions for attaching 

the lanyard assembly torsion spring to 

the PSU rail. For these reasons, we have 

updated this SNPRM to refer to Boeing 

Service Bulletin 737–25–1707, Revision 

1, dated May 18, 2018. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Service Bulletin 

737–25–1707, Revision 1, dated May 18, 

2018. This service information describes 

procedures for modifying the PSUs and 

life vest panels by replacing the existing 

inboard lanyard and installing two new 

lanyards on the outboard edge of the 

PSUs and life vest panels, measuring the 

distance between the hooks of the 

torsion spring of the lanyard assembly, 

replacing any discrepant lanyard 

assemblies, and re-identifying 

serviceable lanyard assemblies. 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 the same 

type design. Certain changes described 

above expand the scope of the NPRM. 

As a result, we have determined that it 

is necessary to reopen the comment 

period to provide additional 

opportunity for the public to comment 

on this SNPRM. 

Proposed Requirements of This SNPRM 

This SNPRM would require 

accomplishment of the actions 

identified as ‘‘RC’’ (required for 

compliance) in the Accomplishment 

Instructions of Boeing Service Bulletin 

737–25–1707, Revision 1, dated May 18, 

2018, described previously, except as 

discussed under ‘‘Differences Between 

this SNPRM and the Service 

Information,’’ and except for any 

differences identified as exceptions in 

the regulatory text of this proposed AD. 

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–2016– 

9189. 

Differences Between This SNPRM and 

the Service Information 

The effectivity of Boeing Service 

Bulletin 737–25–1707, Revision 1, dated 

May 18, 2018, is limited to Model 737– 

600, –700, –700C, –800, –900, and 

–900ER series airplanes, line numbers 1 

through 6009, without a Boeing Sky 

Interior (BSI). However, the 

applicability of this proposed AD 

includes all Boeing Model 737–600, 

–700, –700C, –800, –900, and –900ER 

series airplanes without a BSI. Because 

the affected lanyard assemblies are 

rotable parts, we have determined that 

these parts could later be installed on 

airplanes that were initially delivered 

with acceptable lanyard assemblies, 

thereby subjecting those airplanes to the 

unsafe condition. This difference has 

been coordinated with Boeing. 

Costs of Compliance 

We estimate that this proposed AD 

affects 2,015 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 

Inspection and modification ................. Up to 75 work-hours × $85 per hour = 

Up to $6,375.

Up to $11,760 ....... Up to $18,135 ....... Up to $36,542,025 

According to the manufacturer, some 

or all of the costs of this proposed AD 

may be covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all known 

costs in our cost estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 


daltland on DSKBBV9HB2PROD with PROPOSALS
Federal Register / Vol. 83, No. 179 / Friday, September 14, 2018 / Proposed Rules 46669 

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 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 to the Director of the 

System Oversight Division. 

Regulatory Findings 

We 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 this 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 adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2016–9189; Product Identifier 2016– 

NM–114–AD. 

(a) Comments Due Date 

We must receive comments by October 29, 

2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 737–600, –700, –700C, 

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

certificated in any category, without a Boeing 

Sky Interior (BSI). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/furnishings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

passenger service units (PSUs) becoming 

detached from the supporting airplane 

structure in several Model 737 series 

airplanes during survivable accidents. We are 

issuing this AD to address PSUs and life vest 

panels detaching from the supporting 

airplane structure, which could lead to 

passenger injuries and impede passenger and 

crew egress during evacuation. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Within 60 months after the effective date 

of this AD, do all applicable actions 

identified as ‘‘RC’’ (required for compliance) 

in, and in accordance with, the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–25–1707, Revision 1, 

dated May 18, 2018. 

(h) Parts Installation Prohibition 

As of the applicable time specified in 

paragraph (h)(1) or (h)(2) of this AD, no 

person may install on any airplane a PSU or 

life vest panel, unless the lanyard assembly 

has been updated as required by paragraph 

(g) of this AD. 

(1) For airplanes that have PSUs or life vest 

panels without the updated lanyard 

assemblies installed: After modification of 

the airplane as required by this AD. 

(2) For airplanes that have PSUs or life vest 

panels with the updated lanyard assemblies 

installed: As of the effective date of this AD. 

(i) 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 (j)(1) of 

this AD. Information may be emailed to: 9- 

ANM-Seattle-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 (i)(4)(i) and (i)(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. 

(j) Related Information 

(1) For more information about this AD, 

contact Scott Craig, Aerospace Engineer, 

Cabin Safety and Environmental Systems 

Section, FAA, Seattle ACO Branch, 2200 

South 216th St., Des Moines, WA 98198; 

phone and fax: 206–231–3566; email: 

michael.s.craig@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 

August 29, 2018. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2018–19838 Filed 9–13–18; 8:45 am] 

BILLING CODE 4910–13–P 


daltland on DSKBBV9HB2PROD with PROPOSALS