Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Proposed Rules 80295 

and (g)(4) of this AD into the AFM. When 

these TRs have been included in general 

revisions of the AFM, the general revisions 

may be inserted in the AFM, provided the 

relevant information in the general revision 

is identical to that in the applicable TRs, and 

the TRs may be removed. 

(1) Canadair TR 600/29, dated June 20, 

2014, to the Canadair CL–600–1A11 AFM. 

(2) Canadair TR 600/30, dated June 6, 2014, 

to the Canadair CL–600–1A11 AFM. 

(3) Canadair TR 600–1/24, dated June 20, 

2014, to the Canadair CL–600–1A11 AFM 

(Winglets) including Erratum, Publication 

No. PSP 600–1AFM (US), TR No. 600–1/24, 

June 20, 2014. 

(4) Canadair TR 600–1/26, dated June 6, 

2014, to the Canadair CL–600–1A11 AFM 

(Winglets). 

(h) Retained Repetitive Inspections With No 

Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2014–16–02, 

Amendment 39–17926 (79 FR 46968, August 

12, 2014), with no changes. Within 25 flight 

cycles or 90 days, whichever occurs first, 

after August 12, 2014 (the effective date of 

AD 2014–16–02), do detailed inspections 

(including a borescope inspection) of both 

engine thrust reversers for cracks, in 

accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin A600–0769, Revision 01, dated June 

26, 2014. 

(1) If no cracking is found during any 

inspection required by paragraph (h) of this 

AD, repeat the inspection required by 

paragraph (h) of this AD thereafter at 

intervals not to exceed 100 flight cycles until 

the repair or modification specified in 

paragraph (i) or (k) of this AD is done. 

(2) If any cracking is found during any 

inspection required by paragraph (h) of this 

AD, before further flight, modify the thrust 

reversers on both engines, in accordance with 

the Accomplishment Instructions of 

Bombardier Alert Service Bulletin A600– 

0769, Revision 01, dated June 26, 2014. 

(i) Retained Optional Terminating 

Modification With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2014–16–02, Amendment 

39–17926 (79 FR 46968, August 12, 2014), 

with no changes. Modifying the thrust 

reversers on both engines, in accordance with 

the Accomplishment Instructions of 

Bombardier Alert Service Bulletin A600– 

0769, Revision 01, dated June 26, 2014, 

terminates the inspections required by 

paragraph (h) of this AD. 

(j) Retained Credit for Previous Actions With 

No Changes 

This paragraph restates the requirements of 

paragraph (j) of AD 2014–16–02, Amendment 

39–17926 (79 FR 46968, August 12, 2014), 

with no changes. This paragraph provides 

credit for actions required by paragraphs (h) 

and (i) of this AD, if those actions were 

performed before August 12, 2014 (the 

effective date of AD 2014–16–02) using 

Bombardier Alert Service Bulletin A600– 

0769, dated June 19, 2014, which is not 

incorporated by reference in this AD. 

(k) New Requirement of This AD: Repair/

Modify 

Within 24 months after the effective date 

of this AD, repair or modify the thrust 

reversers on both engines, using a method 

approved by the Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA; 

or Transport Canada Civil Aviation (TCCA); 

or Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). Accomplishment of the 

repair or modification of all thrust reversers 

terminates the requirements of paragraphs (h) 

and (i) of this AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, 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 New York ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone: 516–228–7300; fax: 516–794– 

5531. 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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, New York ACO, ANE–170, 

FAA; or TCCA; or Bombardier, Inc.’s TCCA 

DAO. If approved by the DAO, the approval 

must include the DAO-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

AD CF–2014–19, dated June 20, 2014, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2015–7529. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone: 514–955–5000; fax: 514– 

855–7401; email: thd.crj

@aero.bombardier.com; Internet http:// 

www.bombardier.com. 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. 

Issued in Renton, Washington, on 

December 11, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service, 

[FR Doc. 2015–32085 Filed 12–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0651; Directorate 

Identifier 2014–NM–043–AD] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace Corporation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for all Gulfstream Aerospace 

Corporation Model GV and GV–SP 

airplanes. The NPRM proposed to 

supersede Airworthiness Directive (AD) 

2013–22–19, which 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 or inspection 

program to include revised instructions 

for continued airworthiness. The NPRM 

also proposed to require revising the 

airplane maintenance program to 

include a fuel leak check of the fuel 

boost pumps, using new service 

information. The NPRM was prompted 

by reports of two independent types of 

failure of the fuel boost pump: overheat 

damage on the internal components and 

external housing, and fuel leakage. This 

action revises the NPRM by reducing 

the compliance time for revising the 

airplane maintenance program. We are 

proposing this supplemental NPRM 

(SNPRM) to prevent fuel leakage in 

combination with a capacitor clearance 

issue, which could result in an 

uncontrolled fire in the wheel well. 

Since these actions impose an 

additional burden over that proposed in 

the NPRM, we are reopening the 

comment period to allow the public the 

chance to comment on these proposed 

changes. 

DATES: We must receive comments on 

this SNPRM by February 8, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 


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W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed 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, 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–2014– 

0651; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjana Murthy, Aersopace Engineer, 

ACE–118A, FAA, Atlanta Aircraft 

Certification Office, 1701 Columbia 

Avenue, College Park, GA 30337; 

telephone: 404–474–5573; fax: 404– 

474–5567; email: sanjana.murthy@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0651; Directorate Identifier 

2014–NM–043–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We issued an NPRM to amend 14 CFR 

part 39 to supersede AD 2013–22–19, 

Amendment 39–17651 (78 FR 72554, 

December 3, 2013), which applies to all 

Gulfstream Aerospace Corporation 

Model GV and GV–SP airplanes. The 

NPRM published in the Federal 

Register on October 1, 2014 (79 FR 

59162). The NPRM proposed to 

continue to require 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 or inspection 

program to include revised instructions 

for continued airworthiness. The NPRM 

also proposed to require revising the 

airplane maintenance program to 

include a fuel leak check of the fuel 

boost pumps, using new service 

information. 

Actions Since Previous NPRM (79 FR 

59162, October 1, 2014) Was Issued 

Since we issued the NPRM (79 FR 

59162, October 1, 2014), we have 

determined it is necessary to reduce the 

compliance time for revising the 

airplane maintenance or inspection 

program in order to address the 

identified unsafe condition in a timely 

manner. Paragraph (i) of the proposed 

AD specifies a compliance time of 

‘‘within 500 flight hours after the 

effective date of this AD’’ to accomplish 

the revision, which incorporates the fuel 

leak check inspection of the fuel boost 

pumps. The leak check is intended to be 

performed at 500-hour increments after 

the installation of the part number (P/ 

N) 1159SCP500–7 boost pump. 

However, operators that have already 

installed the P/N 1159SCP500–7 boost 

pump would not be required to perform 

the leak check until after the 

maintenance or inspection program is 

revised, i.e., within 500 flight hours 

after the effective date of the AD instead 

of within 500 flight hours after 

installation. We have determined a 

compliance time of ‘‘within 30 days 

after the effective date of this AD’’ 

represents an appropriate interval of 

time to revise the airplane maintenance 

or inspection program. We have revised 

paragraph (i) of this proposed AD 

accordingly. 

Comments 

We gave the public the opportunity to 

participate in developing this proposed 

AD. The following presents the 

comments received on the NPRM (79 FR 

59162, October 1, 2014) and the FAA’s 

response to each comment. 

Request To Use Later Revision of the 

Service Information 

Gulfstream requested that the FAA 

reference the upcoming revision to the 

airworthiness limitations section of the 

GV, G500, and G550 maintenance 

manuals. Gulfstream stated that the 

maintenance manuals will include a 

revised fuel leak check interval of 500 

hours ±50 hours. Gulfstream stated that 

drafts of the maintenance manuals were 

scheduled to be submitted to the FAA 

by December 2014, with FAA approval 

expected. Gulfstream also stated that the 

revisions to the airplane maintenance 

program include revised instructions for 

continued airworthiness to avoid future 

AD revisions on this subject. Gulfstream 

stated that AD 2013–22–19, Amendment 

39–17651 (78 FR 72554, December 3, 

2013), references the 05–20–00, Table 

20 Fuel Boost Pump fuel leak check 

interval of 500 hours, which would 

prohibit the ±50-hour provision that the 

Gulfstream safety assessment allows, 

limiting the flexibility of Gulfstream’s 

operators to perform this fuel leak check 

concurrently with other scheduled 

maintenance. 

We have reviewed the supporting data 

for this request and we agree with the 

request to change the compliance time. 

We have revised paragraph (i) of this 

proposed AD to accommodate this 

request. In order to decrease the burden 

on operators, we are adding 50 hours to 

the compliance time, which will enable 

operators to complete the requirements 

of this proposed AD as well as their 

mandatory inspection requirement 

during the same overhaul. 

Operators may request approval to use 

a later revision of the referenced service 

information, when it is approved, as an 

alternative method of compliance 

(AMOC) under the provisions of 

paragraph (m) of this proposed AD. 

Request To Revise the Compliance 

Time 

Gulfstream requested that a 

compliance time specified in paragraph 

(i)(2) of the proposed AD (79 FR 59162, 

October 1, 2014) be revised. Gulfstream 

requested that the following language be 

included in paragraph (i)(2) of the 

proposed AD, which is for airplanes on 

which the inspection required by 

paragraph (g) of the proposed AD 

reveals that a fuel boost pump with 


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Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Proposed Rules 80297 

Gulfstream P/N 1159SCP500–7 has been 

installed: 

The initial compliance time . . . is within 

500 flight hours after installation of the P/N 

11 59SCP500–7 pump, or within 50 flight 

hours after doing the inspection required by 

paragraph (g) of this AD if 500 flight hours 

have accumulated since installation of the P/ 

N 1159SCP500–7 pump and an initial leak 

check of the pump has not been 

accomplished. 

We agree to revise the compliance 

time. The leak check is intended to be 

performed at 500-hour increments ± 50 

flight hours after the installation of the 

P/N 1159SCP500–7 boost pump. We 

have added new paragraph (i)(2)(i) to 

this proposed AD to specify 

compliances times relative to 

installation of the P/N 1159SCP500–7 

pump. 

FAA’s Determination 

We are proposing this SNPRM 

because we evaluated all the relevant 

information and determined the unsafe 

condition described previously is likely 

to exist or develop in other products of 

the same type design. Certain changes 

described above expand the scope of the 

proposed AD (79 FR 59162, October 1, 

2014). As a result, we have determined 

that it is necessary to reopen the 

comment period to provide additional 

opportunity for the public to comment 

on this SNPRM. 

Proposed Requirements of This SNPRM 

This SNPRM would require 

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 

or inspection program to include 

revised instructions for continued 

airworthiness. 

Related Service Information Under 1 

CFR Part 51 

We have reviewed Gulfstream G500 

Customer Bulletin 122, dated April 11, 

2012 (for Model GV–SP airplanes 

designated as G500), which describes 

procedures for inspecting and replacing 

the fuel boost pumps. 

We have also reviewed the following 

service information, as applicable, 

which describes, among other actions, a 

fuel leak check of the fuel boost pumps 

and inspection intervals: 

• Table 18, 500 Flight Hours 

Scheduled Inspection Table, in Section 

05–20–00, of Chapter 5, Time Limits/

Maintenance Checks, of the Gulfstream 

V Maintenance Manual, Revision 42, 

dated June 20, 2013; 

• Task 28–26–01, Fuel Boost 

Pumps—Fuel Leak Check, of Chapter 

28, Fuel, of the Gulfstream V 

Maintenance Manual, Revision 42, 

dated June 20, 2013; 

• Task 28–26–01, Fuel Boost 

Pumps—Fuel Leak Checks, in Table 20, 

500 Flight Hours Scheduled Inspection 

Table, in Section 05–20–00, of Chapter 

5, Time Limits/Maintenance Checks, of 

the Gulfstream G500 Maintenance 

Manual, Revision 23, dated June 20, 

2013; 

• Task 28–26–01, Fuel Boost 

Pumps—Fuel Leak Check, of Section 26, 

Fuel Boost Pumps, of Chapter 28, Fuel, 

of the Gulfstream G550 Maintenance 

Manual, Revision 23, dated June 20, 

2013; 

• Task 28–26–01, Fuel Boost 

Pumps—Fuel Leak Check, in Table 20, 

500 Flight Hours Scheduled Inspection 

Table, in Section 05–20–00, of Chapter 

5, Time Limits/Maintenance Checks, of 

the Gulfstream G550 Maintenance 

Manual, Revision 23, dated June 20, 

2013; and 

• Task 28–26–01, Fuel Boost 

Pumps—Fuel Leak Check, of Section 26, 

Fuel Boost Pumps, of Chapter 28, Fuel, 

of the Gulfstream G550 Maintenance 

Manual, Revision 23, dated June 20, 

2013. 

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 proposed AD 

would affect 357 airplanes of U.S. 

registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on 

U.S. 

operators 

Inspection to determine if a certain part number is installed [retained actions from AD 2013–22–19, 

Amendment 39–17651 (78 FR 72554, December 

3, 2013)].

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

Maintenance program revision [new proposed action] 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: 

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 


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products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2013–22–19, Amendment 39–17651 (78 

FR 72554, December 3, 2013), and 

adding the following new AD: 

Gulfstream Aerospace Corporation: FAA– 

2014–0651; Directorate Identifier 2014– 

NM–043–AD. 

(a) Comments Due Date 

We must receive comments by February 8, 

2016. 

(b) Affected ADs 

This AD replaces AD 2013–22–19, 

Amendment 39–17651 (78 FR 72554, 

December 3, 2013). 

(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 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by reports of two 

independent types of failure of the fuel boost 

pump: overheat damage on the internal 

components and external housing, and fuel 

leakage. 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) Retained Inspection To Determine the 

Part Number, With Revised Service 

Information 

This paragraph restates the actions 

required by paragraph (g) of AD 2013–22–19, 

Amendment 39–17651 (78 FR 72554, 

December 3, 2013), with revised service 

information. Within 36 months after January 

7, 2014 (the effective date of AD 2013–22– 

19), inspect the fuel boost pumps to 

determine whether Gulfstream part number 

(P/N) 1159SCP500–5 is installed, in 

accordance with the Accomplishment 

Instructions of the applicable service 

information identified in paragraphs (g)(1), 

(g)(2), and (g)(3) of this AD; including 

Triumph Aerostructures Service Bulletin SB– 

TAGV/GVSP–28–JG0162, dated August 30, 

2011; and GE Service Bulletin 31760–28–100, 

dated February 15, 2011. 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) For Model GV airplanes: Gulfstream V 

Customer Bulletin 197, dated April 11, 2012. 

(2) For Model GV–SP airplanes designated 

as G500: Gulfstream G500 Customer Bulletin 

122, dated April 11, 2012; or Gulfstream 

G550 Customer Bulletin 122, dated April 11, 

2012. 

(3) For Model GV–SP airplanes designated 

as G550: Gulfstream G550 Customer Bulletin 

122, dated April 11, 2012. 

(h) Retained Replacement With Revised 

Service Information 

This paragraph restates the actions 

required by paragraph (h) of AD 2013–22–19, 

Amendment 39–17651 (78 FR 72554, 

December 3, 2013), with revised service 

information. 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 January 7, 2014 (the 

effective date of AD 2013–22–19), replace the 

fuel boost pump with a serviceable pump 

having Gulfstream P/N 1159SCP500–7, in 

accordance with the applicable service 

information identified in paragraphs (h)(1), 

(h)(2), and (h)(3) of this AD; including 

Triumph Aerostructures Service Bulletin SB– 

TAGV/GVSP–28–JG0162, dated August 30, 

2011; and GE Service Bulletin 31760–28–100, 

dated February 15, 2011. 

(1) For Model GV airplanes: Gulfstream V 

Customer Bulletin 197, dated April 11, 2012. 

(2) For Model GV–SP airplanes designated 

as G500: Gulfstream G500 Customer Bulletin 

122, dated April 11, 2012; or Gulfstream 

G550 Customer Bulletin 122, dated April 11, 

2012. 

(3) For Model GV–SP airplanes designated 

as G550: Gulfstream G550 Customer Bulletin 

122, dated April 11, 2012. 

(i) New Revision of the Maintenance or 

Inspection Program 

Within 30 days after the effective date of 

this AD, revise the airplane maintenance or 

inspection program, as applicable, to include 

the fuel leak check inspection of the fuel 

boost pumps specified in the applicable task 

identified in paragraph (j) of this AD. 

(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 

leak check inspection specified in the 

applicable task identified in paragraph (j) of 

this AD is within 550 flight hours after doing 

the replacement specified in paragraph (h) of 

this AD, or within 30 days after the effective 

date of this AD, whichever occurs later. 

(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: The initial 

compliance time for the leak check 

inspection specified in the applicable task 

identified in paragraph (j) of this AD, is at the 

later of the times specified in paragraphs 

(i)(2)(i) and (i)(2)(ii) of this AD. 

(i) Within 550 flight hours after the 

installation of the P/N 1159SCP500–7 pump; 

except if 550 flight hours have accumulated 

since installation of the P/N 1159SCP500–7 

pump and an initial leak check of the pump 

has not been accomplished, the compliance 

time is within 50 flight hours after doing the 

inspection required by paragraph (g) of this 

AD. 

(ii) Within 30 days after the effective date 

of this AD. 

(j) Service Information for Maintenance 

Program Revision 

Use the applicable service information 

specified in paragraph (j)(1), (j)(2), or (j)(3) of 

this AD to revise the airplane maintenance or 

inspection program, as applicable, as 

required by paragraph (i) of this AD. 

(1) For Model GV airplanes: Use table 

18, ‘‘500 Flight Hours Scheduled 

Inspection Table,’’ in section 05–20–00, 

of chapter 5, Time Limits/Maintenance 

Checks; and task 28–26–01, Fuel Boost 

Pumps—Fuel Leak Check, of chapter 28, 

Fuel; of the Gulfstream V Maintenance 

Manual, Revision 42, dated June 20, 

2013. 

(2) For Model GV–SP airplanes 

designated as G500: Use task 28–26–01, 

Fuel Boost Pumps—Fuel Leak Checks, 

in table 20, ‘‘500 Flight Hours 

Scheduled Inspection Table,’’ in section 

05–20–00, of chapter 5, Time Limits/

Maintenance Checks; and task 28–26– 

01, Fuel Boost Pumps—Fuel Leak 

Check, of section 26, Fuel Boost Pumps, 

of chapter 28, Fuel; of the Gulfstream 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Proposed Rules 80299 

G500 Maintenance Manual, Revision 23, 

dated June 20, 2013. 

(3) For Model GV–SP airplanes 

designated as G550: Use task 28–26–01, 

Fuel Boost Pumps—Fuel Leak Check, in 

table 20, ‘‘500 Flight Hours Scheduled 

Inspection Table,’’ in section 05–20–00, 

of chapter 5, Time Limits/Maintenance 

Checks; and task 28–26–01, Fuel Boost 

Pumps—Fuel Leak Check, of section 26, 

Fuel Boost Pumps, of chapter 28, Fuel; 

of the Gulfstream G550 Maintenance 

Manual, Revision 23, dated June 20, 

2013. 

(k) 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 (m) of this AD. 

(l) Parts Installation Prohibition 

As of January 7, 2014 (the effective 

date of AD 2013–22–19, Amendment 

39–17651 (78 FR 72554, December 3, 

2013)), no person may install a fuel 

boost pump having Gulfstream P/N 

1159SCP500–5 on any airplane. 

(m) 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 (n)(1) 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. 

(3) AMOCs approved for AD 2013– 

22–19, Amendment 39–17651 (78 FR 

72554, December 3, 2013), are approved 

as AMOCs for the corresponding 

provisions of this AD. 

(4) For service information that 

contains steps that are labeled as 

Required for Compliance (RC), the 

provisions of paragraphs (m)(4)(i) and 

(m)(4)(ii) apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any 

figures identified in an RC step, must be 

done to comply with the AD. An AMOC 

is required for any deviations to RC 

steps, including substeps and identified 

figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods 

in accordance with the operator’s 

maintenance or inspection program 

without obtaining approval of an 

AMOC, provided the RC steps, 

including substeps and identified 

figures, can still be done as specified, 

and the airplane can be put back in an 

airworthy condition. 

(n) Related Information 

(1) For more information about this 

AD, contact Sanjana Murthy, Aersopace 

Engineer, ACE–118A, FAA, Atlanta 

Aircraft Certification Office, 1701 

Columbia Avenue, College Park, GA 

30337; telephone: 404–474–5573; fax: 

404–474–5567; email: sanjana.murthy@

faa.gov. 

(2) For 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, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

November 24, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–30810 Filed 12–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–7530; Directorate 

Identifier 2014–NM–257–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Fokker Services B.V. Model F.28 Mark 

0070 and 0100 airplanes. This proposed 

AD was prompted by a report of 

cracking in a certain section of the 

secondary structure of the wing. This 

proposed AD would require a one-time 

inspection of the trailing edge rib, and 

corrective action if necessary. We are 

proposing this AD to detect and correct 

cracking that could lead to failure of the 

affected rib and consequent reduced 

control of the airplane. 

DATES: We must receive comments on 

this proposed AD by February 8, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Fokker 

Services B.V., Technical Services Dept., 

P.O. Box 1357, 2130 EL Hoofddorp, the 

Netherlands; telephone +31 (0)88–6280– 

350; fax +31 (0)88–6280–111; email 

technicalservices@fokker.com; Internet 

http://www.myfokkerfleet.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–2015–

7530; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, ANM 

116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; telephone 425–227– 

1137; fax 425–227–1139. 


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