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

17098 

Vol. 81, No. 59 

Monday, March 28, 2016 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1068; Directorate 

Identifier 2010–NM–189–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for all Boeing Model 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. The NPRM proposed to 

require installing an automatic shutoff 

system for the center and auxiliary tank 

fuel boost pumps, as applicable; 

installing a placard in the airplane flight 

deck if necessary; replacing the P5–2 

fuel system module assembly; installing 

the ‘‘uncommanded ON’’ (UCO) 

protection system for the fuel boost 

pumps; revising the airplane flight 

manual to advise the flightcrew of 

certain operating restrictions for 

airplanes equipped with an automatic 

shutoff system; and revising the 

maintenance program by incorporating 

new airworthiness limitations for fuel 

tank systems to satisfy Special Federal 

Aviation Regulation No. 88 

requirements. The NPRM was prompted 

by fuel system reviews conducted by the 

manufacturer. This action revises the 

NPRM by proposing to require updated 

or additional actions that are necessary 

for certain airplane configurations. We 

are proposing this supplemental NPRM 

(SNPRM) to prevent operation of the 

center and auxiliary tank fuel boost 

pumps with continuous low pressure, 

which could lead to friction sparks or 

overheating in the fuel pump inlet that 

could create a potential ignition source 

inside the center and auxiliary fuel 

tanks. These conditions, in combination 

with flammable fuel vapors, could result 

in a fuel tank explosion and consequent 

loss of the airplane. Since these actions 

impose an additional burden over that 

proposed in the NPRM, we are 

reopening the comment period to allow 

the public the chance to comment on 

these proposed changes. 

DATES: We must receive comments on 

this SNPRM by May 12, 2016. 

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 Boeing service information 

identified in this SNPRM, contact 

Boeing Commercial Airplanes, 

Attention: Data & Services Management, 

P.O. Box 3707, MC 2H–65, Seattle, WA 

98124–2207; telephone: 206–544–5000, 

extension 1; fax: 206–766–5680; Internet 

https://www.myboeingfleet.com. 

For BAE Systems service information 

identified in this SNPRM, contact BAE 

Systems, Attention: Commercial 

Product Support, 600 Main Street, Room 

S18C, Johnson City, NY 13790–1806; 

phone: 607–770–3084; fax: 607–770– 

3015; email: CS-Customer.Service@

baesystems.com; Internet: http://

www.baesystems-ps.com/customer

support. 

You may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. The 

referenced Boeing service bulletins are 

also available on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2011– 

1068. 

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–2011– 

1068; 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 proposed AD, 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: 

Christopher Baker, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6498; 

fax: 425–917–6590; email: 

Christopher.R.Baker@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–1068; Directorate Identifier 

2010–NM–189–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD 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 an NPRM to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Boeing Model 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes. The NPRM published 

in the Federal Register on October 12, 

2011 (76 FR 63229) (‘‘the NPRM’’). The 

NPRM proposed to require installing an 

automatic shutoff system for the center 

and auxiliary tank fuel boost pumps, as 


Lhorne on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / Proposed Rules 17099 

applicable; installing a placard in the 

airplane flight deck if necessary; 

replacing the P5–2 fuel system module 

assembly; installing the UCO protection 

system for the center and auxiliary tank 

fuel boost pumps, as applicable; 

revising the airplane flight manual to 

advise the flightcrew of certain 

operating restrictions for airplanes 

equipped with an automatic shutoff 

system; and revising the maintenance 

program by incorporating new 

airworthiness limitations for fuel tank 

systems to satisfy Special Federal 

Aviation Regulation No. 88 

requirements. 

Actions Since the NPRM Was Issued 

Since we issued the NPRM, we 

learned of certain inadequacies in the 

referenced service information. Boeing 

has since developed, and we have 

approved, revised service information. 

We have determined it is necessary to 

mandate the revised service 

information, which includes additional 

actions necessary for airplanes in 

certain configurations. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 737–28A1210, dated August 2, 

2010; Revision 1, dated May 13, 2011; 

and Revision 2, dated October 25, 2012. 

The service information describes 

procedures for replacing the P5-2 fuel 

system module assembly for Model 

737–100, –200, –200C, –300, –400, and 

–500 airplanes. 

We reviewed Boeing Alert Service 

Bulletin 737–28A1216, dated July 29, 

2010; Revision 1, dated March 26, 2012; 

Revision 2, dated November 12, 2012; 

and Revision 3, dated July 16, 2014. The 

service information describes 

procedures for installing an automatic 

shutoff system for the center and 

auxiliary fuel tank boost pumps for 

Model 737–300, –400, and –500 

airplanes. 

We reviewed Boeing Alert Service 

Bulletin 737–28A1227, dated August 2, 

2010; Revision 1, dated July 18, 2011; 

and Revision 2, dated September 23, 

2014. The service information describes 

procedures for installing a UCO 

protection system for the center and 

auxiliary fuel boost pumps for Model 

737–100, –200, –200C, –300, –400, and 

–500 airplanes. 

We reviewed Boeing Alert Service 

Bulletin 737–28A1228, dated August 2, 

2010; and Revision 1, dated June 28, 

2012. The service information describes 

procedures for installing an automatic 

shutoff system for the center and 

auxiliary fuel tank boost pumps for 

Model 737–100, –200, and –200C 

airplanes. 

We also reviewed Section C, ‘‘Fuel 

Systems Airworthiness Limitations,’’ of 

Section 9 of the Boeing 737–100/200/

200C/300/400/500 Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs), 

Document D6–38278–CMR, Revision 

June 2014, contains AWLs 28–AWL–21, 

28–AWL–22, 28–AWL–24, and 28– 

AWL–25 for Model 737–100, –200, and 

–200C airplanes, and AWLs 28–AWL– 

20, 28–AWL–21, 28–AWL–23, and 28– 

AWL–24 for Model 737–300, –400, and 

–500 airplanes, which are airworthiness 

limitation instructions for an 

operational check of the installed 

automatic shutoff 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. 

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. The Air Line Pilots 

Association, International, submitted its 

support for the NPRM. 

Request To Match Compliance Times 

Japan Transocean Air requested that 

we revise paragraphs (g) and (h) of the 

proposed AD to extend the compliance 

time from 36 months to 60 months to 

match the compliance time specified in 

paragraph (m) of the proposed AD (in 

the NPRM). The commenter noted that 

the service information specified in 

paragraph (m) of the proposed AD (in 

the NPRM) recommends the concurrent 

accomplishment of the actions specified 

in paragraph (g)(3) of the proposed AD. 

The commenter asserted that requiring 

the same compliance time (60 months) 

for paragraphs (g), (h), and (m) of the 

proposed AD (in the NPRM) would 

prevent complications associated with 

different configurations. 

We disagree that it is necessary to 

revise the compliance time as requested. 

We infer that the commenter has 

assumed that all of those actions must 

be done at the same maintenance visit. 

As the commenter stated, the 

‘‘concurrent’’ actions (in paragraph 

(g)(3) of this proposed AD) are to be 

done ‘‘before or at the same time as’’ the 

actions required by paragraph (m) of 

this proposed AD. We have determined 

that the compliance time for the actions 

specified in paragraphs (g) and (h) of 

this proposed AD is necessary to ensure 

an adequate level of safety. We have 

further determined that doing the 

actions required by paragraph (m) of 

this proposed AD later than the actions 

specified in paragraphs (g)(3) of this 

proposed AD would not affect safety, 

and would not affect the airplane 

configuration in a way that would 

complicate accomplishment of the 

proposed AD requirements for the fleet. 

In light of the identified unsafe 

condition, the proposed requirements, 

and the manufacturer’s 

recommendations, we have determined 

that no change to this proposed AD is 

warranted regarding this issue. 

Request To Require Two Placards 

Japan Transocean Air requested that 

we revise paragraph (i) of the proposed 

AD (in the NPRM) to require the 

installation of two placards, instead of 

one, adjacent to the primary flight 

displays. The commenter stated that 

both pilots operate the fuel pumps, and 

placards are therefore necessary for both 

pilots’ primary flight displays. 

We partially agree with the request. 

The intent of this SNPRM is to ensure 

that the placard is visible to both pilots. 

Although we have determined that two 

placards are not necessary to achieve 

that goal, operators may choose to 

install an additional placard or use a 

different location, if approved by an 

appropriate FAA principal operations 

inspector. We have revised paragraph (i) 

of this proposed AD to specify these 

options. 

Request To Correct Service Information 

Specifications 

Boeing requested certain corrections 

to the referenced service information. 

Since that comment was submitted, 

Boeing has included these corrections in 

the revised service information that is 

referenced in this SNPRM. Therefore, no 

additional change to this SNPRM is 

necessary. 

FAA’s Determination 

We are proposing this SNPRM 

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 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 


Lhorne on DSK5TPTVN1PROD with PROPOSALS
17100 Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / Proposed Rules 

‘‘Differences Between this AD and the 

Service Information.’’ 

Differences Between This Proposed AD 

and the Service Information 

Where service information referenced 

in this proposed AD specifies that 

certain operators may contact the 

manufacturer for modification 

instructions, this proposed AD would 

require those operators to do the 

modification in one of the following 

ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Boeing Alert Service Bulletin 737– 

28A1216, Revision 3, dated July 16, 

2014, specifies a 24-month compliance 

time to accomplish the actions specified 

in that service information. However, 

paragraph (g) of this proposed AD 

would require accomplishing the 

actions specified in that service 

information within 36 months. We have 

determined this compliance time will 

provide an acceptable level of safety. 

We have coordinated this difference 

with Boeing. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 499 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 

Install auto shutoff protection for 

Model 737–100, –200, –200C 

airplanes (82 airplanes).

Between 92 and 155 work-hours 

× $85 per hours = Between 

$7,820 and $13,175 1.

Between $10,792 and 

$15,548 1.

Between $18,612 and 

$28,723 1.

Between $1,526,184 

and $2,355,286.1

Install auto shutoff protection for 

Model 737–300, –400, and 

–500 airplanes (417 airplanes).

Between 92 and 152 work-hours 

× $85 per hours = Between 

$7,820 and $12,920 1.

Between $9,869 and 

$16,236 1.

Between $17,689 and 

$29,156 1.

Between $7,376,313 

and $12,158,052.1

Install P5–2 module ................... 1 work-hour × $85 per hour = 

$85.

$0 ................................ $85 .............................. $42,415. 

Install UCO protection (499 airplanes).Between 38 and 67 work-hours 

× $85 per hours = Between 

$3,230 and $5,6951.

Between $3,742 and 

$4,861 1.

Between $6,972 and 

$10,556 1.

Between $3,479,028 

and $5,267,444.1

Revise aircraft flight manual ...... 1 work-hour × $85 per hour = 

$85.

$0 ................................ $85 .............................. $42,415. 

Revise Maintenance Program ... 1 work-hour × $85 per hour = 

$85.

$0 ................................ $85 .............................. $42,415. 

1 Depending on group. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

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– 

2011–1068; Directorate Identifier 2010– 

NM–189–AD. 

(a) Comments Due Date 

We must receive comments by May 12, 

2016. 

(b) Affected ADs 

Certain requirements of this AD terminate 

certain requirements of AD 2001–08–24, 

Amendment 39–12201 (66 FR 20733, April 

25, 2001). 

(c) Applicability 

This AD affects all The Boeing Company 

Model 737–100, –200, –200C, –300, –400, 

and –500 series airplanes; certificated in any 

category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 


Lhorne on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / Proposed Rules 17101 

(e) Unsafe Condition 

This AD was prompted by fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent operation of 

the center and auxiliary tank fuel boost 

pumps with continuous low pressure, which 

could lead to friction sparks or overheating 

in the fuel pump inlet that could create a 

potential ignition source inside the center 

and auxiliary fuel tanks. These conditions, in 

combination with flammable fuel vapors, 

could result in a fuel tank explosion and 

consequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation of Automatic Shutoff System 

for the Center and Auxiliary Tank Fuel 

Boost Pumps 

Within 36 months after the effective date 

of this AD, do the applicable actions 

specified in paragraph (g)(1), (g)(2), or (g)(3) 

of this AD. If a placard has been previously 

installed on an airplane, in accordance with 

the requirements of paragraph (i) of this AD, 

the placard may be removed from the flight 

deck of only that airplane after the automatic 

shutoff system has been installed, as 

specified in paragraph (g)(1), (g)(2), or (g)(3) 

of this AD, as applicable. 

(1) For Model 737–100, –200, and –200C 

series airplanes, in Groups 2 through 19, as 

identified in Boeing Alert Service Bulletin 

737–28A1228, Revision 1, dated June 28, 

2012: Install the automatic shutoff system for 

the center and auxiliary fuel tank boost 

pumps, as applicable, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–28A1228, Revision 1, 

dated June 28, 2012. For airplanes that do not 

have airstairs, accomplishment of the actions 

specified in Boeing Alert Service Bulletin 

737–28A1228, dated August 2, 2010, is 

acceptable for compliance with the 

requirements of this paragraph, provided 

markers are installed on the J2802 Box for 

‘‘POS 1’’ and ‘‘POS 2’’ within 90 days after 

the effective date of this AD, in accordance 

with Boeing Alert Service Bulletin 737– 

28A1228, Revision 1, dated June 28, 2012. 

(2) For Model 737–100, –200, and –200C 

series airplanes in Group 1, as identified in 

Boeing Alert Service Bulletin 737–28A1228, 

Revision 1, dated June 28, 2012: Install the 

automatic shutoff system for the center and 

auxiliary fuel tank boost pumps, as 

applicable, using a method approved in 

accordance with the procedures specified in 

paragraph (r) of this AD. 

(3) For Model 737–300, –400, and –500 

series airplanes in Groups 1 through 31, as 

identified in Boeing Alert Service Bulletin 

737–28A1216, Revision 3, dated July 16, 

2014: Install the automatic shutoff system for 

the center and auxiliary fuel tank boost 

pumps, as applicable, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–28A1216, Revision 3, 

dated July 16, 2014. For airplanes that do not 

have airstairs: Accomplishment of the actions 

specified in Boeing Service Bulletin 737– 

28A1216, dated July 29, 2010, is acceptable 

for compliance with the requirements of this 

paragraph, provided markers are installed on 

the J2802 Box for ‘‘POS 1’’ and ‘‘POS 2’’ 

within 90 days after the effective date of this 

AD, in accordance with Boeing Alert Service 

Bulletin 737–28A1216, Revision 1, dated 

March 26, 2012; or Boeing Alert Service 

Bulletin 737–28A1216, Revision 2, dated 

November 12, 2012. 

(h) Concurrent Installation of P5–2 Fuel 

System Module Assembly 

Before or concurrently with 

accomplishment of the actions required by 

paragraph (g) of this AD, do the actions 

specified in paragraph (h)(1) or (h)(2) of this 

AD, as applicable. Accomplishment of the 

actions specified in Boeing Alert Service 

Bulletin 737–28A1210, dated August 2, 2010, 

or Boeing Service Bulletin 737–28A1210, 

Revision 1, dated May 13, 2011, is acceptable 

for compliance with the requirements of 

paragraph (h)(1) of this AD, provided that for 

any original P5–2 Fuel System Module P/N 

69–37335–129 installed that has been 

reworked as specified in BAE Systems 

Service Bulletin 69–37335–28–04, Revision 

2, dated February 10, 2010, the P/N marking 

is etched/scribed or labeled as P/N 69– 

37335–2129, within 90 days after the 

effective date of this AD. 

(1) For airplanes in Group 2, as identified 

in Boeing Service Bulletin 737–28A1210, 

Revision 2, dated October 25, 2012: Replace 

the P5–2 fuel system module assembly with 

a modified or new P5–2 fuel system module 

assembly having a new part number, in 

accordance with Boeing Service Bulletin 

737–28A1210, Revision 2, dated October 25, 

2012. 

Note 1 to paragraph (h)(1) of this AD: 

Boeing Service Bulletin 737–28A1210, 

Revision 2, dated October 25, 2012, refers to 

BAE Systems Service Bulletin 69–37335–28– 

04 as an additional source of guidance for 

modifying and updating the existing P5–2 

fuel system module assembly part numbers. 

(2) For airplanes in Group 1, as identified 

in Boeing Service Bulletin 737–28A1210, 

Revision 2, dated October 25, 2012, replace 

the P5–2 fuel system module assembly, as 

applicable, using a method approved in 

accordance with the procedures specified in 

paragraph (r) of this AD. 

(i) Concurrent Installation of a Placard for 

Mixed Fleet Operation 

Concurrently with accomplishment of the 

actions required by paragraph (g) of this AD, 

install a placard adjacent to the pilot’s 

primary flight display on all airplanes in the 

operator’s fleet not equipped with an 

automatic shutoff system for the center and 

auxiliary tank fuel boost pumps, as 

applicable. The placard must include the 

statement in figure 1 to paragraph (i) of this 

AD. Optionally, the placard may include 

alternative text or be installed in a different 

location, or an additional placard may be 

installed, if approved by an appropriate FAA 

principal operations inspector. Installing an 

automatic shutoff system on an airplane, in 

accordance with the requirements of 

paragraph (g) of this AD, terminates the 

placard installation required by this 

paragraph for only that airplane. 

(j) Airplane Flight Manual (AFM) Revisions 

for Airplanes Without Boeing Auxiliary Fuel 

Tanks 

For airplanes without Boeing auxiliary fuel 

tanks: Concurrently with accomplishment of 

the actions required by paragraph (g) of this 

AD, do the actions specified in paragraphs 

(j)(1) and (j)(2) of this AD. 

(1) Revise Section 1 of the Limitations 

section of the applicable Boeing 737 AFM to 

include the statement in figure 2 to paragraph 

(j)(1) of this AD. This may be done by 

inserting a copy of this AD into the AFM. 

When a statement identical to that in figure 

2 to paragraph (j)(1) of this AD has been 

included in the general revisions of the 

applicable Boeing 737 AFM, the general 

revisions may be inserted into the AFM, and 

the copy of this AD may be removed from the 

AFM. 


Lhorne on DSK5TPTVN1PROD with PROPOSALSEP28MR16.016</GPH>
17102 Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / Proposed Rules 

(2) Revise Section 3 of the Normal 

Procedures section of the applicable Boeing 

737 AFM to include to include the text 

specified in figure 3 to paragraph (j)(2) of this 

AD. This may be done by inserting a copy of 

this AD into the AFM. Alternative statements 

that meet the intent of the following 

requirements may be used if approved by an 

appropriate FAA principal operations 

inspector. 

BILLING CODE 4910–13–P 


Lhorne on DSK5TPTVN1PROD with PROPOSALSEP28MR16.017</GPH>
Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / Proposed Rules 17103 

(k) AFM Revisions for Airplanes With 

Boeing Auxiliary Fuel Tanks 

For airplanes with Boeing auxiliary fuel 

tanks: Concurrently with accomplishment of 

the actions required by paragraph (g) of this 

AD, do the actions specified in paragraphs 

(k)(1) and (k)(2) of this AD. 

(1) Revise Section 1 of the Limitations 

section of the applicable Boeing 737 AFM to 

include the text specified in figure 4 to 

paragraph (k)(1) of this AD. This may be done 

by inserting a copy of this AD into the AFM. 

When a statement identical to that in figure 

4 to paragraph (k)(1) of this AD has been 

included in the general revisions of the 

applicable Boeing 737 AFM, the general 

revisions may be inserted into the AFM, and 

the copy of this AD may be removed from the 

AFM. 


Lhorne on DSK5TPTVN1PROD with PROPOSALSEP28MR16.018</GPH>

Figure 3 to paragraph G)(2) of this AD 

NORMAL FUEL USAGE 

Center tank fuel pumps must not be "ON" unless personnel 

are available in the flight deck to monitor low pressure 

lights. 

For ground operation, center tank fuel pump switches must 

not be positioned "ON" unless the center tank fuel quantity 

exceeds 1,000 pounds (453 kilograms), except when 

defueling or transferring fuel. Upon positioning the center 

tank fuel pump switches "ON," verify momentary 

illumination of each center tank fuel pump low pressure 

light. 

For ground and flight operations, the corresponding center 

tank fuel pump switch must be positioned "OFF" when a 

center tank fuel pump low pressure light illuminates [1]. 

Both center tank fuel pump switches must be positioned 

"OFF" when the first center tank fuel pump low pressure 

light illuminates if the center tank is empty. 

[1] When established in a level flight attitude, both center 

tank pump switches should be positioned "ON" again if the 

center tank contains usable fuel. 

DEFUELING AND FUEL TRANSFER 

When transferring fuel or defueling center or main tanks, 

the fuel pump low pressure lights must be monitored and 

the fuel pumps positioned to "OFF" at the first indication of 

the fuel pump low pressure [1]. 

Defueling the main tanks with passengers on board is 

prohibited if the main tank fuel pumps are powered [2]. 

Defueling the center tank with passengers on board is 

prohibited if the center tank fuel pumps are powered and the 

auto-shutoff system is inhibited [2]. 

[1] Prior to transferring fuel or defueling, conduct a lamp 

test of the respective fuel pump low pressure lights. 

[2] Fuel may be transferred from tank to tank or the aircraft 

may be defueled with passengers on board, provided fuel 

quantity in the tank from which fuel is being taken is 

maintained at or above 2,000 pounds (907 kilograms). 
17104 Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / Proposed Rules 

(2) Revise Section 3 of the Normal 

Procedures section of the applicable Boeing 

737 AFM to include the text specified in 

figure 5 to paragraph (k)(2) of this AD. This 

may be done by inserting a copy of this AD 

into the AFM. Alternative statements that 

meet the intent of the following requirements 

may be used if approved by an appropriate 

FAA principal operations inspector. 


Lhorne on DSK5TPTVN1PROD with PROPOSALSEP28MR16.019</GPH>
Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / Proposed Rules 17105 

BILLING CODE 4910–13–C 

(l) Airworthiness Limitations (AWLs) 

Revision for Automatic Shutoff System 

Concurrently with accomplishment of the 

actions required by paragraph (g) of this AD, 

or within 30 days after the effective date of 

this AD, whichever occurs later: Revise the 

maintenance program by incorporating the 

AWLs specified in paragraphs (l)(1), (l)(2), 

(l)(3), and (l)(4) of this AD, as applicable. The 

initial compliance time for the actions 

specified in the applicable AWLs is within 1 

year after accomplishment of the installation 

required by paragraph (g) of this AD, or 

within 1 year after the effective date of this 

AD, whichever occurs later. 

(1) For Model 737–100, –200, and –200C 

series airplanes without Boeing auxiliary fuel 

tanks installed: Incorporate AWL No. 28– 

AWL–21 of Section C, ‘‘Fuel Systems 

Airworthiness Limitations,’’ of Section 9 of 

the Boeing 737–100/200/200C/300/400/500 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), Document D6–38278–CMR, Revision 

June 2014. 

(2) For Model 737–100, –200, and –200C 

series airplanes with Boeing auxiliary fuel 

tanks installed: Incorporate AWL No. 28– 

AWL–21 and AWL No. 28–AWL–22 of 

Section C, ‘‘Fuel Systems Airworthiness 

Limitations,’’ of Section 9 of the Boeing 737– 

100/200/200C/300/400/500 Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs), 

Document D6–38278–CMR, Revision June 

2014. 

(3) For Model 737–300, –400, and –500 

series airplanes without Boeing auxiliary fuel 

tanks installed: Incorporate AWL No. 28– 


Lhorne on DSK5TPTVN1PROD with PROPOSALSEP28MR16.020</GPH>
17106 Federal Register / Vol. 81, No. 59 / Monday, March 28, 2016 / Proposed Rules 

AWL–20 of Section C, ‘‘Fuel Systems 

Airworthiness Limitations,’’ of Section 9 of 

the Boeing 737–100/200/200C/300/400/500 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), Document D6–38278–CMR, Revision 

June 2014. 

(4) For Model 737–300, –400, and –500 

series airplanes with Boeing auxiliary fuel 

tanks installed: Incorporate AWL No. 28– 

AWL–20 and AWL No. 28–AWL–21 of 

Section C, ‘‘Fuel Systems Airworthiness 

Limitations,’’ of Section 9 of the Boeing 737– 

100/200/200C/300/400/500 Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs), 

Document D6–38278–CMR, Revision June 

2014. 

(m) Installation of Un-Commanded ON 

(UCO) Protection System 

Within 60 months after the effective date 

of this AD, do the actions required by 

paragraph (m)(1) or (m)(2) of this AD, as 

applicable. 

(1) For airplanes in Groups 2 through 13, 

as identified in Boeing Alert Service Bulletin 

737–28A1227, Revision 2, dated September 

23, 2014: Install the UCO protection system 

for the center and auxiliary tank fuel boost 

pumps, as applicable, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–28A1227, Revision 2, 

dated September 23, 2014. For airplanes with 

enlarged J2802 box assembly relay cutouts to 

fit the body of relays R3334, R3336, R3338, 

or R3340, with BACS12HN08–10 screws for 

the installation of the relays as specified in 

Information Notice 737–28A1227 IN 05: 

Accomplishment of the actions specified in 

Boeing Alert Service Bulletin 737–28A1227, 

dated August 2, 2010, or Revision 1, dated 

July 18, 2011, is acceptable for compliance 

with the requirements of this paragraph, 

provided markers are installed that identify 

the function of the switches installed on the 

J2802 box within 90 days after the effective 

date of this AD, in accordance with figure 1 

or figure 5, as applicable, of Boeing Alert 

Service Bulletin 737–28A1227, Revision 2, 

dated September 23, 2014. 

(2) For airplanes in Group 1, as identified 

in Boeing Alert Service Bulletin 737– 

28A1227, Revision 2, dated September 23, 

2014: Install the UCO protection system for 

the center and auxiliary tank fuel boost 

pumps, as applicable, using a method 

approved in accordance with the procedures 

specified in paragraph (r) of this AD. 

(n) AWLs Revision for UCO Protection 

System 

Concurrently with accomplishment of the 

actions required by paragraph (m) of this AD, 

or within 30 days after the effective date of 

this AD, whichever occurs later: Revise the 

maintenance program by incorporating the 

AWLs specified in paragraphs (n)(1), (n)(2), 

(n)(3), and (n)(4) of this AD, as applicable. 

The initial compliance time for the actions 

specified in applicable AWLs is within 1 year 

after accomplishment of the installation 

required by paragraph (m) of this AD, or 

within 1 year after the effective date of this 

AD, whichever occurs later. 

(1) For Model 737–100, –200, and –200C 

series airplanes without Boeing auxiliary fuel 

tanks: Incorporate AWL No. 28–AWL–24 of 

Section C, ‘‘Fuel Systems Airworthiness 

Limitations,’’ of Section 9 of the Boeing 737– 

100/200/200C/300/400/500 Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs), 

Document D6–38278–CMR, Revision June 

2014. 

(2) For Model 737–100, –200, and –200C 

series airplanes with Boeing auxiliary fuel 

tanks: Incorporate AWL No. 28–AWL–24 and 

AWL No. 28–AWL–25 of Section C, ‘‘Fuel 

Systems Airworthiness Limitations,’’ of 

Section 9 of the Boeing 737–100/200/200C/ 

300/400/500 Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs), Document D6–38278– 

CMR, Revision June 2014. 

(3) For Model 737–300, –400, and –500 

series airplanes without Boeing auxiliary fuel 

tanks: Incorporate AWL No. 28–AWL–23 of 

Section C, ‘‘Fuel Systems Airworthiness 

Limitations,’’ of Section 9 of the Boeing 737– 

100/200/200C/300/400/500 Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs), 

Document D6–38278–CMR, Revision June 

2014. 

(4) For Model 737–300, –400, and –500 

series airplanes with Boeing auxiliary fuel 

tanks: Incorporate AWL No. 28–AWL–23 and 

AWL No. 28–AWL–24 of Section C, ‘‘Fuel 

Systems Airworthiness Limitations,’’ of 

Section 9 of the Boeing 737–100/200/200C/ 

300/400/500 Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs), Document D6–38278– 

CMR, Revision June 2014. 

(o) No Alternative Inspections or Inspection 

Intervals 

After accomplishment of the applicable 

actions specified in paragraphs (l) and (n) of 

this AD, no alternative inspections or 

inspection intervals may be used unless the 

inspections or inspection intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (r) of this 

AD. 

(p) Method of Compliance for Paragraph (l) 

of This AD 

Incorporating AWLs No. 28–AWL–21 and 

No. 28–AWL–22 for Model 737–100, –200, 

and –200C series airplanes; and AWLs No. 

28–AWL–20 and No. 28–AWL–21 for Model 

737–300, –400, and –500 series airplanes; in 

accordance with paragraphs (g)(1) and (g)(2) 

of AD 2008–10–09 R1, Amendment 39–16148 

(74 FR 69264, December 31, 2009), is 

acceptable for compliance with the 

corresponding AWL incorporation required 

by paragraph (l) of this AD. 

(q) Method of Compliance for Paragraph (a) 

of AD 2001–08–24, Amendment 39–12201 

(66 FR 20733, April 25, 2001) 

Accomplishment of the actions required by 

paragraphs (g), (h), (i), and (l) of this AD, and 

paragraph (j) or (k) of this AD as applicable, 

is an acceptable method of compliance with 

the requirements of paragraph (a) of AD 

2001–08–24, Amendment 39–12201 (66 FR 

20733, April 25, 2001). 

(r) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (s)(1) of this AD. Information may 

be emailed to 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(s) Related Information 

(1) For more information about this AD, 

contact Christopher Baker, Aerospace 

Engineer, Propulsion Branch, ANM–140S, 

FAA, Seattle ACO, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6498; fax: 425–917–6590; email: 

Christopher.R.Baker@faa.gov. 

(2) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone: 

206–544–5000, extension 1; fax: 206–766– 

5680; Internet https://

www.myboeingfleet.com. For BAE Systems 

service information identified in this AD, 

contact BAE Systems, Attention: Commercial 

Product Support, 600 Main Street, Room 

S18C, Johnson City, NY 13790–1806; phone: 

607–770–3084; fax: 607–770–3015; email: 

CS-Customer.Service@baesystems.com; 

Internet: http://www.baesystems-ps.com/

customersupport. You may view this 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on February 

25, 2016. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–04966 Filed 3–25–16; 8:45 am] 

BILLING CODE 4910–13–P 


Lhorne on DSK5TPTVN1PROD with PROPOSALS