75908 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Proposed Rules 

with a new bellcrank, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–55, dated June 15, 

2011. 

(i) Actions for Certain Other Model DHC–8– 

400 Series Airplanes 

For Model DHC–8–400, –401, and –402 

airplanes that have accumulated more than 

15,000 total flight hours as of the effective 

date of this AD: Within 600 flight hours after 

the effective date of this AD, measure the 

edge-to-edge length of the clevis holes of 

each bellcrank, and inspect for cracking of 

each bellcrank using liquid penetrant; in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–55, dated June 15, 2011. 

(1) If no cracking is found, and the edgeto-edge length of all clevis holes is less than 

or equal to 0.218 inch: At the later of the 

compliance times specified in paragraphs 

(i)(1)(i) and (i)(1)(ii) of this AD, rework or 

replace the bellcrank, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–55, dated June 15, 

2011. 

(i) Within 6,000 flight hours after the 

effective date of this AD, but not to exceed 

15,600 total flight hours. 

(ii) Within 1,200 flight hours after the 

effective date of this AD. 

(2) If no cracking is found, and any clevis 

hole edge-to-edge length is greater than 0.218 

inch but less than or equal to 0.248 inch: 

Within 6,000 flight hours after the effective 

date of this AD, replace the bellcrank with a 

new bellcrank, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–55, dated June 15, 

2011. 

(3) If no cracking is found, and any clevis 

hole edge-to-edge length is greater than 0.248 

inch but less than or equal to 0.278 inch: 

Within 1,200 flight hours after the effective 

date of this AD, replace the bellcrank with a 

new bellcrank, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–55, dated June 15, 

2011. 

(4) If any cracking is found, or any clevis 

hole edge-to-edge length exceeds 0.278 inch: 

Before further flight, replace the bellcrank 

with a new bellcrank, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–55, dated June 15, 

2011. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(k) Related Information 

(1) Refer to MCAI Canadian Airworthiness 

Directive CF–2011–32, dated August 15, 

2011, and the service bulletins specified in 

paragraphs (k)(1) (i) and (k)(1)(ii) of this AD, 

for related information. 

(i) Bombardier Service Bulletin 8–27–111, 

dated June 15, 2011. 

(ii) Bombardier Service Bulletin 84–27–55, 

dated June 15, 2011. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., Q–Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. You 

may review copies of the 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 

December 17, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–30925 Filed 12–21–12; 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] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace Corporation 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Gulfstream Aerospace Corporation 

Model GV and GV–SP airplanes. This 

proposed AD was prompted by reports 

of two failures of the fuel boost pump 

and over-heat damage found on the 

internal components and external 

housing. 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, and revising the 

airplane maintenance program to 

include revised instructions for 

continued airworthiness. We are 

proposing this AD to prevent fuel 

leakage into the dry cavity of the boost 

pump and outside of the fuel pump, and 

to prevent capacitor clearance issues in 

the dry cavity, which together could 

result in an uncontrolled fire in the 

wheel well. 

DATES: We must receive comments on 

this proposed AD by February 11, 2013. 

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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For Gulfstream, Triumph 

Aerostructures, and GE Aviation 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 review copies of the 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; 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. 


ebenthall on DSK5TPTVN1PROD with 
Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Proposed Rules 75909 

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; 

telephone (404) 474–5573; fax (404) 

474–5606; email: 

darby.mirocha@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–1313; Directorate Identifier 2012– 

NM–080–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 have received a report of failure 

of the fuel boost pump and over-heat 

damage found on the internal 

components and external housing. A 

subsequent investigation identified 

inadequate clearance between the 

internal capacitor and a printed circuit 

board as the root cause of the failure. 

Additionally, on other components, a 

damaged o-ring between the ‘‘wet’’ and 

‘‘dry’’ cavities of the boost pump 

resulted in fuel ingress into the ‘‘dry’’ 

cavity. Product improvements have 

been incorporated into the boost pumps 

to modify the capacitor installation to 

prevent external shorting and 

incorporate an inspection port to allow 

for inspection of the ‘‘dry’’ cavity. This 

condition, if not corrected, could cause 

fuel leakage into the dry cavity of the 

boost pump and outside of the fuel 

pump, and capacitor clearance issues in 

the dry cavity, which together could 

result in an uncontrolled fire in the 

wheel well. 

Relevant Service Information 

We reviewed Gulfstream V Service 

Bulletin 197 (for Model GV airplanes), 

and Gulfstream G550 Service Bulletin 

122 (for Model GV–SP airplanes), both 

dated April 11, 2012, both including the 

following service information: 

• Triumph Service Bulletin SB– 

TAGV/GVSP–28–JG0162, dated August 

30, 2011. 

• GE Service Bulletin 31760–28–100, 

dated February 15, 2011. 

This service information describes 

procedures for doing an inspection to 

determine if fuel boost pumps having a 

certain part number are installed, and 

replacing the fuel boost pumps having 

a certain part number. 

We have also reviewed Gulfstream 

Document GV–GER–0003, Instructions 

for Continued Airworthiness, Fuel Boost 

Pump with Leak Check Port, dated 

November 24, 2010. This service 

information describes procedures for 

fuel leak checks of the fuel boost pump. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Information.’’ 

Differences Between the Proposed AD 

and the Service Information 

Gulfstream V Service Bulletin 197 (for 

Model GV airplanes) and Gulfstream 

G550 Service Bulletin 122 (for Model 

GV–SP airplanes), both dated April 11, 

2012, specify a compliance time of 42 

months after the release of those service 

bulletins for accomplishing the actions 

in those service bulletins. This proposed 

AD requires a compliance time of 36 

months after the effective date of this 

proposed AD. In developing the 

compliance time, we considered not 

only the degree of urgency associated 

with addressing the subject unsafe 

condition, but the manufacturer’s 

recommendation for an appropriate 

compliance time, the availability of 

required parts, and the practical aspect 

of doing the actions within an interval 

of time that corresponds to the typical 

scheduled maintenance for the majority 

of affected operators. This difference has 

been coordinated with Gulfstream. 

Costs of Compliance 

We estimate that this proposed AD 

affects 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.

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

Maintenance program revision 1 work-hour X $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 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

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


ebenthall on DSK5TPTVN1PROD with 
75910 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Proposed Rules 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Gulfstream Aerospace Corporation: Docket 

No. FAA–2012–1313; Directorate 

Identifier 2012–NM–080–AD. 

(a) Comments Due Date 

We must receive comments by February 

11, 2013. 

(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 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 2822, Fuel boost pump. 

(e) Unsafe Condition 

This AD was prompted reports of two 

failures of the fuel boost pump and over-heat 

damage found on the internal components 

and external housing. We are issuing this AD 

to prevent fuel leakage into the dry cavity of 

the boost pump and outside of the fuel 

pump, and to prevent capacitor clearance 

issues in the dry cavity, which together 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 P/N 1159SCP500–5 is 

installed, in accordance with the 

Accomplishment Instructions of Gulfstream 

V Service Bulletin 197, dated April 11, 2012 

(for Model GV airplanes); or Gulfstream G550 

Service Bulletin 122, dated April 11, 2012 

(for Model GV–SP airplanes); including the 

service information specified in paragraphs 

(g)(1) and (g)(2) of this AD. 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 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 P/ 

N 1159SCP500–5: Before further flight, 

replace the fuel boost pump with a 

serviceable pump having P/N 1159SCP500– 

7, in accordance with Gulfstream V Service 

Bulletin 197, dated April 11, 2012 (for Model 

GV airplanes); or Gulfstream G550 Service 

Bulletin 122, dated April 11, 2012 (for Model 

GV–SP airplanes); including the service 

information specified in paragraphs (h)(1) 

and (h)(2) of this AD. 

(1) Triumph 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 

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 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 (AMOC) 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 

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 the 

Related Information section 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 

(1) 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; telephone (404) 

474–5573; fax (404) 474–5606; email: 

darby.mirocha@faa.gov. 

(2) For Gulfstream, Triumph 

Aerostructures, and GE Aviation service 

information identified in this AD, contact 

Gulfstream Aerospace Corporation, Technical 

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


ebenthall on DSK5TPTVN1PROD with 
Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Proposed Rules 75911 

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 

review copies of the 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. 

Issued in Renton, Washington, on 

December 17, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–31036 Filed 12–21–12; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1230; Directorate 

Identifier 2011–NM–107–AD] 

RIN 2120–AA64 

Airworthiness Directives; Embraer S.A. 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain Embraer S.A. 

Model ERJ 170 and ERJ 190 airplanes. 

The existing AD currently requires, for 

certain airplanes, repetitively replacing 

the low-stage check valve and 

associated seals of the right hand (RH) 

engine’s engine bleed system with a 

new check valve and new seals, 

replacing the low pressure check valves 

(LPCV), and revising the maintenance 

program. For certain other airplanes, the 

existing AD requires replacing a certain 

low-stage check valve with an improved 

low-stage check valve. Since we issued 

that AD, we have received reports of 

uncommanded engine shutdowns on 

both Model ERJ 170 and ERJ 190 

airplanes due to excessive wear and 

failure of LPCVs having certain part 

numbers. This proposed AD would also, 

for certain airplanes, require replacing 

certain LPCVs of the left-hand (LH) and 

RH engines, which would be an option 

for other airplanes. We are proposing 

this AD to prevent the possibility of a 

dual engine in-flight shutdown due to 

LPCV failure. 

DATES: We must receive comments on 

this proposed AD by February 11, 2013. 

ADDRESSES: You may send comments 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 Embraer S.A., 

Technical Publications Section (PC 

060), Av. Brigadeiro Faria Lima, 2170— 

Putim—12227–901 Sa ̃o Jose dos 

Campos—SP—BRASIL; telephone +55 

12 3927–5852 or +55 12 3309–0732; fax 

+55 12 3927–7546; email 

distrib@embraer.com.br; Internet http:// 

www.flyembraer.com. You may review 

copies of the 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 Operations office 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: 

Cindy Ashforth, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–2768; 

fax (425) 227–1149. 

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–2012–1230; Directorate Identifier 

2011–NM–107–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 based on 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 

On June 23, 2010, we issued AD 

2010–14–14, Amendment 39–16359 (75 

FR 42585, July 22, 2010). That AD 

required actions intended to address an 

unsafe condition on Embraer S.A. 

Model ERJ 170 and ERJ 190 airplanes. 

Since we issued AD 2010–14–14, 

Amendment 39–16359 (75 FR 42585, 

July 22, 2010), there have been 

occurrences of uncommanded engine 

shutdowns on both Model ERJ 170 and 

Model ERJ 190 airplanes due to 

excessive wear and failure of LPCVs 

having part number 1001447–3 and 

1001447–4. Both engines of the 

airplanes have the same valves, which 

leads to the possibility of a dual engine 

in-flight shutdown due to LPCV failure. 

The Ageˆncia Nacional de Aviac ̧a ̃o Civil 

(ANAC), which is the aviation authority 

for Brazil, has issued Brazilian 

Airworthiness Directives 2005–09–03R3 

and 2006–11–01R6, both effective May 

30, 2011 (referred to after this as ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI for 

Embraer S.A. Model ERJ 170 airplanes 

states: 

It has been found the occurrence of an 

engine in-flight shutdown * * * caused by 

the LPCV [low pressure check valves] failure 

P/N [part number] 1001447–3 with 3,900 

Flight Hours (FH) installed on ERJ–170. This 

valve failed [to] open due [to] excessive wear. 

[I]t was found the occurrence of an engine 

shutdown on-ground, caused by the LPCV 

failure P/N 1001447–4 with 1,802 FH 

installed on ERJ–190 failed due [to] low cycle 

fatigue. Since the behavior of a valve P/N 

1001447–4 removed from ERJ–190 is 

unknown on ERJ–170 and the P/N 1001447– 

4 is common between ERJ–170 and ERJ–190 

airplane fleet, an action is necessary to 

prevent the installation, in ERJ–170 

airplanes, of LPCVs P/N 1001447–4 

previously installed in ERJ–190 airplanes. 

* * * * * 

The MCAI for Embraer S.A. Model 

ERJ 190 airplanes states: 

It has been found the occurrence of an 

engine in-flight shutdown * * * caused by 

the LPCV failure P/N [part number] 1001447– 

3 with 3,900 Flight Hours (FH) installed on 

ERJ–170. This valve failed [to] open due [to] 

excessive wear. [I]t was found the occurrence 

of an engine shutdown on-ground, caused by 


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