This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

8461 

Vol. 75, No. 37 

Thursday, February 25, 2010 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1021; Directorate 

Identifier 2009–NM–054–AD; Amendment 

39–16217; AD 2009–06–05 R1] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–1A11 (CL–600), CL– 

600–2A12 (CL–601), and CL–600–2B16 

(CL–601–3A, CL–601–3R, and CL–604) 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are revising an existing 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

[S]everal cases of wing anti-ice piccolo 

duct failure reported on CL–600–2B19 (CRJ) 

aircraft. Although there have been no failures 

reported on Challenger aircraft, similar ducts 

are installed on the * * * [other] Challenger 

models. 

* * * * * 

Cracking of the wing anti-ice piccolo ducts 

could result in air leakage, with an adverse 

effect on the anti-ice air distribution pattern 

and a possible unannunciated insufficient 

heat condition. * * * 

The unsafe condition is anti-ice 

system air leakage with a possible 

adverse effect on the anti-ice air 

distribution pattern and anti-ice 

capability without annunciation to the 

flightcrew, and consequent reduced 

controllability of the airplane. We are 

issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective April 

1, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 1, 2010. 

On April 28, 2009 (74 FR 12225, 

March 24, 2009), the Director of the 

Federal Register approved the 

incorporation by reference of certain 

other publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Parrillo, Aerospace Engineer, Airframe 

and Mechanical Systems, ANE–171, 

FAA, New York Aircraft Certification 

Office, 1600 Stewart Avenue, Suite 410, 

Westbury, New York 11590; telephone 

(516) 228–7305; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to revise an existing AD that 

applies to certain Model CL–600–1A11 

(CL–600), CL–600–2A12 (CL–601), and 

CL–600–2B16 (CL–601–3A, CL–601–3R, 

and CL–604) airplanes. That NPRM was 

published in the Federal Register on 

November 5, 2009 (74 FR 57273), and 

proposed to revise AD 2009–06–05, 

Amendment 39–15841 (74 FR 12225, 

March 24, 2009). That AD required 

actions intended to address an unsafe 

condition for the products listed above. 

Actions Since Issuance of AD 2009–06– 

05 

Since we issued AD 2009–06–05, 

Bombardier requested that we change 

paragraphs (f)(2) and (f)(4) of AD 2009– 

06–05 to allow compliance within 2,000 

flight hours or 60 months after the 

effective date of the AD, whichever 

occurs first, instead of prior to the 

accumulation of 2,000 total flight hours 

or within 60 months after the effective 

date of the AD, whichever occurs first. 

We agreed and proposed to revise 

paragraphs (f)(2) and (f)(4) of AD 2009– 

06–05 accordingly in the NPRM. The 

compliance time matches the intent of 

Transport Canada Civil Aviation (TCCA) 

AD CF–2008–18, dated May 9, 2008, 

and represents the maximum interval of 

time allowable for the affected airplanes 

to operate safely. 

Bombardier also requested that we 

change Table 2 of AD 2009–06–05 to 

replace references to two temporary 

revisions (TRs): Canadair TR 600/23, 

dated August 16, 2006, to the Canadair 

Challenger Model CL–600–1A11 

Airplane Flight Manual (AFM); and 

Canadair TR 600–1/19, dated August 16, 

2006, to the Canadair Challenger Model 

CL–600–1A11 AFM (Winglets). These 

two TRs are approved by TCCA, and 

should be replaced in AD 2009–06–05 

with references to the following FAAapproved TRs: Canadair TR 600/22, 

dated August 16, 2006, to the Canadair 

Challenger Model CL–600–1A11 AFM; 

and Canadair TR 600–1/17, dated 

August 16, 2006, to the Canadair 

Challenger Model CL–600–1A11 AFM 

(Winglets). We agreed and proposed to 

revise Table 2 of AD 2009–06–05 

accordingly in the NPRM. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Explanation of Change Made to the 

Manufacturer Name 

We have revised this AD to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

Explanation of Change to the 

Alternative Methods of Compliance 

We have revised the ‘‘Alternative 

Methods of Compliance (AMOCs)’’ 

paragraph (g)(1) in this AD to specify 

the current contact information. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 


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8462 Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Rules and Regulations 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a Note within the AD. 

Explanation of Change to Costs of 

Compliance 

Since issuance of the NPRM, we have 

increased the labor rate used in the 

Costs of Compliance from $80 per workhour to $85 per work-hour. The Costs of 

Compliance information, below, reflects 

this increase in the specified hourly 

labor rate. 

Costs of Compliance 

We estimate that this AD will affect 

about 108 products of U.S. registry. 

The actions that are required by AD 

2009–06–05 and retained in this AD 

take about 37 work-hours per product, 

at an average labor rate of $85 per work 

hour. Required parts cost about $0 per 

product. Based on these figures, the 

estimated cost of the currently required 

actions is $339,660, or $3,145 per 

product. 

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 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 this AD: 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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 

removing Amendment 39–15841 (74 FR 

12225, March 24, 2009) and adding the 

following new AD: 

2009–06–05R1 Bombardier, Inc.: 

Amendment 39–16217. Docket No. 

FAA–2009–1021; Directorate Identifier 

2009–NM–054–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 1, 2010. 

Affected ADs 

(b) This AD revises AD 2009–06–05, 

Amendment 39–15841. 

Applicability 

(c) This AD applies to the airplanes 

identified in Table 1, paragraphs (c)(1), (c)(2), 

(c)(3), and (c)(4) of this AD, certificated in 

any category. 

TABLE 1—AIRPLANES AFFECTED BY THIS AD 

Bombardier, Inc. model Serial Nos. 

(1) CL–600–1A11 (CL–600) airplanes ..................................................................................................... 1004 through 1085 inclusive. 

(2) CL–600–2A12 (CL–601) airplanes ..................................................................................................... 3001 through 3066 inclusive. 

(3) CL–600–2B16 (CL–601–3A & CL–601–3R) airplanes ....................................................................... 5001 through 5194 inclusive. 

(4) CL–600–2B16 (CL–604) airplanes ..................................................................................................... 5301 through 5635 inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 30: Ice and Rain Protection. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

There have been several cases of wing antiice piccolo duct failure reported on CL–600– 

2B19 (CRJ) aircraft. Although there have been 

no failures reported on Challenger aircraft, 

similar ducts are installed on the * * * 

[other] Challenger models. 

Upon investigation, it has been determined 

that ducts manufactured since June 2000, and 

installed since 1 August 2000, are susceptible 

to cracking due to the process used to drill 

the holes in the ducts. These ducts were 

installed on CL–600–2B16 aircraft, serial 

numbers 5469 through 5635 in production, 

but may also have been installed as 

replacements on CL–600–1A11, CL–600– 

2A12 and other CL–600–2B16 aircraft. 

Cracking of the wing anti-ice piccolo ducts 

could result in air leakage, with an adverse 

effect on the anti-ice air distribution pattern 

and a possible unannunciated insufficient 

heat condition. As a result, the airplane flight 

manual (AFM) instructions have been revised 


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Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Rules and Regulations 8463 

to provide proper annunciation of an 

insufficient heat condition, utilizing existing 

messages and indications, with instructions, 

to the pilot, to leave icing conditions if 

sufficient heat cannot be achieved or 

maintained. 

This directive mandates the amendment of 

the AFM procedures, in addition to checking 

the part numbers and serial numbers of the 

installed wing anti-ice piccolo ducts and 

replacing them as necessary. 

The unsafe condition is anti-ice system air 

leakage with a possible adverse effect on the 

anti-ice air distribution pattern and anti-ice 

capability without annunciation to the 

flightcrew, and consequent reduced 

controllability of the airplane. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) For airplanes identified in paragraphs 

(c)(1), (c)(2), (c)(3), and (c)(4) of this AD: 

Within 30 days after the effective date of this 

AD, revise the Normal and Abnormal 

Procedures sections of the applicable 

Canadair Challenger Airplane Flight Manual 

(AFM) by inserting a copy of the applicable 

temporary revision (TR) listed in Table 2 of 

this AD. When the information in the 

applicable TR is included in the general 

revisions of the AFM, the general revisions 

may be inserted in the AFM, as applicable, 

and the TR may be removed. 

TABLE 2—TEMPORARY REVISIONS

Canadair TR— Dated— To the— 

(i) 600/22 ......................................... August 16, 2006 ............................ Canadair Challenger Model CL–600–1A11 AFM. 

(ii) 600–1/17 .................................... August 16, 2006 ............................ Canadair Challenger Model CL–600–1A11 AFM (Winglets). 

(iii) 601/14 ....................................... August 16, 2006 ............................ Canadair Challenger Model CL–600–2A12 AFM, Product Support 

Publication (PSP) 601–1B–1. 

(iv) 601/15 ....................................... August 16, 2006 ............................ Canadair Challenger Model CL–600–2A12 AFM, PSP 601–1A–1. 

(v) 601/19 ........................................ August 16, 2006 ............................ Canadair Challenger Model CL–600–2A12 AFM, PSP 601–1B. 

(vi) 601/26 ....................................... August 16, 2006 ............................ Canadair Challenger Model CL–600–2B16 AFM, PSP 601A–1. 

(vii) 601/27 ...................................... August 16, 2006 ............................ Canadair Challenger Model CL–600–2A12 AFM. 

(viii) 601/27 ...................................... August 16, 2006 ............................ Canadair Challenger Model CL–600–2B16 AFM, PSP 601A–1–1. 

(ix) 604/20 ....................................... April 17, 2006 ................................ Canadair Challenger Model CL–604 AFM, PSP 604–1. 

(2) For airplanes identified in paragraphs 

(c)(1), (c)(2), and (c)(3) of this AD, and for 

Model CL–600–2B16 (CL–604) airplanes, 

serial numbers 5301 through 5468 inclusive: 

Within 2,000 flight hours or 60 months after 

the effective date of this AD, whichever 

occurs first, review the airplane maintenance 

records to determine if any anti-ice piccolo 

ducts or complete leading edge sections were 

replaced on or after August 1, 2000. 

(3) For airplanes identified in paragraphs 

(c)(1), (c)(2), and (c)(3) of this AD, and for 

Model CL–600–2B16 (CL–604) airplanes, 

serial numbers 5301 through 5468 inclusive: 

If, during the accomplishment of the action 

required by paragraph (f)(2) of this AD, it is 

determined that any anti-ice piccolo duct has 

been replaced on or after August 1, 2000, 

before further flight, inspect to determine if 

any affected serial number identified in 

paragraph 2.C. of the applicable service 

bulletin listed in Table 3 of this AD is 

installed. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the serial number of the duct 

can be conclusively determined from that 

review. If any affected serial number is 

installed, before further flight, replace the 

piccolo duct with a serviceable piccolo duct 

that does not have a serial number identified 

in paragraph 2.C. of the applicable service 

bulletin listed in Table 3 of this AD. Do all 

actions in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin listed in Table 3 

of this AD. 

TABLE 3—SERVICE BULLETINS

Model— 

Bombardier 

Service 

Bulletin— 

Revision— Dated— 

(i) CL–600–1A11 (CL–600) airplanes .......................................... 600–0734 Original ..................................... November 30, 2006. 

(ii) CL–600–2A12 (CL–601) airplanes ......................................... 601–0585 Original ..................................... November 30, 2006. 

(iii) CL–600–2B16 (CL–601–3A, CL–601–3R) airplanes ............ 601–0585 Original ..................................... November 30, 2006. 

(iv) CL–600–2B16 (CL–604) airplanes ........................................ 604–30–003 01 ............................................. January 21, 2008. 

(4) For Model CL–600–2B16 (CL–604) 

airplanes, serial numbers 5469 through 5635 

inclusive: Within 2,000 flight hours or 60 

months after the effective date of this AD, 

whichever occurs first, inspect the anti-ice 

piccolo ducts to determine if any affected 

serial number identified in paragraph 2.C. of 

Bombardier Service Bulletin 604–30–003, 

Revision 01, dated January 21, 2008, is 

installed. If any affected serial number is 

installed, before further flight, replace the 

piccolo duct with a serviceable piccolo duct 

that does not have a serial number identified 

in paragraph 2.C. of Bombardier Service 

Bulletin 604–30–003, Revision 01, dated 

January 21, 2008. Do all actions in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

604–30–003, Revision 01, dated January 21, 

2008. 

(5) As of April 28, 2009 (the effective date 

of AD 2009–06–05), no person may install on 

any airplane an anti-ice piccolo duct with a 

serial number identified in paragraph 2.C. of 

the applicable service bulletin identified in 

Table 3 of this AD. 

(6) Actions done before April 28, 2009, in 

accordance with Bombardier Service Bulletin 

604–30–003, dated November 30, 2006, are 

acceptable for compliance with the 

corresponding actions in 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, New York Aircraft 

Certification Office, ANE–170, 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: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone 516–228–7300; fax 516– 

794–5531. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your appropriate principal 

maintenance inspector (PMI) or principal 

avionics inspector (PAI), as appropriate, or 

lacking a principal inspector, your local 

Flight Standards District Office. 

(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 


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8464 Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Rules and Regulations 

actions are considered FAA-approved 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 

(44 U.S.C. 3501 et seq.), 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–2008–18, dated May 9, 2008, 

and the service information identified in 

Table 2 and Table 3 of this AD, for related 

information. 

Material Incorporated by Reference 

(i) You must use the service information 

specified in Table 4 and Table 5 of this AD, 

as applicable, to do the actions required by 

this AD, unless the AD specifies otherwise. 

TABLE 4—SERVICE BULLETINS INCORPORATED BY REFERENCE

Bombardier Service Bulletin— Revision— Dated— 

600–0734 ........................................ Original .......................................... November 30, 2006. 

601–0585 ........................................ Original .......................................... November 30, 2006. 

604–30–003 .................................... 01 ................................................... January 21, 2008. 

TABLE 5—TEMPORARY REVISIONS INCORPORATED BY REFERENCE

Canadair TR— Dated— To the— 

600/22 .................................................. August 16, 2006 ................................. Canadair Challenger Model CL–600–1A11 Airplane Flight Manual (AFM). 

600–1/17 .............................................. August 16, 2006 ................................. Canadair Challenger Model CL–600–1A11 AFM (Winglets). 

601/14 .................................................. August 16, 2006 ................................. Canadair Challenger Model CL–600–2A12 AFM, PSP 601–1B– 

1. 

601/15 .................................................. August 16, 2006 ................................. Canadair Challenger Model CL–600–2A12 AFM, PSP 601–1A– 

1. 

601/19 .................................................. August 16, 2006 ................................. Canadair Challenger Model CL–600–2A12 AFM, PSP 601–1B. 

601/26 .................................................. August 16, 2006 ................................. Canadair Challenger Model CL–600–2B16 AFM, PSP 601A–1. 

601/27 .................................................. August 16, 2006 ................................. Canadair Challenger Model CL–600–2A12 AFM. 

601/27 .................................................. August 16, 2006 ................................. Canadair Challenger Model CL–600–2B16 AFM, PSP 601A–1– 

1. 

604/20 .................................................. April 17, 2006 ..................................... Canadair Challenger Model CL–604 AFM, PSP 604–1. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in Table 6 

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

part 51. 

TABLE 6—NEW MATERIAL INCORPORATED BY REFERENCE

Canadair TR— Dated— To the— 

600/22 ............................................. August 16, 2006 ............................ Canadair Challenger Model CL–600–1A11 AFM. 

600–1/17 ......................................... August 16, 2006 ............................ Canadair Challenger Model CL–600–1A11 AFM (Winglets). 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of the service information 

contained in Table 7 and Table 8 of this AD 

on April 28, 2009 (74 FR 12225, March 24, 

2009). 

TABLE 7—SERVICE BULLETINS PREVIOUSLY INCORPORATED BY REFERENCE

Bombardier Service Bulletin— Revision— Dated— 

600—0734 ....................................... Original .......................................... November 30, 2006. 

601–0585 ........................................ Original .......................................... November 30, 2006. 

604–30–003 .................................... 01 ................................................... January 21, 2008. 

TABLE 8—TEMPORARY REVISIONS PREVIOUSLY INCORPORATED BY REFERENCE

Canadair TR— Dated— To the— 

601/14 .................................................. August 16, 2006 ................................. Canadair Challenger Model CL–600–2A12 AFM, PSP 601–1B– 

1. 

601/15 .................................................. August 16, 2006 ................................. Canadair Challenger Model CL–600–2A12 AFM, PSP 601–1A– 

1. 

601/19 .................................................. August 16, 2006 ................................. Canadair Challenger Model CL–600–2A12 AFM, PSP 601–1B. 

601/26 .................................................. August 16, 2006 ................................. Canadair Challenger Model CL–600–2B16 AFM, PSP 601A–1. 

601/27 .................................................. August 16, 2006 ................................. Canadair Challenger Model CL–600–2A12 AFM. 

601/27 .................................................. August 16, 2006 ................................. Canadair Challenger Model CL–600–2B16 AFM, PSP 601A–1– 

1. 


jlentini on DSKJ8SOYB1PROD with RULES
Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Rules and Regulations 8465 

TABLE 8—TEMPORARY REVISIONS PREVIOUSLY INCORPORATED BY REFERENCE—Continued 

Canadair TR— Dated— To the— 

604/20 .................................................. April 17, 2006 ..................................... Canadair Challenger Model CL–604 AFM, PSP 604–1. 

(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 

16, 2010. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–3463 Filed 2–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0783; Directorate 

Identifier 2009–NM–081–AD; Amendment 

39–16213; AD 2010–05–04] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Corporation Model MD–90–30 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Model MD–90–30 airplanes. This AD 

requires repetitive inspections for 

cracking of the overwing frames at 

stations 883, 902, 924, 943, and 962, left 

and right sides, and corrective actions if 

necessary. This AD results from reports 

of cracked overwing frames. We are 

issuing this AD to detect and correct 

such cracking, which could sever the 

frame, increase the loading of adjacent 

frames, and result in damage to adjacent 

structure and loss of overall structural 

integrity of the airplane. 

DATES: This AD is effective April 1, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 1, 2010. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, California 90846–0001; 

telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.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: 

Roger Durbin, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; telephone (562) 

627–5233; fax (562) 627–5210. 

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 all 

Model MD–90–30 airplanes. That NPRM 

was published in the Federal Register 

on September 4, 2009 (74 FR 45785). 

That NPRM proposed to require 

repetitive inspections for cracking of the 

overwing frames at stations 883, 902, 

924, 943, and 962, left and right sides, 

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 sole commenter. 

Request To Revise Wording in the 

Summary Section and Unsafe 

Condition Paragraph of the NPRM 

The Boeing Company requests that we 

revise the wording of the precipitating 

event in the Summary section and 

Unsafe Condition paragraph of the 

NPRM to clarify that the reported 

cracking was found on Model MD–80 

airplanes, and that frames of the same 

design are installed on Model MD–90 

airplanes. The commenter explains that 

the proposed revision will be in line 

with the first paragraph of the 

‘‘Discussion’’ section of the NPRM. The 

commenter asserts that otherwise, the 

Summary section and paragraph (e) of 

the NPRM read that ‘‘Model MD–90 

overwing frames have cracked,’’ which 

is not the case. 

We agree that clarification might be 

necessary. While the commenter’s 

proposed revision is more precise with 

respect to the history of the service 

difficulties, the Summary section of ADs 

is designed to provide only a brief 

description of the action being 

proposed. Likewise, the Unsafe 

Condition paragraph in the regulatory 

text of an AD is meant to be only a brief 

statement. Detailed background 

information is provided in the 

Discussion section of a proposed AD. 

We addressed the issues raised by the 

commenter in the Discussion section of 

the NPRM. That section is not restated 

in this final rule. We have not changed 

the AD in this regard. 

Request To Revise Wording in the 

Discussion Section of the NPRM 

The Boeing Company requests that we 

revise the first sentence of the second 

paragraph of the ‘‘Discussion’’ section of 

the NPRM to read, ‘‘The cracked 

overwing frames on McDonnell Douglas 

Model MD–90–30 airplanes have the 

same design as those installed on Model 

MD–80 series airplanes.’’ The 

commenter explains that the proposed 

revision sounds more logical than how 

it reads in the NPRM and that the issue 

is the Model MD–90 frames cracking, 

not the Model MD–80 frames. 

We agree that clarification is needed. 

The proposed revision would indicate 

that we have reports of cracks on Model 

MD–90–30 airplanes, which is not the 

case. As stated in the NPRM, the reports 


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