65864 Federal Register / Vol. 81, No. 186 / Monday, September 26, 2016 / Rules and Regulations 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A300–54–0073, 

Revision 03, dated October 11, 2012. 

(ii) Airbus Service Bulletin A300–54–6014, 

Revision 07, dated September 5, 2012. 

(iii) Airbus Service Bulletin A310–54– 

2017, Revision 06, dated October 3, 2012. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(4) You may view this 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 12, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–22460 Filed 9–23–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1068; Directorate 

Identifier 2010–NM–189–AD; Amendment 

39–18647; AD 2016–18–16] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. This AD was prompted by 

fuel system reviews conducted by the 

manufacturer. This AD requires 

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 

(AFM) to advise the flight crew 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. 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. 

DATES: This AD is effective October 31, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 31, 2016. 

ADDRESSES: For Boeing service 

information identified in this final rule, 

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 final rule, 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. It is 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Serj 

Harutunian, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 

562–627–5254; fax: 562–627–5210; 

email: Serj.Harutunian@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 by adding an AD 

that would apply to all The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes. 

The SNPRM published in the Federal 

Register on March 28, 2016 (81 FR 

17098) (‘‘the SNPRM’’). We preceded 

the SNPRM with a notice of proposed 

rulemaking (NPRM) that 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 

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 fuel boost pumps; 

revising the airplane flight manual to 

advise the flight crew 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. The SNPRM proposed to 

require updated or additional actions for 

certain airplane configurations. 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

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Federal Register / Vol. 81, No. 186 / Monday, September 26, 2016 / Rules and Regulations 65865 

received on the SNPRM and the FAA’s 

response to each comment. Boeing 

concurred with the SNPRM. 

Grouping Clarification for Airplanes 

With Removed Airstairs 

Phillippe Akot Azougo, ASLF, 

reported on a discussion with Boeing 

regarding the applicable airplane group 

for an airplane from which the airstair 

has been removed. Boeing indicated that 

if all of the support structure is not 

removed, the airplane is considered in 

the group with airstairs. Based on this 

comment, there is no need to change 

this final rule regarding this issue. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

the installation of winglets per 

Supplemental Type Certificate (STC) 

ST01219SE does not affect the 

accomplishment of the manufacturer’s 

service instructions. 

We agree with the commenter that 

STC ST01219SE does not affect the 

accomplishment of the manufacturer’s 

service instructions. Therefore, the 

installation of STC ST01219SE does not 

affect the ability to accomplish the 

actions required by this AD. We have 

not changed this AD in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

this AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following service 

information: 

The following describe procedures for 

replacing the P5–2 fuel system module 

assembly for Model 737–100, –200, 

–200C, –300, –400, and –500 airplanes. 

• Boeing Alert Service Bulletin 737– 

28A1210, dated August 2, 2010. 

• Boeing Service Bulletin 737– 

28A1210, Revision 1, dated May 13, 

2011. 

• Boeing Service Bulletin 737– 

28A1210, Revision 2, dated October 25, 

2012. 

The following describe procedures for 

installing an automatic shutoff system 

for the center and auxiliary fuel tank 

boost pumps for Model 737–300, –400, 

and –500 airplanes. 

• Boeing Alert Service Bulletin 737– 

28A1216, dated July 29, 2010. 

• Boeing Service Bulletin 737– 

28A1216, Revision 1, dated March 26, 

2012. 

• Boeing Service Bulletin 737– 

28A1216, Revision 2, dated November 

12, 2012. 

• Boeing Service Bulletin 737– 

28A1216, Revision 3, dated July 16, 

2014. 

The following describe 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. 

• Boeing Alert Service Bulletin 737– 

28A1227, dated August 2, 2010. 

• Boeing Alert Service Bulletin 737– 

28A1227, Revision 1, dated July 18, 

2011. 

• Boeing Service Bulletin 737– 

28A1227, Revision 2, dated September 

23, 2014. 

The following describe procedures for 

installing an automatic shutoff system 

for the center and auxiliary fuel tank 

boost pumps for Model 737–100, –200, 

and –200C airplanes. 

• Boeing Alert Service Bulletin 737– 

28A1228, dated August 2, 2010. 

• Boeing Alert Service Bulletin 737– 

28A1228, Revision 1, dated June 28, 

2012. 

• Boeing 737–100/200/200C/300/400/ 

500 Airworthiness Limitations (AWLs) 

and Certification Maintenance 

Requirements (CMRs), Document D6– 

38278–CMR, Revision June 2014, 

contains, among other requirements, 

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. These AWLs provide 

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. 

Costs of Compliance 

We estimate that this AD affects 499 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

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 (499 airplanes) 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 $5,695 1.

Between $3,742 and 

$4,861 1.

Between $6,972 and 

$10,556 1.

Between $3,479,028 

and $5,267,444 1. 

Revise airplane flight manual (499 

airplanes).

1 work-hour × $85 per hour = $85 $0 ............................. $85 ........................... $42,415 

Revise maintenance program (499 

airplanes).

1 work-hour × $85 per hour = $85 $0 ............................. $85 ........................... $42,415 

1 Depending on group. 

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65866 Federal Register / Vol. 81, No. 186 / Monday, September 26, 2016 / Rules and Regulations 

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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2016–18–16 The Boeing Company: 

Amendment 39–18647; Docket No. 

FAA–2011–1068; Directorate Identifier 

2010–NM–189–AD. 

(a) Effective Date 

This AD is effective October 31, 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) (‘‘AD 2001–08–24’’). 

(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. 

(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 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 

Service Bulletin 737–28A1216, Revision 3, 

dated July 16, 2014. For airplanes that do not 

have airstairs: Accomplishment of the actions 

specified in Boeing Alert 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 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, 

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Federal Register / Vol. 81, No. 186 / Monday, September 26, 2016 / Rules and Regulations 65867 

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. 

BILLING CODE 4910–13–P 

(2) Revise Section 3 of the Normal 

Procedures section of the applicable Boeing 

737 AFM 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. 


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65868 Federal Register / Vol. 81, No. 186 / Monday, September 26, 2016 / Rules and Regulations 

BILLING CODE 4910–13–C 

(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. 


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Figure 3 to Paragraph (j)(2) of this AD -Normal fuel usage 

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 ifthe 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 ifthe 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). 
Federal Register / Vol. 81, No. 186 / Monday, September 26, 2016 / Rules and Regulations 65869 

BILLING CODE 4910–13–P 

(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. 


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65870 Federal Register / Vol. 81, No. 186 / Monday, September 26, 2016 / Rules and Regulations 

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., Airworthiness 

Limitations—Systems, of 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., Airworthiness Limitations— 

Systems,’’ of 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– 

AWL–20 of Section C., Airworthiness 

Limitations—Systems, of 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 


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Federal Register / Vol. 81, No. 186 / Monday, September 26, 2016 / Rules and Regulations 65871 

Section C., Airworthiness Limitations— 

Systems, of 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 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 

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 

Boeing Service Bulletin 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 Service 

Bulletin 737–28A1227, Revision 2, dated 

September 23, 2014. 

(2) For airplanes in Group 1, as identified 

in Boeing 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., Airworthiness Limitations— 

Systems, of 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., 

Airworthiness Limitations, of 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, –00, and –500 

series airplanes without Boeing auxiliary fuel 

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

Section C., Airworthiness Limitations— 

Systems, of 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 

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 AWL No. 28–AWL–21 and 

AWL No. 28–AWL–22 for Model 737–100, 

–200, and –200C series airplanes; and AWL 

No. 28–AWL–20 and AWL 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 

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. 

(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 Serj Harutunian, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, Los 

Angeles Aircraft Certification Office (ACO), 

3960 Paramount Boulevard, Lakewood, CA 

90712–4137; phone: 562–627–5254; fax: 562– 

627–5210; email: Serj.Harutunian@faa.gov. 

(2) For BAE Systems service information 

identified in this AD that is not incorporated 

by reference, 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. It 

is also available at the address specified in 

paragraph (t)(5) of this AD. Boeing service 

information identified in this AD that is not 

incorporated by reference is also available at 

the addresses specified in paragraphs (t)(4) 

and (t)(5) of this AD. 

(t) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on October 31, 2016. 

(i) Boeing Alert Service Bulletin 737– 

28A1210, dated August 2, 2010. 

(ii) Boeing Alert Service Bulletin 737– 

28A1216, dated July 29, 2010. 

(iii) Boeing Alert Service Bulletin 737– 

28A1216, Revision 1, dated March 26, 2012. 

(iv) Boeing Alert Service Bulletin 737– 

28A1227, dated August 2, 2010. 

(v) Boeing Alert Service Bulletin 737– 

28A1227, Revision 1, dated July 18, 2011. 

(vi) Boeing Alert Service Bulletin 737– 

28A1228, dated August 2, 2010. 

(vii) Boeing Alert Service Bulletin 737– 

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

(viii) Boeing Service Bulletin 737– 

28A1210, Revision 1, dated May 13, 2011. 

(ix) Boeing Service Bulletin 737–28A1210, 

Revision 2, dated October 25, 2012. 

(x) Boeing Service Bulletin 737–28A1216, 

Revision 2, dated November 12, 2012. 

(xi) Boeing Service Bulletin 737–28A1216, 

Revision 3, dated July 16, 2014. 

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65872 Federal Register / Vol. 81, No. 186 / Monday, September 26, 2016 / Rules and Regulations 

(xii) Boeing Service Bulletin 737–28A1227, 

Revision 2, dated September 23, 2014. 

(xiii) 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 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. 

(5) 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. 

(6) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on August 

25, 2016. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–21602 Filed 9–23–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0935; Directorate 

Identifier 2014–NM–243–AD; Amendment 

39–18652; AD 2016–19–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–200C, 747–200F, 747–300, 747– 

400, 747–400D, 747–400F, 747SR, and 

747SP series airplanes. This AD was 

prompted by several reports of chafing 

of the wire bundles inside the electrical 

conduit of the forward and aft boost 

pumps of the numbers 1 and 4 main fuel 

tanks due to high vibration. These wire 

bundles can chafe through the wire 

sleeving into the insulation, exposing 

the wire conductors. This AD requires 

replacing the wire bundles inside the 

electrical conduit of the forward and aft 

boost pumps of the numbers 1 and 4 

main fuel tanks with new, improved 

wire bundles inserted into conduit 

liners. This AD also requires adding a 

revision to the maintenance or 

inspection program, as applicable, to 

include critical design configuration 

control limitations (CDCCLs) for the fuel 

boost pump wiring. We are issuing this 

AD to prevent chafing of the wire 

bundles and subsequent arcing between 

the wiring and the electrical conduit 

creating an ignition source in the fuel 

tanks, which could result in a fire and 

consequent fuel tank explosion. 

DATES: This AD is effective October 31, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 31, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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. 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0935. 

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–2015– 

0935; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6505; fax: 

425–917–6590; email: tung.tran@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 by adding an AD 

that would apply to certain The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747– 

400D, 747–400F, 747SR, and 747SP 

series airplanes. The SNPRM published 

in the Federal Register on March 8, 

2016 (81 FR 12041) (‘‘the SNPRM’’). We 

preceded the SNPRM with a notice of 

proposed rulemaking (NPRM) that 

published in the Federal Register on 

May 1, 2015 (80 FR 24850) (‘‘the 

NPRM’’). The NPRM proposed to 

require replacing the wire bundles 

inside the electrical conduit of the 

forward and aft boost pumps of the 

numbers 1 and 4 main fuel tanks with 

new, improved wire bundles inserted 

into conduit liners. The NPRM was 

prompted by several reports of chafing 

of the wire bundles inside the electrical 

conduit of the forward and aft boost 

pumps of the numbers 1 and 4 main fuel 

tanks due to high vibration. These wire 

bundles can chafe through the wire 

sleeving into the insulation, exposing 

the wire conductors. The SNPRM 

proposed to require a revision to the 

maintenance or inspection program, as 

applicable, to include CDCCLs for the 

fuel boost pump wiring. We are issuing 

this AD to prevent chafing of the wire 

bundles and subsequent arcing between 

the wiring and the electrical conduit 

creating an ignition source in the fuel 

tanks, which could result in a fire and 

consequent fuel tank explosion. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

The Air Line Pilots Association 

International, Boeing, and United 

Airlines supported the SNPRM. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

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