## 8717 Federal Register / Vol. 74, No. 37 / Thursday, February 26, 2009 / Rules and Regulations

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:
2009–02–11 Bombardier Inc. (Formerly Canadair): Amendment 39–15801. Docket No. FAA–2008–1115; Directorate Identifier 2008–NM–134–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective April 2, 2009.

Affected ADs

(b) None.
Applicability

(c) This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category.

(1) Bombardier Model CL–600–2C10 (Regional Jet Series 700, 701, & 702) airplanes, serial numbers 10003 through 10169 inclusive.

(2) Bombardier Model CL–600–2D24 (Regional Jet Series 900) airplanes, serial numbers 15001 through 15030 inclusive.
Subject

(d) Air Transport Association (ATA) of America Code 24: Electrical Power.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states:

Bombardier Aerospace has completed a system safety review of the CL–600–2C10/ CL–600–2D24 aircraft fuel system against the new fuel tank safety standards, introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment(NPA) 2002–043. The identified noncompliances were assessed using Transport Canada Policy Letter No. 525–001 to determine if mandatory corrective action was required.

The assessment showed that a single failure due to chafing of fuel system wiring with high power wiring at the centre fuel tank front spar could result in overheating of the fuel boost pump. The assessment also showed that chafing of the high power wiring with the centre fuel tank front spar structures could result in overheating of the fuel tank wall. Overheating of the fuel boost pump or the fuel tank wall could lead to hot surface ignition resulting in a fuel tank explosion. To correct the unsafe condition, this directive mandates separation of the high power wiring from the fuel system wiring at the centre fuel tank front spar area and the installation of additional clamping and support for the high power wiring [ i.e.

, modifying the routing and support of electrical wires in the center fuel tank front spar area]. Required actions also include an inspection to determine if pins have a minimum of one thread above the nuts, and a visual inspection for damage of the sealant. Corrective actions include replacing pins and nuts and applying sealant.
Actions and Compliance

(f) Unless already done, do the following actions.

(1) Within 4,500 flight hours after the effective date of this AD, modify the routing and support of the electrical wires in the center fuel tank front spar area (including an inspection to determine if pins have a minimum of one thread above the nuts, and a visual inspection for damage of the sealant, and applicable corrective actions) in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 670BA–24–012, Revision B, dated July 25, 2007. Do all applicable related investigative and corrective actions before further flight.

(2) Actions done before the effective date of this AD in accordance with Bombardier Service Bulletin 670BA–24–012, dated April 18, 2005; or Revision A, dated October 25, 2006; are acceptable for compliance with the corresponding requirements of this AD.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information as follows: No differences.

Other FAA AD Provisions

(g) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, Airframe and Propulsion Branch, ANE–171, New York Aircraft Certification Office, 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: Rocco Viselli, Aerospace Engineer, Airframe and Propulsion Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7331; fax (516) 794–5531. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(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 FAAapproved 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: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056.

Related Information

(h) Refer to MCAI Canadian Airworthiness Directive CF–2008–24, dated July 3, 2008, and Bombardier Service Bulletin 670BA–24– 012, Revision B, dated July 25, 2007, for related information.
Material Incorporated by Reference

(i) You must use Bombardier Service Bulletin 670BA–24–012, Revision B, dated July 25, 2007, 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 Bombardier, Inc., 400 Co ˆ teVertu Road West, Dorval, Que  ́ bec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; e-mail thd.crj@aero.bombardier.com; Internet http:// www.bombardier.com.

(3) You may review copies of the service information that is incorporated by reference 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 or
425–227–1152.

(4) You may also review copies of the service information 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 Renton, Washington, on January 15, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. E9–3364 Filed 2–25–09; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2008–0150; Directorate Identifier 2007–NM–325–AD; Amendment**  **39–15818; AD 2009–04–12]**

**RIN 2120–AA64**



### Airworthiness Directives; Boeing **Model 767–200, –300, and –400ER Series Airplanes** 

**AGENCY** 

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

**ACTION** 

### : Final rule.

**SUMMARY** 

### : The FAA is superseding an existing airworthiness directive (AD),


## 8718 Federal Register / Vol. 74, No. 37 / Thursday, February 26, 2009 / Rules and Regulations

which applies to certain Boeing Model 767 series airplanes. That AD currently requires a one-time inspection for missing, damaged, or incorrectly installed parts in the separation link assembly on the deployment bar of the emergency escape system on the entry or service door, and installation of new parts if necessary. This new AD requires replacing the separation link assembly on the applicable entry and service doors with an improved separation link assembly, and doing related investigative and corrective actions if necessary; and inspecting for discrepancies of the unloaded spring dimensions in the separation link assembly, and doing corrective actions if necessary. This AD also removes certain airplanes from the applicability. This AD results from reports that entry and service doors did not open fully during deployment of emergency escape slides, and additional reports of missing snap rings. We are issuing this AD to prevent failure of an entry or service door to open fully in the event of an emergency evacuation, which could impede exit from the airplane. This condition could result in injury to passengers or crewmembers.

**DATES** 

### : This AD becomes effective April 2, 2009.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of April 2, 2009.

**ADDRESSES** 

### : For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207; telephone 206–544–9990; fax 206–766– 5682; e-mail DDCS@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** 

### : Keith Ladderud, 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) 917–6435; fax (425) 917–6590.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

The FAA issued a supplemental notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2001–26–19, amendment 39–12585 (67 FR 265, January 3, 2002). The existing AD applies to certain Boeing Model 767 series airplanes. That supplemental NPRM was published in the Federal Register on September 23, 2008 (73 FR 54747). That supplemental NPRM proposed to require replacing the separation link assembly on the applicable entry and service doors with an improved separation link assembly, and doing related investigative and corrective actions if necessary; and inspecting for discrepancies of the unloaded spring dimensions in the separation link assembly, and doing corrective actions if necessary. That supplemental NPRM also proposed to remove certain airplanes from the applicability.

Comments

We provided the public the opportunity to participate in the development of this AD. No comments have been received on the supplemental NPRM or on the determination of the cost to the public.

Conclusion

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

There are about 1,225 airplanes of the affected design in the worldwide fleet. This AD affects about 355 airplanes of U.S. registry. The new actions take up to about 6 work hours per airplane, at an average labor rate of $80 per work hour. Required parts cost up to about $10,671 per airplane. Based on these figures, the estimated cost of the new actions specified in this AD for U.S. operators is $3,958,605, or $11,151 per airplane. 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 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.

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 removing amendment 39–12585 (67 FR 265, January 3, 2002) and by adding the following new airworthiness directive (AD):


## 8719 Federal Register / Vol. 74, No. 37 / Thursday, February 26, 2009 / Rules and Regulations

2009–04–12 Boeing: Amendment 39–15818. Docket No. FAA–2008–0150; Directorate Identifier 2007–NM–325–AD.

Effective Date

(a) This AD becomes effective April 2,

2009.

Affected ADs

(b) This AD supersedes AD 2001–26–19.
Applicability

(c) This AD applies to Boeing Model 767– 200, –300, and –400ER series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 767–25–0428, dated August 23, 2007.

Unsafe Condition

(d) This AD results from reports that entry and service doors did not open fully during deployment of emergency escape slides, and additional reports of missing snap rings. We are issuing this AD to prevent failure of an entry or service door to open fully in the event of an emergency evacuation, which could impede exit from the airplane. This condition could result in injury to passengers or crewmembers.
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.
Replacement

(f) Within 48 months after the effective date of this AD, replace the separation link assembly on the deployment bar of the emergency escape system on all the applicable entry and service doors with an improved separation link assembly, and do all the applicable related investigative and corrective actions before further flight, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 767–25–0428, dated August 23, 2007; or Revision 1, dated May 8, 2008. After the effective date of this AD only Boeing Special Attention Service Bulletin 767–25–0428, Revision 1, may be used.
Alternative Methods of Compliance (AMOCs)

(g)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, ATTN: Keith Ladderud, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 917–6435; fax (425) 917–6590; has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.

(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 appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Material Incorporated by Reference (h) You must use Boeing Special Attention Service Bulletin 767–25–0428, dated August 23, 2007; or Boeing Special Attention Service Bulletin 767–25–0428, Revision 1, dated May 8, 2008; as applicable; 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 Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207; telephone 206– 544–9990; fax 206–766–5682; e-mail DDCS@boeing.com; Internet https:// www.myboeingfleet.com.

(3) You may review copies of the service information that is incorporated by reference 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 or 425–227–1152.

(4) You may also review copies of the service information 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 Renton, Washington, on January 22, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–3263 Filed 2–25–09; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2008–0731; Directorate Identifier 2008–NM–058–AD; Amendment**  **39–15812; AD 2009–04–06]**

**RIN 2120–AA64**



### Airworthiness Directives; Boeing **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), Department of Transportation (DOT).

**ACTION** 

### : Final rule.

**SUMMARY** 

### : The FAA is superseding an existing airworthiness directive (AD), which applies to all Boeing Model 747 series airplanes. That AD currently requires repetitive detailed inspections of the aft pressure bulkhead for indications of ‘‘oil cans’’ and previous oil can repairs, and corrective actions if necessary. An oil can is an area on a pressure dome web that moves when pushed from the forward side. This new AD requires a reduced compliance time for the initial detailed inspection and revises the applicability. This ADresults from a report that cracks in oilcanned areas were found during an inspection of the aft pressure bulkhead. We are issuing this AD to detect and correct the propagation of fatigue cracks in the vicinity of oil cans on the web of the aft pressure bulkhead, which could result in rapid decompression of the airplane and overpressurization of the tail section, and consequent loss of control of the airplane.

**DATES** 

### : This AD becomes effective April 2, 2009.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of April 2, 2009.

On September 13, 2004 (69 FR 48133, August 9, 2004), the Director of the Federal Register approved the incorporation by reference of a certain other publication.

**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** 

### : Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 917–6437; fax (425) 917–6590.

**SUPPLEMENTARY INFORMATION** 

### :