Federal Register / Vol. 77, No. 244 / Wednesday, December 19, 2012 / Proposed Rules 75073 

Dissipation is rapid dilution of the 

smoke by ventilation air. Mobility is 

rapid movement of the smoke into and 

out of the occupied area. In no case 

should a light haze indicative of 

stagnant airflow form, as this indicates 

that the ventilation system is failing to 

meet the requirements of 14 CFR 25.831, 

iii. The smoke from a source below 

the main deck must not rise above 

armrest height on the main deck, and 

iv. The smoke from a source in the 

main deck must dissipate rapidly via 

dilution with fresh air and be evacuated 

from the airplane. The Airplane Flight 

Manual (AFM) must include procedures 

to evacuate smoke from the occupied 

areas. To demonstrate that the quantity 

of smoke is small, a flight test must be 

conducted which simulates the 

emergency procedures used in the event 

of a fire during flight, including the use 

of VMO/MMO descent profiles and a 

simulated landing, if such conditions 

are specified in the emergency 

procedure. 

2. Requirement for smoke or fire 

detection in electrical/electronic 

equipment bays: A smoke or fire 

detection system compliant with 

§§ 25.855(a), (b), (c), and (d); and 

§ 25.858 must be provided for each 

electrical/electronic equipment bay in 

the pressurized cabin. Each system must 

provide a visual indication to the flight 

deck within one minute after the start of 

a fire. Airplane flight tests must be 

conducted to show compliance with 

these requirements, and the 

performance of the detectors must be 

shown in accordance with Advisory 

Circular 25–9A, Smoke Detection, 

Penetration, and Evacuation Tests and 

Related Flight Manual Emergency 

Procedures, or other means acceptable 

to the FAA. 

3. Requirement for AFM procedures 

safety analysis: It shall be demonstrated 

that the AFM procedures to shut down 

electrical/electronic equipment bays, or 

part of them, in case of smoke/fire 

detection, do not compromise the safe 

operation of the aircraft. If a procedure 

requests to shut down only part of the 

equipment, the remaining equipment 

shall be incorporated with safety 

precautions against fire propagation. 

Issued in Renton, Washington, on 

December 13, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–30493 Filed 12–18–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1285; Directorate 

Identifier 2010–SW–073–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (SNPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for Eurocopter Deutschland GmbH 

(Eurocopter) Model BO–105A, BO– 

105C, BO–105LS A–1, BO–105LS A–3, 

and BO–105S helicopters, which 

proposed inspecting for debonding of 

the erosion protective shell (abrasion 

strip) on the leading edge of each main 

rotor blade. This SNPRM proposes to 

revise those inspection requirements by 

identifying specific dates of replacement 

of the applicable parts and identifying a 

specific inspection method for 

debonding of an abrasion strip. 

DATES: We must receive comments on 

this proposed AD by February 4, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 service information identified in 

this proposed AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, Texas 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http:// 

www.eurocopter.com/techpub. You may 

review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: Jim 

Grigg, Manager, Safety Management 

Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

jim.grigg@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

On November 29, 2011, we issued a 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an AD that would apply to 

Eurocopter Model BO–105A, BO–105C, 

BO–105LS A–1, BO–105LS A–3, and 

BO–105S helicopters with a main rotor 

blade, part number (P/N) 105–15103, 

105–15141, 105–15141V001, 105– 

15143, 105–15150, 105–15150V001, 

105–15152, 105–81013, 105–87214, 

1120–15101, or 1120–15103; where the 

main rotor blade erosion protective shell 

was replaced between September 2006 


wreier-aviles on DSK5TPTVN1PROD with 
75074 Federal Register / Vol. 77, No. 244 / Wednesday, December 19, 2012 / Proposed Rules 

and March 2010. This proposal was 

published in the Federal Register as a 

notice of proposed rulemaking (NPRM) 

on December 6, 2011 (76 FR 76068). The 

NPRM proposed to require a one-time 

inspection of each main rotor blade for 

debonding of the erosion protective 

shell within 50 hours time-in-service 

(TIS). If debonding was detected during 

the inspection, the NPRM proposed 

replacing the main rotor blade with an 

airworthy main rotor blade before 

further flight. The proposed 

requirements were intended to detect 

debonding of the main rotor blade 

erosion protective shell, which could 

lead to an unbalanced main rotor, high 

vibration, damage to the tail boom or 

tail rotor, and loss of control of the 

helicopter. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Emergency AD 

No. 2010–0216–E, dated October 21, 

2010 (corrected October 29, 2010), 

applicable to Eurocopter Model BO105 

A, BO105 C, BO105 D, BO105 LS A–1, 

BO105 LS A–3, and BO105 S 

helicopters, all variants (except variants 

CB–5 and DBS–5). EASA advises that 

during an inspection on a BO105 

helicopter, debonding was found on the 

erosion protective shell of a main rotor 

blade, and investigation showed the 

debonding was caused by incorrect 

installation of the erosion protective 

shell. In addition, EASA states that an 

incident occurred where a second 

BO105 helicopter lost its erosion 

protective shell during hover flight. 

EASA advises that this condition, if not 

corrected, could result in loss of the 

main rotor blade erosion protective shell 

during flight, leading to an unbalanced 

main rotor and high vibrations, which 

could damage the tail boom or tail rotor 

or result in loss of tail rotor control and 

loss of control of the helicopter. 

Actions Since Previous NPRM Was 

Issued 

Since we issued the previous NPRM 

(76 FR 76068, December 6, 2011), we 

discovered the need for identifying 

specific dates of replacement of the 

applicable parts and identifying that a 

tap inspection would be the required 

method for inspecting for debonding of 

an abrasion strip. The previous NPRM 

stated the proposed AD would apply to 

certain part-numbered main rotor blades 

with a main rotor blade abrasion strip 

that was replaced between September 

2006 and March 2010. This 

supplemental NPRM proposes clarifying 

the date range to be inclusive of 

September 1, 2006 through March 31, 

2010. The previous NPRM also 

proposed to require inspecting for 

debonding of the abrasion strip along 

the leading edge of each main rotor 

blade. This supplemental NPRM 

clarifies that the proposed inspection 

method is a tap inspection. 

Because these proposed changes 

expand the applicability and may 

increase the economic burden on some 

operators, the FAA will reopen the 

comment period to provide additional 

opportunity for public comment. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all known relevant 

information and determined that an 

unsafe condition is likely to exist or 

develop on other helicopters of these 

same type designs. Certain changes 

described above expand the scope of the 

original NPRM (76 FR 76068, December 

6, 2011). As a result, we have 

determined that it is necessary to reopen 

the comment period to provide 

additional opportunity for the public to 

comment. 

Related Service Information 

Eurocopter has issued Emergency 

Alert Service Bulletin (ASB) No. ASB 

BO105–10–124, dated July 14, 2010, for 

the Model BO105 helicopter, with a 

main rotor blade, P/N 105–15103, 105– 

15141, 105–15141V001, 105–15143, 

105–15150, 105–15150V001, 105– 

15152, 105–81013, 105–87214, 1120– 

15101, or 1120–15103, where the main 

rotor blade erosion protective shell was 

replaced between September 2006 and 

March 2010. Eurocopter also issued 

Emergency ASB No. ASB–BO105LS– 

10–12, dated July 14, 2010, for the 

Model BO105LS A–3 helicopter, with a 

main rotor blade, P/N 105–15141, where 

the main rotor blade erosion protective 

shell was replaced between September 

2006 and March 2010. Both Emergency 

ASBs exclude helicopters from this 

inspection if each main rotor blade was 

inspected at the last 600 flight hour 

inspection and no debonding was 

detected during the inspection. Both 

Emergency ASBs specified a one-time 

inspection of the main rotor blades 

within the next 50 flight hours to 

determine if debonding of the main 

rotor blade erosion protective shell has 

occurred. 

Eurocopter subsequently issued 

Emergency ASB No. ASB BO105–10– 

124, Revision 1, dated October 18, 2010, 

and Emergency ASB No. ASB– 

BO105LS–10–12, Revision 1, dated 

October 20, 2010. These service 

bulletins specify the same inspection 

requirements as the original service 

bulletins, but revise the inspection 

compliance time from 50 flight hours to 

10 flight hours. EASA classified these 

service bulletins as mandatory and 

issued EASA Emergency AD No. 2010– 

0216–E, dated October 21, 2010 

(corrected October 29, 2010) to ensure 

the continued airworthiness of these 

helicopters. 

Proposed Requirements of the 

Supplemental NPRM 

This proposed AD would require, 

within 50 hours TIS, inspecting for 

debonding by tap testing the abrasion 

strip of the leading edge of each main 

rotor blade. If there is debonding in any 

area of the abrasion strip, this proposed 

AD would require, before further flight, 

replacing the main rotor blade. 

Differences Between This Supplemental 

NPRM and the EASA AD 

The differences between this 

proposed AD and the EASA AD are: 

• The EASA AD allows compliance 

within ‘‘10 flight hours, or 4 flight 

cycles, or 4 weeks, whichever occurs 

first,’’ and this proposed AD would 

require compliance within 50 hours TIS. 

• The EASA AD allows you to replace 

the main rotor blade erosion protective 

shell if debonding is detected, and this 

proposed AD would require you to 

replace the main rotor blade with an 

airworthy main rotor blade if debonding 

is detected. 

• The EASA AD is applicable to the 

Model BO105 D helicopter; however, 

this proposed AD would not include 

this model because it does not have a 

type certificate in the U.S. 

Costs of Compliance 

We estimate that this AD would affect 

97 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this proposed AD. It would take about 

1.0 work-hour per helicopter to perform 

the inspection at an average labor rate 

of $85 per work-hour. Based on these 

figures, we estimate the cost of the 

inspection on U.S. operators would be 

$8,245 or $85 per helicopter. If there is 

debonding, we estimate that it would 

take about 2 work-hours to replace a 

main rotor blade and required parts 

would cost $114,182, for a total cost of 

$114,352 per blade. We have no way of 

determining how many operators will 

incur replacement costs. 

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 


wreier-aviles on DSK5TPTVN1PROD with 
Federal Register / Vol. 77, No. 244 / Wednesday, December 19, 2012 / Proposed Rules 75075 

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, 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); 

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. 

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 airworthiness 

directive (AD): 

Eurocopter Deutschland GmbH: Docket No. 

FAA–2011–1285; Directorate Identifier 

2010–SW–073–AD. 

(a) Applicability 

This AD applies to Model BO–105A, BO– 

105C, BO–105LS A–1, BO–105LS A–3, and 

BO–105S helicopters, with a main rotor 

blade, part number 105–15103, 105–15141, 

105–15141V001, 105–15143, 105–15150, 

105–15150V001, 105–15152, 105–81013, 

105–87214, 1120–15101, or 1120–15103; 

where the main rotor blade erosion protective 

shell (abrasion strip) was replaced between 

September 1, 2006 and March 31, 2010, 

inclusive; certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

debonding of a main rotor blade erosion 

protective shell (abrasion strip). This 

condition could result in loss of the abrasion 

strip and an unbalanced main rotor, high 

vibration, damage to the tail boom or tail 

rotor, and loss of control of the helicopter. 

(c) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(d) Required Actions 

(1) Within 50 hours time-in-service, 

inspect the main rotor blade for debonding of 

the erosion protective shell by tap testing the 

abrasion strip of the leading edge of each 

main rotor blade. 

(2) If the abrasion strip is debonding in any 

area, before further flight, replace the main 

rotor blade. 

(e) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Jim Grigg, 

Manager, Safety Management Group, 

Rotorcraft Directorate, FAA, 2601 Meacham 

Blvd., Fort Worth, Texas 76137; telephone 

(817) 222–5110; email jim.grigg@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(f) Additional Information 

(1) Eurocopter Emergency Alert Service 

Bulletin No. ASB BO105–10–124, Revision 1, 

dated October 18, 2010, and No. ASB– 

BO105LS–10–12, Revision 1, dated October 

20, 2010, which are not incorporated by 

reference, contain additional information 

about the subject of this AD. For this service 

information, contact American Eurocopter 

Corporation, 2701 N. Forum Drive, Grand 

Prairie, Texas 75052; telephone (972) 641– 

0000 or (800) 232–0323; fax (972) 641–3775; 

or at http://www.eurocopter.com/techpub. 

You may review a copy of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency Emergency 

AD No. 2010–0216–E, dated October 21, 2010 

(corrected October 29, 2010). 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6210, Main Rotor Blades. 

Issued in Fort Worth, Texas, on December 

12, 2012. 

S. Frances Cox, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–30588 Filed 12–18–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF JUSTICE 

Drug Enforcement Administration 

21 CFR Part 1308 

[Docket No. DEA–369] 

Schedules of Controlled Substances: 

Placement of Lorcaserin Into 

Schedule IV 

AGENCY: Drug Enforcement 

Administration, Department of Justice. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Drug Enforcement 

Administration (DEA) proposes placing 

the substance lorcaserin, including its 

salts, isomers, and salts of isomers 

whenever the existence of such salts, 

isomers, and salts of isomers is possible, 

into Schedule IV of the Controlled 

Substances Act (CSA). This proposed 

action is based on a recommendation 

from the Assistant Secretary for Health 

of the Department of Health and Human 

Services (HHS) and on an evaluation of 

all other relevant data by DEA. If 

finalized, this action would impose the 

regulatory controls and criminal 

sanctions of Schedule IV on the 

manufacture, distribution, dispensing, 

importation, exportation, and 

possession of lorcaserin and products 

containing lorcaserin. 

DATES: DEA will permit interested 

persons to file written comments on this 

proposal pursuant to 21 CFR 1308.43(g). 

Electronic comments must be submitted 

and written comments must be 

postmarked on or before January 18, 

2013. Commenters should be aware that 

the electronic Federal Docket 

Management System will not accept 

comments after midnight Eastern Time 

on the last day of the comment period. 


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