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

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 CoˆteVertu 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): 

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

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 AD 

results 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: