33176 Federal Register / Vol. 76, No. 110 / Wednesday, June 8, 2011 / Proposed Rules 

Note 1: Bombardier Service Bulletin 8–52– 

54 refers to Bombardier Series 100/300 

Modification Summary (Modsum) 8Q100859 

as an additional source of guidance for 

installing a hinge pin with a two-point 

attachment. Bombardier Service Bulletin 8– 

52–58 refers to Bombardier Series 100/300 

Modsum 8Q900267 as an additional source 

of guidance for reworking and installing the 

cockpit door, and reworking the lower hinge 

attachment to provide a downward-facing 

pin with a two-point attachment. 

Prior/Concurrent Requirements 

(h) Prior to or concurrently with the 

modification in paragraph (g) of this AD, do 

the applicable actions specified in Table 3 of 

this AD, according to a method approved by 

either the Manager, New York Aircraft 

Certification (ACO), FAA; or Transport 

Canada Civil Aviation (TCCA) (or its 

delegated agent). 

TABLE 3—BOMBARDIER SERVICE BULLETINS FOR REQUIREMENTS OF PARAGRAPH (H) OF THIS AD 

For airplanes affected by Bombardier Service 

Bulletin— That have these serial numbers— Do these actions— 

8–52–54, Revision A, dated November 5, 2004 003 through 407 inclusive, 409 through 412 

inclusive, and 414 through 433 inclusive.

Rework the cockpit door emergency release. 

.......................................................................... Install a new label regarding alternate release 

of the door. 

8–52–58, dated May 12, 2004 ........................... 452, 464, 490, 506, and 508 through 557 inclusive.Install the cockpit door. 

Note 2: Bombardier Service Bulletin 8–52– 

54, Revision A, dated November 5, 2004, 

refers to De Havilland Aircraft of Canada, 

Limited, Modification 8/2337 as an 

additional source of guidance for reworking 

the cockpit door emergency release; and 

Modification 8/3339 as additional source of 

guidance for installing a new label regarding 

alternate release of the door, on airplanes 

having serial numbers 003 through 407 

inclusive, 409 through 412 inclusive, and 414 

through 433 inclusive. 

Note 3: Bombardier Service Bulletin 8–52– 

58, dated May 12, 2004; and Revision A, 

dated November 17, 2006; refer to 

Bombardier Modsum 8Q200015, as an 

additional source of guidance for installing 

the cockpit door, on airplanes having serial 

numbers 452, 464, 490, 506, and 508 through 

557 inclusive. 

Actions Done In Accordance With Previous 

Revision of Service Bulletin 

(i) Actions done before July 18, 2006, in 

accordance with Bombardier Service Bulletin 

8–52–54, dated May 12, 2004, are acceptable 

for compliance with the corresponding 

requirements in paragraph (g) of this AD. 

New Requirements of This AD 

(j) For airplanes having S/N 452, 464, 490, 

506, and 508 through 557 inclusive, and on 

which the requirements in paragraph (g) of 

this AD have been done as of the effective 

date of this AD: Within 12 months after the 

effective date of this AD rework the cockpit 

door striker plate and replace the latch block, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–52–61, dated October 20, 2006. 

(k) For airplanes having S/Ns 452, 464, 

490, 506, and 508 through 557 inclusive, and 

on which the requirements in paragraph (g) 

of this AD have not been done as of the 

effective date of this AD: Prior to or 

concurrently with doing the modification 

required in paragraph (g) of this AD, rework 

the cockpit door striker plate and replace the 

latch block, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–52–61, dated October 20, 

2006. 

FAA AD Differences 

Note 4: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(l) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office, ANE–170, FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, New York 11590; 

telephone 516–228–7300; fax 516–794–5531. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(m) Refer to MCAI Canadian Airworthiness 

Directive CF–2005–34R1, dated August 15, 

2007; Bombardier Service Bulletin 8–52–54, 

Revision A, dated November 5, 2004; 

Bombardier Service Bulletin 8–52–58, 

Revision A, dated November 17, 2006; and 

Bombardier Service Bulletin 8–52–61, dated 

October 20, 2006; for related information. 

Issued in Renton, Washington, on May 27, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–14091 Filed 6–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0478; Directorate 

Identifier 2010–NM–138–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–103, B4–203, and B4–2C 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede an existing AD. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as: 

One operator reported a failure of the MLG 

[main landing gear] retraction actuator 

sliding rod. This incident occurred at a 

number of operating flight cycles lower than 

the limit value imposed by the MLG 

manufacturer. 

This condition, if not detected and 

corrected, results in undampened extension 

of the MLG, leading to higher than usual 

loads on the MLG attachment. Higher loads 


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Federal Register / Vol. 76, No. 110 / Wednesday, June 8, 2011 / Proposed Rules 33177 

affect the structural integrity of the MLG and 

could lead to MLG failure. 

* * * * * 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by July 25, 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 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For Airbus service information 

identified in this proposed AD, contact 

Airbus SAS–EAW (Airworthiness 

Office), 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone 

+33 5 61 93 36 96; fax +33 5 61 93 44 

51; e-mail account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. For Messier-Dowty 

service information identified in this 

proposed AD, contact Messier-Dowty: 

Messier Services Americas, Customer 

Support Center, 45360 Severn Way, 

Sterling, Virginia 20166–8910; 

telephone 703–450–8233; fax 703–404– 

1621; Internet https://techpubs.services/ 

messier-dowty.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 Operations office 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 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

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–2011–0478; Directorate Identifier 

2010–NM–138–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 

On November 29, 2007, we issued AD 

2007–25–15, Amendment 39–15297 (72 

FR 69601, December 10, 2007). That AD 

required actions intended to address an 

unsafe condition on all Airbus Model 

A300 series airplanes and all Airbus 

Model A300–600 series airplanes. 

Since we issued AD 2007–25–15, the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0102, 

dated June 8, 2010 (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

One operator reported a failure of the MLG 

[main landing gear] retraction actuator 

sliding rod. This incident occurred at a 

number of operating flight cycles lower than 

the limit value imposed by the MLG 

manufacturer. 

This condition, if not detected and 

corrected, results in undampened extension 

of the MLG, leading to higher than usual 

loads on the MLG attachment. Higher loads 

affect the structural integrity of the MLG and 

could lead to MLG failure. 

To address and correct this unsafe 

condition, EASA issued AD 2006–0075 (now 

at Revision 2) [which corresponds to FAA 

AD 2007–25–15] to require repetitive 

inspections of the retraction actuator sliding 

rod as installed on A300, A300–600 and 

A300–600ST aeroplanes and, depending on 

findings, repair or replacement of the affected 

parts. 

Since this event, studies have been 

performed by Airbus, the consequences of 

which are that for A300 aeroplanes, a new 

inspection program (new threshold and 

interval) has been established. 

For the reason described above, this new 

[EASA] AD retains the requirements of AD 

2006–0075R2, which is superseded and 

requires the accomplishment of the repetitive 

inspections and associated corrective actions 

at the new intervals. In addition, the Airbus 

A300 Aircraft Maintenance Manual (AMM) 

Chapter 12–22–32 (associated to 

Maintenance Planning Document (MPD) task 

321112–0505–1) has been revised to 

introduce a greasing action at the level of the 

pick-up jack fitting. Consequently, this AD 

also requires the repetitive lubrication task. 

For A300–600 and A300–600ST 

aeroplanes, the analyses have shown that, 

due to design differences, the loads induced 

on the MLG attachments are within 

acceptable margins. For that reason, this AD 

does not apply to those aeroplanes which 

were previously included in the applicability 

of EASA AD 2006–0075R2. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A300–32–0450, including 

Appendix 1, Revision 02, dated July 28, 

2009; and Task 321112–0505–1 of the 

A300 Maintenance Planning Document, 

Revision 30, dated April 1, 2010. 

Messier-Dowty has issued Special 

Inspection Service Bulletin 470–32–806, 

dated October 27, 2005. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. 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 or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 


jlentini on DSK4TPTVN1PROD with PROPOSALS
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We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 3 products of U.S. registry. 

We estimate that it would take about 

6 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$1,530, or $510 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 6 work-hours and require parts 

costing $0, for a cost of $510 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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 a regulatory 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 39–15297 (72 FR 

69601, December 10, 2007) and adding 

the following new AD: 

Airbus: Docket No. FAA–2011–0478; 

Directorate Identifier 2010–NM–138–AD. 

Comments Due Date 

(a) We must receive comments by July 25, 

2011. 

Affected ADs 

(b) This AD supersedes AD 2007–25–15, 

Amendment 39–15297. 

Applicability 

(c) This AD applies to all Airbus Model 

A300 B4–103, B4–203, and B4–2C airplanes; 

certificated in any category; equipped with 

MLG retraction actuator having part number 

(P/N) C23129 fitted with sliding rod P/N 

C69029–2 or C69029–3. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

One operator reported a failure of the MLG 

[main landing gear] retraction actuator 

sliding rod. This incident occurred at a 

number of operating flight cycles lower than 

the limit value imposed by the MLG 

manufacturer. 

This condition, if not detected and 

corrected, results in undampened extension 

of the MLG, leading to higher than usual 

loads on the MLG attachment. Higher loads 

affect the structural integrity of the MLG and 

could lead to MLG failure. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Revised Compliance Times for Inspection of 

MLG Retraction Actuator and Corrective 

Actions 

(g) At the applicable time specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD: 

Remove the MLG retraction actuator having 

P/N C23129 and do a detailed and high 

frequency eddy current inspection for defects 

that exceed the criteria defined in MessierDowty Special Inspection Service Bulletin 

470–32–806, dated October 27, 2005, of the 

retraction actuator sliding rods having P/N 

C69029–2 or C69029–3, in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–32–0450, 

Revision 02, dated July 28, 2009. 

(1) For airplanes on which the retraction 

actuator sliding rod has accumulated 12,000 

or fewer total flight cycles as of the effective 

date of this AD: Inspect at the later of the 

times specified in paragraphs (g)(1)(i) and 

(g)(1)(ii) of this AD. 

(i) Before the accumulation of 12,000 total 

flight cycles on the retraction actuator sliding 

rod. 

(ii) Within 2,000 flight cycles or 24 months 

after the effective date of this AD, whichever 

occurs first. 

(2) For airplanes on which the retraction 

actuator sliding rod has accumulated more 

than 12,000 total flight cycles, and 22,000 or 

fewer total flight cycles, as of the effective 

date of this AD: Inspect at the earliest of the 

times specified in paragraphs (g)(2)(i), 

(g)(2)(ii), and (g)(2)(iii) of this AD. 

(i) Before the accumulation of 23,000 total 

flight cycles on the retraction actuator sliding 

rod. 

(ii) Within 2,000 flight cycles after the 

effective date of this AD. 

(iii) Within 24 months after the effective 

date of this AD. 

(3) For airplanes on which the retraction 

actuator sliding rod has accumulated more 

than 22,000 total flight cycles as of the 

effective date of this AD: Inspect within 

1,000 flight cycles or 12 months after the 

effective date of this AD, whichever occurs 

first. 

(h) Thereafter, repeat the inspection 

required by paragraph (g) of this AD at 

intervals not to exceed 12,000 flight cycles. 

(i) If, during any inspection required by 

paragraph (g) or (h) of this AD, any defect is 

detected that exceeds the criteria defined in 

Messier-Dowty Special Inspection Service 

Bulletin 470–32–806, dated October 27, 2005, 

before further flight, replace the affected 

sliding rod with a serviceable unit in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–32–0450, Revision 02, dated 

July 28, 2009. 

(j) Before the accumulation of 32,000 flight 

cycles on any retraction actuator sliding rod, 

it must be replaced with a serviceable unit 


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in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–32–0450, Revision 02, dated 

July 28, 2009. Parts removed from an airplane 

as required by this paragraph must be 

returned to Messier-Dowty within 30 days 

after removing the part from the airplane. 

(k) As of the effective date of this AD, any 

MLG retraction actuator sliding rod having P/ 

N C69029–2 or C69029–3 that has 

accumulated less than 32,000 total flight 

cycles, may be installed on any airplane, 

provided that the inspections required by 

paragraphs (g) and (h) of this AD are 

accomplished at the compliance times 

specified in paragraphs (g) and (h) of this AD 

and all applicable replacements required by 

paragraphs (i) and (j) of this AD are done. 

Lubrication of the MLG Assembly 

(l) Within 1,500 flight hours after the 

effective date of this AD: Clean and lubricate 

the MLG assembly, in accordance with Task 

321112–0505–1 of the Airbus A300 

Maintenance Planning Document, Revision 

30, dated April 1, 2010. Repeat the cleaning 

and lubrication thereafter at intervals not to 

exceed 1,500 flight hours. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(m) Inspections accomplished before the 

effective date of this AD, in accordance with 

Airbus Service Bulletin A300–32–0450, 

dated December 1, 2005; or Airbus 

Mandatory Service Bulletin A300–32–0450, 

Revision 01, dated May 10, 2006; are 

acceptable for compliance with the 

corresponding requirements of this AD. 

FAA AD Differences 

Note 1 : This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(n) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. Information may be e-mailed to: 9- 

ANM–116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. AMOCs approved previously in 

accordance with AD 2007–25–15, 

amendment 39–15297, are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(o) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2010– 

0102, dated June 8, 2010; Airbus Mandatory 

Service Bulletin A300–32–0450, Revision 02, 

dated July 28, 2009; Messier-Dowty Special 

Inspection Service Bulletin 470–32–806, 

dated October 27, 2005; and Task 321112– 

0505–1 of the Airbus A300 Maintenance 

Planning Document, Revision 30, dated April 

1, 2010; for related information. 

Issued in Renton, Washington, on May 27, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–14094 Filed 6–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

CONSUMER PRODUCT SAFETY 

COMMISSION 

16 CFR 1460 

Petition Requesting Safeguards for 

Glass Fronts of Gas Vented Fireplaces 

AGENCY: U.S. Consumer Product Safety 

Commission. 

ACTION: Notice. 

SUMMARY: The U.S. Consumer Product 

Safety Commission (‘‘Commission’’ or 

‘‘we’’) has received a petition (CP 11–1) 

requesting that the Commission initiate 

rulemaking to require safeguards for 

glass fronts of gas vented fireplaces. We 

invite written comments concerning the 

petition. 

DATES: The Office of the Secretary must 

receive comments on the petition by 

August 8, 2011. 

ADDRESSES: You may submit comments, 

identified by Docket No. CPSC–2011– 

0028, by any of the following methods: 

Electronic Submissions 

Submit electronic comments in the 

following way: 

Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

To ensure timely processing of 

comments, the Commission is no longer 

accepting comments submitted by 

electronic mail (e-mail), except through 

http://www.regulations.gov. 

Written Submissions 

Submit written submissions in the 

following way: 

Mail/Hand delivery/Courier (for 

paper, disk, or CD–ROM submissions), 

preferably in five copies, to: Office of the 

Secretary, U.S. Consumer Product 

Safety Commission, Room 820, 4330 

East West Highway, Bethesda, MD 

20814; telephone (301) 504–7923. 

Instructions: All submissions received 

must include the agency name and 

petition number for this rulemaking. All 

comments received may be posted 

without change, including any personal 

identifiers, contact information, or other 

personal information provided, to: 

http://www.regulations.gov. Do not 

submit confidential business 

information, trade secret information, or 

other sensitive or protected information 

electronically. Such information should 

be submitted in writing. 

Docket: For access to the docket to 

read background documents or 

comments received, go to: http:// 

www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: 

Rockelle Hammond, Office of the 

Secretary, U.S. Consumer Product 

Safety Commission, Room 820, 4330 

East West Highway, Bethesda, MD 

20814; telephone (301) 504–6833. 

SUPPLEMENTARY INFORMATION: The 

Commission has received 

correspondence from Carol PollackNelson, Ph.D. (‘‘petitioner’’), dated May 

23, 2011, requesting that we initiate 

rulemaking to require safeguards for 

glass fronts of gas vented fireplaces. We 

are docketing this request as a petition 

under the Consumer Product Safety Act. 

15 U.S.C. 2056 and 2058. Petitioner 

notes that the industry standard for gas 

vented fireplace heaters allows glass 

fronts to reach temperatures of 500 

degrees Fahrenheit, and that these glass 

fronts are accessible to children. 

Petitioner claims that, according to the 

U.S. Consumer Product Safety 

Commission’s National Electronic Injury 

Surveillance System database (NEISS), 

more than 2,000 children ages 0–5 years 

suffered burn injuries on gas fireplaces 

in the period between 1999 and March 

2009. Petitioner believes the hazard 

posed by gas fireplaces is due to a 

combination of factors, ‘‘including the 

high surface temperature of the fireplace 

glass, the accessible location of the glass 

front, the attractiveness of fire to young 

children, and the lack of consumer 

awareness of the hazard.’’ Petitioner 

states that passive interventions, such as 

an ‘‘integral safety screen,’’ are needed to 

protect children. Petitioner asks the 

Commission to develop a mandatory 

standard for gas fireplaces that requires 


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