4224 Federal Register / Vol. 76, No. 16 / Tuesday, January 25, 2011 / Rules and Regulations 

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, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Related Information 

(n) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6577; fax (425) 917–6590. Information 

may be e-mailed to: 9-ANM-Seattle-ACOAMOC-Requests@faa.gov. 

Material Incorporated by Reference 

(o) You must use Boeing Alert Service 

Bulletin 727–53A0233, dated February 19, 

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 727–53A0233, 

dated February 19, 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, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet 

https://www.myboeingfleet.com. 

(3) You may review copies of the service 

information 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 January 

5, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–464 Filed 1–24–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0796; Directorate 

Identifier 2010–NM–007–AD; Amendment 

39–16579; AD 2011–02–06] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 767–300 Series 

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 inspections for cracks in the 

fuselage skin and backup structure at 

the lower VHF antenna cutout at station 

1197 + 99 between stringers 39 left and 

39 right, and corrective actions if 

necessary. Certain repairs terminate 

certain inspection requirements. This 

AD was prompted by reports of cracking 

found in the section 46 fuselage lower 

skin around the periphery of the VHF 

antenna baseplate at station 1197 + 99. 

We are issuing this AD to detect and 

correct fatigue cracks in the fuselage 

skin and internal backup structure, 

which could result in rapid 

decompression of the airplane. 

DATES: This AD is effective March 1, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 1, 2011. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

425–917–6577; fax 425–917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to the 

specified products. That NPRM was 

published in the Federal Register on 

August 11, 2010 (75 FR 48623). That 

NPRM proposed to require repetitive 

inspections for cracks in the fuselage 

skin and backup structure at the lower 

VHF antenna cutout at station 1197 + 99 

between stringers 39L and 39R, and 

corrective actions if necessary. Certain 

repairs proposed by that NPRM would 

terminate certain inspection 

requirements. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the proposal and the FAA’s 

response to the comment. 

Request To Clarify Compliance Time 

Boeing requested that we change the 

NPRM to explain that the internal 

detailed inspection may be deferred up 

to 6,000 flight cycles after the effective 

date of the AD if no fuselage skin cracks 

are found during the external detailed 

inspection. Paragraph (g) of the NPRM 

referred to Boeing Special Attention 

Service Bulletin 767–53–0207, dated 

December 17, 2009 (‘‘the service 

bulletin’’), for the proposed compliance 

times for the external and internal 

detailed inspections. The Relevant 

Service Information section in the 

NPRM preamble explained that, if no 

cracks were found during the external 

detailed inspection, the internal 

detailed inspection may be deferred ‘‘for 

an additional 6,000 flight cycles.’’ 

Boeing stated, however, that this service 

bulletin instead allows deferral of the 

internal detailed inspection for a 

maximum of 6,000 flight cycles after the 

date on the service bulletin. 


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Federal Register / Vol. 76, No. 16 / Tuesday, January 25, 2011 / Rules and Regulations 4225 

We partially agree. We agree that 

Boeing’s suggested change reflects the 

intent of this service bulletin. Boeing 

published this revision in Service 

Bulletin Information Notice 767–53– 

0207 IN 01, dated July 8, 2010, to clarify 

a compliance time. We have added new 

paragraphs (h) and (i) in this final rule 

to explain the exceptions to this service 

bulletin’s compliance times and to 

incorporate the information in the 

information notice. We have reidentified subsequent paragraphs 

accordingly. We do not agree to correct 

this information in the Relevant Service 

Information section of the NPRM 

because that section is not repeated in 

a final rule. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

We estimate that this AD affects 93 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour 

Cost per 

product 

Number of 

U.S.- 

registered 

airplanes 

Fleet cost 

Inspections ............................................................................ 3 $85 $255 93 $23,715 

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): 

2011–02–06 The Boeing Company: 

Amendment 39–16579; Docket No. 

FAA–2010–0796; Directorate Identifier 

2010–NM–007–AD. 

Effective Date 

(a) This AD is effective March 1, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 767–300 series airplanes, 

certificated in any category, as identified in 

Boeing Special Attention Service Bulletin 

767–53–0207, dated December 17, 2009. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD was prompted by reports of 

cracking found in the section 46 fuselage 

lower skin around the periphery of the very 

high frequency (VHF) antenna baseplate at 

station 1197 + 99. The Federal Aviation 

Administration is issuing this AD to detect 

and correct fatigue cracks in the fuselage skin 

and internal backup structure, which could 

result in rapid decompression of the airplane. 

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. 

Inspections 

(g) Inspect for cracks in the fuselage skin 

and backup structure at the lower VHF 

antenna cutout at station 1197 + 99, between 

stringers 39L and 39R, by doing an external 

detailed inspection, with the antenna 

removed, of the fuselage structure at the 

lower aft VHF antenna cutout, and an 

internal detailed inspection of the backup 

structure. Do the inspections in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

767–53–0207, dated December 17, 2009. Do 

the inspections at the applicable time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

767–53–0207, dated December 17, 2009, 

except as required by paragraphs (h) and (i) 

of this AD. 

(1) If no crack is found, repeat the external 

detailed inspection, without removing the 

antenna, at intervals not to exceed 3,000 

flight cycles. 

(2) If any crack is found in the fuselage 

skin, repair before further flight, in 

accordance with Boeing Special Attention 

Service Bulletin 767–53–0207, dated 

December 17, 2009. Accomplishment of this 

repair terminates the repetitive external 

detailed inspections of the fuselage skin 

required by this AD. 

(3) If any crack is found in the backup 

structure, before further flight, repair or 

replace the cracked part(s), in accordance 

with Boeing Special Attention Service 

Bulletin 767–53–0207, dated December 17, 

2009. 


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4226 Federal Register / Vol. 76, No. 16 / Tuesday, January 25, 2011 / Rules and Regulations 

Exceptions to Service Bulletin Specifications 

(h) Where Boeing Special Attention Service 

Bulletin 767–53–0207, dated December 17, 

2009, specifies a compliance time after the 

date on the service bulletin, this AD requires 

compliance within the specified time after 

the effective date of this AD. 

(i) The internal detailed inspection 

specified in Boeing Special Attention Service 

Bulletin 767–53–0207, dated December 17, 

2009, and required by paragraph (g) of this 

AD must be done at the later of the times 

specified in paragraphs (i)(1) and (i)(2) of this 

AD. 

(1) Before the accumulation of 25,000 total 

flight cycles. 

(2) At the applicable time specified in 

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

(i) If any fuselage skin crack is found 

during the external detailed inspection 

required by paragraph (g) of this AD: Within 

3,000 flight cycles after the effective date of 

this AD. 

(ii) If no fuselage skin crack is found 

during the external detailed inspection 

required by paragraph (g) of this AD: Within 

6,000 flight cycles after the effective date of 

this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle 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. 

Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(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, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Related Information 

(k) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; phone: 425–917– 

6577; fax: 425–917–6590; e-mail: 

berhane.alazar@faa.gov. 

Material Incorporated by Reference 

(l) You must use Boeing Special Attention 

Service Bulletin 767–53–0207, dated 

December 17, 2009, 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 

the service information under 5 U.S.C. 552(a) 

and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet 

https://www.myboeingfleet.com. 

(3) You may review copies of the service 

information 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 January 

6, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–462 Filed 1–24–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0053; Directorate 

Identifier 2010–CE–073–AD; Amendment 

39–16581; AD 2011–02–08] 

RIN 2120–AA64 

Airworthiness Directives; Aircraft 

Industries a.s. Model L 23 Super Blanik 

Sailplanes 

AGENCY: Federal Aviation 

Administration (FAA), 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) 

issued by the aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Cracks were reported on the rear horizontal 

stabilizer bracket of two L 23 SUPER– 

BLANIK sailplanes. 

This condition, if not corrected, could 

result in no longer retaining the horizontal 

stabilizer in place and consequent loss of 

control of the aeroplane. 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

February 14, 2011. 

On February 14, 2011, the Director of 

the Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

We must receive comments on this 

AD by March 11, 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 20590, 

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

through Friday, except Federal holidays. 

For service information identified in 

this AD, contact Aircraft Industries, a.s.- 

Na zahonech 1177, 686 04 Kunovice, 

Czech Republic; telephone: +420 572 

817 660; fax: +420 572 816 112; e-mail: 

ots@let.cz; Internet: http://www.let.cz/. 

You may review copies of the 

referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call 816–329– 

4148. 

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 street address for 

the Docket 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: Jim 

Rutherford, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 

329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 


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