## 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) 24between 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–


## 63273 Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules

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 Age ˆ ncia 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 switchis 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


## 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


## 63275 Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules

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