430 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 

auxiliary spar area on the left side of the 

aircraft, and modify the left wing rib and left 

and right debris shields, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 700–29–021 (for 

Model BD–700–1A10 airplanes) or 700– 

1A11–29–004 (for Model BD–700–1A11 

airplanes), both Revision 01, both dated 

January 25, 2010, as applicable. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Actions accomplished before the 

effective date of this AD in accordance with 

Bombardier Service Bulletin 700–29–021 or 

700–1A11–29–004, both dated April 3, 2009, 

as applicable, are considered acceptable for 

compliance with the corresponding actions 

specified 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 

(i) 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. 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 principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards 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. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(j) Refer to MCAI Canadian Airworthiness 

Directive CF–2010–10, dated March 26, 2010; 

and Bombardier Service Bulletins 700–29– 

021 and 700–1A11–29–004, both Revision 

01, both dated January 25, 2010; for related 

information. 

Material Incorporated by Reference 

(k) You must use Bombardier Service 

Bulletin 700–29–021, Revision 01, dated 

January 25, 2010; or Bombardier Service 

Bulletin 700–1A11–29–004, Revision 01, 

dated January 25, 2010; as applicable; to do 

the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact 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 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–32996 Filed 1–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0953; Directorate 

Identifier 2010–NM–010–AD; Amendment 

39–16565; AD 2011–01–11] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model MD–90–30 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

repetitive high frequency eddy current 

inspections for cracking on the hinge 

bearing lugs of the left and right sides 

of the center section ribs of the 

horizontal stabilizer, and related 

investigative and corrective actions if 

necessary. This AD was prompted by 

reports of cracks found on either the left 

or right (or in one case, both) sides of 

the center section ribs of the horizontal 

stabilizer. We are issuing this AD to 

detect and correct cracking in the hinge 

bearing lugs of the center section of the 

left and right ribs, which could result in 

failure of the hinge bearing lugs and 

consequent inability of the horizontal 

stabilizer to sustain the required loads. 

DATES: This AD is effective February 9, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of February 9, 2011. 

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. You 

may review copies of the referenced 

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. 

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 (phone: 800–647–5527) is 

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 

(ACO), 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

telephone (562) 627–5233; fax (562) 

627–5210. 

SUPPLEMENTARY INFORMATION: 

WReier-Aviles on DSKGBLS3C1PROD with RULES

Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 431 

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 the 

specified products. That NPRM 

published in the Federal Register on 

October 1, 2010 (75 FR 60665). That 

NPRM proposed to require repetitive 

high frequency eddy current inspections 

for cracking on the hinge bearing lugs of 

the left and right sides of the center 

section ribs of the horizontal stabilizer, 

and related investigative and corrective 

actions if necessary. 

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 to Applicability 

We have revised the existing AD to 

identify model designations as 

published in the most recent type 

certificate data sheet for the affected 

models. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed—except for minor editorial 

changes and the change described 

previously. We have determined that 

these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Interim Action 

We consider this AD interim action. 

The manufacturer is currently 

developing a modification that will 

address the unsafe condition identified 

in this AD. Once this modification is 

developed, approved, and available, we 

might consider additional rulemaking. 

Costs of Compliance 

We estimate that this AD affects 16 

airplanes of U.S. registry. We also 

estimate that it takes about 2 work-hours 

per product to comply with this AD. 

The average labor rate is $85 per workhour. Based on these figures, we 

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

operators to be $2,720, or $170 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 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 

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 airworthiness 

directive (AD): 

2011–01–11 The Boeing Company: 

Amendment 39–16565; Docket No. 

FAA–2010–0953; Directorate Identifier 

2010–NM–010–AD. 

Effective Date 

(a) This AD is effective February 9, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model MD–90–30 airplanes, 

certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

Unsafe Condition 

(e) This AD results from reports of cracks 

found on either the left or right (or in one 

case, both) sides of the center section ribs of 

the horizontal stabilizer. The Federal 

Aviation Administration is issuing this AD to 

detect and correct cracking in the hinge 

bearing lugs of the center section of the left 

and right ribs, which could result in failure 

of the hinge bearing lugs and consequent 

inability of the horizontal stabilizer to sustain 

the required loads. 

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. 

Repetitive Inspections and Corrective 

Actions for Cracking 

(g) At the applicable time in paragraph 

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

Bulletin MD90–55A016, Revision 1, dated 

February 17, 2010, except as required by 

paragraph (n) of this AD, do a high frequency 

eddy current (HFEC) inspection for cracking 

on the hinge bearing lugs of the left and right 

sides of the center section ribs of the 

horizontal stabilizer, and do all applicable 

related investigative actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin MD90–55A016, 

Revision 1, dated February 17, 2010. Do all 

applicable related investigative actions before 

further flight. 

(h) If during any inspection required by 

paragraph (g) of this AD, no cracking is 

found, repeat the inspection required by 

paragraph (g) of this AD thereafter at 

intervals not to exceed 1,680 flight cycles. 

(i) If during any inspection required by 

paragraph (g) or (h) of this AD, any crack is 

found having a length between Points ‘A’ and 

‘B’ less than or equal to 0.15 inch and crack 

length between Points ‘C’ and ‘D’ less than 

or equal to 0.05 inch, as identified in Boeing 

Alert Service Bulletin MD90–55A016, 

Revision 1, dated February 17, 2010: Before 

further flight, blend out the crack; and within 

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432 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 

1,000 flight cycles after doing the blend out, 

do an HFEC inspection of the blend out on 

the center section rib hinge bearing lug; in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–55A016, Revision 1, dated February 

17, 2010. Repeat the HFEC inspection of the 

blend out thereafter at intervals not to exceed 

400 flight cycles until the replacement 

specified by paragraph (j) is done. 

(j) If any cracking is detected during any 

inspection required by paragraph (i) of this 

AD, before further flight, replace the 

horizontal stabilizer center section rib with a 

new horizontal stabilizer center section rib, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–55A016, Revision 1, dated February 

17, 2010. 

(k) If during any inspection required by 

paragraph (g) or (h) of this AD, any crack is 

found having a length between Points ‘A’ and 

‘B’ greater than 0.15 inch or crack length 

between Points ‘C’ and ‘D’ greater than 0.05 

inch, as identified in Boeing Alert Service 

Bulletin MD90–55A016, Revision 1, dated 

February 17, 2010: Before further flight, 

replace the horizontal stabilizer center 

section rib with a new horizontal stabilizer 

center section rib, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD90–55A016, Revision 1, 

dated February 17, 2010. 

(l) For any airplane having a horizontal 

stabilizer center section rib replaced during 

the actions required by paragraph (j) or (k) of 

this AD: Before the accumulation of 7,200 

total flight cycles on the new horizontal 

stabilizer center section rib, do the actions 

required by paragraph (g) of this AD, and do 

all applicable actions specified in paragraphs 

(h), (i), (j), and (k) of this AD. 

Credit for Actions Accomplished According 

to Previous Issue of Service Bulletin 

(m) Actions accomplished before the 

effective date of this AD according to Boeing 

Alert Service Bulletin MD90–55A016, dated 

December 16, 2009, are considered 

acceptable for compliance with the 

corresponding actions required by 

paragraphs (g), (h), (i), (j), and (k) of this AD. 

Exception to the Service Bulletin 

(n) Where Boeing Alert Service Bulletin 

MD90–55A016, Revision 1, dated February 

17, 2010, specifies a compliance time ‘‘after 

the original issue date on the service 

bulletin,’’ this AD requires compliance within 

the specified compliance time after the 

effective date of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(o)(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. Send information to ATTN: Roger 

Durbin, Aerospace Engineer, Airframe 

Branch, ANM–120L, FAA, Los Angeles ACO, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; telephone (562) 627– 

5233; fax (562) 627–5210. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(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 the 

approval must specifically refer to this AD. 

Related Information 

(p) For more information about this AD, 

contact Roger Durbin, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; telephone 

(562) 627–5233; fax (562) 627–5210. 

Material Incorporated by Reference 

(q) You must use Boeing Alert Service 

Bulletin MD90–55A016, Revision 1, dated 

February 17, 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 

Boeing Alert Service Bulletin MD90–55A016, 

Revision 1, dated February 17, 2010, 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 

December 22, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–32993 Filed 1–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0952; Directorate 

Identifier 2010–NM–131–AD; Amendment 

39–16555; AD 2011–01–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–201, –202, –203, –223, and –243 

Airplanes; Airbus Model A330–300 

Series Airplanes; and Airbus Model 

A340–200 and –300 Series 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: 

[T]he FAA published SFAR 88 (Special 

Federal Aviation Regulation 88). 

By mail referenced 04/00/02/07/01–L296 

of March 4th, 2002 and 04/00/02/07/03–L024 

of February 3rd, 2003 the JAA [Joint Aviation 

Authorities] recommended to the National 

Aviation Authorities (NAA) the application 

of a similar regulation. 

The aim of this regulation is to require 

* * * a definition review against explosion 

hazards. 

* * * * * 

Failure of the auxiliary power unit 

(APU) bleed leak detection system could 

result in overheat of the fuel tank 

located in the horizontal stabilizer and 

ignition of the fuel vapors in that tank, 

which could result in a fuel tank 

explosion and consequent loss of the 

airplane. We are issuing this AD to 

require actions to correct the unsafe 

condition on these products. 

DATES: This AD becomes effective 

February 9, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 9, 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: 

Vladimir Ulyanov, Aerospace Engineer, 

WReier-Aviles on DSKGBLS3C1PROD with RULES