Federal Register / Vol. 74, No. 46 / Wednesday, March 11, 2009 / Rules and Regulations 10469 

Bombardier Canadair Regional Jet CRJ100/ 

200/440 Fault Isolation Manual CSP A–009, 

Volume 1, Revision 38, dated January 10, 

2008, contains the following effective pages: 

List of Effective Pages 

Page title/description Page number(s) Revision 

number Date shown on page(s) 

FIM Title Page ................................................... None shown ............................. 38 January 10, 2008. 

Transmittal Letter ............................................... 1 ............................................... 38 January 10, 2008. 

Record of Revisions ........................................... 1 ............................................... .................... January 10, 2008. 

FIM Volume 1 Title Page ................................... None shown ............................. 38 January 10, 2008. 

Chapter 27 Effective Pages 

1–3 ........................................... 38 January 10, 2008. 

4 ............................................... 37 January 10, 2007. 

Section 27–50–00 

101 ........................................... 28 August 26, 2003. 

102–153 ................................... 38 January 10, 2008. 

154, 156 ................................... 30 March 17, 2004. 

155 ........................................... 34 April 10, 2005. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in Table 3 

of this AD under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

TABLE 3—NEW MATERIAL INCORPORATED BY REFERENCE

Service information Revision level Date 

Bombardier Service Bulletin 601R–27–151 ........................................................................... B ..................................... June 12, 2008. 

Bombardier Service Bulletin 601R–11–090 ........................................................................... Original ........................... August 15, 2008. 

Canadair Regional Jet TR RJ/165–1, including pages 05–11–5 through 05–11–14, to the 

Canadair Regional Jet AFM CSP A–012.

Original ........................... August 7, 2008. 

Canadair Regional Jet TR 05–035 to the Canadair Regional Jet AMM ................................ Original ........................... July 13, 2007. 

Section 27–50–00 of Chapter 27 of the Bombardier Canadair Regional Jet CRJ100/200/ 

440 Fault Isolation Manual CSP A–009, Volume 1.

38 ................................... January 10, 2008. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Bombardier Service Bulletin 

601R–27–150, including Appendix A, dated 

July 12, 2007; and Canadair Regional Jet 

Temporary Revision RJ/165, dated July 6, 

2007, to the Canadair Regional Jet Airplane 

Flight Manual CSP A–012; on September 5, 

2007 (72 FR 46555, August 21, 2007). 

(3) 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. 

(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 or 425–227–1152. 

(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 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 February 

26, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–5290 Filed 3–10–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0671; Directorate 

Identifier 2008–NM–017–AD; Amendment 

39–15796; AD 2009–02–06] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–300, –400, and –500 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 737–300, –400, and –500 

series airplanes. This AD requires 

repetitive high frequency eddy current 

inspections for cracking of the 1.04-inch 

nominal diameter wire penetration hole 

in the frame and frame reinforcement, 

between stringers S–20 and S–21, on 

both the left and right sides of the 

airplane, and related investigative and 

corrective actions if necessary. This AD 

results from reports of cracking in the 

frame, or in the frame and frame 

reinforcement, common to the 1.04-inch 

nominal diameter wire penetration hole 

intended for wire routing. We are 

issuing this AD to detect and correct 

cracking in the fuselage frames and 

frame reinforcements, which could 

reduce the structural capability of the 

frames to sustain limit loads, and result 

in cracking in the fuselage skin and 

subsequent rapid depressurization of 

the airplane. 

DATES: This AD is effective April 15, 

2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 15, 2009. 


rwilkins on PROD1PC63 with RULES
10470 Federal Register / Vol. 74, No. 46 / Wednesday, March 11, 2009 / Rules and Regulations 

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: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6447; 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 Boeing Model 737–300, –400, 

and –500 series airplanes. That NPRM 

was published in the Federal Register 

on June 24, 2008 (73 FR 35598). That 

NPRM proposed to require repetitive 

high frequency eddy current (HFEC) 

inspections for cracking of the 1.04-inch 

nominal diameter wire penetration hole 

in the frame and frame reinforcement, 

between stringers S–20 and S–21, on 

both the left and right sides of the 

airplane, and related investigative and 

corrective actions if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received from 

the single commenter. 

Request To Revise Paragraph (h) To 

Correct References to Parts of the 

Service Bulletin 

KLM Royal Dutch Airlines (KLM) 

requests that we revise paragraph (h) of 

the NPRM to correct the references to 

certain parts of Boeing Alert Service 

Bulletin 737–53A1279, dated December 

18, 2007 (‘‘the service bulletin’’), for 

doing certain actions. KLM points out 

that paragraph (h) of the NPRM refers to 

Part 3 of the service bulletin for doing 

the repair and to Part 4 of the service 

bulletin for doing the preventative 

modification. KLM further points out 

that Part 4 of the service bulletin 

concerns repeat inspections, not the 

preventative modification. The 

preventative modification is provided in 

Part 5 of the service bulletin. 

We agree with the commenter. It was 

our intention to refer to Part 5 of the 

service bulletin for doing the 

preventative modification provided in 

paragraph (h) of the NPRM. Therefore, 

we have revised paragraph (h) of this 

AD to refer to Part 5 of the service 

bulletin for doing the preventative 

modification. 

Request To Revise Paragraph (e) To 

Clarify Compliance Times 

KLM requests that we revise 

paragraph (e) of the NPRM to refer to 

paragraph 1.E., ‘‘Compliance,’’ of the 

service bulletin. KLM asserts that 

adding a reference to the location of the 

compliance times in the service bulletin 

would be helpful. 

We do not agree to revise paragraph 

(e) of this AD. A reference to paragraph 

1.E., ‘‘Compliance,’’ of Boeing Service 

Bulletin 737–53A1279, dated December 

18, 2007, is already provided in 

paragraph (g) of this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We also determined that this change 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

We estimate that this AD affects 616 

airplanes of U.S. registry. The following 

table provides the estimated costs for 

U.S. operators to comply with this AD. 

The average labor rate is $80 per work 

hour. 

ESTIMATED COSTS

Action Work hours Parts Cost per 

product 

Number 

of U.S.- 

registered 

airplanes 

Fleet cost 

Inspection ............................ Between 6 and 8 (depending on airplane configuration), per inspection cycle.$0 Between $480 and $640, 

per inspection cycle.

616 Between $295,680 and 

$394,240, per inspection 

cycle. 

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 

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 


rwilkins on PROD1PC63 with RULES
Federal Register / Vol. 74, No. 46 / Wednesday, March 11, 2009 / Rules and Regulations 10471 

(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, 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: 

2009–02–06 Boeing: Amendment 39–15796. 

Docket No. FAA–2008–0671; Directorate 

Identifier 2008–NM–017–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective April 15, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 737– 

300, –400, and –500 series airplanes, 

certificated in any category; as identified in 

Boeing Alert Service Bulletin 737–53A1279, 

dated December 18, 2007. 

Unsafe Condition 

(d) This AD results from reports of cracking 

in the frame, or in the frame and frame 

reinforcement, common to the 1.04-inch 

nominal diameter wire penetration hole 

intended for wire routing. We are issuing this 

AD to detect and correct cracking in the 

fuselage frames and frame reinforcements, 

which could reduce the structural capability 

of the frames to sustain limit loads, and 

result in cracking in the fuselage skin and 

subsequent rapid depressurization of the 

airplane. 

Compliance 

(e) Comply with this AD within the 

compliance times specified, unless already 

done. 

Service Bulletin Reference Paragraph 

(f) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1279, dated December 18, 2007. 

(1) The ‘‘condition’’ column of paragraph 

1.E. of Boeing Alert Service Bulletin 737– 

53A1279, dated December 18, 2007, refers to 

total flight cycles ‘‘at the date given on this 

service bulletin.’’ This AD applies to the 

airplanes with the specified total flight cycles 

as of the effective date of this AD. 

(2) Where the service bulletin specifies to 

contact Boeing for instructions for removing 

damage and repairing cracking: Before 

further flight, remove the damage or repair 

the cracking using a method approved in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

(3) Although the service bulletin 

referenced in this AD specifies to submit 

information to the manufacturer, this AD 

does not include that requirement. 

Inspections, Related Investigative and 

Corrective Actions 

(g) At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of the service 

bulletin, except as specified by paragraph 

(f)(1) of this AD: Do a high frequency eddy 

current (HFEC) surface inspection or an 

HFEC hole/edge inspection for cracking of 

the 1.04-inch nominal diameter wire 

penetration hole in the frame and frame 

reinforcement, between stringer S–20 and S– 

21; and do all applicable related investigative 

and corrective actions; by accomplishing all 

the actions specified in the Accomplishment 

Instructions of the service bulletin, except as 

specified by paragraphs (f)(2) and (f)(3) of 

this AD. Do all applicable related 

investigative and corrective actions before 

further flight. Thereafter, repeat the 

inspections at the applicable intervals 

specified in paragraph 1.E. of the service 

bulletin. 

Terminating Action 

(h) Doing the repair in Part 3 or the 

preventative modification in Part 5 of the 

service bulletin terminates the repetitive 

inspection requirements of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, ATTN: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6447; 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Material Incorporated by Reference 

(j) You must use Boeing Alert Service 

Bulletin 737–53A1279, dated December 18, 

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 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. 

(3) You may review copies of the service 

information 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 

9, 2009. 

Stephen P. Boyd, 

Assistant Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–4734 Filed 3–10–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30654; Amdt. No 3310] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This establishes, amends, 

suspends, or revokes Standard 

Instrument Approach Procedures 

(SIAPs) and associated Takeoff 

Minimums and Obstacle Departure 

Procedures for operations at certain 

airports. These regulatory actions are 

needed because of the adoption of new 

or revised criteria, or because of changes 

occurring in the National Airspace 

System, such as the commissioning of 

new navigational facilities, adding new 

obstacles, or changing air traffic 

requirements. These changes are 

designed to provide safe and efficient 


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