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

45743 

Vol. 82, No. 189 

Monday, October 2, 2017 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0814; Product 

Identifier 2017–NM–066–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 adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–600, 

–700, –700C, –800, –900, and –900ER 

series airplanes. This proposed AD was 

prompted by significant changes made 

to the airworthiness limitations (AWL) 

related to fuel tank ignition prevention 

and the nitrogen generation system. 

This proposed AD would require 

revision of the maintenance or 

inspection program, as applicable, to 

include the latest revision of the AWLs. 

We are proposing this AD to address the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by November 16, 

2017. 

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.myboeing

fleet.com. You may view this service 

information at the FAA, Transport 

Standards Branch, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

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–2017– 

0814; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Tak 

Kobayashi, Aerospace Engineer, 

Propulsion Section, FAA, Seattle ACO 

Branch, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6499; 

fax: 425–917–6590; email: 

takahisa.kobayashi@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– 

2017–0814; Product Identifier 2017– 

NM–066–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 NPRM. 

Discussion 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a final rule titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, that 

rule included Amendment 21–78, 

which established Special Federal 

Aviation Regulation No. 88 (‘‘SFAR 88’’) 

at 14 CFR part 21. Subsequently, SFAR 

88 was amended by: Amendment 21–82 

(67 FR 57490, September 10, 2002; 

corrected at 67 FR 70809, November 26, 

2002) and Amendment 21–83 (67 FR 

72830, December 9, 2002; corrected at 

68 FR 37735, June 25, 2003, to change 

‘‘21–82’’ to ‘‘21–83’’). 

Among other actions, SFAR 88 

requires certain type design (i.e., type 

certificate (TC) and supplemental type 

certificate (STC)) holders to substantiate 

that their fuel tank systems can prevent 

ignition sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the final rule published on May 7, 

2001, we intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, we 

have established four criteria intended 

to define the unsafe conditions 

associated with fuel tank systems that 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

Single failures, single failures in 

combination with another latent 


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condition(s), and in-service failure 

experience. For all four criteria, the 

evaluations included consideration of 

previous actions taken that may mitigate 

the need for further action. 

We issued AD 2008–10–10 R1, 

Amendment 39–16164 (75 FR 1529, 

January 12, 2010) (‘‘AD 2008–10–10 

R1’’), which applies to certain The 

Boeing Company Model 737–600, –700, 

–700C, –800, and –900 series airplanes. 

AD 2008–10–10 R1 requires 

incorporation of fuel system AWLs and 

also requires an initial inspection to 

phase in certain repetitive inspections, 

and repair if necessary. The fuel system 

AWLs were developed to satisfy SFAR 

88 requirements and included in the 

Airworthiness Limitations Section 

(ALS) of the manufacturer’s Instructions 

for Continued Airworthiness. Since we 

issued AD 2008–10–10 R1, the ALS has 

been significantly revised by the 

manufacturer to correct technical and 

editorial errors and also to add new 

requirements. Those changes affect the 

fuel system and nitrogen generation 

system AWLs. We have determined that 

the specific revisions of the ALS 

mandated by AD 2008–10–10 R1, and 

the revisions of the ALS that have been 

delivered with airplanes as part of the 

type design and airworthiness 

certificate, on or after March 31, 2006 

(see paragraph (c), ‘‘Applicability,’’ of 

AD 2008–10–10 R1, which applied to 

airplanes with an original standard 

airworthiness certificate or original 

export certificate of airworthiness 

issued before March 31, 2006), are 

inadequate to provide information 

necessary to maintain critical design 

features and perform inspections. 

We propose to adopt this new AD to 

require revising the maintenance or 

inspection program, as applicable, to 

incorporate the AWLs provided in 

Boeing 737–600/700/700C/800/900/ 

900ER Special Compliance Items/ 

Airworthiness Limitations, dated 

January 2017 (the latest revision of the 

ALS). We are proposing this AD to 

prevent the potential for ignition 

sources inside the fuel tanks and also to 

prevent increasing the flammability 

exposure of the center fuel tank caused 

by latent failures, alterations, repairs, or 

maintenance actions, which could result 

in a fuel tank explosion and consequent 

loss of an airplane. 

We have determined that 

accomplishing the revision required by 

paragraph (g) of this proposed AD 

would terminate the following 

requirements for that airplane: 

• All requirements of AD 2008–10–10 

R1. 

• The revision required by paragraphs 

(h) and (h)(1) of AD 2008–06–03, 

Amendment 39–15415 (73 FR 13081, 

March 12, 2008). 

• The revision required by paragraph 

(g) of AD 2008–17–15, Amendment 39– 

15653 (73 FR 50714, August 28, 2008). 

• The revision required by paragraph 

(k) of AD 2011–18–03, Amendment 39– 

16785 (76 FR 53317, August 26, 2011). 

• All requirements of AD 2013–15– 

17, Amendment 39–17533 (78 FR 

52838, August 27, 2013). 

Airworthiness Limitations Based on 

Type Design 

The FAA recently became aware of an 

issue related to the applicability of ADs 

that require incorporation of the 

Airworthiness Limitations section (ALS) 

of the Instructions for Continued 

Airworthiness (ICA) into an operator’s 

maintenance or inspection program. 

U.S. operators must operate their 

airplanes in an airworthy condition, in 

accordance with 14 CFR 91.7(a). 

Included in this obligation is the 

requirement to perform any 

maintenance or inspections specified in 

the ALS, and in accordance with the 

ALS as specified in 14 CFR 43.16 and 

91.403(c), unless an alternative has been 

approved by the FAA. 

When a type certificate is issued for 

a type design, the specific ALS, 

including its revision level, is part of 

that type design, as specified in 14 CFR 

21.31(c). 

The sum effect of these operational 

and maintenance requirements is an 

obligation to comply with the ALS 

revision defined in the type design 

referenced in the manufacturer’s 

conformity statement. This obligation 

may introduce a conflict with an AD if 

the AD requires a specific ALS revision 

for new airplanes that are delivered 

with a later ALS revision as part of their 

type design. 

The FAA has approved alternative 

methods of compliance (AMOCs) that 

allow operators to incorporate the most 

recent ALS revision into their 

maintenance/inspection programs, in 

lieu of the ALS revision required by the 

AD. This enables the operator to comply 

with both the AD and the type design. 

However, compliance with AMOCs is 

normally optional, and we recently 

became aware that some operators 

choose to retain the AD-mandated ALS 

revision in their fleet-wide 

maintenance/inspection programs, 

including those for new airplanes 

delivered with later ALS revisions, to 

help standardize the maintenance of the 

fleet. To ensure that operators comply 

with the applicable ALS revision for 

newly delivered airplanes containing a 

later revision than that specified in an 

AD, we plan to mandate the latest ALS 

revision as of the effective date of an 

AD, if we are to mandate a specific ALS 

revision, and limit the applicability to 

those airplanes delivered on or before 

the effective date of that AD. 

This proposed AD therefore mandates 

the latest ALS revision as of the 

effective date of the AD for Model 737– 

600, –700, –700C, –800, –900, and 

–900ER series airplanes with an original 

certificate of airworthiness or original 

export certificate of airworthiness that 

was issued on or before the effective 

date of the AD. Operators of airplanes 

with an original certificate of 

airworthiness or original export 

certificate of airworthiness issued after 

that date must comply with the 

airworthiness limitations specified as 

part of the approved type design. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing 737–600/700/ 

700C/800/900/900ER Special 

Compliance Items/Airworthiness 

Limitations, D626A001–9–04, dated 

January 2017. This service information 

describes AWLs that include 

airworthiness limitation instructions 

(ALI) and critical design configuration 

control limitations (CDCCL) tasks 

related to fuel tank ignition prevention 

and the nitrogen generation system. 

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. 

Proposed AD Requirements 

This proposed AD would require 

revisions to 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 (k) of this proposed AD. The 

request should include a description of 

changes to the required inspections that 

will ensure the continued operational 

safety of the airplane. 


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Notwithstanding any other 

maintenance or operational 

requirements, components that have 

been identified as airworthy or installed 

on the affected airplanes before 

accomplishing the revision of the 

airplane maintenance or inspection 

program specified in this proposed AD 

do not need to be reworked in 

accordance with the latest revision of 

the CDCCLs specified by this proposed 

AD for incorporation. However, once 

the airplane maintenance or inspection 

program has been revised as required by 

this proposed AD, future maintenance 

actions on these components must be 

done in accordance with the CDCCLs 

specified by this proposed AD. 

Differences With the Service 

Information 

The ‘‘description’’ column of AWL 

No. 28–AWL–20 identifies certain 

operational tests. However, airplanes on 

which the actions specified in 

paragraph (g)(2)(ii) of AD 2011–20–07 

have been done are not required to do 

the operational test for left center tank 

fuel boost pump relay R54 and right 

center tank fuel boost pump relay R55. 

Paragraph (g) of this proposed AD 

would require operators to revise their 

maintenance or inspection program by 

incorporating, in part, AWL No. 28– 

AWL–05, ‘‘Wire Separation 

Requirements for New Wiring Installed 

in Proximity to Wiring That Goes Into 

the Fuel Tanks’’ in Boeing 737–600/700/ 

700C/800/900/900ER Special 

Compliance Items/Airworthiness 

Limitations, D626A001–9–04, dated 

January 2017. Paragraph (h) of this 

proposed AD would allow certain 

changes to be made to the requirements 

specified in AWL No. 28–AWL–05 as an 

option. 

Clarification of the Service Information 

The ‘‘applicability’’ column of AWL 

No. 28–AWL–19 identifies affected 

airplanes. For airplanes on which the 

actions specified in paragraph (s) of AD 

2011–18–03 have been done, 

incorporation of Boeing Service Bulletin 

737–28A1206 is not required. Therefore, 

those airplanes are not affected by AWL 

No. 28–AWL–19 and are not required to 

do the functional test. 

The ‘‘applicability’’ column of AWL 

No. 28–AWL–23 identifies affected 

airplanes. For airplanes on which the 

actions specified in paragraph (s) of AD 

2011–18–03 have been done, 

incorporation of Boeing Service Bulletin 

737–28A1248 is not required. Therefore, 

those airplanes are not affected by AWL 

No. 28–AWL–23 and are not required to 

do the functional test. 

Alternative Methods of Compliance 

(AMOC) Previously Approved for 

Compliance With AD 2008–10–10 R1 

The FAA has previously issued 

AMOC approvals for compliance with 

paragraph (g)(3) of AD 2008–10–10 R1 

to allow operators to incorporate 

alternative versions of AWL No. 28– 

AWL–05. AWL No. 28–AWL–05 

includes the requirements for new 

wiring introduced by any alterations or 

changes to the type design, including 

STC modifications, in proximity to 

wiring that penetrates the fuel tank wall. 

Certain STCs that introduced new 

wiring near the fuel quantity indicating 

system (FQIS) wiring utilized design 

features that were different from the 

critical design features for fuel tank 

ignition prevention specified in the ADmandated version of AWL No. 28– 

AWL–05. For those STCs, we have 

approved alternative versions of AWL 

No. 28–AWL–05 that specified critical 

design features associated with STC 

modifications. We have determined that 

certain critical design features specified 

in the AMOC-approved versions of 

AWL No. 28–AWL–05 are not 

acceptable to meet the intent of this 

AWL. Therefore, this proposed AD does 

not allow credit for AMOCs previously 

approved under AD 2008–10–10 R1. 

However, based on our assessment of 

critical design features, we have 

provided an optional action under 

paragraph (h) of this proposed AD to 

allow certain changes to be made to the 

requirements specified in AWL No. 28– 

AWL–05. Under this optional action, 

certain critical design features we have 

previously approved and consider to be 

acceptable can be specified in AWL No. 

28–AWL–05. 

The requirements for new wiring 

versus existing wiring are specified in 

AWL No. 28–AWL–05. Based on these 

requirements, any STC modifications 

that are installed after the incorporation 

of AWL No. 28–AWL–05 (version 

required by paragraph (g) of this AD) 

must comply with AWL No. 28–AWL– 

05, including any mandatory rework, or 

the operator must request approval of an 

AMOC according to paragraph (k) of this 

proposed AD. Any STC modifications 

that are installed prior to the 

incorporation of AWL No. 28–AWL–05 

(version required by paragraph (g) of 

this AD) are not required to be reworked 

for compliance with the new wiring 

requirements of AWL No. 28–AWL–05, 

except that future repair and 

replacement of existing wiring must 

follow AWL No. 28–AWL–05. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,417 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 

Revising the maintenance or inspection program.1 work-hour × $85 per hour = $85 ................. $0 $85 $120,445 

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 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 


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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– 

2017–0814; Product Identifier 2017– 

NM–066–AD. 

(a) Comments Due Date 

We must receive comments by November 

16, 2017. 

(b) Affected ADs 

This AD affects the ADs specified in 

paragraphs (b)(1) through (b)(5) of this AD. 

(1) AD 2008–06–03, Amendment 39–15415 

(73 FR 13081, March 12, 2008) (‘‘AD 2008– 

06–03’’). 

(2) AD 2008–10–10 R1, Amendment 39– 

16164 (75 FR 1529, January 12, 2010) (‘‘AD 

2008–10–10 R1’’). 

(3) AD 2008–17–15, Amendment 39–15653 

(73 FR 50714, August 28, 2008) (‘‘AD 2008– 

17–15’’). 

(4) AD 2011–18–03, Amendment 39–16785 

(76 FR 53317, August 26, 2011) (‘‘AD 2011– 

18–03’’). 

(5) AD 2013–15–17, Amendment 39–17533 

(78 FR 52838, August 27, 2013) (‘‘AD 2013– 

15–17’’). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–600, –700, –700C, –800, –900, 

and –900ER series airplanes, certificated in 

any category, with an original standard 

airworthiness certificate or original export 

certificate of airworthiness issued on or 

before the effective date of this AD. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by significant 

changes made to airworthiness limitations 

(AWL) related to fuel tank ignition 

prevention and the nitrogen generation 

system. We are issuing this AD to prevent the 

development of an ignition source inside the 

fuel tanks and also to prevent increasing the 

flammability exposure of the center fuel tank, 

which could lead to fuel tank explosion and 

consequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision of Maintenance or Inspection 

Program 

Within 60 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate the 

information in Section A, including 

Subsections A.1, A.2, and A.3, of Boeing 

737–600/700/700C/800/900/900ER Special 

Compliance Items/Airworthiness 

Limitations, D626A001–9–04, dated January 

2017; except as provided by paragraph (h) of 

this AD. The initial compliance times for the 

airworthiness limitation instructions (ALI) 

tasks are within the applicable compliance 

times specified in paragraphs (g)(1) through 

(g)(11) of this AD: 

(1) For AWL No. 28–AWL–01, ‘‘External 

Wires Over Center Fuel Tank’’: Within 120 

months after the date of issuance of the 

original standard airworthiness certificate or 

the date of issuance of the original export 

certificate of airworthiness, or within 120 

months after the most recent inspection was 

performed as specified in AWL No. 28– 

AWL–01, whichever is later. 

(2) For AWL No. 28–AWL–03, ‘‘Fuel 

Quantity Indicating System (FQIS)—Out 

Tank Wiring Lightning Shield to Ground 

Termination’’: Within 120 months after the 

date of issuance of the original standard 

airworthiness certificate or the date of 

issuance of the original export certificate of 

airworthiness, or within 120 months after the 

most recent inspection was performed as 

specified in AWL No. 28–AWL–03, 

whichever is later. 

(3) For AWL No. 28–AWL–19, ‘‘Center 

Tank Fuel Boost Pump Automatic Shutoff 

System’’: Within 12 months after the date of 

issuance of the original standard 

airworthiness certificate or the date of 

issuance of the original export certificate of 

airworthiness, within 12 months after 

accomplishment of the actions specified in 

Boeing Service Bulletin 737–28A1206, or 

within 12 months after the most recent 

inspection was performed as specified in 

AWL No. 28–AWL–19, whichever is latest. 

This AWL does not apply to airplanes that 

have complied with paragraph (s) of AD 

2011–18–03. 

(4) For AWL No. 28–AWL–20, ‘‘OverCurrent and Arcing Protection Electrical 

Design Features Operation—Boost Pump 

Ground Fault Interrupter (GFI)’’: Within 12 

months after the date of issuance of the 

original standard airworthiness certificate or 

the date of issuance of the original export 

certificate of airworthiness, within 12 months 

after accomplishment of the actions specified 

in Boeing Service Bulletin 737–28A1201, or 

within 12 months after the most recent 

inspection was performed as specified in 

AWL No. 28–AWL–20, whichever is latest. 

For airplanes that have complied with 

paragraph (g)(2)(ii) of AD 2011–20–07, the 

operational test for left center tank fuel boost 

pump relay R54 and right center tank fuel 

boost pump relay R55 does not apply. 

(5) For AWL No. 28–AWL–23, ‘‘Center 

Tank Fuel Boost Pump Power Failed On 

Protection System’’: Within 12 months after 

the date of issuance of the original standard 

airworthiness certificate or the date of 

issuance of the original export certificate of 

airworthiness, within 12 months after 

accomplishment of the actions specified in 

Boeing Service Bulletin 737–28A1248, or 

within 12 months after the most recent 

inspection was performed as specified in 

AWL No. 28–AWL–23, whichever is latest. 

This AWL does not apply to airplanes that 

have complied with paragraph (s) of AD 

2011–18–03. 

(6) For AWL No. 28–AWL–24, ‘‘Spar Valve 

Motor Operated Valve (MOV) Actuator— 

Lightning and Fault Current Protection 

Electrical Bond’’: Within 72 months after 

accomplishment of the actions specified in 

Boeing Service Bulletin 737–28A1207, or 

within 72 months after the most recent 

inspection was performed as specified in 

AWL No. 28–AWL–24, whichever is later. 

(7) For AWL No. 28–AWL–29, ‘‘Full 

Cushion Clamps and Teflon Sleeving (If 

Installed) Installed on Out-of-Tank Wire 

Bundles Installed on Brackets that are 

Mounted Directly on the Fuel Tanks’’: For 

airplanes having line numbers (L/N) 1 

through 1754 inclusive, within 120 months 

after accomplishment of the actions specified 

in Boeing Service Bulletin 737–57A1279. For 

airplanes having L/N 1755 and on, within 

120 months after the date of issuance of the 

original standard airworthiness certificate or 

the date of issuance of the original export 

certificate of airworthiness, or within 24 

months after the effective date of this AD, 

whichever is later. 

(8) For AWL No. 47–AWL–04, ‘‘Nitrogen 

Generation System—Thermal Switch’’: 

Within 22,500 flight hours after the date of 


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issuance of the original standard 

airworthiness certificate or the date of 

issuance of the original export certificate of 

airworthiness, within 22,500 flight hours 

after accomplishment of the actions specified 

in Boeing Service Bulletin 737–47–1003, or 

within 22,500 flight hours after the most 

recent inspection was performed as specified 

in AWL No. 47–AWL–04, whichever is latest. 

(9) For AWL No. 47–AWL–06, ‘‘Nitrogen 

Generation System (NGS)—Cross Vent Check 

Valve’’: Within 13,000 flight hours after the 

date of issuance of the original standard 

airworthiness certificate or the date of 

issuance of the original export certificate of 

airworthiness, within 13,000 flight hours 

after accomplishment of the actions specified 

in Boeing Service Bulletin 737–47–1003, or 

within 13,000 flight hours after the most 

recent inspection was performed as specified 

in AWL No. 47–AWL–06, whichever is latest. 

(10) For AWL No. 47–AWL–07, ‘‘Nitrogen 

Generation System (NGS)—Nitrogen 

Enriched Air (NEA) Distribution Ducting 

Integrity’’: Within 6,500 flight hours after the 

date of issuance of the original standard 

airworthiness certificate or the date of 

issuance of the original export certificate of 

airworthiness, within 6,500 flight hours after 

accomplishment of the actions specified in 

Boeing Service Bulletin 737–47–1003, or 

within 6,500 flight hours after the most 

recent inspection was performed as specified 

in AWL No. 47–AWL–07, whichever is latest. 

(11) For AWL No. 28–AWL–101, ‘‘Engine 

Fuel Suction Feed Operational Test’’: Within 

7,500 flight hours or 36 months, whichever 

occurs first, after the date of issuance of the 

original airworthiness certificate or the date 

of issuance of the original export certificate 

of airworthiness; or within 7,500 flight hours 

or 36 months, whichever occurs first, after 

the most recent inspection was performed as 

specified in AWL No. 28–AWL–101; 

whichever is later. 

(h) Exceptions to Service Information 

As an option, when accomplishing the 

actions required by paragraph (g) of this AD, 

the changes specified in paragraphs (h)(1) 

and (h)(2) of this AD can be made to AWL 

No. 28–AWL–05. 

(1) Where AWL No. 28–AWL–05 identifies 

wire types BMS 13–48, BMS 13–58, and BMS 

13–60, add the following acceptable wire 

types: MIL–W–22759/16, MIL–W–22759/32, 

MIL–W–22759/34, MIL–W–22759/41, MIL– 

W–22759/86, MIL–W–22759/87, and MIL– 

W–22759/92; and MIL–C–27500 cables 

constructed from these wire types. 

(2) Where AWL No. 28–AWL–05 identifies 

TFE–2X Standard wall for wire sleeving, add 

the following acceptable sleeving materials: 

Roundit 2000NX and Varglas Type HO, HP, 

or HM. 

(i) No Alternative Actions, Intervals, and 

Critical Design Configuration Control 

Limitations (CDCCLs) 

After the maintenance or inspection 

program, as applicable, has been revised as 

required by paragraph (g) of this AD, no 

alternative actions (e.g., inspections), 

intervals, and CDCCLs may be used unless 

the actions, intervals, and CDCCLs are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

(j) Terminating Actions 

Accomplishment of the revision required 

by paragraph (g) of this AD terminates the 

requirements specified in paragraphs (j)(1) 

through (j)(5) of this AD for that airplane: 

(1) The revision required by paragraphs (h) 

and (h)(1) of AD 2008–06–03. 

(2) All requirements of AD 2008–10–10 R1. 

(3) The revision required by paragraph (g) 

of AD 2008–17–15. 

(4) The revision required by paragraph (k) 

of AD 2011–18–03; and 

(5) All requirements of AD 2013–15–17. 

(k) 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 (l)(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, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact Tak Kobayashi, Aerospace Engineer, 

Propulsion Section, FAA, Seattle ACO 

Branch, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6499; fax: 425– 

917–6590; email: takahisa.kobayashi@

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, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

September 14, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–20560 Filed 9–29–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2017–0822; Airspace 

Docket No. 17–AEA–10] 

Proposed Revocation of Class E 

Airspace; Centerville, MD 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

remove Class E airspace extending 

upward from 700 feet above the surface 

at Centerville, MD. Because the 

Maryland State Police Trooper 6 

Heliport has moved, controlled airspace 

is no longer required at this location. 

Another rulemaking will be forthcoming 

establishing controlled airspace at the 

heliport’s new location. 

DATES: Comments must be received on 

or before November 16, 2017. 

ADDRESSES: Send comments on this rule 

to: U.S. Department of Transportation, 

Docket Operations, 1200 New Jersey 

Avenue SE., West Bldg. Ground Floor, 

Rm. W12–140, Washington, DC 20590; 

Telephone: 1–800–647–5527, or (202) 

366–9826.You must identify the Docket 

No. FAA–2017–0822; Airspace Docket 

No. 17–AEA–10, at the beginning of 

your comments. You may also submit 

and review received comments through 

the Internet at http://

www.regulations.gov. You may review 

the public docket containing the 

proposal, any comments received, and 

any final disposition in person in the 

Dockets Office between 9:00 a.m. and 

5:00 p.m., Monday through Friday, 

except federal holidays. 

FAA Order 7400.11B, Airspace 

Designations and Reporting Points, and 

subsequent amendments can be viewed 

online at http://www.faa.gov/air_traffic/ 

publications/. For further information, 

you can contact the Airspace Policy 

Group, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone: (202) 267–8783. The Order is 

also available for inspection at the 

National Archives and Records 

Administration (NARA). For 


sradovich on DSK3GMQ082PROD with PROPOSALS