12710 Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Proposed Rules 

Order to specify that the Council will be 

composed of 16 members and their 

alternates rather than 14. Also, this rule 

would revise section 1218.40(a)(3) of the 

Order to specify three importers and 

alternates instead of one importer and 

alternate. In addition, this rule would 

revise section 1218.45 (a) of the Order 

to increase the minimum quorum level 

at Council meetings from seven to nine 

members. 

Nominations and appointments to the 

Council are conducted pursuant to 

sections 1218.40, 1218.41, and 1218.42 

of the Order. Appointments to the 

Council are made by the Secretary from 

a slate of nominated candidates. 

Pursuant to section 1218.41(d) of the 

Order, nominations for the importer, 

exporter, handler, and public member 

positions are made by the Council. 

Nominations are submitted to the 

Secretary for appointment to the 

Council. 

A 20-day comment period is provided 

to allow interested persons to respond 

to this proposal. Twenty days is deemed 

appropriate so that the proposed 

amendments, if adopted, may be 

implemented with the other importer 

seats up for appointment in spring 2010. 

All written comments received in 

response to this rule by the date 

specified would be considered prior to 

finalizing this action. 

List of Subjects in 7 CFR Part 1218 

Administrative practice and 

procedure, Advertising, Consumer 

information, Marketing agreements, 

Blueberry promotion, Reporting and 

recordkeeping requirements. 

For the reasons set forth in the 

preamble, 7 CFR part 1218 is proposed 

to be amended as follows: 

PART 1218—BLUEBERRY 

PROMOTION, RESEARCH, AND 

INFORMATION ORDER 

1. The authority citation for 7 CFR 

part 1218 continues to read as follows: 

Authority: 7 U.S.C. 7411–7425; 7 U.S.C. 

7401. 

2. In § 1218.40, paragraph (a) 

introductory text and paragraph (a)(3) 

are revised to read as follows: 

§ 1218.40 Establishment and membership. 

(a) Establishment of the U.S. 

Highbush Blueberry Council. There is 

hereby established a U.S. Highbush 

Blueberry Council, hereinafter called 

the Council, composed of no more than 

16 members and alternates, appointed 

by the Secretary from nominations as 

follows: 

* * * * * 

(3) Three importers and alternates. 

* * * * * 

3. Section 1218.45 paragraph (a) is 

revised to read as follows: 

§ 1218.45 Procedure. 

(a) At a Council meeting, it will be 

considered a quorum when a minimum 

of nine members, or their alternates 

serving in the absence, are present. 

* * * * * 

Dated: March 11, 2010. 

David R. Shipman, 

Acting Administrator, Agricultural Marketing 

Service. 

[FR Doc. 2010–5773 Filed 3–16–10; 8:45 am] 

BILLING CODE 3410–02–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0229; Directorate 

Identifier 2009–NM–115–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc., Model DHC–8–400 Series 

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. 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: Certain main landing gear 

components have experienced 

premature failure during certification 

testing. Revision has been made to the 

DHC–8–400 Maintenance Requirements 

Manual, Airworthiness Limitation 

Items, to incorporate the revised safe life 

limits for the main landing gear lock 

actuator assembly, retraction actuator 

assembly rod end and piston, and the 

upper bearing in the main landing gear 

shock strut assembly. Failure of these 

components could adversely affect the 

structural integrity of the main landing 

gear. 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 May 3, 2010. 

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 service information identified in 

this proposed AD, contact Bombardier, 

Inc., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; 

e-mail 

thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.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: 

Craig Yates, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7355; fax (516) 794–5531. 

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–2010–0229; Directorate Identifier 

2009–NM–115–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Proposed Rules 12711 

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 have lengthened the 30-day 

comment period for proposed ADs that 

address MCAI originated by aviation 

authorities of other countries to provide 

adequate time for interested parties to 

submit comments. The comment period 

for these proposed ADs is now typically 

45 days, which is consistent with the 

comment period for domestic transport 

ADs. 

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 

Transport Canada Civil Aviation, 

which is the aviation authority for 

Canada, has issued Canadian 

Airworthiness Directive CF–2009–17, 

dated April 22, 2009 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Certain main landing gear components 

have experienced premature failure during 

certification testing. Revision has been made 

to the DHC–8–400 Maintenance 

Requirements Manual, Airworthiness 

Limitation Items, to incorporate the revised 

safe life limits for the main landing gear lock 

actuator assembly, retraction actuator 

assembly rod end and piston, and the upper 

bearing in the main landing gear shock strut 

assembly. Failure of these components could 

adversely affect the structural integrity of the 

main landing gear. 

This [Canadian] directive is issued to 

ensure safe operation of the main landing 

gear during its service life. 

The corrective actions include 

revising the Airworthiness Limitations 

Section of the Instructions for 

Continued Airworthiness, replacing the 

upper bearing on certain airplanes, and 

replacing certain rod ends. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Relevant Service Information 

Bombardier has issued Temporary 

Revision ALI–82, dated August 15, 

2008; and Temporary Revision ALI–89, 

dated March 27, 2009; to Part 2, 

Airworthiness Limitation Items, of the 

Bombardier Dash 8 Q400 Maintenance 

Requirements Manual, PSM 1–84–7. 

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. 

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 62 products of U.S. registry. 

We also estimate that it would take 

about 22 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $18,588 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these costs. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$1,268,396, or $20,458 per product. 

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 adding 

the following new AD: 

Bombardier, Inc.: Docket No. FAA– 

2010–0229; Directorate Identifier 

2009–NM–115–AD. 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
12712 Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Proposed Rules 

Comments Due Date 

(a) We must receive comments by May 3, 

2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

Model DHC–8–400, –401, and –402 

airplanes, having serial numbers (S/Ns) 4001, 

4003, 4004, 4006, and 4008 through 4227 

inclusive, certificated in any category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (i) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued damage tolerance of the affected 

structure. The FAA has provided guidance 

for this determination in Advisory Circular 

(AC) 25.1529–1A. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Certain main landing gear components 

have experienced premature failure during 

certification testing. Revision has been made 

to the DHC–8–400 Maintenance 

Requirements Manual, Airworthiness 

Limitation Items (ALI), to incorporate the 

revised safe life limits for the main landing 

gear lock actuator assembly, retraction 

actuator assembly rod end and piston, and 

the upper bearing in the main landing gear 

shock strut assembly. Failure of these 

components could adversely affect the 

structural integrity of the main landing gear. 

This [Canadian] directive is issued to 

ensure safe operation of the main landing 

gear during its service life. 

The corrective actions include revising the 

Airworthiness Limitations Section (ALS) of 

the Instructions for Continued Airworthiness, 

replacing the upper bearing on certain 

airplanes, and replacing certain rod ends. 

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. 

Actions 

(g) For Model DHC–8–400, –401, and –402 

airplanes having S/Ns 4001, 4003, 4004, 

4006, and 4008 through 4210 inclusive: Do 

the actions specified in paragraphs (g)(1) and 

(g)(2) of this AD. 

(1) Within 60 days after the effective date 

of this AD: Revise the ALS of the Instructions 

for Continued Airworthiness by 

incorporating the revised structural safe life 

limit for the upper bearing having part 

number (P/N) 46114–1, as provided in 

Bombardier Temporary Revision (TR), ALI– 

82, dated August 15, 2008, to Part 2, 

Airworthiness Limitation Items, of the 

Bombardier Dash 8 Q400 Maintenance 

Requirements Manual (MRM), PSM 1–84–7. 

The initial compliance time for replacing the 

upper bearing is specified in paragraph (g)(2) 

of this AD. 

(2) Replace the upper bearing having P/N 

46114–1 with a new or serviceable upper 

bearing, in accordance with Goodrich 

Dressed Shock Strut Assembly Main Landing 

Gear Part No. 46100–29/–31/–33/–35/–37/– 

39/–41/–43/–45/–47/–49/–51/–53 and –55 

Component Maintenance Manual with 

Illustrated Parts List 32–11–03, Revision 11, 

dated August 22, 2008, at the applicable time 

specified in paragraphs (g)(2)(i), (g)(2)(ii), and 

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

(i) For airplanes having accumulated fewer 

than 15,000 total flight cycles as of the 

effective date of this AD: Replace prior to the 

accumulation of 15,000 total flight cycles. 

(ii) For airplanes having accumulated 

15,000 total flight cycles or more, but fewer 

than 20,000 total flight cycles, as of the 

effective date of this AD: Replace prior to the 

accumulation of 20,000 total flight cycles. 

(iii) For airplanes having accumulated 

20,000 total flight cycles or more as of the 

effective date of this AD: Replace before 

further flight. 

(h) For Model DHC–8–400, –401, and –402 

series airplanes having S/Ns 4001, 4003, 

4004, 4006, and 4008 through 4227 inclusive: 

Do the applicable actions specified in 

paragraphs (h)(1) and (h)(2) of this AD. 

(1) Within 60 days after the effective date 

of this AD: Revise the ALS of the Instructions 

for Continued Airworthiness to incorporate 

the revised safe life limits for the retraction 

actuator assembly rod end having P/N 

P3A2750 and P3A2750–1; retraction actuator 

assembly piston having P/N 46570–5; lock 

actuator cylinder assembly having P/N 

46601–1/–3; and lock actuator assembly 

having P/N 46600–1/–3/–5/–7; as provided in 

Bombardier TR ALI–89, dated March 27, 

2009, to Part 2, Airworthiness Limitation 

Items, of the Bombardier Dash 8 Q400 MRM, 

PSM 1–84–7. The initial compliance time for 

the replacement is specified in the TR, except 

as provided by paragraph (h)(2) of this AD. 

(2) For airplanes with a main landing gear 

retraction actuator assembly rod end that has 

accumulated more than 9,850 total flight 

cycles as of the effective date of this AD: 

Within 600 flight cycles after the effective 

date of this AD, replace any affected rod end 

having P/Ns P3A2750 and P3A2750–1 with 

a new or serviceable rod end, in accordance 

with Goodrich Dressed Shock Strut Assembly 

Main Landing Gear Part No. 46100–29/–31/ 

–33/–35/–37/–39/–41/–43/–45/–47/–49/–51/ 

–53 and –55 Component Maintenance 

Manual with Illustrated Parts List 32–11–03, 

Revision 11, dated August 22, 2008. 

(i) After accomplishing the revision 

specified in paragraph (g)(1) or (h)(1) of this 

AD, except as provided in paragraph (j) of 

this AD, no alternative replacement times 

may be approved for this part. 

Note 2: The ALI revisions required by 

paragraphs (g) and (h) of this AD may be 

done by inserting a copy of Bombardier TRs 

ALI–82 and ALI–89 into Part 2, 

Airworthiness Limitation Items, of the 

Bombardier Dash 8 Q400 MRM, PSM 1–84– 

7. When these TRs have been included in the 

general revision of the MRM, the general 

revision may be inserted into the MRM, 

provided the relevant information in the 

general revision is identical to that in 

Bombardier TRs ALI–82 and ALI–89. 

FAA AD Differences 

Note 3: This AD differs from the MCAI 

and/or service information as follows: The 

MCAI and service information do not contain 

replacement procedures for the upper 

bearings and rod ends. This AD requires 

replacing the upper bearings and rod ends in 

accordance with Goodrich Dressed Shock 

Strut Assembly Main Landing Gear Part No. 

46100–29/–31/–33/–35/–37/–39/–41/–43/ 

–45/–47/–49/–51/–53 and –55 Component 

Maintenance Manual with Illustrated Parts 

List 32–11–03, Revision 11, dated August 22, 

2008. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. Send information 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 

on any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards 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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

(4) Special Flight Permits: Special flight 

permits, as described in Section 21.197 and 

Section 21.199 of the Federal Aviation 

Regulations (14 CFR 21.197 and 21.199), are 

allowed, provided that the actions required 

in paragraph (h) of this AD have been 

accomplished. 

Related Information 

(k) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–17, dated April 22, 2009; 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
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Bombardier TR ALI–82, dated August 15, 

2008, and Bombardier TR ALI–89, dated 

March 27, 2009, to Part 2, Airworthiness 

Limitation Items, of the Bombardier Dash 8 

Q400 Maintenance Requirements Manual, 

PSM 1–84–7; and Goodrich Dressed Shock 

Strut Assembly Main Landing Gear Part No. 

46100–29/–31/–33/–35/–37/–39/–41/–43/– 

45/–47/–49/–51/–53 and –55 Component 

Maintenance Manual with Illustrated Parts 

List 32–11–03, Revision 11, dated August 22, 

2008; for related information. 

Issued in Renton, Washington, on March 9, 

2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–5858 Filed 3–16–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0272; Directorate 

Identifier 2010–CE–009–AD] 

RIN 2120–AA64 

Airworthiness Directives; AVOX 

Systems and B/E Aerospace Oxygen 

Cylinders as Installed on Various 14 

CFR Part 23 and CAR 3 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

AVOX Systems and B/E Aerospace 

oxygen cylinders, as installed on 

various 14 CFR part 23 or CAR 3 

airplanes. This proposed AD would 

require inspecting for and removing 

substandard oxygen cylinders from the 

airplane. This proposed AD was 

prompted by the reported rupture of a 

high-pressure gaseous oxygen cylinder, 

which had insufficient strength 

characteristics due to improper heat 

treatment. We are proposing this AD to 

prevent an oxygen cylinder from 

rupturing, which, depending on the 

location, could result in structural 

damage and rapid decompression of the 

airplane, damage to adjacent essential 

flight equipment, deprivation of the 

necessary oxygen supply for the 

flightcrew, and injury to cabin 

occupants or other support personnel. 

DATES: We must receive comments on 

this proposed AD by May 3, 2010. 

ADDRESSES: Use one of the following 

addresses to comment 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. 

For service information identified in 

this proposed AD, contact B/E 

Aerospace, Inc., Commercial Aircraft 

Products Group, RGA Department, 

10800 Pflumm Road, Lenexa, Kansas 

66215; telephone: (913) 338–9800; fax: 

(913) 338–8419; Internet: http:// 

www.beaerospace.com; and AVOX 

Systems, 225 Erie Street, Lancaster, New 

York 14086–9502; telephone: (716) 683– 

5100; fax: (716) 681–1089; Internet: 

http://www.avoxsys.com, as applicable. 

FOR FURTHER INFORMATION CONTACT: 

David Hirt, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4050; fax: (816) 

329–4090; e-mail: david.hirt@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under the 

ADDRESSES section. Include the docket 

number, ‘‘FAA–2010–0272; Directorate 

Identifier 2010–CE–009–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed 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 we receive 

concerning this proposed AD. 

Discussion 

During routine hydrostatic testing, a 

United States Department of 

Transportation Type 3HT–1850 highpressure gaseous oxygen cylinder 

ruptured under what would be 

considered normal operating conditions. 

Further investigation indicates that the 

cylinder had insufficient strength 

characteristics due to improper heat 

treatment. The improper heat treatment 

is limited to specific production 

batches, but the affected oxygen 

cylinders may be installed on various 14 

CFR part 23 or CAR 3 airplanes and 

aircraft certificated in other categories. 

The oxygen cylinders contain gaseous 

oxygen under high pressure. Rupture of 

an oxygen cylinder, depending on its 

location, could result in structural 

damage and rapid decompression of the 

airplane, damage to adjacent essential 

flight equipment, deprivation of the 

necessary oxygen supply for the 

flightcrew, and injury to cabin 

occupants or maintenance or other 

support personnel. 

Relevant Service Information 

We have reviewed B/E Aerospace 

Service Bulletin 176000–35–01, dated 

November 2, 2009; and Zodiac 

Aerospace AVOX Systems Inc. Service 

Bulletin 6084–34–35–01, Revision 1, 

dated December 9, 2009. 

The service information describes 

procedures for inspecting the oxygen 

cylinder to determine the serial number 

and for removing affected oxygen 

cylinders. 

FAA’s Determination and Requirements 

of the Proposed AD 

We are proposing this AD because we 

evaluated all information and 

determined the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. This proposed AD would 

require removing the affected oxygen 

cylinder from various 14 CFR part 23 or 

CAR 3 airplanes. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 10,000 airplanes in the 

U.S. registry. 

We estimate the following costs to do 

the proposed inspection: 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1