27954 Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Proposed Rules 

Texas 76137, telephone (817) 222–5130, fax 

(817) 222–5961, for information about 

previously approved alternative methods of 

compliance. 

(c) The Joint Aircraft System/Component 

(JASC) Code is 2700: Flight Control System. 

Note: The subject of this AD is addressed 

in Direction Generale de l’Aviation Civile 

(France) AD No. F–2005–175, dated October 

26, 2005, and Eurocopter Alert Service 

Bulletin No. 67A011, Revision 1, dated 

October 7, 2005 

Issued in Fort Worth, Texas, on April 27, 

2011. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–11752 Filed 5–12–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0454; Directorate 

Identifier 2009–SW–54–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model SA–365C, SA–365C1, 

SA–365C2, SA–365N, SA–365N1, AS– 

365N2, AS 365 N3, and SA–366G1 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

specified Eurocopter France (ECF) 

model helicopters. This proposed AD 

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 that the manufacturer has 

received some reports of deterioration 

and two reports of failure of Starflex star 

arm ends. These deteriorations 

generated high-amplitude vibrations in 

flight requiring precautionary landings. 

They state these deteriorations are due 

to the strong effect of temperature on the 

strength of the bush-to-Starflex star arm 

end attachment. Consequently, the 

MCAI AD requires modification of the 

frequency adapters and the frequency 

adapter bushes to improve the 

ventilation in the area on the star arm 

end. This proposed AD is intended to 

require modifying the main rotor 

frequency adapters to reduce the 

temperature in the area, to prevent 

failure of the star arm end, severe 

vibration, and subsequent loss of control 

of the helicopter. 

DATES: We must receive comments on 

this proposed AD by June 13, 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. 

You may get the service information 

identified in this proposed AD from 

American Eurocopter Corporation, 2701 

Forum Drive, Grand Prairie, Texas 

75053–4005, telephone (800) 232–0323, 

fax (972) 641–3710 or at http:// 

www.eurocopter.com. 

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 proposed 

AD, the economic evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

DOT/FAA Southwest Region, Gary 

Roach, ASW–111, Aviation Safety 

Engineer, Rotorcraft Directorate, 

Regulations and Guidance Group, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5130, fax 

(817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–0454; Directorate Identifier 

2009–SW–54–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 proposed AD. 

Discussion 

The EASA, which is the Technical 

Agent for the Member States of the 

European Community, has issued EASA 

Emergency AD (EAD) No. 2006–0362–E, 

dated November 30, 2006, to correct an 

unsafe condition for the specified 

Eurocopter model helicopters. The 

MCAI AD states: ‘‘This Emergency 

Airworthiness Directive is issued 

following some reports of deterioration 

and two reports of failure of Starflex star 

arm ends. These deteriorations 

generated high-amplitude vibrations in 

flight, compelling the pilot to carry out 

a precautionary landing, in each of these 

cases. The failure of the Starflex star 

arm end could make it impossible to 

control the helicopter. These 

deteriorations are due to the strong 

effect of temperature on the strength of 

the bush-to-Starflex star arm end 

attachment. Consequently, this EAD 

requires modification (MOD 0762C39) 

of the frequency adapters and the 

frequency adapter bushes, in order to 

improve the ventilation in the area on 

the star arm end, on helicopters 

operated in hot climatic conditions and/ 

or tropical and damp atmosphere.’’ 

You may obtain further information 

by examining the MCAI AD and service 

information in the AD docket. 

Related Service Information 

ECF has issued one Emergency Alert 

Service Bulletin, dated November 23, 

2006, with four different numbers: No. 

62.00.24 is for the civil Model SA– 

365N, AS–365N1, AS–365N2, and AS– 

365 N3; No. 62.14 is for the civil Model 

SA–366G1; No. 65.45 is for the Model 

SA–365C, C1, and C2; and No. 62.00.10 

is for the non-FAA type certificated 

military Model 565 helicopters. 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 

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, EASA, their 

Technical Agent, has informed us of the 

unsafe condition described in the MCAI 

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Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Proposed Rules 27955 

AD and the referenced service 

information. We are proposing this AD 

because we evaluated all the 

information provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of these same type designs. 

Differences Between This Proposed AD 

and the MCAI AD 

This proposed AD differs from the 

MCAI AD as follows: 

• We refer to flight hours as hours 

time-in-service. 

• We refer to a check as an inspection 

if it is an action performed by 

maintenance personnel rather than a 

pilot. 

• We omit the phrase ‘‘hot climatic 

conditions and/or in tropical and damp 

atmosphere’’ because it is unenforceable. 

Costs of Compliance 

We estimate that this proposed AD 

would affect about 37 helicopters of 

U.S. registry. We also estimate that it 

would take about 12 work-hours per 

helicopter to modify the frequency 

adapters and bushes. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $960 per 

helicopter. Based on these figures, we 

estimate the cost of the proposed AD on 

U.S. operators to be $73,260. 

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 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. 

For the reasons discussed above, I 

certify this 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 

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 adding 

the following new AD: 

Eurocopter France: Docket No. FAA–2011– 

0454; Directorate Identifier 2009–SW– 

54–AD. 

Comments Due Date 

(a) We must receive comments by June 13, 

2011. 

Other Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model SA–365C, 

SA–365C1, SA–365C2, SA–365N, SA–365N1, 

AS–365N2, AS 365 N3, and SA–366G1 

helicopters, certificated in any category. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) AD states 

that the manufacturer has received some 

reports of deterioration and two reports of 

failure of Starflex star arm ends. These 

deteriorations generated high-amplitude 

vibrations in flight requiring precautionary 

landings. They state these deteriorations are 

due to the strong effect of temperature on the 

strength of the bush-to-Starflex star arm end 

attachment. Consequently, the MCAI AD 

requires modification of the frequency 

adapters and the frequency adapter bushes to 

improve the ventilation in the area on the 

star arm end. The proposed AD is intended 

to require modifying the main rotor 

frequency adapters to reduce the temperature 

in the area, to prevent failure of the star arm 

end, severe vibration, and subsequent loss of 

control of the helicopter. 

Actions and Compliance 

(e) For a main rotor head frequency 

adapter, pre MOD 0762C39, within 110 hours 

time-in-service (TIS), remove the main rotor 

blades, modify the frequency adapters and 

bushes, and change the part number of the 

frequency adapter as shown in Figures 1 

through 5 and by following the 

Accomplishment Instructions, paragraph 

2.B.2., of Eurocopter Emergency Alert Service 

Bulletin (EASB) No. 62.00.24 for the Model 

SA–365N, N1, AS–365N2, and AS 365 N3; 

No. 62.14 for the Model SA–366G1; and No. 

65.45 for the Model SA–365C, C1, and C2 

helicopters; all dated November 23, 2006. 

This modification is MOD 0762C39. 

Note: The one Eurocopter EASB contains 

four different EASB numbers, three (Nos. 

62.00.24, 62.14, and 65.45) that apply to 

different civil Eurocopter model helicopters 

and one (No. 62.00.10) that only applies to 

non-FAA type-certificated military Model 

565 helicopters and is not incorporated by 

reference. 

(f) For each main rotor head frequency 

adapter modified per MOD 0762C39, within 

10 hours TIS, unless accomplished 

previously, and thereafter at intervals not to 

exceed 10 hours TIS, inspect to determine 

whether the safety wire is in place on the 

trailing edge of the frequency adapter and 

whether the holes in the frequency adapters 

and the frequency adapter bushes, as shown 

in Figure 5 of the EASB for your model 

helicopter, are blocked. 

(1) If the lockwire is missing from the 

trailing edge of the frequency adapter, before 

further flight, reposition the bush if it has 

turned and install more safety wire. 

(2) If a hole is blocked, before further flight, 

unblock the hole. 

(g) Before installing a frequency adapter or 

bush, modify the frequency adapter or bush 

and change the part number in accordance 

with paragraph (e) of this AD. 

Differences Between This AD and the MCAI 

AD 

(h) This AD differs from the MCAI AD as 

follows: 

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

(2) We refer to the check specified in the 

MCAI AD as an inspection because it is an 

action performed by maintenance personnel 

rather than a pilot. 

(3) We omit the phrase ‘‘hot climatic 

conditions and/or in tropical and damp 

atmosphere’’ because it is unenforceable. 

Other Information 

(i) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, DOT/FAA Southwest Region, Gary 

Roach, ASW–111, Aviation Safety Engineer, 

Rotorcraft Directorate, Regulations and 

Guidance Group, 2601 Meacham Blvd., Fort 

Worth, Texas 76137, telephone (817) 222– 

5130, fax (817) 222–5961, has the authority 

to approve AMOCs for this AD, if requested, 

using the procedures found in 14 CFR 39.19. 

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27956 Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Proposed Rules 

Related Information 

(j) MCAI AD No. 2006–0362–E, dated 

November 30, 2006, contains related 

information. 

Joint Aircraft System/Component (JASC) 

Code 

(k) The Joint Aircraft System/Component 

(JASC) Code is 5311: Main Rotor Head. 

Issued in Fort Worth, Texas, on April 28, 

2011. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–11878 Filed 5–12–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0453; Directorate 

Identifier 2008–SW–16–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland Model EC135 Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for 

Eurocopter Deutschland (ECD) Model 

EC135 helicopters. This proposed AD 

results from a mandatory continuing 

airworthiness information (MCAI) AD 

issued by the aviation authority of the 

Federal Republic of Germany, with 

which we have a bilateral agreement, to 

identify and correct an unsafe 

condition. The MCAI AD states that in 

the past, the FADEC FAIL caution light 

illuminated on a few EC135 T1 

helicopters. They state that this was 

caused by a discrepancy in the 

parameters which were generated 

within the fuel main metering unit and 

transmitted to the FADEC. This 

discrepancy led to the display of the 

FADEC FAIL caution light and 

‘‘freezing’’ of the fuel main metering 

valve at its position resulting in loss of 

the automatic engine control in the 

affected system. With the EASA AD, a 

synchronization procedure for pilots, 

which was already used in the past, is 

being re-introduced, which prevents the 

parameter discrepancy arising and thus 

sustains the automatic engine control. 

The proposed AD actions are 

intended to prevent failure of the 

FADEC to automatically meter fuel, 

indicated by a FADEC FAIL cockpit 

caution light, and subsequent loss of 

control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by June 13, 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. 

You may get the service information 

identified in this proposed AD from 

American Eurocopter Corporation, 2701 

Forum Drive, Grand Prairie, Texas 

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

fax (972) 641–3527. 

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 proposed 

AD, the economic evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Eric 

Haight, Aviation Safety Engineer, FAA, 

Rotorcraft Directorate, Regulations and 

Guidance Group, Fort Worth, Texas 

76137, telephone (817) 222–5204, fax 

(817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–0453; Directorate Identifier 

2008–SW–16–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 proposed AD. 

Discussion 

Luftfahrt-Bundesamt, which is the 

aviation authority for the Federal 

Republic of Germany, has issued AD 

No. 2002–333, dated September 16, 

2002, to correct an unsafe condition for 

this German-certificated product. The 

MCAI AD states that in the past, the 

FADEC FAIL caution light illuminated 

on a few EC135 T1 helicopters. They 

state that this was caused by a 

discrepancy in the parameters which 

were generated within the fuel main 

metering unit and transmitted to the 

FADEC. This discrepancy led to the 

display of the FADEC FAIL caution light 

and ‘‘freezing’’ of the fuel main metering 

valve at its position resulting in loss of 

the automatic engine control in the 

affected system. Despite measures 

undertaken by Turbomeca to eliminate 

this problem (software improvements 

TU19C, TU23C and TU45C), additional 

FADEC FAIL cases have occurred on EC 

135 T1 helicopters for which no 

explanation has been found. Therefore, 

a discrepancy in the parameters similar 

to those in the past cannot be ruled out. 

With this proposed AD, a 

synchronization procedure for pilots, 

which was already used in the past, is 

being re-introduced, which prevents the 

parameter discrepancy arising and thus 

sustains the automatic engine control. 

To date, there is no terminating action 

to this required manual pilot 

synchronization procedure. 

You may obtain further information 

by examining the MCAI AD and the 

service information in the AD docket. 

Related Service Information 

ECD has issued Alert Service Bulletin 

No. EC135–71A–024, dated August 6, 

2002 (ASB). The ASB contains copies of 

special information to be inserted into 

the Rotorcraft Flight Manual (RFM) for 

synchronizing fuel control components 

for sustaining automatic engine control. 

The ASB specifies making copies of the 

RFM pages contained in the ASB, 

cutting them out, and filing them in the 

RFM. The actions described in the 

MCAI AD are intended to correct the 

same unsafe condition as that identified 

in this service information. 

FAA’s Determination and Requirements 

of This Proposed AD 

This model 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 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS