63272 Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

Airbus: Docket No. FAA–2012–1076; 

Directorate Identifier 2011–NM–274–AD. 

(a) Comments Due Date 

We must receive comments by November 

30, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A320– 

214, –232, and –233; and Model A321–211, 

–213, and –231 airplanes; certificated in any 

category; manufacturer serial numbers 4338, 

4371, 4374, 4375, 4377, 4381 through 4384 

inclusive, 4386, 4387, 4388, 4390 through 

4402 inclusive, 4404 through 4409 inclusive, 

4411 through 4417 inclusive, 4419, 4420, 

4421, 4423, 4424, 4426, 4429 through 4436 

inclusive, 4438 through 4443 inclusive, 4445 

through 4450 inclusive, 4453, 4454, 4456 

through 4469 inclusive, 4471, 4472, 4474 

through 4481 inclusive, 4483 through 4498 

inclusive, 4500, 4504, 4505, 4506, and 4509. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of a 

missing fastener between certain stringers of 

the fuselage frame which connects the frame 

to a tee. We are issuing this AD to detect and 

correct cracking in the fuselage that could 

result in reduced structural integrity of the 

airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspection 

Before the accumulation of 24,000 total 

flight cycles since first flight of the airplane, 

or within 30 days after the effective date of 

this AD, whichever occurs later: Do a rototest 

inspection for cracking of the two adjacent 

fastener holes at fuselage frame (FR) 24 

between stringer 25 and stringer 26 righthand side, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1247, excluding 

Appendix 01, dated July 15, 2011. 

(1) If, during the rototest inspection 

required by paragraph (g) of this AD, any 

crack is found, before further flight, repair 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). 

(2) If, during the rototest inspection 

required by paragraph (g) of this AD, no crack 

is found, before the accumulation of 24,000 

total flight cycles since first flight of the 

airplane, or within 30 days after the effective 

date of this AD, whichever occurs later, 

modify fuselage frame FR 24 between stringer 

25 and stringer 26 right-hand side, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1247, excluding Appendix 01, dated July 

15, 2011. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1405; fax (425) 227– 

1149. Information may be emailed to: 9-

ANM-116-AMOC-REQUESTS@faa.gov. 

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. 

(i) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2011–0229, dated 

December 6, 2011; and Airbus Service 

Bulletin A320–53–1247, excluding Appendix 

01, dated July 15, 2011. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.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 October 

5, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–25461 Filed 10–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1077; Directorate 

Identifier 2012–NM–146–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 adopt a new 

airworthiness directive (AD) for certain 

Embraer S.A. Model ERJ 170 and ERJ 

190 airplanes. This proposed AD was 

prompted by a report that high rate 

discharge (HRD) bottle explosive 

cartridges of a cargo compartment fire 

extinguisher system were swapped 

between the forward and aft cargo 

compartments. Additional investigation 

also revealed the possibility of 

swapping between the electrical 

connectors of the HRD and low rate 

discharge (LRD) bottles, and a rotated 

installation of the HRD bottle. Improper 

assembly of the fire extinguishing bottle 

might cause the extinguishing agent to 

be discharged toward the unselected 

cargo compartment rather than toward 

the cargo compartment with fire. This 

proposed AD would require an 

inspection of the HRD bottle for correct 

installation and to determine if the 

pressure switch is in the correct 

position, and re-installation if 

necessary; an inspection of the HRD and 

LRD bottle discharge heads to determine 

the part number and replacement if 

necessary; and, for certain airplanes, an 

inspection to determine the part 

numbers of the HRD and LRD electrical 

connectors, and relocation if necessary. 

We are proposing this AD to prevent the 

inability of the fire extinguishing system 

to suppress fire. 

DATES: We must receive comments on 

this proposed AD by November 30, 

2012. 

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– 


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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–2012–1077; Directorate Identifier 

2012–NM–146–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 

The Ageˆncia Nacional de Aviac ̧a ̃o 

Civil (ANAC), which is the aviation 

authority for Brazil, has issued Brazilian 

Airworthiness Directives 2012–07–01 

and 2012–07–02, both effective July 30, 

2012 (referred to after this as ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

It was found during an inspection of the 

cargo compartment fire extinguisher system 

that High Rate Discharge (HRD) bottle 

explosive cartridges were swapped between 

forward and aft cargo compartments. 

Additional investigation has also revealed 

the possibility of swapping between the 

electrical connectors of the HRD and Low 

Rate Discharge (LRD) bottles and a rotated 

installation of the HRD bottle. Such improper 

assembly of the fire extinguishing bottle may 

cause the extinguishing agent to be 

discharged toward the unselected cargo 

compartment rather than toward the cargo 

compartment with fire, resulting in an 

insufficient concentration of fire 

extinguishing agent in the cargo 

compartment with fire, and consequent 

inability of the fire extinguishing system to 

suppress fire. 

* * * * * 

Required actions include an inspection 

of the HRD bottle for correct installation 

and to determine if the pressure switch 

is in the correct position, and reinstallation if necessary; an inspection 

of the HRD and LRD bottle discharge 

heads to determine the part number and 

replacement if necessary; and, for 

certain airplanes, an inspection to 

determine the part numbers of the HRD 

and LRD electrical connectors, and 

relocation if necessary. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Embraer has issued the following 

service bulletins to correct the unsafe 

condition identified in the MCAI. 

• EMBRAER Service Bulletin 170– 

26–0011, Revision 01, dated June 19, 

2012 (for Model ERJ 170–100 LR, –100 

STD, –100 SE, and –100 SU airplanes; 

and Model ERJ 170–200 LR, –200 SU, 

and –200 STD airplanes). 

• EMBRAER Service Bulletin 190– 

26–0011, Revision 01, dated June 19, 

2012 (for Model ERJ 190–100 STD, –100 

LR, –100 ECJ, and –100 IGW airplanes; 

and Model ERJ 190–200 STD, –200 LR, 

and –200 IGW airplanes). 

• EMBRAER Service Bulletin 

190LIN–26–0006, Revision 01, dated 

June 19, 2012 (for Model ERJ 190–100 

STD, –100 LR, –100 ECJ, and –100 IGW 

airplanes; and Model ERJ 190–200 STD, 

–200 LR, and –200 IGW airplanes). 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 163 products of U.S. 

registry. We also estimate that it would 

take about 7 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$96,985, or $595 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 1 work-hour and require parts 

costing $68,588, for a cost of $68,673 

per product. We have no way of 

determining the number of products 

that may need these actions. 

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 


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63274 Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 AD: 

Embraer S.A.: Docket No. FAA–2012–1077; 

Directorate Identifier 2012–NM–146–AD. 

(a) Comments Due Date 

We must receive comments by November 

30, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD. 

(1) Embraer S.A. Model ERJ 170–100 LR, 

–100 STD, –100 SE, and –100 SU airplanes; 

and Model ERJ 170–200 LR, –200 SU, and 

–200 STD airplanes; certificated in any 

category; as identified in EMBRAER Service 

Bulletin 170–26–0011, Revision 01, dated 

June 19, 2012. 

(2) Embraer S.A. Model ERJ 190–100 STD, 

–100 LR, –100 ECJ, and –100 IGW airplanes; 

and Model ERJ 190–200 STD, –200 LR, and 

–200 IGW airplanes; certificated in any 

category; as identified in EMBRAER Service 

Bulletins 190–26–0011, Revision 01, dated 

June 19, 2012, and 190LIN–26–0006, 

Revision 01, dated June 19, 2012. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 26, Fire Protection. 

(e) Reason 

This AD was prompted by a report that 

high rate discharge (HRD) bottle explosive 

cartridges of a cargo compartment fire 

extinguisher system were swapped between 

the forward and aft cargo compartments. 

Additional investigation also revealed the 

possibility of swapping between the 

electrical connectors of the HRD and low rate 

discharge (LRD) bottles, and a rotated 

installation of the HRD bottle. We are issuing 

this AD to prevent the inability of the fire 

extinguishing system to suppress fire. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspections and Corrective Actions for 

Group 1 Airplanes 

For airplanes on which EMBRAER Service 

Bulletin 170–26–0011, dated December 1, 

2011 (for Model ERJ 170–100 LR, –100 STD, 

–100 SE, and –100 SU airplanes; and Model 

ERJ 170–200 LR, –200 SU, and –200 STD 

airplanes); EMBRAER Service Bulletin 190– 

26–0011, dated December 1, 2011 (for Model 

ERJ 190–100 STD, –100 LR, –100 ECJ, and 

–100 IGW airplanes; and Model ERJ 190–200 

STD, –200 LR, and –200 IGW airplanes); or 

EMBRAER Service Bulletin 190LIN–26–0006, 

dated December 1, 2011 (for Model ERJ 190– 

100 STD, –100 LR, –100 ECJ, and –100 IGW 

airplanes; and Model ERJ 190–200 STD, –200 

LR, and –200 IGW airplanes); has not been 

accomplished as of the effective date of this 

AD: Within 3,000 flight hours after the 

effective date of this AD, do the actions 

specified in paragraphs (g)(1), (g)(2), and 

(g)(3) of this AD. All actions must be done 

in accordance with Part I and Part II, as 

applicable, of the Accomplishment 

Instructions of EMBRAER Service Bulletin 

170–26–0011, Revision 01, dated June 19, 

2012 (for Model ERJ 170–100 LR, –100 STD, 

–100 SE, and –100 SU airplanes; and Model 

ERJ 170–200 LR, –200 SU, and –200 STD 

airplanes); EMBRAER Service Bulletin 190– 

26–0011, Revision 01, dated June 19, 2012 

(for Model ERJ 190–100 STD, –100 LR, –100 

ECJ, and –100 IGW airplanes; and Model ERJ 

190–200 STD, –200 LR, and –200 IGW 

airplanes); or EMBRAER Service Bulletin 

190LIN–26–0006, Revision 01, dated June 19, 

2012 (for Model ERJ 190–100 STD, –100 LR, 

–100 ECJ, and –100 IGW airplanes; and 

Model ERJ 190–200 STD, –200 LR, and –200 

IGW airplanes). 

(1) Do a general visual inspection of the 

HRD bottle to determine if it is correctly 

installed and if the pressure switch is in the 

correct position. If the bottle is not correctly 

installed or the pressure switch is in the 

incorrect position, before further flight, 

remove and re-install the HRD bottle. 

(2) Inspect the HRD and LRD bottle 

discharge heads to determine the part 

number. If the part number of the discharge 

heads is not the part number specified in 

Figure 3 of EMBRAER Service Bulletin 170– 

26–0011, Revision 01, dated June 19, 2012 

(for Model ERJ 170–100 LR, –100 STD, –100 

SE, and –100 SU airplanes; and Model ERJ 

170–200 LR, –200 SU, and –200 STD 

airplanes); EMBRAER Service Bulletin 190– 

26–0011, Revision 01, dated June 19, 2012 

(for Model ERJ 190–100 STD, –100 LR, –100 

ECJ, and –100 IGW airplanes; and Model ERJ 

190–200 STD, –200 LR, and –200 IGW 

airplanes); or EMBRAER Service Bulletin 

190LIN–26–0006, Revision 01, dated June 19, 

2012 (for Model ERJ 190–100 STD, –100 LR, 

–100 ECJ, and –100 IGW airplanes; and 

Model ERJ 190–200 STD, –200 LR, and –200 

IGW airplanes); before further flight, replace 

the discharge bottle with a discharge bottle 

having the same part number. 

(3) Inspect to determine the part numbers 

of the HRD and LRD bottle electrical 

connectors. If the part numbers of the HRD 

or LRD bottle electrical connectors are not 

the part numbers specified in Figure 1 of 

EMBRAER Service Bulletin 170–26–0011, 

Revision 01, dated June 19, 2012 (for Model 

ERJ 170–100 LR, –100 STD, –100 SE, and 

–100 SU airplanes; and Model ERJ 170–200 

LR, –200 SU, and –200 STD airplanes); 

EMBRAER Service Bulletin 190–26–0011, 

Revision 01, dated June 19, 2012 (for Model 

ERJ 190–100 STD, –100 LR, –100 ECJ, and 

–100 IGW airplanes; and Model ERJ 190–200 

STD, –200 LR, and –200 IGW airplanes); or 

EMBRAER Service Bulletin 190LIN–26–0006, 

Revision 01, dated June 19, 2012 (for Model 

ERJ 190–100 STD, –100 LR, –100 ECJ, and 

–100 IGW airplanes; and Model ERJ 190–200 

STD, –200 LR, and –200 IGW airplanes); 

before further flight, relocate the HRD or LRD 

bottle electrical connectors by re–routing the 

electrical harness. 

(h) Inspections and Corrective Actions for 

Group 2 Airplanes 

For airplanes on which EMBRAER Service 

Bulletin 170–26–0011, dated December 1, 

2011 (for Model ERJ 170–100 LR, –100 STD, 

–100 SE, and –100 SU airplanes; and Model 

ERJ 170–200 LR, –200 SU, and –200 STD 

airplanes); EMBRAER Service Bulletin 190– 

26–0011, dated December 1, 2011 (for Model 

ERJ 190–100 STD, –100 LR, –100 ECJ, and 

–100 IGW airplanes; and Model ERJ 190–200 

STD, –200 LR, and –200 IGW airplanes); or 

EMBRAER Service Bulletin 190LIN–26–0006, 

dated December 1, 2011 (for Model ERJ 190– 

100 STD, –100 LR, –100 ECJ, and –100 IGW 

airplanes; and Model ERJ 190–200 STD, –200 

LR, and –200 IGW airplanes); has been 

accomplished as of the effective date of this 

AD: Within 3,000 flight hours after the 

effective date of this AD, do the actions 

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

this AD. All actions must be done in 

accordance with Part III of the 

Accomplishment Instructions of EMBRAER 

Service Bulletins 170–26–0011, Revision 01, 

dated June 19, 2012 (for Model ERJ 170–100 

LR, –100 STD, –100 SE, and –100 SU 

airplanes; and Model ERJ 170–200 LR, –200 

SU, and –200 STD airplanes); EMBRAER 

Service Bulletin 190–26–0011, Revision 01, 

dated June 19, 2012 (for Model ERJ 190–100 

STD, –100 LR, –100 ECJ, and –100 IGW 

airplanes; and Model ERJ 190–200 STD, –200 

LR, and –200 IGW airplanes); or EMBRAER 

Service Bulletin 190LIN–26–0006, Revision 


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01, dated June 19, 2012 (for Model ERJ 190– 

100 STD, –100 LR, –100 ECJ, and –100 IGW 

airplanes; and Model ERJ 190–200 STD, –200 

LR, and –200 IGW airplanes). 

(1) Do a general visual inspection of the 

HRD bottle to determine if it is correctly 

installed and if the pressure switch is in the 

correct position. If the bottle is not correctly 

installed or the pressure switch is in the 

incorrect position, before further flight, 

remove and re–install the HRD bottle. 

(2) Inspect the HRD and LRD bottle 

discharge heads to determine the part 

number. If the part number of the discharge 

heads is not the part number specified in 

Figure 3 of EMBRAER Service Bulletin 170– 

26–0011, Revision 01, dated June 19, 2012 

(for Model ERJ 170–100 LR, –100 STD, –100 

SE, and –100 SU airplanes; and Model ERJ 

170–200 LR, –200 SU, and –200 STD 

airplanes); EMBRAER Service Bulletin 190– 

26–0011, Revision 01, dated June 19, 2012 

(for Model ERJ 190–100 STD, –100 LR, –100 

ECJ, and –100 IGW airplanes; and Model ERJ 

190–200 STD, –200 LR, and –200 IGW 

airplanes); or EMBRAER Service Bulletin 

190LIN–26–0006, Revision 01, dated June 19, 

2012 (for Model ERJ 190–100 STD, –100 LR, 

–100 ECJ, and –100 IGW airplanes; and 

Model ERJ 190–200 STD, –200 LR, and –200 

IGW airplanes), before further flight, replace 

the discharge bottle with a discharge bottle 

having the same part number. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 International Branch, send it to ATTN: 

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. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. 

(j) Related Information 

(1) Refer to MCAI Brazilian Airworthiness 

Directives 2012–07–01 and 2012–07–02, both 

effective July 30, 2012, and the service 

bulletins identified in paragraphs (j)(1)(i), 

(j)(1)(ii), and (j)(1)(iii) of this AD, for related 

information. 

(i) EMBRAER Service Bulletin 170–26– 

0011, Revision 01, dated June 19, 2012. 

(ii) EMBRAER Service Bulletin 190–26– 

0011, Revision 01, dated June 19, 2012. 

(iii) EMBRAER Service Bulletin 190LIN– 

26–0006, Revision 01, dated June 19, 2012. 

(2) For service information identified in 

this 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. 

Issued in Renton, Washington, on October 

5, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–25459 Filed 10–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1078; Directorate 

Identifier 2011–NM–012–AD] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company 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 all Lockheed Martin 

Corporation/Lockheed Martin 

Aeronautics Company Model L–1011 

series airplanes. The existing AD 

currently requires repetitive inspections 

to detect corrosion or fatigue cracking of 

certain structural elements of the 

airplane; corrective actions if necessary; 

and incorporation of certain structural 

modifications. Since we issued that AD, 

we have received reports of small cracks 

in additional areas outside those 

addressed in the existing AD, prior to 

the inspection threshold required by the 

existing AD. This proposed AD would 

reduce certain compliance times for the 

initial inspection, and the repetitive 

inspection interval for certain airplanes. 

We are proposing this AD to prevent 

corrosion or fatigue cracking of certain 

structural elements, which could result 

in reduced structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by November 30, 

2012. 

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 service information identified in 

this AD, contact Lockheed Martin 

Corporation/Lockheed Martin 

Aeronautics Company, Airworthiness 

Office, Dept. 6A0M, Zone 0252, Column 

P–58, 86 S. Cobb Drive, Marietta, 

Georgia 30063; telephone 770–494– 

5444; fax 770–494–5445; email 

ams.portal@lmco.com; Internet http:// 

www.lockheedmartin.com/ams/tools/ 

TechPubs.html. 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. 

FOR FURTHER INFORMATION CONTACT: Carl 

Gray, Aerospace Engineer, Airframe 

Branch, ACE–117A, FAA, Atlanta 

Aircraft Certification Office (ACO), 1701 

Columbia Avenue, College Park, Georgia 

30337; phone: 404–474–5554; fax: 404– 

474–5605; email: carl.w.gray@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1