Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations 78701 

(3) For Bell service information identified 

in this AD, contact Bell Helicopter Textron 

Canada Limited, 12,800 Rue de l’Avenir, 

Mirabel, Quebec J7J1R4, telephone (450) 

437–2862 or (800) 363–8023, fax (450) 433– 

0272, or at http://www.bellcustomer.com/

files/. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on December 

5, 2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–30186 Filed 12–26–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0421; Directorate 

Identifier 2013–NM–003–AD; Amendment 

39–17701; AD 2013–25–05] 

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 737–300, 

–400, and –500 series airplanes. This 

AD was prompted by fuel system 

reviews conducted by the manufacturer. 

This AD requires, depending on 

airplane configuration, replacing fuel 

pump power control relays with new 

relays having a ground fault interrupter 

(GFI) feature, installing ground studs 

and a bonding jumper, doing certain 

bonding resistance measurements, and 

changing the GFI relay position. This 

AD also requires revising the 

maintenance program to incorporate 

certain airworthiness limitations. We 

are issuing this AD to prevent damage 

to the fuel pumps caused by electrical 

arcing that could introduce an ignition 

source in the fuel tank, which, in 

combination with flammable fuel 

vapors, could result in a fuel tank 

explosion and consequent loss of the 

airplane. 

DATES: This AD is effective January 31, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 31, 2014. 

ADDRESSES: For 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. 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; 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: 

Georgios Roussos, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6482; 

fax: 425–917–6590; email: 

georgios.roussos@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on May 16, 2013 (78 FR 28764). 

The NPRM proposed to require, 

depending on airplane configuration, 

replacing fuel pump power control 

relays with new relays having a ground 

fault interrupter (GFI) feature, installing 

ground studs and a bonding jumper, 

doing certain bonding resistance 

measurements, and changing the GFI 

relay position. The NPRM also proposed 

to require revising the maintenance 

program to incorporate certain 

airworthiness limitations. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 28764, 

May 16, 2013) and the FAA’s response 

to each comment. 

Support for the NPRM 

Boeing concurred with the content of 

the proposed rule. 

Request To Include Certain Instructions 

and Delete Certain Step 

All Nippon Airways (ANA) requested 

that we include instructions for the 

removal and installation of certain relay 

sockets, and for removal of paint on the 

mounting panel under Step 5 of Figure 

5 of Boeing Alert Service Bulletin 737– 

28A1212, Revision 2, dated October 18, 

2012. ANA stated that without removal 

of the paint on the mounting panel, the 

required bonding resistance 

measurements cannot be obtained. In 

addition, ANA requested that we delete 

step 6 of Figure 5 of Boeing Alert 

Service Bulletin 737–28A1212, Revision 

2, dated October 18, 2012, which 

describes removal of paint around the 

relay cutout. ANA stated that paint 

removal around the relay cutout is not 

needed since the relay sockets are 

mounted to the cutout area of the panel 

and the relays are a spacer-mounted 

type. 

We disagree with providing 

additional instructions that would 

expand the scope of this final rule, 

requiring additional notice and 

comment. We find that delaying this 

action would be inappropriate in light 

of the urgency of the identified unsafe 

condition. Operators should note that a 

general AMOC, which was requested by 

Boeing on behalf of all operators, has 

been issued for AD 2011–12–09, 

Amendment 39–16716 (76 FR 33988, 

June 10, 2011). The AMOC provides 

essentially the same relief as that 

requested by the commenter. Once this 

final rule is effective, we may issue a 

similar AMOC. Any person may request 

approval of an alternative method of 

compliance (AMOC) under the 

provisions of paragraph (l) of this AD for 

procedures that help them meet the 

bonding resistance requirements. We 

have not changed this final rule 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 


tkelley on DSK3SPTVN1PROD with RULES
78702 Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

28764, May 16, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 28764, 

May 16, 2013). 

Costs of Compliance 

We estimate that this AD affects 14 

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 

Replace fuel pump power control relays, install ground 

studs and a bonding jumper, and do certain bonding 

resistance measurements, and change the GFI relay 

position, depending on airplane configuration.

Up to 31 work-hours × $85 

per hour = $2,635.

Up to $21,338 .. Up to $23,973 .. Up to $335,622. 

Maintenance program revision ......................................... 1 work-hour × $85 per hour 

= $85.

$0 ..................... $85 ................... $1,190. 

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): 

2013–25–05 The Boeing Company: 

Amendment 39–17701; Docket No. 

FAA–2013–0421; Directorate Identifier 

2013–NM–003–AD. 

(a) Effective Date 

This AD is effective January 31, 2014. 

(b) Affected ADs 

Certain requirements of this AD terminate 

certain requirements of AD 2011–12–09, 

Amendment 39–16716 (76 FR 33988, June 

10, 2011). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–300, –400, and –500 series 

airplanes; certificated in any category; 

identified as Groups 5, 6, 7, and 9 in Boeing 

Alert Service Bulletin 737–28A1212, 

Revision 2, dated October 18, 2012. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 2822, Fuel boost pump. 

(e) Unsafe Condition 

This AD was prompted by fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent damage to the 

fuel pumps caused by electrical arcing that 

could introduce an ignition source in the fuel 

tank, which, 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 Ground Studs and Bonding 

Jumper and Fuel Boost Pump Relays 

Replacement 

For airplanes in Groups 5, 6, 7, and 9, 

Configuration 1, as identified in Boeing Alert 

Service Bulletin 737–28A1212, Revision 2, 

dated October 18, 2012 (airplanes on which 

Boeing Alert Service Bulletin 737–28A1212 

was not done): Within 60 months after the 

effective date of this AD, install ground studs 

and a bonding jumper, replace fuel boost 

pump relays, and do certain bonding 

resistance measurements, in accordance with 

Part 1 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–28A1212, 

Revision 2, dated October 18, 2012. Doing the 

actions required by this paragraph terminates 

the requirements of paragraph (g) of AD 

2011–12–09, Amendment 39–16716 (76 FR 

33988, June 10, 2011), for airplanes in 

Groups 5, 6, 7, and 9, Configuration 1 only, 

provided that the requirements of paragraph 

(g) of this AD are done at the time given in 

AD 2011–12–09. 

(h) Ground Studs and Bonding Jumper 

Installation and GFI Relay Position Change 

For airplanes in Groups 5, 6, 7, and 9, 

Configuration 2, as identified in Boeing Alert 

Service Bulletin 737–28A1212, Revision 2, 

dated October 18, 2012 (airplanes on which 

Boeing Alert Service Bulletin 737–28A1212, 

dated July 23, 2009 was done): Within 60 

months after the effective date of this AD, 

install ground studs and a bonding jumper, 

change the GFI relay position, and do certain 

bonding resistance measurements, in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–28A1212, Revision 2, 

dated October 18, 2012. Doing the actions 

required by this paragraph terminates the 

requirements of paragraph (h) of AD 2011– 

12–09, Amendment 39–16716 (76 FR 33988, 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations 78703 

June 10, 2011), for airplanes in Groups 5, 6, 

7, and 9, Configuration 2 only, provided that 

the requirements of paragraph (h) of this AD 

are done at the time given in AD 2011–12– 

09. 

(i) Ground Fault Interrupt (GFI) Relay 

Position Change 

For airplanes in Groups 5, 6, 7, and 9, 

Configuration 3, as identified in Boeing Alert 

Service Bulletin 737–28A1212, Revision 2, 

dated October 18, 2012 (certain airplanes on 

which Boeing Alert Service Bulletin 737– 

28A1212, Revision 1, dated August 27, 2010 

was done): Within 60 months after the 

effective date of this AD, change the GFI 

relay position and do certain bonding 

resistance measurements, in accordance with 

Part 4 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–28A1212, 

Revision 2, dated October 18, 2012. 

(j) Maintenance Program Revision 

Concurrently with accomplishing the 

actions required by paragraph (g), (h), or (i) 

of this AD, or within 30 days after the 

effective date of this AD, whichever occurs 

later: Revise the maintenance program by 

incorporating Airworthiness Limitation 28– 

AWL–22 of Boeing 737–100/200/200C/300/

400/500 AWL and Certification Maintenance 

Requirements (CMRs), Document D6–38278– 

CMR, Revision August 2012. The initial 

compliance time for the actions specified in 

AWL 28–AWL–22 of Boeing 737–100/200/

200C/300/400/500 AWL and Certification 

Maintenance Requirements (CMRs), 

Document D6–38278–CMR, Revision August 

2012, is within 1 year after accomplishing the 

installation required by paragraph (g), (h), or 

(i) of this AD, or within 1 year after the 

effective date of this AD, whichever occurs 

later. 

(k) No Alternative Actions, Intervals, and/or 

Critical Design Configuration Control 

Limitations (CDCCLs) 

After accomplishing the revision required 

by paragraph (j) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (l) of this 

AD. 

(l) 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 (m) 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. 

(m) Related Information 

For more information about this AD, 

contact Georgios Roussos, Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

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

6482; fax: 425–917–6590; email: 

georgios.roussos@faa.gov. 

(n) 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. 

(i) Boeing Alert Service Bulletin 737– 

28A1212, Revision 2, dated October 18, 2012. 

(ii) Airworthiness Limitation 28–AWL–22 

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

AWL and Certification Maintenance 

Requirements (CMRs), Document D6–38278– 

CMR, Revision August 2012. Page 1.0–33, 

where Airworthiness Limitation 28–AWL–22 

is listed, is dated May 2009. 

(3) For 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. 

(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 

December 4, 2013. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–29670 Filed 12–26–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0706; Directorate 

Identifier 2013–NM–067–AD; Amendment 

39–17708; AD 2013–25–12] 

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 DC–9–10, 

DC–9–30, and DC–9–40 series airplanes. 

This AD was prompted by an evaluation 

by the design approval holder (DAH) 

indicating that the aft pressure bulkhead 

web area is subject to widespread 

fatigue damage (WFD). This AD requires 

modifying the aft pressure bulkhead. 

The modification includes inspecting 

for cracks around the rivet holes, and 

repair of any cracking. We are issuing 

this AD to prevent fatigue cracking of 

the aft pressure bulkhead, which could 

result in reduced structural integrity of 

the airplane. 

DATES: This AD is effective January 31, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 31, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, CA 90846–0001; telephone 

206–544–5000, extension 2; fax 206– 

766–5683; 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. 

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–2013– 

0706; 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: Eric 

Schrieber, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

CA 90712–4137; phone: (562) 627–5348; 

fax: (562) 627–5210; email: 

eric.schrieber@faa.gov. 

SUPPLEMENTARY INFORMATION: 


tkelley on DSK3SPTVN1PROD with RULES