### 29855 Federal Register / Vol. 77, No. 98 / Monday, May 21, 2012 / Rules and Regulations

Issued in Washington, DC, on May 15,
2012. David G. Frantz, Acting Executive Director, Loan Programs Office.

For the reasons set forth in the preamble, DOE hereby amends Part 609 of chapter II of title 10 of the Code of Federal Regulations as set forth below:

**PART 609—LOAN GUARANTEES FOR PROJECTS THAT EMPLOY**  **INNOVATIVE TECHNOLOGIES**

■ 1. The authority citation for part 609 continues to read as follows:

Authority: 42 U.S.C. 7254, 16511–16514.

■ 2. In § 609.8 revise paragraph (d) to read as follows:

**§ 609.8 Term sheets and conditional commitments.** 
* * * * *

(d) DOE’s obligations under each Conditional Commitment are conditional upon statutory authority having been provided in advance of the execution of the Loan Guarantee Agreement sufficient under FCRA and Title XVII for DOE to execute the Loan Guarantee Agreement, and payment in full of the Credit Subsidy Cost for the loan guarantee that is the subject of the Conditional Commitment from one of the following:

(1) A Congressional appropriation of funds;

(2) A payment from the Borrower deposited into the Treasury; or

(3) A combination of one or more appropriations under paragraph (d)(1) and one or more payments from the Borrower under paragraph (d)(2) of this section.

* * * * *

■ 3. In § 609.9 revise paragraph (d)(1) to read as follows:

**§ 609.9 Closing on the Loan Guarantee Agreement.** 
* * * * *

(d) * * * (1) Pursuant to section 1702(b) of the Act, DOE has received payment in full of the Credit Subsidy Cost of the loan guarantee from one of the following:

(i) A Congressional appropriation of funds;

(ii) A payment from the Borrower deposited into the Treasury; or

(iii) A combination of one or more appropriations under paragraph (d)(1)(i) and one or more payments from the Borrower under paragraph (d)(1)(ii) of this section.

* * * * *

■ 4. In § 609.10 revise paragraph (d)(17) to read as follows: **§ 609.10 Loan Guarantee Agreement.**
* * * * *

(d) * * * (17) If Borrower is to make payment in full or in part for the Credit Subsidy Cost of the loan guarantee pursuant to section 1702(b)(2) of the Act, such payment must be received by DOE prior to, or at the time of, closing;

* * * * * [FR Doc. 2012–12218 Filed 5–18–12; 8:45 am]

**BILLING CODE 6450–01–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0184; Directorate Identifier 2011–NM–118–AD; Amendment**  **39–17055; AD 2012–10–06]**

**RIN 2120–AA64**

**Airworthiness Directives; Saab AB, Saab Aerosystems Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for all Saab AB, Saab Aerosystems Model SAAB 2000 airplanes. This AD was prompted by reports that environmentally friendly de-icing agents used on certain electrical connectors and braids could cause corrosion damage. This AD requires performing, in certain locations, a detailed inspection for corrosion of the electrical and electronics installation, and if corrosion is found repairing each affected harness braid or replacing each affected component and/or wiring harness. We are issuing this AD to detect and correct corrosion of critical system wiring, which could result in arcing and, in combination with other factors, a fire and consequent damage to the airplane.

**DATES :**  This AD becomes effective June 25, 2012.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 25, 2012.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC.

**FOR FURTHER INFORMATION CONTACT :**  Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM– 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1112; fax (425) 227–1149.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on February 28, 2012 (77 FR 11791). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

Environmentally friendly de-/anti-icing agents (acetates or formats) are a known cause of corrosion damage to components of the Electrical Wiring Interconnection System (EWIS) on aeroplanes.

Investigations by SAAB have identified certain electrical connectors and braids which are susceptible to such damage, in zones 191 and 192 of the center wing fuselage and in zones 323, 332 and 342, affecting the wiring harnesses of elevator and rudder servos.

This condition, if not detected and corrected, could lead to damage of critical system wiring, possibly resulting in arcing and, in combination with other factors, a fire and consequent damage to, or loss of, the aeroplane.

To address this unsafe condition, SAAB have issued Service Bulletin (SB) 2000–92– 005 and SB 2000–92–006 to provide instructions to detect unacceptable corrosion on electrical and electronic installation wiring.

For the reasons described above, this [EASA] AD requires a one-time [detailed] inspection of the affected components in the designated area, the reporting of all inspections results to SAAB and, depending on findings, appropriate corrective action [repair or replacement]. You may obtain further information by examining the MCAI in the AD docket.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (77 FR 11791, February 28, 2012) or on the determination of the cost to the public.

Conclusion

We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance

We estimate that this AD will affect 10 products of U.S. registry. We also estimate that it will take about 360 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour.


### 29856 Federal Register / Vol. 77, No. 98 / Monday, May 21, 2012 / Rules and Regulations

Based on these figures, we estimate the cost of this AD to the U.S. operators to be $306,000, or $30,600 per product.

In addition, we estimate that any necessary follow-on actions would take about 40 work-hours and require parts costing $12,454, for a cost of $15,854 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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify that this AD:

1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866;

2. Is not a ‘‘significant rule’’ under 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 AD and placed it in the AD docket. 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 the NPRM (77 FR 11791, February 28, 2012), 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. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:

**PART 39—AIRWORTHINESS DIRECTIVES** 

■ 1. The authority citation for part 39 continues to read as follows:

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

**§ 39.13 [Amended]**

■ 2. The FAA amends § 39.13 by adding the following new AD:
2012–10–06 Saab AB, Saab Aerosystems: Amendment 39–17055. Docket No. FAA–2012–0184; Directorate Identifier 2011–NM–118–AD.
(a) Effective Date

This airworthiness directive (AD) becomes effective June 25, 2012.

(b) Affected ADs

None. (c) Applicability

This AD applies to all Saab AB, Saab Aerosystems Model SAAB 2000 airplanes; certificated in any category.
(d) Subject

Air Transport Association (ATA) of America Code 92.

(e) Reason

This AD was prompted by reports that environmentally friendly de-icing agents used on certain electrical connectors and braids could cause corrosion damage. We are issuing this AD to detect and correct corrosion of critical system wiring, which could result in arcing and, in combination with other factors, a fire and consequent damage to 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

Within 24 months after the effective date of this AD, do a detailed inspection for corrosion of the electrical and electronics installation, at the locations specified in and in accordance with the Accomplishment Instructions of SAAB Service Bulletin 2000– 92–005, Revision 01, dated March 1, 2011; and SAAB Service Bulletin 2000–92–006, Revision 01, dated August 18, 2010. These inspections do not need to be accomplished concurrently.
(h) Corrective Action

If any corrosion is found during any inspection required in paragraph (g) of this AD: Before next flight, repair each affected harness braid or replace each affected component and/or wiring harness, as applicable, in accordance with the Accomplishment Instructions of SAAB Service Bulletin 2000–92–005, Revision 01, dated March 1, 2011; and SAAB Service Bulletin 2000–92–006, Revision 01, dated August 18, 2010.
(i) Credit for Previous Actions

This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using SAAB Service Bulletin 2000–92–005, dated May 5, 2010; and SAAB Service Bulletin 2000–92–006, dated March 29, 2010.
(j) Reporting Requirement

Submit a report of the findings (both positive and negative) of the inspection required by paragraph (g) of this AD, using the Feedback Form in SAAB Service Bulletin 2000–92–005, Revision 01, dated March 1, 2011; and SAAB Service Bulletin 2000–92– 006, Revision 01, dated August 18, 2010. Send the report to SAAB Aerotech, Support Services Division, SE–581 88 Linkoping, Sweden; fax +46 13 18 4874; email saab2000.techsupport@saabgroup.com; at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD. The report must include the level of corrosion found on each
connector.

(1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.

(2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
(k) 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: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–1112; fax (425) 227–1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify


### 29857 Federal Register / Vol. 77, No. 98 / Monday, May 21, 2012 / Rules and Regulations

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.

(3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200.
(l) Related Information

Refer to MCAI EASA Airworthiness Directive 2011–0079, dated May 5, 2011, and the service information specified in paragraphs (l)(1) and (l)(2) of this AD, for related information.

(1) SAAB Service Bulletin 2000–92–005, Revision 01, dated March 1, 2011.

(2) SAAB Service Bulletin 2000–92–006, Revision 01, dated August 18, 2010.
(m) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise.

(i) SAAB Service Bulletin 2000–92–005, Revision 01, dated March 1, 2011.

(ii) SAAB Service Bulletin 2000–92–006, Revision 01, dated August 18, 2010.

(3) For Saab AB, Saab Aerosystems service information identified in this AD, contact Saab AB, Saab Aerosystems, SE–581 88, Linko  ̈ ping, Sweden; telephone +46 13 18 5591; fax +46 13 18 4874; email saab2000.techsupport@saabgroup.com; Internet http://www.saabgroup.com.

(4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call
425–227–1221.

(5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202–741– 6030, or go to http://www.archives.gov/ federal

_register/code

_ of

_ federal

_regulations/ ibr

_ locations.html. Issued in Renton, Washington, on May 9,
2012. Michael Kaszycki, Acting Manager,Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2012–11957 Filed 5–18–12; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0645; Directorate Identifier 2010–NM–009–AD; Amendment**  **39–17052; AD 2012–10–03]**

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 747 series airplanes. That AD currently requires repetitive inspections for cracks of the fuselage skin lap splice between body station (BS) 400 and BS 520 at stringers S–6L and S–6R, and repair if necessary. This new AD shortens the interval for the repetitive inspections, requires modification for certainairplanes, and requires certain postmodification inspections for other airplanes. This AD was prompted by reports of multiple adjacent cracks on an airplane, and a recent fleet-wide evaluation of widespread fatigue damage of skin lap joints, which indicated the need for revised procedures and reduced compliance times. We are issuing this AD to detect and correct cracking of the fuselage skin lap splice between BS 400 and BS 520 at stringers S–6L and S–6R, which could result in sudden loss of cabin pressurization and the inability of the fuselage to withstand fail-safe loads.

**DATES :**  This AD is effective June 25,
2012.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of June 25, 2012.

**ADDRESSES :**  For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; email me.boecom@boeing.com; Internet https://www.myboeingfleet.com. 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

**FOR FURTHER INFORMATION CONTACT :**  Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917–6432; fax: 425–917–6590; email: bill.ashforth@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 90–21–17, Amendment 39–6768 (55 FR 41510, October 12, 1990). That AD applies to the specified products. The NPRM was published in the Federal Register on June 29, 2011 (76 FR 38074). That NPRM proposed to continue to require repetitive inspections for cracks of the fuselage skin lap splice between body station (BS) 400 and BS 520 at stringers S–6L and S–6R, and repair if necessary; and added modification for certain airplanes and certain post-modification inspections for other airplanes.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (76 FR 38074, June 29, 2011) and the FAA’s response to each comment.