39254 Federal Register / Vol. 76, No. 129 / Wednesday, July 6, 2011 / Rules and Regulations 

Unsafe Condition 

(e) This AD was prompted by a report of 

a crack found in the upper center skin panel 

at the aft inboard corner of a right horizontal 

stabilizer. We are issuing this AD to detect 

and correct cracks in the horizontal stabilizer 

upper center skin panel. Uncorrected cracks 

might ultimately lead to the loss of overall 

structural integrity of the horizontal 

stabilizer. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Inspections 

(g) Before the accumulation of 20,000 total 

flight cycles, or within 4,379 flight cycles 

after the effective date of this AD, whichever 

occurs later, do eddy current inspections to 

detect cracking of the left and right upper 

center skin panels of the horizontal stabilizer, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD80–55A068, dated July 16, 2010. 

(1) If no crack is found during any 

inspection required by paragraph (g) of this 

AD, repeat the applicable inspections 

thereafter at the applicable times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin MD80–55A068, dated 

July 16, 2010. 

(2) If any crack is found during any 

inspection required by paragraph (g) of this 

AD, before further flight, replace the skin 

panel with a new skin panel, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin MD80–55A068, 

dated July 16, 2010. Within 20,000 flight 

cycles after the replacement, do eddy current 

inspections as required by paragraph (g) of 

this AD. 

Alternative Methods of Compliance 

(AMOCs) 

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

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

Related Information 

(i) For more information about this AD, 

contact Roger Durbin, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office (ACO), 

3960 Paramount Blvd., Lakewood, California 

90712–4137; phone: 562–627–5233; fax: 562– 

627–5210; e-mail: Roger.Durbin@faa.gov. 

Material Incorporated by Reference 

(j) You must use Boeing Alert Service 

Bulletin MD80–55A068, dated July 16, 2010, 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, California 90846– 

0001; phone: 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 June 16, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–15990 Filed 7–5–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0593; Directorate 

Identifier 2011–SW–002–AD; Amendment 

39–16723; AD 2011–12–16] 

RIN 2120–AA64 

Airworthiness Directives; Schweizer 

Aircraft Corporation (Schweizer) Model 

269A, A–1, B, C, C–1, and TH–55 Series 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding an 

existing emergency airworthiness 

directive (EAD) for the specified 

Schweizer model helicopters that was 

previously sent to all known U.S. 

owners and operators. That EAD 

currently requires removing each 

locknut and verifying sufficient drag 

torque and retorquing, or if the locknut 

does not have sufficient drag torque, 

replacing the locknut with an airworthy 

locknut. This AD retains the existing 

EAD requirements but also requires 

within a specified time, modifying the 

expandable bolts and installing a cotter 

pin. This AD is prompted by a locknut 

working loose from a bolt attaching the 

tailboom support strut at the aft cluster 

fitting because the locknut installed on 

the expandable bolt did not have the 

proper threads. We are issuing this AD 

to modify each expandable bolt to allow 

adding a cotter pin to prevent the strut 

and driveshaft separating from the 

helicopter and subsequent loss of 

control of the helicopter. 

DATES: This AD is effective July 21, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of July 21, 2011. 

We must receive any comments on 

this AD by September 6, 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 Schweizer Aircraft 

Corporation, Elmira/Corning Regional 

Airport, 1250 Schweizer Road, 

Horseheads, NY 14845, telephone (607) 

739–3821, fax: (607) 796–2488, e-mail 

address schweizer@sacusa.com, or at 

http://www.sacusa.com/support. 

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– 

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Federal Register / Vol. 76, No. 129 / Wednesday, July 6, 2011 / Rules and Regulations 39255 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Stephen Kowalski, Aviation Safety 

Engineer, FAA, Airframe and 

Propulsion Branch, ANE–171, 1600 

Stewart Ave., Suite 410, Westbury, New 

York 11590, telephone (516) 228–7327, 

fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On December 20, 2010, we issued 

EAD 2011–01–52, Directorate Identifier 

2010–SW–111–AD, for the specified 

Schweizer model helicopters. That EAD 

requires, before further flight, removing 

the locknut and reinstalling the locknut 

while determining the locknut drag 

torque. If the drag torque is a minimum 

of 2 in-lbs, retorquing the locknut to 23 

in-lbs is required. If the drag torque is 

not at least 2 in-lbs, replacing the 

locknut with an airworthy locknut is 

required. That AD resulted from a 

locknut working loose from a bolt 

attaching the tailboom support strut at 

the aft cluster fitting. Further 

investigation revealed that the locknut 

installed on the expandable bolt did not 

have the proper threads. We issued that 

EAD to prevent the strut and driveshaft 

separating from the helicopter and 

subsequent loss of control of the 

helicopter. 

Actions Since AD Was Issued 

Since we issued AD 2011–01–52, the 

manufacturer has introduced a 

modification of the expandable bolts to 

allow the addition of a cotter pin. 

Relevant Service Information 

We reviewed Schweizer Service 

Bulletins No. B–295 for Model 269A, A– 

1, B, and C helicopters, and No. C1B– 

032 for Model 269C–1 helicopters, both 

dated December 21, 2010. The service 

information specifies verifying 

sufficient drag torque on each locknut 

and applying the proper torque to each 

locknut. The service information also 

specifies modifying both expandable 

bolts to allow the addition of a cotter 

pin. 

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 on other helicopters of these 

same type designs. 

AD Requirements 

This AD retains the requirements in 

the existing EAD. This AD also requires, 

within 10 hours time-in-service (TIS), 

modifying both expandable bolts by 

drilling a hole through each bolt to 

allow the addition of a cotter pin. 

Thereafter, you may not install an 

expandable bolt unless that bolt has 

been modified in accordance with this 

AD. Modifying both expandable bolts in 

accordance with this AD is terminating 

action for the requirements of 

paragraphs (e)(1) and (e)(2) of this AD. 

Differences Between the AD and the 

Service Information 

We refer to flight hours as hours TIS. 

FAA’s Justification and 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 this condition, if not 

corrected, could result in the strut and 

driveshaft separating from the 

helicopter and subsequent loss of 

control of the helicopter. Therefore, we 

find that notice and opportunity for 

prior public comment are impracticable 

because of the short compliance time 

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 

we did not provide notice and an 

opportunity to comment before it 

becomes effective. 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–2011–0593 and 

Directorate Identifier 2011–SW–002–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 585 

helicopters of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

helicopter 

Cost on U.S. 

operators 

Inspection ......................... .5 work-hour × $85 per hour = $43 ............................ negligible .......................... $43 $25,155 

Modification ...................... 1.5 work-hours × $85 per hour = $128 ...................... negligible .......................... 128 74,880 

We estimate the total cost impact of 

this AD to be $100,035. 

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. 

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39256 Federal Register / Vol. 76, No. 129 / Wednesday, July 6, 2011 / Rules and Regulations 

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 to the extent that it justifies 

making any regulatory distinctions, 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 Part 39 of the Federal 

Aviation Regulations (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: 

2011–12–16 Schweizer Aircraft 

Corporation (Schweizer): Amendment 

39–16723; Docket No. FAA–2011–0593; 

Directorate Identifier 2011–SW–002–AD. 

Effective Date 

(a) This AD is effective July 21, 2011. 

Affected ADs 

(b) This AD supersedes Emergency AD 

2011–01–52, issued December 20, 2010; 

Directorate Identifier 2010–SW–111–AD. 

Applicability 

(c) Schweizer Model 269A, A–1, B, C 

helicopters (serial number (S/N) 1846 and 

larger); C–1 helicopters (S/N 0156 and 

larger); and TH–55 series helicopters with an 

Aft Cluster Fitting Modification Kit, part 

number (P/N) SA–269K–106, installed; 

certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by a locknut 

working loose on the tailboom aft cluster 

fitting strut because the locknut installed on 

one expandable bolt did not have the proper 

threads. This AD contains terminating action 

to require modifying each expandable bolt to 

allow installing a cotter pin to prevent the 

strut and driveshaft separating from the 

helicopter and subsequent loss of control of 

the helicopter. 

Compliance 

(e) Required as indicated, unless already 

done. 

(1) Before further flight, remove both the 

left-hand and right-hand locknuts, P/N 

MS21043–3. Reinstall the locknuts while 

determining the locknut drag torque. If the 

drag torque is a minimum of 2 in-lbs., 

retorque the locknut to 23 in-lbs. If the drag 

torque is not at least 2 in-lbs, replace the 

locknut with an airworthy locknut. 

(2) Within 10 hours time-in-service, modify 

each expandable bolt, P/N ADB221–1A, 

torque locknut, P/N MS21043–3, and install 

cotter pin, P/N MS24665–132 or MS24665– 

151, in accordance with the Procedure 

Section, Part II, of Schweizer Service Bulletin 

(SB) No. B–295, dated December 21, 2010, for 

Model 269A, A–1, B, C, and TH–55 series 

helicopters or SB No. C1B–032, dated 

December 21, 2010, for Model 269C–1 

helicopters. 

(3) Before installing an expandable bolt, 

P/N ADB221–1A, to secure the tailboom 

support strut to the tailboom aft cluster 

fitting, modify the expandable bolt in 

accordance with paragraph (e)(2) of this AD. 

(f) Modifying both expandable bolts by 

torquing the locknuts and installing the 

cotter pins as required by this AD is 

terminating action for the requirements of 

paragraph (e)(1) and (e)(2) of this AD. 

Special Flight Permit 

(g) Special flight permits will not be 

issued. 

Alternative Methods of Compliance 

(AMOCs) 

(h) The Manager, New York Aircraft 

Certification Office (NYACO), 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 NYACO, send it to the 

attention of the Program Manager, 

Continuing Operational Safety. 

Note: Before using any approved AMOC, 

we request that you notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office or certificate holding 

district office. 

Related Information 

(i) For more information about this AD, 

contact Stephen Kowalski, Aviation Safety 

Engineer, FAA, Airframe and Propulsion 

Branch, ANE–171, 1600 Stewart Ave., Suite 

410, Westbury, New York 11590, telephone 

(516) 228–7327, fax (516) 794–5531. 

Subject 

(j) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 5302: Rotorcraft Tailboom. 

Material Incorporated by Reference 

(k) You must use the specified portions of 

the service information contained in 

Schweizer Service Bulletins B–295 or C1B– 

032, both dated December 21, 2010, for your 

model helicopter to do the actions required 

by this AD. 

(2) For service information identified in 

this AD, contact Schweizer Aircraft 

Corporation, Elmira/Corning Regional 

Airport, 1250 Schweizer Road, Horseheads, 

NY 14845, telephone (607) 739–3821, fax: 

(607) 796–2488, e-mail address 

schweizer@sacusa.com, or at http:// 

www.sacusa.com/support. 

(3) You may also review copies of the 

service information that is incorporated by 

reference at the FAA, Office of the Regional 

Counsel, 2601 Meacham Blvd., Room 663, 

Fort Worth, Texas, or 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 Fort Worth, Texas, on June 3, 

2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–16571 Filed 7–5–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0152; Directorate 

Identifier 2010–NM–079–AD; Amendment 

39–16739; AD 2011–14–04] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Model FALCON 7X 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: 

On some Falcon 7X aeroplanes, it has been 

determined potential low clearance between 

electrical wiring or hydraulic pipe and 

nearby structure. 

Although no in service incident has been 

reported, there is no certainty that the 

minimum clearances would be maintained 

over time. In the worst case, interference or 

contact with structure might occur and lead 

to electrical short circuits or fluid leakage, 

potentially resulting in loss of several 

functions essential for safe flight. 

* * * * * 

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