Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 41653 

and could lead to the loss of the vertical 

stabilizer. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Inspections 

(g) Within 4,500 flight cycles after the 

effective date of this AD, do a detailed 

inspection for distress in and existing repairs 

to the leading edge structure of the vertical 

stabilizer at the splice at Station Zfs=52.267, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD80–55A067, dated June 24, 2010. 

Repetitive Inspections for Cracks, and 

Related Investigative and Corrective Actions 

(h) Before further flight after doing the 

inspection required by paragraph (g) of this 

AD, inspect for cracks of the left and right 

vertical stabilizer front spar cap, in 

accordance with either Option 1 or Option 2 

as specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD80–55A067, dated June 24, 2010. If any 

crack is found, before further flight, evaluate 

and verify to confirm all crack indications, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD80–55A067, dated June 24, 2010. 

(1) If any cracking is confirmed, before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (l) of this AD. 

(2) If no cracking is confirmed, repeat the 

inspection thereafter at intervals not to 

exceed the applicable interval specified in 

paragraph (h)(2)(i) or (h)(2)(ii) of this AD. 

(i) If the most recent inspection was done 

using Option 1, the next inspection must be 

done within 4,400 flight cycles. 

(ii) If the most recent inspection was done 

using Option 2, the next inspection must be 

done within 3,000 flight cycles. 

Leading Edge Repair 

(i) If leading edge distress is found during 

the detailed inspection required by paragraph 

(g) of this AD, before further flight and after 

accomplishing the inspection required by 

paragraph (h) of this AD, repair the leading 

edge, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD80–55A067, dated June 

24, 2010. 

Inspection for Loose/Missing Fasteners 

(j) For airplanes on which no cracking is 

confirmed during the initial inspection 

required by paragraph (h) of this AD: At the 

applicable time specified in paragraph (j)(1) 

or (j)(2) of this AD, do a detailed inspection 

for indications of loose and missing fasteners, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD80–55A067, dated June 24, 2010. If any 

loose or missing fastener is found, before 

further flight, repair the leading edge, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD80–55A067, dated June 24, 2010. 

(1) If the inspection required by paragraph 

(h) was done using Option 1, do the 

inspection required by paragraph (j) of this 

AD within 4,400 flight cycles after 

accomplishing the inspection required by 

paragraph (h) of this AD. 

(2) If inspection required by paragraph (h) 

was done using Option 2, do the inspection 

required by paragraph (j) of this AD within 

3,000 flight cycles after accomplishing the 

inspection required by paragraph (h) of this 

AD. 

(k) For airplanes on which no cracking is 

confirmed during the most recent inspection 

required by paragraph (h) of this AD: Repeat 

the inspection for loose and missing fasteners 

required by paragraph (j) of this AD thereafter 

at intervals not to exceed the applicable time 

specified in paragraph (k)(1) or (k)(2) of this 

AD. 

(1) If the most recent inspection required 

by paragraph (h) was done using Option 1, 

the next inspection required by paragraph (j) 

of this AD must be done within 4,400 flight 

cycles after accomplishing the most recent 

inspection required by paragraph (j) of this 

AD. 

(2) If the most recent inspection required 

by paragraph (h) was done using Option 2, 

the next inspection required by paragraph (j) 

of this AD must be done within 3,000 flight 

cycles after the most recent inspection 

required by paragraph (j) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(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 the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

Related Information 

(m) For more information about this AD, 

contact Roger Durbin, Aerospace Engineer, 

Airframe Branch, ANM–120L, Los Angeles 

Aircraft Certification Office, 3960 Paramount 

Boulevard, Lakewood, California 90712– 

4137; phone: 562–627–5233; fax: 562–627– 

5210; e-mail: Roger.Durbin@faa.gov. 

Material Incorporated by Reference 

(n) You must use Boeing Alert Service 

Bulletin MD80–55A067, dated June 24, 2010, 

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, 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. 

(3) 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. 

(4) 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 an NARA facility, 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 July 1, 

2011. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–17400 Filed 7–14–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1307; Directorate 

Identifier 2010–NM–049–AD; Amendment 

39–16671; AD 2011–09–09] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2A12 (CL–601) and 

CL–600–2B16 (CL–601–3A, CL–601– 

3R, and CL–604 Variants) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

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: 

During flight-testing of a wing anti-ice 

piccolo tube containing a deliberate small 

breach, it was determined that the wing 

leading edge thermal switches were not 

detecting the consequent bleed leak at the 

design threshold. As a result, new 

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41654 Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 

Airworthiness Limitation tasks, consisting of 

a functional test of the wing leading edge 

thermal switches and an inspection of the 

wing anti-ice duct piccolo tubes, have been 

introduced in order to limit exposure to 

dormant failure of the switches in the event 

of piccolo tube failure, which could 

potentially compromise the structural 

integrity of the wing leading edge and the 

effectiveness of the wing anti-ice system. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

August 19, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 19, 2011. 

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: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on January 5, 2011 (76 FR 477). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During flight-testing of a wing anti-ice 

piccolo tube containing a deliberate small 

breach, it was determined that the wing 

leading edge thermal switches were not 

detecting the consequent bleed leak at the 

design threshold. As a result, new 

Airworthiness Limitation tasks, consisting of 

a functional test of the wing leading edge 

thermal switches and an inspection of the 

wing anti-ice duct piccolo tubes, have been 

introduced in order to limit exposure to 

dormant failure of the switches in the event 

of piccolo tube failure, which could 

potentially compromise the structural 

integrity of the wing leading edge and the 

effectiveness of the wing anti-ice system. 

This directive mandates the revision of the 

approved maintenance schedule to include 

these new tasks, including phase-in 

schedules. 

This revision clarifies the applicability of 

the directive for CL–600–2A12 aircraft, serial 

numbers 3001 through 3066, and for CL– 

600–2B16 aircraft, serial numbers 5001 

through 5194. The directive is only 

applicable to these aircraft if Bombardier 

Service Bulletin (SB) 601–0590 [Scheduled 

Maintenance Instructions (MSG–3) Derived— 

Qualification] has been incorporated. There 

is no change required to the approved 

maintenance schedule if SB 601–0590 has 

not been incorporated. 

You may obtain further information by 

examining the MCAI in the AD docket. 

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. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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. 

Costs of Compliance 

We estimate that this AD will affect 

103 products of U.S. registry. We also 

estimate that it will take about 1 workhour per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $8,755, or $85 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 

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 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 proposed 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. 

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Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 41655 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2011–09–09 Bombardier, Inc.: Amendment 

39–16671. Docket No. FAA–2010–1307; 

Directorate Identifier 2010–NM–049–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 19, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the airplanes 

identified in paragraphs (c)(1), (c)(2), (c)(3), 

and (c)(4) of this AD; certificated in any 

category. 

(1) Bombardier, Inc. Model CL–600–2A12 

(CL–601) airplanes, serial numbers 3001 

through 3066 inclusive on which Bombardier 

Service Bulletin 601–0590 has been 

accomplished. 

(2) Bombardier, Inc. CL–600–2B16 (CL– 

601–3A and CL–601–3R Variants) airplanes, 

serial numbers 5001 through 5194 inclusive 

on which Bombardier Service Bulletin 601– 

0590 has been accomplished. 

(3) Bombardier, Inc. CL–600–2B16 (CL–604 

Variants) airplanes, serial numbers 5301 

through 5665 inclusive. 

(4) Bombardier, Inc. CL–600–2B16 (CL–604 

Variants) airplanes, serial numbers 5701 and 

subsequent. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (j) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued operational safety of the airplane. 

Subject 

(d) Air Transport Association (ATA) of 

America Codes 30 and 36: Ice and Rain 

Protection and Pneumatic, respectively. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During flight-testing of a wing anti-ice 

piccolo tube containing a deliberate small 

breach, it was determined that the wing 

leading edge thermal switches were not 

detecting the consequent bleed leak at the 

design threshold. As a result, new 

Airworthiness Limitation tasks, consisting of 

a functional test of the wing leading edge 

thermal switches and an inspection of the 

wing anti-ice duct piccolo tubes, have been 

introduced in order to limit exposure to 

dormant failure of the switches in the event 

of piccolo tube failure, which could 

potentially compromise the structural 

integrity of the wing leading edge and the 

effectiveness of the wing anti-ice system. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 30 days after the effective date 

of this AD: Revise the Airworthiness 

Limitations Section of the Instructions for 

Continued Airworthiness by incorporating 

the applicable tasks identified in table 1 of 

this AD. 

TABLE 1—AIRWORTHINESS LIMITATIONS TASKS

For Bombardier, Inc. model— Incorporate task(s)— Identified in— 

CL-600-2A12 (CL-601) airplanes, serial numbers 3001 through 3066 inclusive on which 

Bombardier Service Bulletin 601-0590 has 

been accomplished.

30–11–00–101, Wing Anti-icing, and 30–11– 

00–102, Wing Anti-icing.

Bombardier Challenger 601 Time Limits/Maintenance Checks, PSP 601–5, Revision 38, 

dated June 19, 2009. 

CL-600-2B16 (CL-601-3A and CL-601-3R 

Variants) airplanes, serial numbers 5001 

through 5194 inclusive on which Bombardier 

Service Bulletin 601–0590 has been accomplished.

30–11–00–101, Wing Anti-icing, and 30–11– 

00–102, Wing Anti-icing.

Bombardier Challenger 601 Time Limits/Maintenance Checks, PSP 601A–5, Revision 34, 

dated June 19, 2009. 

CL–600–2B16 (CL–604 Variants) airplanes, serial numbers 5301 through 5665 inclusive.30–11–00–101, Detailed Inspection of the 

Wing Anti-Ice Duct Piccolo-Tube, and 

36-21-00-101, Functional Test of the Leading Edge Thermal Switches.

Bombardier Challenger 604 Time Limits/Maintenance Checks, CH 604 TLMC, Revision 

13, dated August 12, 2009. 

CL–600–2B16 (CL–604 Variants) airplanes, serial numbers 5701 and subsequent.30–11–00–101, Detailed Inspection of the 

Wing Anti-Ice Duct Piccolo-Tube, and 

36-21-00-101, Functional Test of the Leading Edge Thermal Switches.

Bombardier Challenger 605 Time Limits/Maintenance Checks, CH 605 TLMC, Revision 

1, dated August 12, 2009. 

(h) For all tasks identified in paragraph (g) 

of this AD, the initial compliance times for 

those tasks are within the applicable times 

specified in table 2 of this AD. 

TABLE 2—INITIAL COMPLIANCE TIMES FOR AIRWORTHINESS LIMITATIONS TASKS

Bombardier, Inc. model— Task(s)— Initial compliance time (whichever 

occurs later)— 

CL-600-2A12 (CL-601) airplanes, 

serial numbers 3001 through 

3066 inclusive; and 

CL-600-2B16 (CL-601-3A and 

CL-601-3R Variants) airplanes, 

serial numbers 5001 through 

5194 inclusive; on which Bombardier Service Bulletin 601– 

0590 has been accomplished.

30–11–00–101, Wing Anti-icing ... Prior to the accumulation of 4,800 

total flight hours; or within 4,800 

flight hours after accomplishing 

Task 30-11-06-204 in Section 

5-20–15 of the applicable Time 

Limits/Maintenance Checks 

manual specified in table 1 of 

this AD; whichever occurs later.

Within 240 flight hours after the 

effective date of this AD. 

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41656 Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 

TABLE 2—INITIAL COMPLIANCE TIMES FOR AIRWORTHINESS LIMITATIONS TASKS—Continued 

Bombardier, Inc. model— Task(s)— Initial compliance time (whichever 

occurs later)— 

CL-600-2A12 (CL-601) airplanes, 

serial numbers 3001 through 

3066 inclusive; and 

CL-600-2B16 (CL-601-3A and 

CL-601-3R Variants) airplanes, 

serial numbers 5001 through 

5194 inclusive; on which Bombardier Service Bulletin 601– 

0590 has been accomplished.

30–11–00–102, Wing Anti-icing ... Prior to the accumulation of 4,800 

total flight hours; or within 4,800 

flight hours after accomplishing 

Task 30-13-00-205 in Section 

5-20–15 of the applicable Time 

Limits/Maintenance Checks 

manual specified in table 1 of 

this AD; whichever occurs later.

Within 240 flight hours after the 

effective date of this AD. 

CL–600–2B16 (CL–604 Variants) 

airplanes, serial numbers 5301 

through 5665 inclusive.

30–11–00–101, Detailed Inspection of the Wing Anti-Ice Duct 

Piccolo-Tube, and 

36-21-00-101, Functional Test 

of the Leading Edge Thermal 

Switches.

Prior to the accumulation of 6,400 

total flight hours; except for airplanes having 6,400 total flight 

hours or more as of the effective date of this AD on which 

the task has not been accomplished: prior to the next scheduled 6,400 flight hour task inspection or prior to the next 

scheduled accomplishment of 

Task 57-10-00–208 in the applicable Time Limits/Maintenance 

Checks manual specified in 

table 1 of this AD, whichever 

occurs first.

Within 320 flight hours after the 

effective date of this AD. 

CL–600–2B16 (CL–604 Variants) 

airplanes, serial numbers 5701 

and subsequent.

30–11–00–101, Detailed Inspection of the Wing Anti-Ice Duct 

Piccolo-Tube, and 

36-21-00-101, Functional Test 

of the Leading Edge Thermal 

Switches.

Prior to the accumulation of 6,400 

total flight hours.

Within 320 flight hours after the 

effective date of this AD. 

(i) After accomplishing the actions 

required by paragraph (g) of this AD, no 

alternative tasks or task intervals may be 

used unless the tasks or task intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (j)(1) of 

this AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it 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, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(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. 

Related Information 

(k) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–49R1, dated January 21, 

2010, and the service information specified 

in Table 1 of this AD, for related information. 

Material Incorporated by Reference 

(l) You must use the applicable service 

information contained in table 3 of this AD 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

TABLE 3—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Tasks 30–11–00–101, Wing Anti-icing, and 30–11–00–102, Wing Anti-icing, of the Bombardier Challenger 601 Time Limits/Maintenance Checks, PSP 601–5.38 June 19, 2009. 

Tasks 30–11–00–101, Wing Anti-icing, and 30–11–00–102, Wing Anti-icing, of the Bombardier Challenger 601 Time Limits/Maintenance Checks, PSP 601A–5.34 June 19, 2009. 

Tasks 30–11–00–101, Detailed Inspection of the Wing Anti-Ice Duct Piccolo-Tube, and 36–21–00–101, 

Functional Test of the Leading Edge Thermal Switches, of the Bombardier Challenger 604 Time Limits/ 

Maintenance Checks, CH 604 TLMC.

13 August 12, 2009. 

Tasks 30–11–00–101, Detailed Inspection of the Wing Anti-Ice Duct Piccolo-Tube, and 36–21–00–101, 

Functional Test of the Leading Edge Thermal Switches, of the Bombardier Challenger 605 Time Limits/ 

Maintenance Checks, CH 605 TLMC.

1 August 12, 2009. 

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Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 41657 

The title pages of these documents do not 

indicate the revision level or issue date of the 

documents. Only the Record of Revisions of 

these documents contains the revision level 

of these documents. 

(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 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. 

(4) 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 April 13, 

2011. 

Ali Bahrami, 

Manager,Transport Airplane 

Directorate,Aircraft Certification Service. 

[FR Doc. 2011–17402 Filed 7–14–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0653; Directorate 

Identifier 2010–NM–249–AD; Amendment 

39–16745; AD 2011–14–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–342 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

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: 

* * * * * 

Following a query from an operator, 

investigations revealed that some MSN 

[manufacturer serial number], for which 

Airbus modification 40391 was indicated as 

fully embodied inside the Aircraft Inspection 

Report (AIR), did not have Modification 

Proposal (MP–S10437) which is part of this 

modification embodied in production. 

As a result, ALI [Airworthiness Limitation 

Item] task 533105–01–02 has not been 

performed on the MSN listed in the 

applicability section of this AD, which 

constitutes an unsafe condition. 

* * * * * 

The unsafe condition is fatigue cracking 

of the internal structure of the fuselage, 

which could adversely affect the 

structural integrity of the airplane. This 

AD requires actions that are intended to 

address the unsafe condition described 

in the MCAI. 

DATES: This AD becomes effective 

August 1, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 1, 2011. 

We must receive comments on this 

AD by August 29, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

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 this AD, 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. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0173, 

dated August 17, 2010 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Airworthiness Limitation Item (ALI) task 

533105–01–02 is applicable to aeroplanes on 

which Airbus modification 40391 has not 

been embodied in production. The 

requirements associated to this task are 

applicable to aeroplanes on which 

Modification Proposal (MP–S10437) has not 

been embodied. 

Following a query from an operator, 

investigations revealed that some MSN 

[manufacturer serial numbers], for which 

Airbus modification 40391 was indicated as 

fully embodied inside the Aircraft Inspection 

Report (AIR), did not have Modification 

Proposal (MP–S10437) which is part of this 

modification embodied in production. 

As a result, ALI task 533105–01–02 has not 

been performed on the MSN listed in the 

applicability section of this AD, which 

constitutes an unsafe condition. 

For the reasons described above, this AD 

requires repetitive special detailed 

inspections [for fatigue cracking of the 

internal structure of the fuselage] 

corresponding to ALI task 533105–01–02 and 

the accomplishment of the associated 

corrective actions. 

The unsafe condition is fatigue cracking 

of the internal structure of the fuselage, 

which could adversely affect the 

structural integrity of the airplane. The 

special detailed inspection is defined as 

an ultrasonic inspection in this AD. The 

corrective action is repairing any cracks 

in accordance with a method approved 

by the FAA or EASA (or its delegated 

agent). You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A330–53–3185, including 

Appendices 01 and 02, dated May 20, 

2010. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

mstockstill on DSK4VPTVN1PROD with RULES