### 61639 Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations

Actions Compliance Procedures (5) For Model N24A airplanes: (i) Fabricate a placard that incorporates the

following words (using at least 1 ⁄ 8 -inchletters) and install this placard on the instrument panel within the pilot ’ s clear view: ‘‘ USE 10 ° FLAP FOR TAKE-OFF AND LANDING

—WARNING

— DO NOT EXCEED 10 ° FLAP EXTENSION DURING FLIGHT, LANDING GEAR UP WARNING WILL INITIATE FOR A TORQUE PRESSURE OF LESS THAN 30 PSI ’’ ; and (ii) Incorporate the following information

into the Limitations section of the AFM:

(A) Limit the maximum flap extension

to 10 degrees; and (B) Limit flaps down operations for

landing to 10 ° flap. Within the next 50 hours TIS after December 23, 2003 (the effective date of AD 2003

– 22

– 13), unless already done following Nomad Alert Service Bulletin ANMD

– 57

– 18, dated December 19, 2002. Following Nomad Alert Service Bulletin ANMD

– 57

– 18, Rev 1, dated August 14, 2006. To show compliance with paragraphs (e)(5)(ii)(A) and (e)(5)(ii)(B) of this AD, a copy of this AD may be inserted into the Limitations section of the AFM. The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may do the AFM insertion and the placard requirement of paragraph (e)(5)(i) of this AD. Make an entry into the aircraft records showing compliance with these portions of the AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).

Alternative Methods of Compliance (AMOCs)

(f) The Manager, Standards Staff, FAA, ATTN: Doug Rudolph, Aerospace Engineer, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329

– 4059; fax: (816) 329

– 4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.

(g) AMOCs approved for AD 2003

– 22

– 13 are not approved for this AD. Related Information

(h) This AD relates to Australian AD/GAF

– N22/69, Amendment 5, dated September 14, 2006, which references Nomad Alert Service Bulletin ANMD

– 57

– 18, Rev 1, dated August 14, 2006. Material Incorporated by Reference

(i) You must use Nomad Alert Service Bulletin ANMD

– 57

– 18, Rev 1, dated August 14, 2006, to do the actions required by this AD, unless the AD specifies otherwise.

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

(2) For service information identified in this AD, contact Nomad Operations, Aerospace Support Division, Boeing Australia, PO Box 767, Brisbane, QLD 4000 Australia; telephone 61 7 3306 3366; fax 61 7 3306 3111.

(3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202

– 741

– 6030, or go to: http://www.archives.gov/federal

_register/ code

_ of

_ federal

_regulations/ ibr

_locations.html. Issued in Kansas City, Missouri, on October 13, 2006. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6

– 17425 Filed 10

– 18

– 06; 8:45 am]
**BILLING CODE 4910**

**– 13** 

**– P**  **DEPARTMENT OF TRANSPORTATION**
**Federal Aviation Administration**

**14 CFR Part 39 [Docket No. FAA** 

**– 2006** 

**– 26083; Directorate**  **Identifier 2006**

**– NM** 

**– 185** 

**– AD; Amendment**  **39**

**– 14793; AD 2006** 

**– 21** 

**– 08]** 
**RIN 2120**

**– AA64**  **Airworthiness Directives; Airbus Model A330** 

**– 200, A340** 

**– 200, and A340** 

**– 300**  **Airplanes**

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT). **ACTION :**  Final rule; request for comments.

**SUMMARY :**  The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330

– 200, A340

– 200, and A340

– 300 airplanes. This AD requires the installation of heatshields in the belly fairing of the center fuselage. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent exposing any fuel leaked from the center fuel tank to the hot temperature areas of the air conditioning packs, which could result in a fire and consequent fuel tank explosion.
**DATES :**  This AD becomes effective November 3, 2006.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of November 3, 2006.

We must receive comments on this AD by December 18, 2006. **ADDRESSES :**  Use one of the following addresses to submit comments on this AD.

• DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically.

• Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically.

• Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, Room PL

– 401, Washington, DC 20590.

• Fax: (202) 493

– 2251.

• Hand Delivery: Room PL

– 401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. **FOR FURTHER INFORMATION CONTACT :**  Tim Backman, Aerospace Engineer, International Branch, ANM

– 116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057

– 3356; telephone (425) 227

– 2797; fax (425) 227

– 1149. **SUPPLEMENTARY INFORMATION :**  Discussion

The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled ‘‘ Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements ’’ (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation


### 61640 Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations

Regulation No. 88 ( ‘‘ SFAR 88, ’’ Amendment 21

– 78, and subsequent Amendments 21

– 82 and 21

– 83).

Among other actions, SFAR 88 requires certain type design ( i.e. , type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews.

In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: Single failures, single failures in combination with a latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action.

The Joint Aviation Authorities (JAA) has issued a regulation that is similar to SFAR 88. (The JAA is an associated body of the European Civil Aviation Conference (ECAC) representing the civil aviation regulatory authorities of a number of European States who have agreed to co-operate in developing and implementing common safety regulatory standards and procedures.) Under this regulation, the JAA stated that all members of the ECAC that hold type certificates for transport category airplanes are required to conduct a design review against explosion risks.

We have determined that the actions identified in this AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.

The European Aviation Safety Agency (EASA), which is the airworthiness authority for the European Union, notified us that an unsafe condition may exist on certain Airbus Model A330

– 200, A340

– 200, and A340

– 300 airplanes. The EASA advises that there could be temperatures in excess of 200 degrees Celsius on surfaces in the belly fairing of the center fuselage. Therefore, any fuel leaked from the center fuel tank would be exposed to the hot temperature areas of the air conditioning packs. This condition, if not corrected, could result in a fire and consequent fuel tank explosion. Relevant Service Information

Airbus has issued Service Bulletins A330

– 21

– 3096 and A340

– 21

– 4107, both Revision 01, both dated October 10, 2005. The service bulletins describe procedures for the installation of heatshields in the belly fairing of the center fuselage. The installation includes the following actions:

• Replacing existing heatshields with new heatshields fitted with edges and draining tapping.

• Adding draining systems.

• Adding two heatshields.

• Adding two tight insulation sleeves on the ozone reducer and on the trim pipe.

• Replacing and adding brackets.

• Modifying a heatshield panel. The EASA mandated the service information and issued airworthiness directive 2006

– 0191, dated July 10, 2006, to ensure the continued airworthiness of these airplanes in the European Union.
FAA ’ s Determination and Requirements of this AD

These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. As described in FAA Order 8100.14A, ‘‘ Interim Procedures for Working with the European Community on Airworthiness Certification and Continued Airworthiness, ’’ dated August 12, 2005, the EASA has kept the FAA informed of the situation described above. We have examined the EASA ’ s findings, evaluated all pertinent information, and determined that we need to issue an AD for products of this type design that are certificated for operation in the United States.

Therefore, we are issuing this AD to prevent exposing any fuel leaked from the center fuel tank to the hot temperature areas of the air conditioning packs, which could result in a fire and consequent fuel tank explosion. This AD requires accomplishing the actions specified in the service information described previously, except as discussed in

‘‘ Difference Between EASA Airworthiness Directive and This AD. ’’ Difference Between EASA Airworthiness Directive and This AD

The applicability of EASA airworthiness directive 2006

– 0191 excludes airplanes on which Airbus Service Bulletin A330

– 21

– 3096, Revision 01; or Airbus Service Bulletin A340

– 21

– 4107, Revision 01; have been accomplished in service. However, we have not excluded those airplanes in the applicability of this AD; rather, this AD includes a requirement to accomplish the actions specified in Revision 01 of those service bulletins, as applicable. This requirement would ensure that the actions specified in the service bulletins and required by this AD are accomplished on all affected airplanes. Operators must continue to operate the airplane in the configuration required by this AD unless an alternative method of compliance is approved. Costs of Compliance

None of the airplanes affected by this action are on the U.S. Register. All airplanes affected by this AD are currently operated by non-U.S. operators under foreign registry; therefore, they are not directly affected by this AD action. However, we consider this AD necessary to ensure that the unsafe condition is addressed if any affected airplane is imported and placed on the U.S. Register in the future.

The following table provides the estimated costs to comply with this AD for any affected airplane that might be imported and placed on the U.S. Register in the future.


### E STIMATED 

### C OSTS

Action Work hours Average labor rate per hour Parts cost Cost per airplane
Installation ........................................................................................................ 65 $80 $17, 290 $22,490


### 61641 Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations

FAA ’ s Determination of the Effective Date

No airplane affected by this AD is currently on the U.S. Register. Therefore, providing notice and opportunity for public comment is unnecessary before this AD is issued, and this AD may be made effective in less than 30 days after it is published in the Federal Register

. Comments Invited

This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any relevant written data, views, or arguments regarding this AD. Send your comments to an address listed in the **ADDRESSES** section. Include ‘‘ Docket No. FAA

– 2006

– 26083; Directorate Identifier 2006

–NM

– 185

–AD ’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD that might suggest a need to modify it.

We will post all comments we receive, without change, to http:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT ’ s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477

– 78), or you may visit http://dms.dot.gov. Examining the Docket

You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647

– 5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the **ADDRESSES** section. Comments will be available in the AD docket shortly after the Docket Management System receives them. 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 have 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 the 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); 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.

We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the **ADDRESSES** section for a location to examine the regulatory evaluation. 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 Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): 2006

– 21

– 08 Airbus: Amendment 39

– 14793. Docket No. FAA

– 2006

– 26083; Directorate Identifier 2006

–NM

– 185

–AD. Effective Date

(a) This AD becomes effective November 3, 2006. Affected ADs

(b) None. Applicability

(c) This AD applies to Airbus Model A330

– 200, A340

– 200, and A340

– 300 airplanes, certificated in any category; except airplanes on which Airbus Modification 49520 has been done in production. Unsafe Condition

(d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent exposing any fuel leaked from the center fuel tank to the hot temperature areas of the air conditioning packs, which could result in a fire and consequent fuel tank explosion. Compliance

(e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Installation of Heatshields

(f) Within 27 months after the effective date of this AD, install heatshields in the belly fairing of the center fuselage in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330

– 21

– 3096, Revision 01, dated October 10, 2005 (for Model A330

– 200 airplanes); or Airbus Service Bulletin A340

– 21

– 4107, Revision 01, dated October 10, 2005 (for Model A340

– 200 and A340

– 300 airplanes); as applicable. Alternative Methods of Compliance (AMOCs)

(g)(1) The Manager, International Branch, ANM

– 116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.

(2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information

(h) European Aviation Safety Agency (EASA) airworthiness directive 2006

– 0191, dated July 10, 2006, also addresses the subject of this AD. Material Incorporated by Reference

(i) You must use Airbus Service Bulletin A330

– 21

– 3096, Revision 01, dated October 10, 2005; or Airbus Service Bulletin A340

– 21

– 4107, Revision 01, dated October 10, 2005; as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point


### 61642 Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations

Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL

– 401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, 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 October 10, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6

– 17426 Filed 10

– 18

– 06; 8:45 am]
**BILLING CODE 4910**

**– 13** 

**– P** 

**DEPARTMENT OF TRANSPORTATION**
**Federal Aviation Administration**

**14 CFR Part 39 [Docket No. FAA** 

**– 2006** 

**– 25730; Directorate**  **Identifier 2006**

**– NE** 

**– 31** 

**– AD; Amendment 39** 

**– 14796; AD 2006** 

**– 21** 

**– 11]** 
**RIN 2120**

**– AA64**  **Airworthiness Directives; Turbomeca Turmo IV A and IV C Series Turboshaft**  **Engines**

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT).
**ACTION :**  Final rule; request for comments.

**SUMMARY :**  The FAA is adopting a new airworthiness directive (AD) for Turbomeca Turmo IV A and IV C series turboshaft engines. This AD requires identifying, inspecting and replacing flexible lubrication pipes manufactured after April 1, 2003. If both engines on the same helicopter each have an affected pipe, then this AD requires replacing one of the affected pipes before further flight. This AD also requires initial and repetitive borescope inspections of affected pipes, visual inspections for oil leakage, and visual inspections of the oil filter, on engines that are not required to have an affected pipe replaced before further flight by this AD. This AD results from 7 reports of oil leakage due to the deterioration of flexible lubrication pipes manufactured after April 1, 2003. We are issuing this AD to prevent dual-engine failure on a twin-engine helicopter.
**DATES :**  Effective November 3, 2006.

We must receive any comments on this AD by December 18, 2006. **ADDRESSES :**  Use one of the following addresses to comment on this AD:

• DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically.

• Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically.

• Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL

– 401, Washington, DC 20590

– 0001.

• Fax: (202) 493

– 2251.

• Hand Delivery: Room PL

– 401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Contact Turbomeca, 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15 for the service information identified in this AD. **FOR FURTHER INFORMATION CONTACT :**  Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238

– 7175; fax (781) 238

– 7199. **SUPPLEMENTARY INFORMATION :**  The European Aviation Safety Agency (EASA), which is the airworthiness authority for the European Community, recently notified us that an unsafe condition may exist on certain Turbomeca Turmo IV A and IV C series turboshaft engines. EASA advises that 7 reports were received of oil leakage due to the deterioration of flexible lubrication pipes, part number (P/N) 0 249 92 813 0, installed on Turbomeca Turmo III C4 (military version) turboshaft engines. Turbomeca is still investigating the cause of the deterioration, but links a manufacturing process change, applied by the pipe manufacturer, in 2003. The same process was used to manufacture flexible lubrication pipes, P/N 0 249 92 916 0. Either P/N pipe could be installed on Turmo IV A and IV C series turboshaft engines. Relevant Service Information

We have reviewed and approved the technical contents of Turbomeca Alert Mandatory Service Bulletin (MSB) No. A249 72 0802, Update No. 1, dated August 3, 2006. That Alert MSB describes procedures for identifying affected flexible lubrication pipes by their curing batch number, and replacing one of the affected pipes on atwin-engine helicopter to prevent dualengine failure. That Alert MSB also describes procedures for performing repetitive borescope inspections of all other affected pipes and visual inspections of the oil filter. EASA classified this service bulletin as mandatory and issued AD 2006

– 0240

–E in order to ensure the airworthiness of these Turbomeca Turmo IV A and IV C series turboshaft engines in Europe. Bilateral Airworthiness Agreement

These Turbomeca Turmo IV A and IV C series turboshaft engines are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Under this bilateral airworthiness agreement, EASA kept the FAA informed of the situation described above. We have examined the findings of EASA, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States.
FAA ’ s Determination and Requirements of This AD

The unsafe condition described previously is likely to exist or develop on other Turbomeca Turmo IV A and IV C series turboshaft engines of the same type design. We are issuing this AD toprevent dual-engine failure on a twinengine helicopter. This AD requires identifying affected flexible lubrication pipes by their curing batch number, and replacing the affected pipe before further flight, on one engine if both engines on the same helicopter each have an affected pipe. This AD also requires initial and repetitive borescope inspections of flexible lubrication pipes and visual inspections of the oil filter, on engines that do not have the affected pipe replaced before further flight.
FAA ’ s Determination of the Effective Date

Since an unsafe condition exists that requires the immediate adoption of this AD, we have found that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists for making this amendment effective in less than 30 days. Interim Action

These actions are interim actions and we may take further rulemaking actions in the future. Comments Invited

This AD is a final rule that involves requirements affecting flight safety and