Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations 66655 

mounts, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD90–54A003, Revision 2, 

dated February 12, 2010. Defects include 

missing, loose, and damaged fasteners. 

(1) If no defect is found during any general 

visual inspection required by paragraph (h) 

of this AD, before further flight, insert a 

0.0015-inch feeler gauge between the washer 

and the structure, or between the fastener 

head and structure, as applicable, to detect a 

gap condition, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD90–54A003, Revision 2, 

dated February 12, 2010. A gap condition is 

a defect identified in any location where the 

feeler gauge can slip completely between a 

washer or a fastener head and the structure. 

(i) If no defect is found during any gap 

check required by paragraph (h)(1) of this 

AD, before further flight, apply torque to the 

fasteners of the lower row (Row B) to 

determine if there is a defect, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin MD90–54A003, 

Revision 2, dated February 12, 2010. A defect 

is any fastener that turns with the application 

of the specified torque. If any defect is found, 

before further flight, replace all clearance fit 

fasteners in the lower row (Row B), in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–54A003, Revision 2, dated February 

12, 2010. 

(ii) If any defect is found during any gap 

check required by paragraph (h)(1) of this 

AD, before further flight, replace all clearance 

fit fasteners in the lower row (Row B), in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–54A003, Revision 2, dated February 

12, 2010. 

(2) If any defect is found during any 

general visual inspection required by 

paragraph (h) of this AD, before further flight, 

replace all clearance fit fasteners in the lower 

row (Row B), in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD90–54A003, Revision 2, 

dated February 12, 2010. 

Exception to Service Bulletin Compliance 

Times 

(i) Where Boeing Alert Service Bulletin 

MD90–54A003, Revision 2, dated February 

12, 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. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(j) Replacements and inspections 

accomplished before the effective date of this 

AD in accordance with Boeing Alert Service 

Bulletin MD90–54A003, Revision 1, dated 

November 17, 2009, are considered 

acceptable for compliance with the 

corresponding actions required by this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(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 Principal Maintenance Inspector 

or Principal Avionics Inspector, as 

appropriate, or lacking a principal inspector, 

your local Flight Standards 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 

(l) 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; e-mail: 

Roger.Durbin@faa.gov. 

Material Incorporated by Reference 

(m) You must use Boeing Alert Service 

Bulletin MD90–54A003, Revision 2, dated 

February 12, 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; 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, 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 October 

13, 2010. 

John Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–26555 Filed 10–28–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0849; Directorate 

Identifier 2010–CE–043–AD; Amendment 

39–16488; AD 2010–22–09] 

RIN 2120–AA64 

Airworthiness Directives; PILATUS 

Aircraft Ltd. Model PC–7 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) 

issued 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: 

This Airworthiness Directive (AD) is 

prompted due to an occurrence when an 

aircraft had a partial in-flight separation of 

the aileron outboard bearing support. 

The aileron outboard bearing supports are 

attached with two forward attachment bolts 

and two aft attachment bolts. The forward 

attachment bolts are approximately 3.2 mm 

(0.125 inch) longer than the aft attachment 

bolts. If the aileron outboard bearing supports 

have been removed, it is possible that during 

the reinstallation of the aileron outboard 

bearing supports, the attachment bolts can be 

installed in wrong positions. Bolts that are 

installed in wrong positions can damage the 

threads in the rear attachment anchor nuts. 

Such a condition, if left uncorrected, could 

lead to in-flight separation of the aileron 

outboard bearing support, and as a 

consequence, the loss or limited 

controllability of the aircraft. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

December 3, 2010. 

On December 3, 2010, the Director of 

the Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

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 service information identified in 

this AD, contact Pilatus Aircraft Ltd., 

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66656 Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations 

Customer Service Manager, CH–6371 

STANS, Switzerland; telephone: +41 (0) 

41 619 62 08; fax: +41 (0) 41 619 73 11; 

Internet: http://www.pilatusaircraft.com. 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. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090; e-mail: 

doug.rudolph@faa.gov. 

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 August 26, 2010 (75 FR 

52482). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

This Airworthiness Directive (AD) is 

prompted due to an occurrence when an 

aircraft had a partial in-flight separation of 

the aileron outboard bearing support. 

The aileron outboard bearing supports are 

attached with two forward attachment bolts 

and two aft attachment bolts. The forward 

attachment bolts are approximately 3.2 mm 

(0.125 inch) longer than the aft attachment 

bolts. If the aileron outboard bearing supports 

have been removed, it is possible that during 

the reinstallation of the aileron outboard 

bearing supports, the attachment bolts can be 

installed in wrong positions. Bolts that are 

installed in wrong positions can damage the 

threads in the rear attachment anchor nuts. 

Such a condition, if left uncorrected, could 

lead to in-flight separation of the aileron 

outboard bearing support, and as a 

consequence, the loss or limited 

controllability of the aircraft. 

In order to correct and control the 

situation, this AD requires a one time 

inspection to verify that the bolts are 

installed in the correct positions and the 

threads of the anchor nuts are in good 

condition. The replacement of the attachment 

hardware is required if any damage on the 

anchor nut threads or a bolt at the wrong 

location is found. 

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 

have considered the comment received. 

Pilatus Aircraft Ltd. supports the NPRM 

and its adoption as a final rule AD 

action. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. 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. 

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 

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 FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

12 products of U.S. registry. We also 

estimate that it will take about 2 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate 

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

be $2,040, or $170 per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 25 work-hours and require parts 

costing $200, for a cost of $2,325 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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 

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 Management Facility 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 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. 

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Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations 66657 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2010–22–09 Pilatus Aircraft Ltd.: 

Amendment 39–16488; Docket No. 

FAA–2010–0849; Directorate Identifier 

2010–CE–043–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective December 3, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to PILATUS Aircraft 

Ltd. Model PC–7 airplanes, manufacturer 

serial numbers (MSN) 101 through 618, 

certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

This Airworthiness Directive (AD) is 

prompted due to an occurrence when an 

aircraft had a partial in-flight separation of 

the aileron outboard bearing support. 

The aileron outboard bearing supports are 

attached with two forward attachment bolts 

and two aft attachment bolts. The forward 

attachment bolts are approximately 3.2 mm 

(0.125 inch) longer than the aft attachment 

bolts. If the aileron outboard bearing supports 

have been removed, it is possible that during 

the reinstallation of the aileron outboard 

bearing supports, the attachment bolts can be 

installed in wrong positions. Bolts that are 

installed in wrong positions can damage the 

threads in the rear attachment anchor nuts. 

Such a condition, if left uncorrected, could 

lead to in-flight separation of the aileron 

outboard bearing support, and as a 

consequence, the loss or limited 

controllability of the aircraft. 

In order to correct and control the 

situation, this AD requires a one time 

inspection to verify that the bolts are 

installed in the correct positions and the 

threads of the anchor nuts are in good 

condition. The replacement of the attachment 

hardware is required if any damage on the 

anchor nut threads or a bolt at the wrong 

location is found. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within 1 month after December 3, 2010 

(the effective date of this AD), check the 

airplane maintenance records to determine if 

the left and/or right aileron outboard bearing 

supports have been removed at any time 

during the life of the airplane. Do this check 

following paragraph 3.A. of Pilatus Aircraft 

Ltd. PC–7 Service Bulletin No. 57–015, Rev. 

No. 1, dated July 23, 2010. 

(2) If an entry is found during the airplane 

maintenance records check required in 

paragraph (f)(1) of this AD or it is unclear 

whether or not the left and/or right aileron 

outboard bearing supports have been 

removed at any time during the life of the 

airplane, before further flight, do the actions 

specified in paragraphs 3.A.(2) through 

paragraph 3.E of Pilatus Aircraft Ltd. PC–7 

Service Bulletin No. 57–015, Rev. No. 1, 

dated July 23, 2010. 

FAA AD Differences 

Note: 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, Standards 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: Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4059; fax: (816) 329– 

4090. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(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, 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. 

Special Flight Permit 

(h) Special flight permits will not be 

issued. 

Related Information 

(i) Refer to MCAI Federal Office of Civil 

Aviation (FOCA) AD HB–2010–010, dated 

July 29, 2010; and Pilatus Aircraft Ltd. PC– 

7 Service Bulletin No. 57–015, Rev. No. 1, 

dated July 23, 2010, for related information. 

Material Incorporated by Reference 

(j) You must use Pilatus Aircraft Ltd. PC– 

7 Service Bulletin No. 57–015, Rev. No. 1, 

dated July 23, 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 Pilatus Aircraft Ltd., 

Customer Service Manager, CH–6371 

STANS, Switzerland; telephone: +41 (0) 41 

619 62 08; fax: +41 (0) 41 619 73 11; Internet: 

http://www.pilatus-aircraft.com. 

(3) 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. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri, on 

October 21, 2010. 

Christina L. Marsh, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–27214 Filed 10–28–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0780; Directorate 

Identifier 2009–SW–68–AD; Amendment 39– 

16486; AD 2010–22–07] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Model MBB–BK 

117 C–2 Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule. 

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD) 

for the Eurocopter Deutschland GmbH 

(ECD) Model MBB BK 117 C–2 

helicopters. This amendment results 

from a mandatory continuing 

airworthiness information (MCAI) AD 

issued by the European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community. The MCAI AD 

states there was an in-flight incident in 

which a dynamic weight broke off the 

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