### 47207 Federal Register / Vol. 75, No. 150 / Thursday, August 5, 2010 / Rules and Regulations

products identified in this rulemaking action. Regulatory Findings

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 DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), and

(3) 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.

You can find our regulatory evaluation and the estimated costs of compliance in the AD Docket. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, 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: 2010–16–03 McDonnell Douglas Corporation: Amendment 39–16379. Docket No. FAA–2008–0403; Directorate Identifier 2007–NM–166–AD.

Effective Date

(a) This airworthiness directive (AD) is effective September 9, 2010.

Affected ADs

(b) None. Applicability

(c) This AD applies to McDonnell Douglas Corporation Model MD–11 and MD–11F airplanes, certified in any category, equipped with General Electric CF6–80C2 series engines. Subject

(d) Air Transport Association (ATA) of America Code 30: Ice and rain protection. Unsafe Condition (e) This AD results from reports of several in-flight engine flameouts, includingmultiple dual engine flameout events, in icecrystal icing conditions. We are issuing this AD to ensure that the flightcrew has the proper procedures to follow in certain icing conditions. These certain icing conditions could cause a multiple engine flameout during flight with the potential inability to restart the engines, and consequent forced landing of the airplane.
Compliance

(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Airplane Flight Manual (AFM) Revision

(g) Within 14 days after the effective date of this AD, revise the Limitations Section of the McDonnell Douglas MD–11/MD–11F AFM to include the following statement. This may be done by inserting a copy of this AD into the AFM.

‘‘Prior to reducing thrust for descent when icing conditions (defined by visible moisture in the air and TAT is 6 ° C or below) are present, the ENG IGN OVRD switch and the ENG, WING, and TAIL ANTI-ICE switches must be placed in the ON position. When icing conditions are no longer present or anticipated, place the ENG IGN OVRD switch and the ENG, WING, and TAIL ANTI-ICE switches in the OFF position. ’’

Note 1: When a statement identical to that in paragraph (g) of this AD has been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM.

Alternative Methods of Compliance (AMOCs)

(h)(1) The Manager, Los Angeles 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. Send information to ATTN: Samuel Lee, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712– 4137; telephone (562) 627–5262; fax (562)
627–5210.

(2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD.
Material Incorporated by Reference

(i) None. Issued in Renton, Washington on July 16,
2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–19156 Filed 8–4–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2009–1215; Directorate Identifier 2009–NM–126–AD; Amendment**  **39–16364; AD 2010–14–19]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Model A330–200 and –300 Series Airplanes,**  **and Model A340–200, –300, –500 and –600 Series Airplanes** 

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

**ACTION :**  Final rule; correction.

**SUMMARY :**  The FAA is correcting airworthiness directive (AD) 2010–14– 19, which published in the Federal Register on July 13, 2010. That AD applies to certain Model A330–200 and –300 series airplanes, and Model A340– 200, –300, –500 and –600 series airplanes. A certain service bulletin number in Note 3 of the regulatory section is incorrect. This document corrects that service bulletin number. In all other respects, the original document remains the same.

**DATES :**  This correction is effective August 5, 2010. The effective date of AD 2010–14–19 remains August 17, 2010.

**ADDRESSES :**  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 (telephone 800–647–5527) is the 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 :**  Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149.


### 47208 Federal Register / Vol. 75, No. 150 / Thursday, August 5, 2010 / Rules and Regulations

**SUPPLEMENTARY INFORMATION :**  On June 29, 2010, the FAA issued AD 2010–14– 19, Amendment 39–16364 (75 FR 39814, July 13, 2010), for certain Airbus Model A330–200 and –300 series airplanes, and Model A340–200, –300, –500 and –600 series airplanes. The AD requires replacing or modifying the Halon dual-filter assemblies of the flow metering fire extinguishing system in the forward and bulk cargo compartments, as applicable.

As published, Note 3 of the AD specifies in error Airbus Service Bulletin A340–26–4038. The correct service bulletin is Airbus Service Bulletin A340–26–4030.

No other part of the regulatory information has been changed; therefore, the final rule is not republished in the Federal Register

.

The effective date of this AD remains August 17, 2010.

**§ 39.13 [Corrected]**

■ In the Federal Register of July 13, 2010, on page 39817, in the second and third columns, Note 3 of AD 2010–14– 19 is corrected to read as follows:

* * * * *

Note 3: The Halon dual-filter assembly P/ N QA06753 is embodied in production through Airbus modification 40041. The Halon dual-filter assembly P/N QA06753–01 is only embodied in service through Airbus Service Bulletin A330–26–3030 or Airbus Service Bulletin A340–26–4030. The Halon dual-filter assembly P/N QA06753–02 is embodied in production through modification 47197 or 47883 or 50108 (BCRC) and 51065 or 51329 (LDCC) or in service through Airbus Service Bulletin A330–26–3030 or Airbus Service Bulletin
A340–26–4030.

* * * * *

Issued in Renton, Washington, on July 27,

2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–19151 Filed 8–4–10; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0045; Directorate Identifier 2009–NM–085–AD; Amendment**  **39–16382; AD 2010–16–05]**

**RIN 2120–AA64**
**Airworthiness Directives; The Boeing Company Model 747–100, 747–100B,**  **747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–**  **400D, 747–400F, 747SR, and 747SP Series Airplanes** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Model 747 airplanes. This AD requires inspecting to verify the part number of the low-pressure flex-hoses of the crew oxygen system installed under the oxygen mask stowage boxes in the flight deck, and replacing the flex-hose with anew non-conductive low-pressure flexhose if necessary. This AD results from reports of low-pressure flex-hoses of the crew oxygen system that burned through due to inadvertent electrical current from a short circuit in the audio select panel. We are issuing this AD to prevent inadvertent electrical current,which can cause the low-pressure flexhoses of the crew oxygen system to melt or burn, causing oxygen system leakage and smoke or fire.

**DATES :**  This AD is effective September 9,
2010.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of September 9, 2010.

**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; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. 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 (telephone 800–647–5527) is the 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 :**  Susan L. Monroe, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6457; fax (425) 917–6590.

**SUPPLEMENTARY INFORMATION :** 
Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to certain Model 747 airplanes. That NPRM was published in the Federal Register on January 22, 2010 (75 FR 3658). That NPRM proposed to require inspecting to verify the part number of the low-pressure flex-hoses of the crew oxygen system installed under the oxygen mask stowage boxes in the flight deck, and replacing the flex-hose with anew non-conductive low-pressure flexhose if necessary.

Comments

We gave the public the opportunity to participate in developing this AD. We considered the comments received. Support for the NPRM

Boeing concurs with the contents of the NPRM, and the Air Line Pilots Association, International (ALPA) supports the intent of the NPRM. Request To Shorten Compliance Time

ALPA requests that the 36-month compliance time specified in the NPRM be shortened given the potential consequence of an oxygen-fed fire in the vicinity of the flightcrew station.

We do not agree. In developing an appropriate compliance time, we considered the safety implications, parts availability, and normal maintenance schedules for timely accomplishment of replacement of the fasteners. Further, we arrived at the compliance time with manufacturer concurrence. In consideration of all of these factors, we determined that the compliance time, as proposed, represents an appropriate interval in which the inspections can be done in a timely manner within the fleet, while still maintaining an adequate level of safety. Operators are always permitted to accomplish the requirements of an AD at a time earlier than the specified compliance time; therefore, an operator may choose to do