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 

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Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Proposed Rules 27957 

agreement with that State of Design 

Authority, we have been notified of the 

unsafe condition described in the MCAI 

AD and service information. We are 

proposing this AD because we evaluated 

all pertinent information and 

determined an unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. 

Differences Between This AD and the 

MCAI AD 

We use a 50-hour TIS compliance 

time rather than before further flight as 

used in the MCAI AD. Also, the MCAI 

AD states to follow the ASB and insert 

pages into the RFM. We did not follow 

the ASB, which requires the RFM 

information to be filed in the Section 4, 

Normal Procedures, of the RFM. To 

make compliance with the information 

mandatory, we are requiring that it be 

inserted into the Section 2, Limitations 

Section of the RFM. 

Costs of Compliance 

We estimate that this proposed AD 

would affect about 20 helicopters of 

U.S. registry. We also estimate that it 

would take about 1⁄2 work-hour to copy 

and insert the synchronization 

procedure into the RFM. The average 

labor rate is $85 per hour. We estimate 

the cost of the proposed AD on U.S. 

operators to be $850. 

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, 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 Deutschland: Docket No. FAA– 

2011–0453; Directorate Identifier 2008– 

SW–16–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 EC135 

helicopters with Turbomeca Arrius 2B or 2B1 

engines installed, certificated in any 

category. 

Reason 

(d) The mandatory continuing 

airworthiness information (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. A discrepancy in the 

parameters similar to those in the past cannot 

be ruled out. With this AD, a synchronization 

procedure for pilots is being re-introduced, 

which prevents the parameter discrepancy 

arising and thus sustains the automatic 

engine control. 

Actions and Compliance 

(e) Within 50 hours time-in-service (TIS), 

unless already done, either insert the 

following procedure by making pen and ink 

changes to the Rotorcraft Flight Manual 

(RFM) or by inserting a copy of this AD into 

the Limitations Section of the RFM. 

‘‘SPECIAL INFORMATION FOR OEI/ 

AUTOROTATION TRAINING AND 

APPROACH/LANDING PREPARATION 

In order to prevent a malfunction, which 

could lead to a FADEC FAIL indication, the 

following procedure is mandatory: 

The procedure shown below must be 

performed while in a steady flight condition 

and at a safe altitude: 

—Before initiation of every approach (with or 

without landing) 

—During training of OEI or Autorotation 

before every switch-over to IDLE 

CAUTION: DURING THE RESET 

PROCEDURE DESCRIBED IN THE 

FOLLOWING, NO INPUTS ARE TO BE 

MADE TO THE COLLECTIVE LEVER OR TO 

THE TWIST GRIP FOR MANUAL ENGINE 

CONTROL, SINCE THIS CAN LEAD TO AN 

INEFFECTIVE SYNCHRONIZATION. 

The reset procedure is identical for each of 

two systems and is to be applied for both 

engines, one after the other. 

Procedure 

1. ENG MODE SEL switch—Set from 

NORM TO MAN 

After illumination of the ENG MANUAL 

caution: 

2. ENG MODE SEL switch—Set from MAN 

to NORM: ENG MANUAL caution must go 

off 

Repeat procedure for second engine.’’ 

Differences Between This FAA AD and the 

MCAI AD 

(f) We use a 50-hour TIS compliance time 

rather than before further flight. Also, the 

MCAI AD states to follow the ASB and insert 

pages into the RFM. We did not follow the 

ASB, which requires the RFM information to 

be filed in the Section 4, Normal Procedures, 

of the RFM. To make compliance with the 

information mandatory, we are requiring that 

it be inserted into the Section 2, Limitations 

Section of the RFM. 

Other Information 

(g) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, Rotorcraft Directorate, FAA, ATTN: 

Eric Haight, Aviation Safety Engineer, 

Regulations and Guidance Group, 2601 

Meacham Blvd., Fort Worth, Texas 76137, 

telephone (817) 222–5204, fax (817) 222– 

5961, has the authority to approve AMOCs, 

if requested, for this AD using the procedures 

found in 14 CFR 39.19. 

Related Information 

(h) MCAI AD 2002–333, dated September 

16, 2002, contains related information. 

Air Transport Association of America (ATA) 

Tracking Code 

(i) The ATA Code is 7600: Engine Controls. 

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27958 Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Proposed Rules 

Issued in Fort Worth, Texas on April 28, 

2011. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–11882 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–2011–0449; Directorate 

Identifier 2010–SW–021–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada (Bell) Model 

206A, 206B, and 206B3 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 Bell model helicopters. This 

proposed AD would require revising the 

Operating Limitations, Section 1, of the 

Rotorcraft Flight Manual (RFM) to add 

an operating limitation when a litter kit 

is installed. This proposed AD is 

prompted by the need for corresponding 

operating limitations prohibiting flight, 

including hover, with the litter doorpost 

removed when certain litter kits are 

installed. The actions specified by this 

proposed AD are intended to add an 

operating limitation when a litter kit is 

installed to prohibit flight with the 

doorpost removed to prevent loss of 

structural integrity of the fuselage. 

DATES: Comments must be received on 

or before July 12, 2011. 

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 Bell 

Helicopter Textron Canada Limited, 

12,800 Rue de l’Avenir, Mirabel, Quebec 

J7J1R4, telephone (450) 437–2862 or 

(800) 363–8023, fax (450) 433–0272, or 

at http://www.bellcustomer.com/files/. 

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: 

Mark Wiley, Aviation Safety Engineer, 

FAA, Rotorcraft Directorate, Regulations 

and Guidance Group, 2601 Meacham 

Blvd., Fort Worth, Texas 76137, 

telephone (817) 222–5134, 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 caption 

ADDRESSES. Include the Docket No. 

‘‘FAA–2011–0449, Directorate Identifier 

2010–SW–021–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 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 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 

Bell reissued RFM Supplement 

(RFMS) BHT–206A–FMS–8 for the 

Model 206A, BHT–206B–FMS–8 for the 

Model 206B, and BHT–206B3–FMS–2 

for the Model 206B3 helicopters, all 

dated December 30, 2009, approved by 

Transport Canada and the FAA. The 

revisions to the RFMS were reformatted 

to match the RFM and to add a ‘‘Type 

of Operation’’ paragraph to Section 1 of 

the ‘‘Operating Limitations,’’ which 

states: ‘‘Flight, including hover, with 

litter doorpost removed is not approved. 

Litter doorpost may be removed and reinstalled with rotor turning at flat 

pitch.’’ 

FAA’s Evaluation and Unsafe Condition 

Determination 

These helicopters have been approved 

by the aviation authority of Canada and 

are approved for operation in the United 

States. We are proposing this AD 

because we evaluated all information 

provided by Transport Canada and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

helicopters of these same type designs. 

This proposed AD would require 

revising the RFM by inserting into the 

Operating Limitations, Section 1, of the 

RFM the following statement: ‘‘Flight, 

including hover, with litter doorpost 

removed is prohibited.’’ This revision 

may be made by pen and ink changes, 

inserting a copy of this AD into the 

RFM, or inserting a copy of the RFMS 

dealing with Litter Kits into the RFM as 

follows: For Model 206A helicopters— 

inserting RFMS BHT–206A–FMS–8, 

dated December 30, 2009, into RFM 

BHT–206A–FM–1, dated July 2, 2009; 

for Model 206B helicopters—inserting 

RFMS BHT–206B–FMS–8, dated 

December 30, 2009, into RFM BHT– 

206B–FM–1, dated July 2, 2009; and for 

Model 206B3 helicopters—inserting 

RFMS BHT–206B3–FMS–2, dated 

December 30, 2009, into RFM BHT– 

206B3–FM–1, dated March 24, 2010. 

This limitation is required to prevent 

loss of structural integrity of the 

helicopter fuselage. 

Costs of Compliance 

We estimate this proposed AD would 

affect 1,463 helicopters of U.S. registry. 

The cost to revise the operating 

limitations section of the RFM for each 

helicopter would be negligible, and 

there are no required parts. 

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 

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