48618 Federal Register / Vol. 75, No. 154 / Wednesday, August 11, 2010 / Proposed Rules 

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 

product(s) identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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. 

Therefore, I certify this proposed AD: 

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 proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 

removing Amendment 39–14961 (72 FR 

13679, dated March 23, 2007) and 

adding the following new AD: 

Eurocopter Deutschland GmbH: Docket No. 

FAA–2010–0780; Directorate Identifier 

2009–SW–68–AD. 

Comments Due Date 

(a) We must receive your comments by 

September 10, 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: 

‘‘EASA was informed by the manufacturer of 

an in-flight 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 Guidance 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 (JASC) 

Code 

(l) The JASC Code is 6400: Tail rotor 

system-control lever. 

Issued in Fort Worth, Texas, on August 3, 

2010. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–19817 Filed 8–10–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0781; Directorate 

Identifier 2007–SW–49–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model AS–365N2, AS 365 N3, 

and SA–365N1 Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

specified Eurocopter France model 

helicopters. This proposed AD would 

require replacing the aluminum tail 

rotor (T/R) blade pitch control shaft 

with a steel T/R blade pitch control 

shaft. This proposed AD is prompted by 

an incident involving a Eurocopter 

France Model AS–365N2 helicopter on 

which there was a loss of control of the 

T/R due to a broken shaft. The actions 

specified by this proposed AD are 

intended to prevent failure of the T/R 

blade pitch control shaft, loss of T/R 

control, and subsequent loss of control 

of the helicopter. 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
Federal Register / Vol. 75, No. 154 / Wednesday, August 11, 2010 / Proposed Rules 48619 

DATES: Comments must be received on 

or before October 12, 2010. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD: 

• 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. 

You may get the service information 

identified in this proposed AD from 

American Eurocopter Corporation, 2701 

Forum Drive, Grand Prairie, TX 75053– 

4005, telephone (800) 232–0323, fax 

(972) 641–3710, or at http:// 

www.eurocopter.com. 

You may examine the comments to 

this proposed AD in the AD docket on 

the Internet at http:// 

www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: Jim 

Grigg, Aviation Safety Engineer, Safety 

Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, Texas 76137, telephone 

(817) 222–5126, fax (817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any written 

data, views, or arguments regarding this 

proposed AD. Send your comments to 

the address listed under the caption 

ADDRESSES. Include the docket number 

‘‘FAA–2010–0781, Directorate Identifier 

2007–SW–49–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light 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 with FAA 

personnel concerning this proposed 

rulemaking. Using the search function 

of the docket Web site, you can find and 

read the comments to any of our 

dockets, including the name of the 

individual who sent or signed the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

Examining the Docket 

You may examine the docket that 

contains the proposed AD, any 

comments, and other information in 

person at the Docket Operations office 

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

through Friday, except Federal holidays. 

The Docket Operations office (telephone 

(800) 647–5527) is located in Room 

W12–140 on the ground floor of the 

West Building at the street address 

stated in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD No. 

2007–0220, dated August 13, 2007, to 

correct an unsafe condition for 

Eurocopter AS 365 N2, AS 365 N3, and 

SA 365 N1 helicopters, all serial 

numbers, equipped with an aluminum 

T/R blade pitch control shaft, part 

number (P/N) 365A33.6161.20 or P/N 

365A33.6161.21. The EASA advises of 

an incident in which the pilot of a 

Model AS 365 N2 helicopter 

encountered a loss of control of the T/ 

R, but executed an uneventful run-on 

landing. A subsequent investigation 

revealed that the T/R blade pitch control 

shaft, P/N 365A33.6161.21, had broken 

in the main section of the shaft sliding 

area, which appeared to be damaged by 

peening. The origin of the crack, which 

developed under fatigue loading, could 

not be determined. However, accidental 

damage (i.e., shock impact), is believed 

to have caused the initiation of a crack. 

Related Service Information 

Eurocopter has issued Alert Service 

Bulletin No. 01.00.59, dated June 21, 

2007, which specifies removing any T/ 

R blade pitch control shaft, P/N 

365A33.6161.20 or P/N 

365A33.6161.21, and replacing it with a 

steel T/R blade pitch control shaft, P/N 

365A33.6214.20. The EASA classified 

this alert service bulletin as mandatory 

and issued EASA AD No. 2007–0220, 

dated August 13, 2007, to ensure the 

continued airworthiness of these 

helicopters. 

FAA’s Evaluation and Unsafe Condition 

Determination 

These products have been approved 

by the aviation authority of France, and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, the EASA, their 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are proposing this AD 

because we evaluated all information 

provided by the EASA and determined 

the unsafe condition exists and is likely 

to exist or develop on other products of 

these same type designs. This proposed 

AD would require, within 100 hours 

time-in-service, removing any 

aluminum T/R blade pitch control shaft, 

P/N 365A33.6161.20 or P/N 

365A33.6161.21, and replacing it with a 

steel T/R blade pitch control shaft, P/N 

365A33.6214.20. The actions would be 

required to be accomplished by 

following specified portions of the alert 

service bulletin described previously. 

Differences Between This Proposed AD 

and the EASA AD 

Our proposed AD differs from the 

EASA AD in that we require compliance 

within 100 hours time-in-service instead 

of no later than December 31, 2007, 

since that date has passed. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 36 helicopters of U.S. 

registry and the proposed actions would 

take approximately 12 work hours per 

helicopter to accomplish at an average 

labor rate of $85 per work hour. 

Required parts would cost 

approximately $3,525. Based on these 

figures, we estimate the total cost 

impact of the proposed AD on U.S. 

operators to be $163,620 to replace the 

aluminum T/R blade pitch control shaft 

on the entire fleet, or $4,545 per 

helicopter. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. Additionally, this proposed AD 

would 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 proposed 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 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
48620 Federal Register / Vol. 75, No. 154 / Wednesday, August 11, 2010 / Proposed Rules 

this proposed AD. See the AD docket to 

examine the economic evaluation. 

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. 

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend 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. Section 39.13 is amended by 

adding a new airworthiness directive to 

read as follows: 

Eurocopter France: Docket No. FAA–2010– 

0781; Directorate Identifier 2007–SW– 

49–AD. 

Applicability: Model AS–365N2, AS 365 

N3, and SA–365N1 helicopters, with an 

aluminum tail rotor (T/R) blade pitch control 

shaft, part number (P/N) 365A33.6161.20 or 

P/N 365A33.6161.21, installed, certificated in 

any category. 

Compliance: Required within 100 hours 

time-in-service, unless accomplished 

previously. 

To prevent failure of the T/R blade pitch 

control shaft, loss of T/R control, and 

subsequent loss of control of the helicopter, 

accomplish the following: 

(a) Remove the aluminum T/R blade pitch 

control shaft, P/N 365A33.6161.20 or P/N 

365A33.6161.21, and replace it with a steel 

T/R blade pitch control shaft, P/N 

365A33.6214.20, in accordance with the 

Accomplishment Instructions, Operational 

Procedure, paragraphs 2.B.1. through 2.B.3., 

of Eurocopter Alert Service Bulletin No. 

01.00.59, dated June 21, 2007. 

(b) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Safety 

Management Group, Rotorcraft Directorate, 

FAA, ATTN: Jim Grigg, Aviation Safety 

Engineer, 2601 Meacham Blvd., Fort Worth, 

Texas 76137, telephone (817) 222–5126, fax 

(817) 222–5961. 

(c) The Joint Aircraft System/Component 

(JASC) Code is 6500: Tail Rotor Drive 

System. 

Note: The subject of this AD is addressed 

in European Aviation Safety Agency AD No. 

2007–0220, dated August 13, 2007. 

Issued in Fort Worth, Texas, on August 2, 

2010. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–19823 Filed 8–10–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0761; Directorate 

Identifier 2010–NM–069–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes. This 

proposed AD would require installing 

two warning level indicator lights on 

the P2–2 center instrument panel in the 

flight compartment for certain airplanes. 

For a certain other airplane, this 

proposed AD would require activating 

the cabin altitude warning and takeoff 

configuration warning lights. For all 

airplanes, this proposed AD also would 

require revising the airplane flight 

manual to remove certain requirements 

included by previous AD actions, to 

require new pressure altitude 

limitations for certain airplanes, and to 

advise the flightcrew of the following 

changes: revised emergency procedures 

to use when a cabin altitude warning or 

rapid depressurization occurs, and 

revised cabin pressurization procedures 

for normal operations. This proposed 

AD results from a design change in the 

cabin altitude warning system that 

would address the identified unsafe 

condition. We are proposing this AD to 

prevent failure of the flightcrew to 

recognize and react to a valid cabin 

altitude warning horn, which could 

result in incapacitation of the flightcrew 

due to hypoxia (lack of oxygen in body), 

and consequent loss of control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by September 27, 

2010. 

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 proposed 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 proposed 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. 


jlentini on DSKJ8SOYB1PROD with PROPOSALS