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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66658 Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations 

control lever leading to considerable 

vibrations. A visual inspection revealed 

that the threaded bolt of the control 

lever had broken off. The actions 

specified by this AD are intended to 

prevent separation of dynamic weights, 

severe vibration, and subsequent loss of 

control of the helicopter. 

DATES: Effective December 3, 2010. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of December 

3, 2010. 

ADDRESSES: You may get the service 

information identified in this AD from 

American Eurocopter Corporation, 2701 

Forum Drive, Grand Prairie, Texas 

75053–4005, telephone (972) 641–3460, 

fax (972) 641–3527. 

Examining the Docket: You may 

examine the AD docket on the Internet 

at http://www.regulations.gov, or in 

person at the Docket Operations Office, 

West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC, between 

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

Friday, except Federal holidays. 

FOR FURTHER INFORMATION CONTACT: 

DOT/FAA Southwest Region, Sharon 

Miles, ASW–111, Aviation Safety 

Engineer, Rotorcraft Directorate, 

Regulations and Policy Group, 2601 

Meacham Blvd., ASW–111, Fort Worth, 

Texas 76137, telephone (817) 222–5122, 

fax (817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

A proposal to amend 14 CFR Part 39 

by superseding AD 2006–26–51, 

Amendment 39 14961 (72 FR 13679, 

March 23, 2007) for the specified ECD 

model helicopters was published in the 

Federal Register on August 11, 2010 (75 

FR 48617). AD 2006–26–51 requires 

actions intended to address an unsafe 

condition on the Model MBB–BK 117 

C–2 helicopters. Since we issued AD 

2006–26–51, the manufacturer has 

modified the control lever and dynamic 

weights, which when installed on the 

helicopter will constitute terminating 

action for the requirements in AD 2006– 

26–51. 

EASA, which is the technical agent 

for the Member States of the European 

Community, has issued EASA AD No. 

2007–0237, dated August 31, 2007, to 

correct an unsafe condition for the 

Model MBB–BK 117 C–2 helicopters. 

The MCAI AD states: ‘‘EASA was 

informed by the manufacturer of an inflight incident in which a dynamic 

weight broke off the control lever 

subsequently leading to considerable 

vibrations. A visual inspection revealed 

that the threaded bolt of the control 

lever had broken off.’’ 

You may obtain further information 

by examining the MCAI AD and service 

information in the AD docket. 

Related Service Information 

ECD has issued ECD Alert Service 

Bulletin MBB BK117 C–2–64A–002, 

Revision 2, dated August 6, 2007. The 

actions described in the MCAI AD are 

intended to correct the same unsafe 

condition as that identified in the 

service information. 

FAA’s Evaluation and Unsafe Condition 

Determination 

This helicopter has been approved by 

the aviation authority of the Federal 

Republic of Germany and is approved 

for operation in the United States. 

Pursuant to our bilateral agreement with 

the Federal Republic of Germany, 

EASA, their Technical Agent, has 

notified us of the unsafe condition 

described in the MCAI AD. We are 

issuing this AD because we evaluated 

all information provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

helicopters of this same type design. 

Differences Between the AD and the 

MCAI AD 

We refer to flight hours as hours timein-service. We do not refer to a date of 

October 31, 2007, for replacing the 

levers because the date has passed. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were received on the 

proposal or the FAA’s determination of 

the cost to the public. We have 

determined that air safety and the 

public interest require the adoption of 

the rule as proposed. 

Cost of Compliance 

We estimate that this AD will affect 

41 helicopters of U.S. registry. We also 

estimate that it will take about 20 workhours per helicopter to inspect and 

replace the tail rotor control lever. The 

average labor rate is $85 per work-hour, 

and required parts will cost about 

$10,316 per helicopter. Based on these 

figures, we estimate the total cost of this 

AD to U.S. operators to be $492,656, or 

$12,016 per helicopter, assuming the 

control lever is replaced on the entire 

fleet. 

Regulatory Findings 

We have 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 that the regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

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 an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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. 

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. Section 39.13 is amended by 

removing Amendment 39 14961 (72 FR 

13679, March 23, 2007), and by adding 

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Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations 66659 

a new airworthiness directive (AD), 

Amendment 39 16486, to read as 

follows: 

2010–22–07 Eurocopter Deutschland 

GmbH: Amendment 39–16486; Docket 

No. FAA–2010–0780; Directorate 

Identifier 2009–SW–68–AD. Supersedes 

AD 2006–26–51, Amendment 39 14961, 

Docket No. FAA–2006–26721, 

Directorate Identifier 2006–SW–28–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective on December 3, 2010. 

Other Affected ADs 

(b) This AD supersedes AD 2006–26–51, 

Amendment 39–14961, Docket No. FAA 

2006–26721, Directorate Identifier 2006–SW– 

28–AD. 

Applicability 

(c) This AD applies to Model MBB–BK 117 

C–2 helicopters with a tail rotor control lever 

B642M1009103, installed, certificated in any 

category. 

Reason 

(d) The mandatory continued 

airworthiness information (MCAI) AD states: 

‘‘European Aviation Safety Agency (EASA) 

was informed by the manufacturer of an inflight incident in which a dynamic weight 

broke off the control lever subsequently 

leading to considerable vibrations. A visual 

inspection revealed that the threaded bolt of 

the control lever had broken off.’’ This AD 

requires actions that are intended to prevent 

separation of dynamic weights, severe 

vibration, and subsequent loss of control of 

the helicopter. 

Actions and Compliance 

(e) Before further flight, unless already 

done, mark the position of the weights, 

remove the split pins, remove the weights, 

and visually inspect the tail rotor control 

lever in the area around the split pin bore for 

score marks, notching, scratching, or a crack. 

Inspect by following the Accomplishment 

Instructions, paragraph 3.A.(1) through 

3.A.(3) and Figure 1, of Eurocopter Alert 

Service Bulletin MBB BK 117 C–2–64A–002, 

Revision 2, dated August 6, 2007 (ASB). 

(1) If done previously, within the next 8 

hours time-in-service (TIS) or before reaching 

25 hours TIS after the last inspection, and 

thereafter at intervals not to exceed 8 hours 

TIS, repeat the visual inspection of the tail 

rotor control lever as required by paragraph 

(e) of this AD. 

(2) If you find a score mark, a notch, or a 

scratch that exceeds the maintenance manual 

limits, or find a crack, before further flight: 

(i) Replace the tail rotor control lever with 

an airworthy tail rotor control lever; and 

(ii) Reidentify the tail rotor head, head 

assembly, and drive system with the new 

part numbers by following the 

Accomplishment Instructions, paragraph 

3.B.(1) through 3.B.(8) and 3.C.(1) through 

3.C.(2), of the ASB. 

(f) Within 100 hours TIS, unless already 

done, replace the control levers and 

reidentify the tail rotor head, head assembly, 

and drive system with the new part numbers 

by following the Accomplishment 

Instructions, paragraph 3.B.(1) through 

3.B.(8) and 3.C.(1) through 3.C.(2), of the 

ASB. 

(g) Replacing the control levers and 

reidentifying the part numbers is terminating 

action for the requirements of this AD. 

Differences Between the FAA AD and the 

MCAI AD 

(h) We refer to flight hours as hours TIS. 

We do not refer to a date of October 31, 2007, 

for replacing the levers because the date has 

passed. 

Other Information 

(i) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, ATTN: DOT/FAA Southwest Region, 

Sharon Miles, ASW–111, Aviation Safety 

Engineer, Rotorcraft Directorate, Regulations 

and Policy Group, 2601 Meacham Blvd., Fort 

Worth, Texas 76137, telephone (817) 222– 

5122, fax (817) 222 5961, has the authority 

to approve AMOCs for this AD, if requested, 

using the procedures found in 14 CFR 39.19. 

(j) Special flight permits are prohibited. 

Related Information 

(k) MCAI EASA Airworthiness Directive 

No. 2006–0237, dated August 31, 2007, 

which supersedes EASA Emergency AD 

2007–0189–E, dated July 12, 2007, contains 

related information. 

Joint Aircraft System/Component Code 

(l) The Joint Aircraft System/Component 

Code is 6400: Tail rotor system-control lever. 

Material Incorporated by Reference 

(m) The actions shall be done in 

accordance with the specified portions of 

Eurocopter Deutschland GmbH Alert Service 

Bulletin MBB BK117 C–2–64A–002, Revision 

2, dated August 6, 2007. The Director of the 

Federal Register approved this incorporation 

by reference in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Copies may be 

obtained from American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, Texas 75053–4005, telephone (972) 

641–3460, fax (972) 641–3527. Copies may be 

inspected at the FAA, Office of the Regional 

Counsel, Southwest Region, 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 NARA, 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 October 12, 

2010. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2010–26563 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–2010–0680; Directorate 

Identifier 2008–NM–195–AD; Amendment 

39–16482; AD 2010–22–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 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: 

Analysis performed in the frame of the 

Extended Service Goal has led Airbus to 

modify the inspection programme 

[modification of thresholds, intervals and 

associated configurations] which is currently 

required by DGAC (Direction Ge ́ne ́rale de 

l’Aviation Civile) France AD F–2005–001. 

This modified inspection programme is 

necessary to detect and prevent damage 

associated with a structural fatigue 

phenomenon of the rear spar internal angle 

and the tee fitting located in the centre wing 

box. This condition, if not corrected, could 

affect the structural integrity of the centre 

wing box. 

* * * * * 

The unsafe condition is reduced 

structural integrity of the wings. We are 

issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective 

December 3, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 3, 2010. 

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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149. 

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