Federal Register / Vol. 76, No. 214 / Friday, November 4, 2011 / Rules and Regulations 68299 

(ii) If there is corrosion on a module, before 

further flight, replace the module with an 

airworthy module. 

(b) Modify the Number 2 MAU ventilation 

duct by following the Compliance 

Instructions, paragraphs 6 through 11, of 

Agusta Bollettino Tecnico No. 139–166, 

dated April 6, 2009 (BT). 

(c) Install and operationally test the 

Number 1 and Number 2 MAUs and the 

related PS module, CSIO module, CIO 

module, MAU cabinet, and all related 

connectors. 

(d) Reinstall the AFT right float assembly 

or the lower panel, P/N 3P5340A01631, 

whichever was removed during the 

modification process required by paragraph 

(b) of this AD. 

(e) 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, ATTN: George Schwab, 

Aviation Safety Engineer, FAA, Rotorcraft 

Directorate, Safety Management Group, 2601 

Meacham Blvd., Fort Worth, Texas 76137, 

telephone (817) 222–5114, fax (817) 222– 

5961. 

(f) The Joint Aircraft System/Component 

(JASC) Code is 3425: Navigation, Integrated 

Flight Director System. 

(g) Modifying the ventilation duct shall be 

done by following specified portions of 

Agusta Bollettino Tecnico No. 139–166, 

dated April 6, 2009. 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 Agusta, Via Giovanni Agusta, 

520 21017 Cascina Costa di Samarate (VA), 

Italy, telephone 39 0331–229111, fax 39 

0331–229605/222595, or at http:// 

customersupport.agusta.com/ 

technical_advice.php. 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. 

(h) This amendment becomes effective on 

November 21, 2011. 

Note: The subject of this AD is addressed 

in the European Aviation Safety Agency 

(Italy) AD No. 2010–0189, dated September 

23, 2010. 

Issued in Fort Worth, Texas, on August 29, 

2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–27772 Filed 11–3–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1075; Directorate 

Identifier 2011–SW–011–AD; Amendment 

39–16836; AD 2011–21–13] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH (ECD) Model MBB– 

BK 117 C–2 Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for 

ECD Model MBB–BK 117 C–2 

helicopters. This action requires 

revising the Rotorcraft Flight Manual 

(RFM) by inserting certain temporary 

pages into the Emergency and 

Performance Data sections of the RFM to 

alert the operators to monitor the power 

display when a generator is deactivated 

and provides appropriate actions. This 

amendment is prompted by reports of 

too high a current flow when one 

generator is deactivated. The actions 

specified in this AD are intended to 

prevent failure of the remaining 

generator when one generator is 

deactivated, loss of electrical power, 

loss of systems necessary for flight 

safety, and subsequent loss of control of 

the helicopter. 

DATES: Effective November 21, 2011. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of November 

21, 2011. 

Comments for inclusion in the Rules 

Docket must be received on or before 

January 3, 2012. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

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 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. 

Examining the Docket: You may 

examine the docket that contains the 

AD, any comments, and other 

information 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 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. 

FOR FURTHER INFORMATION CONTACT: 

George Schwab, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Safety Management Group, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5114, fax 

(817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2010– 

0268–E, dated December 21, 2010, to 

correct an unsafe condition for the ECD 

Model MBB–BK 117 C–2 helicopters. 

EASA advises of reports that on some 

helicopters a too high current flow was 

detected when one generator was 

deactivated (for example, during the 

ENGINE POWER CHECK). EASA also 

advises that this situation, if not 

detected and corrected, could lead to 

failure of the generator, likely resulting 

in loss of electrical power and inducing 

loss of systems that are necessary for 

safe flight. Therefore, the EASA AD 

requires additional RFM procedures to 

include visual monitoring of the 

electrical power display during 

switching of a generator. Also, EASA 

advises that their AD is an interim 

measure pending the development of a 

final solution that will prevent this 

particular mode of generator failure. 

Related Service Information 

ECD has issued Alert Service Bulletin 

ASB MBB BK117 C–2–24A–008, dated 

December 20, 2010 (ASB). The ASB 

specifies inserting certain pages from 

the ASB into the RFM to alert operators 

to visually monitor the power display 

generator amperes (GEN AMPS) on the 

Vehicle and Engine Multifunction 


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68300 Federal Register / Vol. 76, No. 214 / Friday, November 4, 2011 / Rules and Regulations 

Display (VEMD) for too high a current 

flow when a generator has been 

deactivated; for example, during the 

ENGINE POWER CHECK. In such a 

situation, the revised RFM provides 

instructions for switching off the two 

main electrical buses (BUS TIEs) on the 

overhead panel to prevent the operating 

generator from being damaged. The ASB 

states that failure of the generator could 

result in subsequent loss of electrical 

power and loss of systems. EASA 

classified this ASB as mandatory and 

issued AD No. 2010–0268–E, dated 

December 21, 2010, to ensure the 

continued airworthiness of these 

helicopters. 

FAA’s Evaluation and Unsafe Condition 

Determination 

These helicopters have been approved 

by the aviation authority of the Federal 

Republic of Germany and are approved 

for operation in the United States. 

Pursuant to our bilateral agreement with 

the Federal Republic of Germany, 

EASA, their technical representative, 

has notified us of the unsafe condition 

described in the EASA 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. 

FAA’s Determination and Requirements 

of This AD 

This unsafe condition is likely to exist 

or develop on other helicopters of the 

same type design. This amendment 

adopts a new AD for ECD Model MBB– 

BK 117 C–2 helicopters. This action 

requires revising the Emergency 

Procedures and Performance Data 

sections of the RFM BK117 C–2 by 

copying or cutting out the temporary 

pages 7, 8, and 11 of the ASB and 

inserting the pages into RFM BK 117 

C–2. This amendment is prompted by 

reports of too high a current flow when 

one generator is deactivated. The 

actions specified in this AD are 

intended to revise the RFM by inserting 

temporary pages into the Emergency 

Procedures and Performance Data 

sections. The revisions to the RFM are 

intended to alert pilots to visually 

monitor the power display GEN AMPS 

on the VEMD when a generator is 

deactivated to detect too high a current 

flow and to switch off the two BUS TIEs 

on the overhead panel to prevent the 

operating generator from being 

damaged. Accomplish the actions by 

copying or cutting out pages 7, 8, and 

11 of the ASB described previously and 

inserting them into the Emergency 

Procedures and Performance Data 

sections of the RFM. 

The short compliance time involved 

is required because the previously 

described critical unsafe condition can 

adversely affect the controllability or 

structural integrity of the helicopter. 

Therefore, revising the Emergency and 

Performance Data sections of the RFM is 

required before further flight, and this 

AD must be issued immediately. 

Since a situation exists that requires 

the immediate adoption of this 

regulation, it is found that notice and 

opportunity for prior public comment 

hereon are impracticable, and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Costs of Compliance 

We estimate that this AD will affect 

about 232 helicopters of U.S. registry. 

We also estimate that it will take a 

minimal amount of time to copy and 

insert the pages into the RFM. 

Therefore, the cost of the AD will be 

minimal. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2011–1075; 

Directorate Identifier 2011–SW–011– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD. We will consider all comments 

received by the closing date and may 

amend the 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 AD. 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 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). 

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); 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; and 

4. 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. 

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, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration amends 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: 

2011–21–13 EUROCOPTER 

DEUTSCHLAND GmbH (ECD): 


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Federal Register / Vol. 76, No. 214 / Friday, November 4, 2011 / Rules and Regulations 68301 

Amendment 39–16836; Docket No. 

FAA–2011–1075; Directorate Identifier 

2011–SW–011–AD. 

Applicability: Model MBB–BK 117 C–2 

helicopters, certificated in any category. 

Compliance: Before further flight, unless 

accomplished previously. 

To prevent failure of a generator, loss of 

electrical power, loss of systems necessary 

for flight safety, and subsequent loss of 

control of the helicopter, do the following: 

(a) Revise the ‘‘Emergency and Malfunction 

Procedures’’ and the ‘‘Performance Data’’ 

sections of the Rotorcraft Flight Manual 

(RFM) BK117 C–2 by copying or cutting out 

temporary pages 7, 8, and 11 (RFM pages 3– 

3 and 3–3a for ‘‘Emergency and Malfunction 

Procedures’’ and page 5–7 for ‘‘Performance 

Data’’) of ECD Alert Service Bulletin No. ASB 

MBB BK117 C–2–24A–008, dated December 

20, 2010, and inserting the pages into RFM 

BK 117 C–2. 

(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, ATTN: George Schwab, 

Aviation Safety Engineer, FAA, Rotorcraft 

Directorate, 2601 Meacham Blvd., Fort 

Worth, Texas 76137, telephone (817) 222– 

5114, fax (817) 222–5961, for information 

about previously approved alternative 

methods of compliance. 

(c) The Joint Aircraft System/Component 

(JASC) Code is 2435: Starter-Generator, 2437: 

DC Indicating System, and 2430: DC 

Generator System. 

(d) Revise the Emergency Procedures and 

Performance Data sections of RFM BK 117 C– 

2 by inserting the specified portions of ECD 

Alert Service Bulletin No. ASB MBB BK117 

C–2–24A–008, dated December 20, 2010, into 

the RFM. 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, TX 75053–4005, 

telephone (800) 232–0323, fax (972) 641– 

3710, or at http://www.eurocopter.com. 

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. 

(e) This amendment becomes effective on 

November 21, 2011. 

Note: The subject of this AD is addressed 

in The European Aviation Safety Agency (the 

Federal Republic of Germany) AD No. 2010– 

0268–E, dated December 21, 2010. 

Issued in Fort Worth, Texas, on September 

29, 2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–27776 Filed 11–3–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1182; Directorate 

Identifier 2010–SW–010–AD; Amendment 

39–16853; AD 2011–23–02] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron, Inc. (Bell), Model 

205A–1, 205B, 210, and 212 Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD) 

for Bell Model 205B and 212 helicopters 

with certain main rotor blade (blade) 

assemblies installed. That AD currently 

requires washing the upper and lower 

surfaces of each blade and visually 

inspecting the grip plates, doublers, and 

the remaining upper and lower surfaces 

of the blades in the area between blade 

stations 24.5 to 40 for an edge void, 

corrosion, or a crack. This amendment 

retains the requirements of that AD for 

the affected part-numbered blades but 

increases the scope and frequency of the 

inspections and expands the 

applicability to include the Model 

205A–1 and 210 helicopters, additional 

blade part numbers, and all helicopter 

serial numbers for the affected 

helicopter models. This amendment 

also requires applying a light coat of 

preservative oil (C–125) to all surfaces 

of the blade in addition to the 

inspection areas as required in the 

existing AD. This amendment is 

prompted by an additional report of a 

fatigue crack on a blade installed on a 

Model 212 helicopter. The actions 

specified by this AD are intended to 

detect an edge void, corrosion, or a 

crack on a blade, and to prevent loss of 

a blade and subsequent loss of control 

of the helicopter. 

DATES: Effective November 21, 2011. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of November 

21, 2011. 

We must receive comments on this 

AD by January 3, 2012. 

ADDRESSES: Use one of the following 

addresses to comment on this 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 AD from Bell 

Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, TX 76101, telephone (817) 

280–3391, fax (817) 280–6466, or at 

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

Examining the Docket: You may 

examine the docket that contains the 

AD, any comments, and other 

information 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 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. 

FOR FURTHER INFORMATION CONTACT: 

Michael Kohner, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Rotorcraft Certification Office, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5170, fax 

(817) 222–5783. 

SUPPLEMENTARY INFORMATION: On 

December 21, 2009, we issued AD 2010– 

03–03, Amendment 39–16186 (75 FR 

5681, February 4, 2010), to require at 

specified intervals washing the upper 

and lower surfaces of each blade and 

visually inspecting the grip plates, 

doublers, and the remaining upper and 

lower surfaces of the blades in the area 

from blade stations 24.5 to 40 for an 

edge void, corrosion, or a crack using a 

3x power or higher magnifying glass. 

That AD was prompted by two reports 

of fatigue cracks on blades installed on 

Model 212 helicopters. The cause of the 

cracks has been attributed to inadequate 

adhesive bonding during manufacture 

in the area between the grip plate and 

mating doubler surface. A crack first 

appears in the grip plate, which can be 

detected visually with the blade 

installed on the helicopter. That 

condition, if not detected, could result 

in loss of a blade and subsequent loss 

of control of the helicopter. 

Since issuing AD 2010–03–03 (75 FR 

5681, February 4, 2010), we have 

received another report of a fatigue 

crack on a blade installed on a Model 

212 helicopter. The crack at the blade 


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