Federal Register / Vol. 76, No. 6 / Monday, January 10, 2011 / Rules and Regulations 1349 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, International Branch, 

ANM–116, 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: Tim Dulin, Aerospace 

Engineer, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2141; fax 

(425) 227–1149. 

(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 refer to this AD. 

Material Incorporated by Reference 

(i) You must use the service information 

contained in Table 2 of this AD, as 

applicable, to do the actions required by this 

AD, unless the AD specifies otherwise. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE

Airbus Service Bulletin— Dated— 

A300–25–0486, including Appendix ............................................................................................................................... September 21, 2009. 

A300–25–6218, including Appendix ............................................................................................................................... September 21, 2009. 

A310–25–2206, including Appendix ............................................................................................................................... September 21, 2009. 

A320–25–1666, including Appendix ............................................................................................................................... September 21, 2009. 

A330–25–3424, including Appendix ............................................................................................................................... September 21, 2009. 

A340–25–4326, including Appendix ............................................................................................................................... September 21, 2009. 

A340–25–5169, including Appendix ............................................................................................................................... September 18, 2009. 

A380–25–8058, including Appendix ............................................................................................................................... September 21, 2009. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in Table 2 

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

part 51. 

(2) Use the contact information specified in 

paragraphs (i)(2)(i), (i)(2)(ii), (i)(2)(iii), and 

(i)(2)(iv), as applicable, for service 

information identified in this AD. 

(i) For Model A300, A300–600, and A310 

series airplanes, 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. 

(ii) For Model A318, A319, A320, and 

A321 series airplanes, contact Airbus, 

Airworthiness Office—EAS, 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. 

(iii) For Model A330–300, A340–200, 

A340–300, A340–500, A340–600 series 

airplanes, and Model A330–201, A330–202, 

A330–203, A330–223, A330–243 airplanes, 

contact Airbus SAS—Airworthiness Office— 

EAL, 1 Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; telephone +33 5 61 

93 36 96; fax +33 5 61 93 45 80; e-mail 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(iv) For Model A380–800 series airplanes, 

contact Airbus SAS—EANA (Airworthiness 

Office); 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

562 110 253; Fax +33 562 110 307; e-mail 

account.airworth-A380@airbus.com; Internet 

http://www.airbus.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 14, 2010. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–33318 Filed 1–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1297; Directorate 

Identifier 2010–CE–068–AD; Amendment 

39–16569; AD 2010–26–54] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company (Cessna) (Type 

Certificate A00003SE Previously Held 

by Columbia Aircraft Manufacturing 

(Previously The Lancair Company)) 

Models LC41–550FG and LC42–550FG 

Airplanes 

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 emergency 

AD was sent previously to all known 

U.S. owners and operators of these 

airplanes. This AD requires obtaining 

written approval from the Manager, 

Wichita Aircraft Certification Office 

(ACO), to operate the airplane. This 

written approval must clearly state that 

operation is approved per Emergency 

AD 2010–26–54. This AD was prompted 

by a Cessna Model LC41–550FG 

airplane that suffered a significant 

structural failure in the wing during a 

production acceptance flight test. We 

are issuing this AD to prevent 

catastrophic failure of the wing due to 

disbonding of the wing skin from the 

wing spar. 

DATES: This AD is effective January 10, 

2011 to all persons except those persons 

to whom it was made immediately 

effective by Emergency AD 2010–26–54, 

issued on December 17, 2010, which 

contained the requirements of this 

amendment. 

We must receive comments on this 

AD by February 24, 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: Deliver to Mail 

address above 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 


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1350 Federal Register / Vol. 76, No. 6 / Monday, January 10, 2011 / Rules and Regulations 

the Docket Operations Office (phone: 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Gary 

Park, Aerospace Engineer, Wichita ACO, 

FAA, 1801 Airport Road, Wichita, KS 

67209; phone: (316) 946–4123; fax: (316) 

946–4107; e-mail: gary.park@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On December 10, 2010, we issued 

Emergency AD 2010–26–53, which 

requires obtaining written approval 

from the Manager, Wichita ACO, to 

operate the airplane. The written 

approval must clearly state that 

operation is approved per Emergency 

AD 2010–26–53. This action was 

prompted by a Cessna Model LC41– 

550FG airplane that suffered a 

significant structural failure in the wing 

during a production acceptance flight 

test. The wing skin disbonded from the 

upper forward wing spar. The length of 

the disbond was approximately 7 feet. 

Since issuing AD 2010–26–53, we 

determined the need to increase the 

serial numbers in the Applicability 

section and to correct a serial number in 

the Applicability section. We issued 

Emergency AD 2010–26–54, dated 

December 17, 2010, which retains the 

actions of the previous AD, adds serial 

numbers to the Applicability section, 

and corrects a serial number in the 

Applicability section. 

This condition, if not corrected, could 

result in catastrophic failure of the wing 

due to disbonding of the wing skin from 

the wing spar. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires obtaining written 

approval from the Manager, Wichita 

ACO, to operate the airplane. The 

written approval must clearly state that 

operation is approved per Emergency 

AD 2010–26–54. 

Interim Action 

We consider this AD interim action. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because disbonding of the wing 

skin from the wing spar could result in 

catastrophic failure of the wing. 

Therefore, we find that notice and 

opportunity for prior public comment 

are impracticable and that good cause 

exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2010–1297 and Directorate 

Identifier 2010–CE–068–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 13 

airplanes of U.S. registry. 

There are no labor or parts costs 

associated with this AD action. 

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, 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): 

2010–26–54 Cessna Aircraft Company 

(Type Certificate A00003SE previously 

held by Columbia Aircraft 

Manufacturing (previously The Lancair 

Company)): Amendment 39–16569; 

Docket No. FAA–2010–1297; Directorate 

Identifier 2010–CE–068–AD. 

Effective Date 

(a) This AD is effective January 10, 2011 to 

all persons except those persons to whom it 

was made immediately effective by 

Emergency AD 2010–26–54, issued on 

December 17, 2010, which contained the 

requirements of this amendment. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the following Cessna 

Aircraft Company (Cessna) (Type Certificate 

A00003SE previously held by Columbia 

Aircraft Manufacturing (previously The 

Lancair Company)) airplanes certified in any 

category, as identified in table 1 of this AD: 


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Federal Register / Vol. 76, No. 6 / Monday, January 10, 2011 / Rules and Regulations 1351 

TABLE 1—APPLICABILITY

Model Serial Nos. 

LC41–550FG ......... 41028, 41705, 411114, 

411160, 411161, 

411162, 411163, 

411164, 411165, 

411167, 411170, and 

411171. 

LC42–550FG ......... 42517. 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 57, Wings. 

Unsafe Condition 

(e) This AD was prompted by a Cessna 

Model LC41–550FG airplane that suffered a 

significant structural failure in the wing 

during a production acceptance flight test. 

The wing skin disbonded from the upper 

forward wing spar. The length of the disbond 

was approximately 7 feet. We are issuing this 

AD to prevent catastrophic failure of the 

wing due to disbonding of the wing skin from 

the wing spar. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Operation Restriction 

(g) As of the effective date of this AD, do 

not operate the airplane without written 

approval from the Manager, Wichita Aircraft 

Certification Office (ACO). This written 

approval must clearly state that operation is 

approved per AD 2010–26–54. 

Special Flight Permit 

(h) A special flight permit requires written 

approval from the Manager, Wichita ACO. 

This written approval must clearly state that 

operation is approved per AD 2010–26–54. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Wichita 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 Principal Maintenance Inspector 

or Principal Avionics Inspector, as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

Related Information 

(j) For further information about this AD, 

contact: Gary Park, Aerospace Engineer, 

Wichita ACO, FAA, 1801 Airport Road, 

Wichita, KS 67209; phone: (316) 946–4123; 

fax: (316) 946–4107; e-mail: 

gary.park@faa.gov. 

Issued in Kansas City, Missouri, on 

December 27, 2010. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2010–33336 Filed 1–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1280; Directorate 

Identifier 2010–NM–270–AD; Amendment 

39–16572; AD 2011–01–15] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 757–200, –200CB, and 

–300 Series Airplanes 

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 requires 

repetitive inspections for cracking of the 

fuselage skin of the crown skin panel 

along the chem-milled step at stringers 

S–4 left and S–4 right, from stations 

(STA) 297 through 439, and repair if 

necessary. This AD also includes 

terminating action for the repetitive 

inspections of the repaired areas only. 

This AD was prompted by reports of 

cracking in the fuselage skin of the 

crown skin panel. We are issuing this 

AD to detect and correct fatigue 

cracking of the fuselage skin of the 

crown skin panel, which could result in 

pressure venting and consequent rapid 

decompression of the airplane. 

DATES: This AD is effective January 25, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of January 25, 2011. 

We must receive comments on this 

AD by February 24, 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 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 street address for 

the Docket Office (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6440; fax (425) 917–6590; 

e-mail: nancy.marsh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We have received reports of cracking 

in the fuselage skin of the crown skin 

panel. On one airplane, the crack was 

10.75 inches long, midway between 

stations (STA) 420 and 439, just above 

the lap joint at stringer 4L (left) of the 

chem-milled step. The airplane had 

accumulated 24,631 total flight cycles. 

On another airplane, there was an 

opening from a crack in the fuselage 

above and aft of the passenger entry 

doorway. One edge of the opening ran 

approximately 18 inches in the forwardto-aft direction; the other edge ran 

approximately 12 inches along the 

chem-milled pocket edge above stringer 

4L. Additionally, a 1.3-inch crack was 

found in the skin forward of the opening 

in the adjacent skin bay also in the 

chem-milled step above stringer 4L. The 

airplane had accumulated 22,450 total 


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