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

12225 

Vol. 74, No. 55 

Tuesday, March 24, 2009 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1216; Directorate 

Identifier 2008–NM–111–AD; Amendment 

39–15841; AD 2009–06–05] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

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 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: 

[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 above 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 

28, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 28, 2009. 

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 Propulsion Branch, 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 include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on November 17, 2008 (73 FR 

67820). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The 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 above 

Challenger models [Bombardier CL–600– 

1A11, CL–600–2A12, and CL–600–2B16 

airplanes]. 

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 

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. 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. 

Change to Applicability 

Since we issued the NPRM, we 

discovered that we inadvertently 

designated duplicate models in 

paragraphs (c)(3) and (c)(4) of Table 1 of 

the NPRM. Those paragraphs both 

specified Bombardier Model ‘‘CL–600– 

2B16 (CL–601–3A, CL–601–3R, & CL– 

604) airplanes.’’ However, paragraph 

(c)(3) of the AD should have identified 

Bombardier Model ‘‘CL–600–2B16 (CL– 

601–3A & CL–601–3R) airplanes,’’ and 

paragraph (c)(4) of the AD should have 

identified Model ‘‘CL–600–2B16 (CL– 

604) airplanes.’’ The serial numbers that 

appeared in paragraphs (c)(3) and (c)(4) 

of the NPRM were identified correctly 

in the NPRM and remain unchanged in 

this final rule. We have changed 

paragraphs (c)(3) and (c)(4) of this AD 

accordingly. 

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. 

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 

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12226 Federal Register / Vol. 74, No. 55 / Tuesday, March 24, 2009 / Rules and Regulations 

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 

108 products of U.S. registry. We also 

estimate that it will take about 37 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Based on these figures, we estimate the 

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

be $319,680, or $2,960 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 adding 

the following new AD: 

2009–06–05 Bombardier, Inc. (Formerly 

Canadair): Amendment 39–15841. 

Docket No. FAA–2008–1216; Directorate 

Identifier 2008–NM–111–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 28, 2009. 

Affected ADs 

(b) None. 

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 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 above 

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 

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 

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Federal Register / Vol. 74, No. 55 / Tuesday, March 24, 2009 / Rules and Regulations 12227 

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 and the TR may 

be removed. 

TABLE 2—TEMPORARY REVISIONS

Canadair TR— Dated— To the— 

(i) 600/23 ......................................... August 16, 2006 ............................ Canadair Challenger Model CL–600–1A11 AFM. 

(ii) 600–1/19 .................................... 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: 

Prior to the accumulation of 2,000 total flight 

hours, or within 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 

since 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 action required by paragraph 

(f)(2) of this AD, it is determined that any 

anti-ice piccolo duct has been replaced since 

August 1, 2000, before further flight do a 

visual inspection to determine if any affected 

serial number is installed as identified in 

paragraph 2.C. of the applicable service 

bulletin identified in Table 3 of this AD. 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 identified 

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 level— Date— 

(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: Prior to the accumulation of 2,000 

total flight hours, or within 60 months after 

the effective date of this AD, whichever 

occurs first, do a visual inspection of the 

anti-ice piccolo ducts to determine if any 

affected serial number identified in 

paragraph 2.C. of the 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 the effective date of this AD, no 

person may install on any airplane an antiice 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 the effective date 

of this AD 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, 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: Dan Parrillo, 

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) 228–7305; 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 

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, 

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 

contained in Tables 4 and 5 of this AD to do 

the actions required by this AD, as 

applicable, unless the AD specifies 

otherwise. 

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12228 Federal Register / Vol. 74, No. 55 / Tuesday, March 24, 2009 / Rules and Regulations 

(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 or 425–227–1152. 

(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. 

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— 

600/23 ............................................. August 16, 2006 ............................ Canadair Challenger Model CL–600–1A11 AFM. 

600–1/19 ......................................... 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. 

Issued in Renton, Washington, on February 

27, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–5968 Filed 3–23–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0018; Directorate 

Identifier 2007–NM–145–AD; Amendment 

39–15842; AD 2009–06–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Series Airplanes and Model 

A300–600 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: This airworthiness directive 

(AD) supersedes two existing ADs. One 

AD applies to certain Airbus Model 

A310–200 and –300 series airplanes. 

That AD currently requires repetitive 

inspections for cracking of the flap 

transmission shafts, and replacement of 

the transmission shafts if necessary. 

That AD also provides an optional 

terminating action for the repetitive 

inspections. The other existing AD 

applies to all Airbus Model A300 B4– 

600, B4–600R, and F4–600R series 

airplanes, and Model C4–605R Variant F 

airplanes (collectively called A300–600 

series airplanes); and Model A310–200 

and –300 series airplanes. That AD 

currently requires a one-time inspection 

of the trimmable horizontal stabilizer 

actuator (THSA), corrective actions if 

necessary, and follow-on repetitive 

tasks. This new AD also requires 

revising the Airworthiness Limitations 

Section of the Instructions for 

Continued Airworthiness to incorporate 

new limitations and maintenance tasks 

for aging systems maintenance. This AD 

results from the manufacturer’s 

determination that life limitations and 

maintenance tasks are necessary to 

ensure continued operational safety of 

the affected airplanes. We are issuing 

this AD to prevent reduced structural 

integrity of these airplanes due to the 

failure of system components. 

DATES: This AD becomes effective April 

28, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of April 28, 2009. 

On August 29, 2006 (71 FR 42021, 

July 25, 2006), the Director of the 

Federal Register approved the 

incorporation by reference of Airbus 

Service Bulletin A300–27–6044, 

Revision 04, dated September 10, 2001; 

and Airbus Service Bulletin A310–27– 

2089, Revision 02, dated June 28, 2001. 

On June 20, 2006 (71 FR 28254, May 

16, 2006), the Director of the Federal 

Register approved the incorporation by 

reference of Airbus Service Bulletin 

A310–27–2092, Revision 02, dated April 

11, 2005; and Airbus Service Bulletin 

A310–27–2095, dated March 29, 2000. 

ADDRESSES: For Airbus service 

information identified in this AD, 

contact Airbus SAS–EAW 

(Airworthiness Office), 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax 

+33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. For 

TRW Aeronautical Systems service 

information identified in this AD, 

contact TRW Syste`mes Ae ́ronautiques 

Civils SAS, Product Support 

Department, 7–9 Avenue de l’Eguillette, 

Saint Ouen l’Aumone BP 7186, 95056 

Cergy-Pontoise Cedex France, telephone 

+33 1 34 32 63 00; fax +33 1 34 32 63 

10. 

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 

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