72554 Federal Register / Vol. 78, No. 232 / Tuesday, December 3, 2013 / Rules and Regulations 

Issued in Burlington, Massachusetts, on 

November 14, 2013. 

Frank P. Paskiewicz, 

Acting Director, Aircraft Certification Service. 

[FR Doc. 2013–28293 Filed 12–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1313; Directorate 

Identifier 2012–NM–080–AD; Amendment 

39–17651; AD 2013–22–19] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace Corporation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Gulfstream Aerospace Corporation 

Model GV and GV–SP airplanes. This 

AD was prompted by reports of two 

independent types of failure of the fuel 

boost pump with overheat damage 

found on the internal components and 

external housing on one of the failure 

types, and fuel leakage on the other. 

This AD requires inspecting to 

determine if fuel boost pumps having a 

certain part number are installed, 

replacing the fuel boost pumps having 

a certain part number, and revising the 

airplane maintenance program to 

include revised instructions for 

continued airworthiness. We are issuing 

this AD to prevent fuel leakage in 

combination with a capacitor clearance 

issue, which could result in an 

uncontrolled fire in the wheel well. 

DATES: This AD is effective January 7, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 7, 2014. 

ADDRESSES: For Gulfstream, Triumph 

Aerostructures, and General Electric 

(GE) Aviation service information 

identified in this AD, contact 

Gulfstream Aerospace Corporation, 

Technical Publications Dept., P.O. Box 

2206, Savannah, GA 31402–2206; 

telephone 800–810–4853; fax 912–965– 

3520; email pubs@gulfstream.com; 

Internet http://www.gulfstream.com/

product_support/technical_pubs/pubs/

index.htm. You may view this 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, 

Washington. 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/

#!docketDetail;D=FAA-2012-1313; 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 

Document 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: 

Darby Mirocha, Aerospace Engineer, 

Propulsion and Services Branch, ACE– 

118A, FAA, Atlanta Aircraft 

Certification Office, 1701 Columbia 

Avenue, College Park, GA 30337; phone: 

(404) 474–5573; fax: (404) 474–5606; 

email: darby.mirocha@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on December 26, 2012 (77 FR 

75908). The NPRM proposed to require 

doing an inspection to determine if fuel 

boost pumps having a certain part 

number (P/N) are installed, replacing 

the fuel boost pumps having a certain 

part number, and revising the airplane 

maintenance program to include revised 

instructions for continued 

airworthiness. 

This AD was prompted by reports of 

two independent types of failure of the 

fuel boost pump with overheat damage 

found on the internal components and 

external housing on one of the failure 

types, and fuel leakage on the other. We 

are issuing this AD to prevent fuel 

leakage in combination with a capacitor 

clearance issue, which could result in 

an uncontrolled fire in the wheel well. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (77 FR 75908, 

December 26, 2012) and the FAA’s 

response to each comment. 

Request To Revise the Precipitating 

Event 

Gulfstream Aerospace Corporation 

(Gulfstream) requested that the 

precipitating event in the SUMMARY

section of the NPRM (77 FR 75908, 

December 26, 2012) be revised to 

provide clarity not provided elsewhere 

in the NPRM—namely, although two 

distinct failure types have been 

reported, there have been no reports of 

any fuel pump exhibiting both failure 

types. 

We agree with Gulfstream’s request. 

We agree that the failures in service 

were separate events and no single 

pump was found with both failure 

modes present. We have changed the 

SUMMARY section and paragraph (e) of 

this final rule to include language 

suggested by the commenter 

emphasizing the independent nature of 

the failure modes. 

Request To Revise the Statement of 

Requirements 

Gulfstream requested that the 

statement of requirements in the 

SUMMARY section of the NPRM (77 FR 

75908, December 26, 2012) be revised. 

Gulfstream proposed to revise the 

wording to read, ‘‘This proposed AD 

would require doing an inspection to 

determine if fuel boost pumps having a 

certain part number are installed, 

replacing the fuel boost pumps having 

a certain part number with a later part 

number, and revising the airplane 

maintenance program to include revised 

instructions for continued airworthiness 

for airplanes with the later pump part 

number installed.’’ Gulfstream stated 

that the rewording increases the content 

clarity in the NPRM. 

We disagree with Gulfstream’s request 

to refer to ‘‘later part numbers’’ because 

this language lacks clarity. This final 

rule requires specific part number 

replacements. Therefore, we would 

need to use specific part numbers to 

identify replacement parts. In addition, 

the intent of the SUMMARY section is to 

provide a brief explanation of the unsafe 

condition and corrective actions; 

therefore, we do not find it appropriate 

to include details regarding specific part 

numbers. We have not changed this 

final rule in this regard. 

Request To Revise the Discussion 

Paragraph of the NPRM (77 FR 75908, 

December 26, 2012) 

Gulfstream requested that the 

Discussion paragraph of the NPRM (77 

FR 75908, December 26, 2012) be 

revised. Gulfstream proposed revising 

the wording to add, ‘‘Additionally, on 

one other fuel pump component, a 


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Federal Register / Vol. 78, No. 232 / Tuesday, December 3, 2013 / Rules and Regulations 72555 

damaged o-ring between the ‘wet’ and 

‘dry’ cavities of the boost pump resulted 

in fuel ingress into the dry cavity and 

outside of the fuel pump via the 

electrical pigtail.’’ Gulfstream stated that 

the rewording clarifies that the 

component referred to is a fuel pump, 

and that there is one recorded incident; 

also additional information related to 

the discovery of the incident is 

provided. 

We agree that the wording suggested 

by Gulfstream clarifies the Discussion 

paragraph of the NPRM (77 FR 75908, 

December 26, 2012), which was drawn 

entirely from paragraph I.B. ‘‘Reason,’’ 

of Gulfstream V Customer Bulletin 197, 

dated April 11, 2012; and Gulfstream 

G550 Customer Bulletin 122, dated 

April 11, 2012. However, that portion of 

the Discussion paragraph is not carried 

over into this final rule; therefore, no 

change is necessary to this final rule in 

this regard. 

Request To Revise the Unsafe Condition 

Gulfstream requested that the unsafe 

condition identified in the NPRM (77 

FR 75908, December 26, 2012) be 

revised. Gulfstream proposed to revise 

the wording to read, ‘‘If not corrected, 

the issue of the fuel leakage in 

combination with the capacitor 

clearance issue could result in an 

uncontrolled fire in the wheel well.’’ 

Gulfstream stated that the revised 

description is consistent with the field 

experience of independent failure types. 

We agree with Gulfstream’s request 

since the rewording provides more 

clarity of the unsafe condition. We have 

revised the SUMMARY section, the 

Discussion paragraph, and paragraph (e) 

of this final rule to state that fuel 

leakage in combination with a capacitor 

clearance issue could result in an 

uncontrolled fire in the wheel well. 

Request To Change the Title of Certain 

Service Information 

Gulfstream requested that we change 

the title of certain service information in 

the NPRM (77 FR 75908, December 26, 

2012). Gulfstream stated that the correct 

title for the Gulfstream service 

information should be referred to as 

‘‘customer bulletins.’’ Gulfstream also 

stated that the Model GV–SP airplanes 

include G500 and G550 airplane types, 

so a G500 Customer Bulletin reference 

should be added. 

We acknowledge Gulfstream’s request 

to correct citations for certain service 

information. We agree that the 

referenced bulletins should be referred 

to as ‘‘customer’’ bulletins; we have 

revised document citations throughout 

this final rule accordingly. However, 

although we agree that G500 and G550 

airplanes are both included in the 

Model GV–SP designation, we do not 

agree to add a reference to a customer 

bulletin for G500 airplanes because 

doing so violates Office of the Federal 

Register (OFR) regulations for approval 

of materials ‘‘incorporated by reference’’ 

in rules. (See 1 CFR 51.1(f).) In general 

terms, we may not include elements in 

a document citation that are not clearly 

specified on the document. Therefore, 

although we agree that Gulfstream G550 

Customer Bulletin 122, dated April 11, 

2012, also applies to G500 airplanes, we 

do not agree to revise the document 

citation in this regard. 

Request To Clarify the Differences 

Between the Proposed AD and the 

Service Information Paragraph of the 

NPRM (77 FR 75908, December 26, 

2012) 

Gulfstream requested clarification of 

the Differences Between the Proposed 

AD and the Service Information 

paragraph of the NPRM (77 FR 75908, 

December 26, 2012) to highlight that the 

proposed 36-month compliance time 

will result in a slightly later completion 

date than the compliance time specified 

in referenced Gulfstream customer 

bulletins, and that the compliance time 

in the proposed AD takes precedence 

over that of the referenced Gulfstream 

customer bulletins. Gulfstream stated 

that it acknowledges a difference in 

compliance time, but stated that the 

NPRM does not provide an explanation 

on the effect on the completion date. 

We partially agree with Gulfstream’s 

request. We agree that this AD has a 

slightly different compliance time than 

that provided in the service information. 

In developing an appropriate 

compliance time, we considered the 

safety implications, parts availability, 

and normal maintenance schedules for 

timely accomplishment of the actions in 

this AD, while still maintaining an 

adequate level of safety. We arrived at 

the compliance time with the 

manufacturer’s concurrence. In 

addition, the Differences Between the 

Proposed AD and the Service 

Information paragraph of the NPRM (77 

FR 75908, December 26, 2012) is not 

restated in this final rule. We have not 

changed this final rule in this regard. 

Request To Clarify Certain Part 

Numbers 

Gulfstream requested that the part 

numbers in the NPRM (77 FR 75908, 

December 26, 2012) be clarified. 

Gulfstream stated that the word 

‘‘Gulfstream’’ should be added in front 

of P/N 1159SCP500–5 and P/N 

1159SCP500–7 since the fuel pumps 

also contain GE part numbers. 

We agree with Gulfstream’s request. 

When referencing P/N 1159SCP500–5 

and P/N 1159SCP500–7, we have added 

the word ‘‘Gulfstream’’ in front of the 

part number in paragraphs (g), (h), and 

(i) of this AD. 

Request To Change the Compliance 

Time 

Gulfstream requested that we change 

the compliance time in paragraph (h) of 

the NPRM (77 FR 75908, December 26, 

2012). Gulfstream proposed to revise the 

compliance time for the replacement of 

the fuel boost pump from ‘‘before 

further flight’’ to ‘‘within 36 months 

after the effective date of this AD.’’ 

Gulfstream stated that approximately 

2,250 fuel pumps having Gulfstream 

P/N 11598SCP500–5 require an upgrade 

to Gulfstream P/N 1159SCP500–7. 

Gulfstream stated that there are a 

limited number of ‘‘seed’’ fuel pumps to 

support this effort. Gulfstream stated 

that the Gulfstream-managed program 

matches customer airplane availability 

with supplier shop loading and seed 

unit availability, which allows for an 

upgrade of all affected fuel boost pumps 

within a 42-month committed 

timeframe without undue burden onto 

operators in terms of aircraft downtime 

and missed trips. In addition, 

Gulfstream stated that a risk assessment 

was presented to the FAA in 2010 that 

supported a change-out interval of 48 

months through a Gulfstream-managed 

program starting in October 2011. 

Gulfstream stated that, based on the risk 

assessment, Gulfstream V Customer 

Bulletin 197, dated April 11, 2012 (for 

Model GV airplanes); and Gulfstream 

G550 Customer Bulletin 122, dated 

April 11, 2012 (for Model GV–SP 

airplanes); were issued to recommend 

replacement of certain fuel pumps 

within 42 months since issuance of the 

service information. 

Gulfstream stated that its proposed 

change to the compliance time is 

consistent with the risk assessment, the 

intent of the managed program, and the 

wording of the Gulfstream and supplier 

service information. Gulfstream stated 

that, in contrast, the requirement to 

change out Gulfstream P/N 

11598SCP500–5 before the next flight is 

unnecessary according to the Gulfstream 

risk assessment, and has the potential to 

severely affect the Gulfstream-managed 

program, since needed planning 

information will not be available to 

Gulfstream. 

We agree with Gulfstream’s request to 

revise the compliance time in paragraph 

(h) of this final rule to 36 months for the 

reasons provided by the commenter. We 

have revised paragraph (h) of this AD 

accordingly. 


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72556 Federal Register / Vol. 78, No. 232 / Tuesday, December 3, 2013 / Rules and Regulations 

Request To Revise Compliance Time for 

Leak Check Inspection 

Gulfstream requested we revise 

paragraph (i)(2) of the NPRM (77 FR 

75908, December 26, 2012) to require 

the initial inspection before 500 flight 

hours have elapsed since installation of 

the Gulfstream P/N 1159SCP500–7 

pump, or before further flight if 500 

flight hours have elapsed since 

installation of the Gulfstream 

1159SCP500–7 pump and an initial fuel 

leak inspection has not been 

accomplished. 

Gulfstream stated that the inspection 

referred to in paragraph (g) of the NPRM 

(77 FR 75908, December 26, 2012) 

determines the part number of the fuel 

boost pump; therefore, a requirement for 

a leak check inspection before further 

flight is inconsistent with the FAAaccepted Instructions for Continued 

Airworthiness, and is only required if 

the initial inspection interval of 500 

flight hours has been exceeded since 

installation of the Gulfstream P/N 

1159SCP500–7 standard pump and an 

initial leak check inspection has not 

been accomplished. 

We partially agree with the 

commenter’s request. We agree that 

mandating the leak check inspection at 

the same time as the part number 

inspection could cause the leak check to 

be done before 500 flight hours has 

elapsed since the installation of the 

Gulfstream P/N 1159SCP500–7 pump, 

because the Gulfstream P/N 

1159SCP500–7 installation might have 

just recently been done. However, we 

disagree with changing the AD in this 

regard because the simplicity of the leak 

check, in addition to the airplane 

already being under inspection in the 

area, places minimal burden on the 

operator. We have not changed this AD 

in this regard. 

Request To Revise Parts Installation 

Prohibition 

Gulfstream requested we revise 

paragraph (k) of the NPRM (77 FR 

75908, December 26, 2012) to prohibit 

replacing a fuel boost pump having 

Gulfstream P/N 1159SCP500–7 with a 

fuel boost pump having Gulfstream P/N 

1159SCP500–5. Gulfstream stated that 

this is to allow a fuel boost pump 

having Gulfstream P/N 1159SCP500–5 

to be replaced by a fuel boost pump of 

the same part number within 36 months 

after the effective date of the AD, if a 

Gulfstream P/N 1159SCP500–7 pump is 

not available, and to require that any 

Gulfstream P/N 1159SCP500–5 pumps 

installed for that reason must be 

replaced with a Gulfstream P/N 

1159SCP500–7 pump within 36 months 

after the effective date of the AD. 

Gulfstream stated that its risk 

assessment supports a replacement at 

intervals of 48 months from April 2012, 

and remains unaffected if a Gulfstream 

P/N 1159SCP500–5 pump is replaced 

with a Gulfstream P/N 1159SCP500–5 

pump, since the total number of 

Gulfstream P/N 1159SCP500–5 pumps 

in service at any time is unchanged. 

Gulfstream stated that its request is 

intended to avoid a situation where an 

airplane is grounded because a 

Gulfstream P/N 1159SCP500–5 pump 

requires replacement for cause and a 

Gulfstream P/N 1159SCP500–7 pump is 

unavailable, but a Gulfstream P/N 

1159SCP500–5 is available. 

We disagree with Gulfstream’s request 

to revise paragraph (k) of this AD. In 

cases where a part is known to be 

unairworthy, such as when it creates an 

unsafe condition, we might determine 

that, as of the effective date of the AD, 

such a part is not allowed to be installed 

on an airplane. ‘‘Parts Installation 

Prohibition’’ paragraphs (like paragraph 

(k) of this AD) are intended to prevent 

an operator from knowingly installing 

an unairworthy part on an airplane. 

We based the compliance time of 36 

months specified in paragraph (g) of this 

AD on a risk assessment of the 

Gulfstream Aerospace Corporation 

Model GV and GV–SP fleet performed 

in August 2010. The risk assessment did 

not consider the possibility that 

additional fuel boost pumps with 

Gulfstream P/N 1159SCP500–5 would 

be introduced into the fleet during the 

36-month compliance time. Therefore, 

we determined that the ‘‘Parts 

Installation Prohibition’’ paragraph 

must prohibit installation of the affected 

part as of the effective date of this AD. 

We have not changed this AD in this 

regard. However, under the provisions 

of paragraph (l) of this AD, we may 

approve requests for adjustments to the 

compliance time if data are submitted to 

substantiate that such an adjustment 

would provide an acceptable level of 

safety. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

75908, December 26, 2012) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 75908, 

December 26, 2012). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 357 

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 

Inspection to determine if a certain part number 

is installed.

1 work-hour × $85 per hour = $85 ....................... $0 $85 $30,345 

Maintenance program revision ............................. 1 work-hour × $85 per hour = $85 ....................... 0 85 30,345 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 


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ON-CONDITION COST

Action Labor cost Parts cost Cost per 

product 

Replacement ..................................................................... 24 work-hours × $85 per hour = $2,040 .......................... $7,600 $9,640 

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): 

2013–22–19 Gulfstream Aerospace 

Corporation: Amendment 39–17651; 

Docket No. FAA–2012–1313; Directorate 

Identifier 2012–NM–080–AD. 

(a) Effective Date 

This AD is effective January 7, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Gulfstream 

Aerospace Corporation Model GV and GV–SP 

airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 2822, Fuel boost pump. 

(e) Unsafe Condition 

This AD was prompted by reports of two 

independent types of failure of the fuel boost 

pump with overheat damage found on the 

internal components and external housing on 

one of the failure types, and fuel leakage on 

the other. We are issuing this AD to prevent 

fuel leakage in combination with a capacitor 

clearance issue, which could result in an 

uncontrolled fire in the wheel well. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection To Determine the Part Number 

(P/N) 

Within 36 months after the effective date 

of this AD, inspect the fuel boost pumps to 

determine whether Gulfstream P/N 

1159SCP500–5 is installed, in accordance 

with the Accomplishment Instructions of 

Gulfstream V Customer Bulletin 197, dated 

April 11, 2012, including the service 

information specified in paragraphs (g)(1) 

and (g)(2) of this AD (for Model GV 

airplanes); or Gulfstream G550 Customer 

Bulletin 122, dated April 11, 2012, including 

the service information specified in 

paragraphs (g)(1) and (g)(2) of this AD (for 

Model GV–SP airplanes). A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the part number of 

the fuel boost pumps can be conclusively 

determined from that review. 

(1) Triumph Aerostructures Service 

Bulletin SB–TAGV/GVSP–28–JG0162, dated 

August 30, 2011. 

(2) GE Service Bulletin 31760–28–100, 

dated February 15, 2011. 

(h) Replacement 

If the inspection required by paragraph (g) 

of this AD reveals a fuel boost pump with 

Gulfstream P/N 1159SCP500–5: Within 36 

months after the effective date of this AD, 

replace the fuel boost pump with a 

serviceable pump having Gulfstream P/N 

1159SCP500–7, in accordance with the 

Accomplishment Instructions of Gulfstream 

V Customer Bulletin 197, dated April 11, 

2012, including the service information 

specified in paragraphs (h)(1) and (h)(2) of 

this AD (for Model GV airplanes); or 

Gulfstream G550 Customer Bulletin 122, 

dated April 11, 2012, including the service 

information specified in paragraphs (h)(1) 

and (h)(2) of this AD (for Model GV–SP 

airplanes). 

(1) Triumph Aerostructures Service 

Bulletin SB–TAGV/GVSP–28–JG0162, dated 

August 30, 2011. 

(2) GE Service Bulletin 31760–28–100, 

dated February 15, 2011. 

(i) Maintenance Program Revision 

Within 500 flight hours after the effective 

date of this AD, revise the airplane 

maintenance program to include Gulfstream 

Document GV–GER–0003, Instructions for 

Continued Airworthiness, Fuel Boost Pump 

with Leak Check Port, dated November 24, 

2010. 

(1) For airplanes on which fuel boost pump 

Gulfstream P/N 1159SCP500–5 has been 

replaced in accordance with paragraph (h) of 

this AD: The initial compliance time for the 

inspection is within 500 flight hours after 

doing the replacement specified in paragraph 

(h) of this AD. 

(2) For airplanes on which the inspection 

required by paragraph (g) of this AD reveals 

that a fuel boost pump with Gulfstream P/N 

1159SCP500–7 has been installed: After 

revising the airplane maintenance program, 

as required by paragraph (i) of this AD, the 

initial inspection is required before further 

flight after doing the inspection required by 

paragraph (g) of this AD. 

(j) No Alternative Actions or Intervals 

After accomplishing the revision required 

by paragraph (i) 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 in accordance with the 

procedures specified in paragraph (l) of this 

AD. 

(k) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install a fuel boost pump having 


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72558 Federal Register / Vol. 78, No. 232 / Tuesday, December 3, 2013 / Rules and Regulations 

Gulfstream P/N 1159SCP500–5 on any 

airplane. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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. 

(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 Darby Mirocha, Aerospace Engineer, 

Propulsion and Services Branch, ACE–118A, 

FAA, Atlanta ACO, 1701 Columbia Avenue, 

College Park, GA 30337; phone: (404) 474– 

5573; fax: (404) 474–5606; email: 

darby.mirocha@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) Gulfstream V Customer Bulletin 197, 

dated April 11, 2012. 

(ii) Gulfstream G550 Customer Bulletin 

122, dated April 11, 2012. 

(iii) Triumph Service Bulletin SB–TAGV/

GVSP–28–JG0162, dated August 30, 2011. 

(iv) General Electric Service Bulletin 

31760–28–100, dated February 15, 2011. 

(v) Gulfstream Document GV–GER–0003, 

Instructions for Continued Airworthiness, 

Fuel Boost Pump with Leak Check Port, 

dated November 24, 2010. 

(3) For Gulfstream, Triumph 

Aerostructures, and General Electric Aviation 

service information identified in this AD, 

contact Gulfstream Aerospace Corporation, 

Technical Publications Dept., P.O. Box 2206, 

Savannah, GA 31402–2206; telephone 800– 

810–4853; fax 912–965–3520; email pubs@

gulfstream.com; Internet 

http://www.gulfstream.com/product_

support/technical_pubs/pubs/index.htm. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, Washington. 

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 October 

25, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–28860 Filed 12–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1317; Directorate 

Identifier 2011–NM–194–AD; Amendment 

39–17687; AD 2013–24–13] 

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 737–100, 

–200, –200C, –300, –400, –500, –600, 

–700, –700C, –800, and –900 series 

airplanes. This AD was prompted by a 

report that the seat track attachment of 

body station 520 flexible joint is 

structurally deficient in resisting a 9g 

forward emergency load condition in 

certain seating configurations. This AD 

requires replacing the pivot link 

assembly on certain seats, modifying the 

existing seat track link assembly 

fastener on certain seats, or replacing 

the seat track link assemblies on certain 

seats. Also, for certain airplanes, this 

AD requires installing a new seat track 

link assembly or modifying the seat 

track link assembly. For certain other 

airplanes, this AD requires inspecting, 

changing, or repairing the seat track link 

assembly. We are issuing this AD to 

prevent seat detachment in an 

emergency landing, which could cause 

injury to occupants of the passenger 

compartment and affect emergency 

egress. 

DATES: This AD is effective January 7, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 7, 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 

Document 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: 

Sarah Piccola, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6483; fax: 

425–917–6590; email: sarah.piccola@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on January 16, 2013 (78 FR 

3365). The NPRM proposed to require 

replacing the pivot link assembly on 

certain seats, and modifying or 

replacing the seat track link assemblies 

on certain seats. Also, for certain 

airplanes, the NPRM proposed to 

require installing a new seat track link 

assembly. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 3365, 

January 16, 2013) and the FAA’s 

response to each comment. 

Request To Incorporate Revised Service 

Information 

Boeing concurred with the content of 

the NPRM (78 FR 3365, January 16, 

2013), but requested that we incorporate 

Boeing Special Attention Service 

Bulletin 737–53–1260, Revision 1, dated 

May 23, 2013, in the AD. Boeing stated 

that due to manufacturing differences, 


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