64854 Federal Register / Vol. 76, No. 202 / Wednesday, October 19, 2011 / Proposed Rules 

TABLE 1—IRN TASK REVISION—Continued 

Model— IRN #— Initial compliance time— Chapter 04 of these documents— 

Model 40, 45 ...... N3220103, N3220104, N3220105, and 

N3220106.

Before the accumulation of 17,000 total 

landings on the component.

Bombardier Learjet 45 Maintenance 

Manual MM–104, Revision 53, dated 

January 10, 2011; or Bombardier 

Learjet 40 Maintenance Manual MM– 

105, Revision 21, dated January 10, 

2011; as applicable. 

Model 45 ............ N5710147, N5710171, and N5710173 .. Before the accumulation of 6,500 total 

flight hours.

Bombardier Learjet 45 Maintenance 

Manual MM–104, Revision 53, dated 

January 10, 2011. 

Model 45 ............ N5710175 ............................................... Before the accumulation of 6,900 total 

flight hours.

Bombardier Learjet 45 Maintenance 

Manual MM–104, Revision 53, dated 

January 10, 2011. 

Model 45 ............ N5710177 ............................................... Before the accumulation of 7,000 total 

flight hours.

Bombardier Learjet 45 Maintenance 

Manual MM–104, Revision 53, dated 

January 10, 2011. 

No Alternative Intervals 

(h) After accomplishing the revisions 

required by paragraphs (g) of this AD, no 

alternative IRN task or IRN task interval may 

be used unless the IRN task or IRN task 

interval is approved as an AMOC in 

accordance with the procedures specified in 

paragraph (i)(1) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Wichita Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) 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. 

Related Information 

(j) For more information about this AD, 

contact William Griffith, Aerospace Engineer, 

Airframe Branch, ACE–118W, FAA, Wichita 

Aircraft Certification Office, 1801 Airport 

Road, Room 100, Mid-Continent Airport, 

Wichita, Kansas 67209; phone: 316–946– 

4116; fax: 316–946–4107; e-mail: 

William.E.Griffith@faa.gov. 

(k) For service information identified in 

this AD, contact Learjet, Inc., One Learjet 

Way, Wichita, Kansas 67209–2942; telephone 

316–946–2000; fax 316–946–2220; e-mail 

ac.ict@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. 

Issued in Renton, Washington, on October 

5, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–27010 Filed 10–18–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1087; Directorate 

Identifier 2011–NM–032–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318, A319, A320, and A321 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 that would 

supersede two existing ADs. 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: 

Following in-service experience, analyses 

of the failure to follow procedure or heed 

existing cockpit cues were conducted to 

assess the consequences of mismanagement 

of thrust levers during landing. 

The investigation results identified the 

need for improvements in the identification 

of throttle mis-positioning and so providing 

further opportunity for the flight crew to 

identify an incorrect thrust lever 

configuration and to correct this. * * * In 

addition, the analysis of the thrust lever 

management issue shows two categories of 

scenarios that could lead to thrust asymmetry 

during landing with controllability and 

deceleration consequences [.] 

* * * * * 

These thrust asymmetry conditions, if not 

corrected, could result in loss of control of 

the aeroplane during landing. 

* * * * * 

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 December 5, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus, 

Airworthiness Office—EAS, 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.airworth-eas@airbus.com; 

Internet http://www.airbus.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. 


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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: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2141; 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–2011–1087; Directorate Identifier 

2011–NM–032–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 October 23, 1997, we issued AD 

97–22–13, Amendment 39–10185 (62 

FR 58891, October 31, 1997) (which 

corresponds to Direction Ge ́ne ́rale de 

l’Aviation Civile (DGAC) AD 96–079– 

079(B), dated April 10, 1996, and which 

supersedes FAA AD 94–20–02, 

Amendment 39–9030 (59 FR 48563, 

September 22, 1994)); and on May 10, 

2002, we issued AD 2002–10–06, 

Amendment 39–12752 (67 FR 35425, 

May 20, 2002) (which corresponds to 

DGAC AD 2000–320–147(B), dated July 

26, 2000). AD 97–22–13 required a 

limitations section revision to the 

airplane flight manual and the 

installation of a new flight warning 

computer (FWC). AD 2002–10–06 

required the replacement of the FWC. 

Since we issued AD 97–22–13, 

Amendment 39–10185 (62 FR 58891, 

October 31, 1997) and AD 2002–10–06, 

Amendment 39–12752 (67 FR 35425, 

May 20, 2002), we have determined in 

consultation with the European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Community, that 

additional actions are necessary to 

address the unsafe condition. EASA has 

issued EASA Airworthiness Directive 

2011–0001, dated January 10, 2011 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

Following in-service experience, analyses 

of the failure to follow procedure or heed 

existing cockpit cues were conducted to 

assess the consequences of mismanagement 

of thrust levers during landing. 

The investigation results identified the 

need for improvements in the identification 

of throttle mis-positioning and so providing 

further opportunity for the flight crew to 

identify an incorrect thrust lever 

configuration and to correct this. For the 

A320 family of aeroplanes this being IDLE or 

REVERSE, which is necessary to enable 

ground spoiler (G/S) extension and autobrake (A/BRK) functions. In addition, the 

analysis of the thrust lever management issue 

shows two categories of scenarios that could 

lead to thrust asymmetry during landing with 

controllability and deceleration 

consequences: 

—One thrust lever kept in forward thrust 

when the other is put in IDLE or REVERSE. 

This has been seen in cases of dispatch 

with one thrust reverser inoperative; and 

—One thrust lever moved in forward position 

after landing, usually when bringing the 

thrust lever back from REVERSE to IDLE. 

These thrust asymmetry conditions, if not 

corrected, could result in loss of control of 

the aeroplane during landing. 

This [EASA] AD supersedes DGAC France 

AD 94–211–059(B) R2 and 96–079–079(B) 

[which corresponds to FAA AD 97–22–13 (62 

FR 58891, October 31, 1997], mandating 

Aircraft Flight Manual Temporary Revision 

reference 9.99.99/20 and the installation of 

FWC P/N 350E017248685 (H1D2) as 

terminating action for both ADs. 

This [EASA] AD retains the requirements 

of DGAC France AD 2000–320–147(B) [which 

corresponds to FAA AD 2002–10–06 (67 FR 

35425, May 20, 2002)], which is also 

superseded, which required the installation 

of FWC P/N 350E017271616 (H1E2). 

For the reasons described above, this 

[EASA] AD requires the replacement of both 

FWC units with minimum FWC P/N 

350E053020909 (H2F5) units, introducing 

‘‘Enhanced RETARD’’ logic. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A320–31–1106, Revision 05, 

dated September 21, 2000; Service 

Bulletin A320–31–1141, Revision 04, 

dated February 14, 2002; Service 

Bulletin A320–31–1334, Revision 04, 

including Appendix 01, dated 

September 12, 2011. 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 729 products of U.S. 

registry. 

The actions that are required by AD 

2002–10–06 Amendment 39–12752 (67 

FR 35425, May 20, 2002) and retained 

in this proposed AD take about 7 workhours per product, at an average labor 

rate of $85 per work-hour. Required 

parts would cost about $0 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 parts. 

As we do not control warranty coverage 

for affected parties, some parties may 

incur costs higher than estimated here. 

Based on these figures, the estimated 

cost of the currently required actions is 

$595 per product. 


srobinson on DSK4SPTVN1PROD with PROPOSALS
64856 Federal Register / Vol. 76, No. 202 / Wednesday, October 19, 2011 / Proposed Rules 

We estimate that it would take about 

4 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Required parts 

would cost about $0 per product. Based 

on these figures, we estimate the cost of 

the proposed AD on U.S. operators to be 

$247,860, or $340 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 

removing Amendment 39–10185 (62 FR 

58891, October 31, 1997) and 

Amendment 39–12752, (67 FR 35425, 

May 20, 2002) and adding the following 

new AD: 

Airbus: Docket No. FAA–2011–1087; 

Directorate Identifier 2011–NM–032–AD. 

Comments Due Date 

(a) We must receive comments by 

December 5, 2011. 

Affected ADs 

(b) This AD supersedes AD 97–22–13, 

Amendment 39–10185 (62 FR 58891, October 

31, 1997); and AD 2002–10–06, Amendment 

39–12752 (67 FR 35425, May 20, 2002). 

Applicability 

(c) This AD applies to Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–111, 

–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes; 

certificated in any category; all serial 

numbers; if equipped with a flight warning 

computer (FWC) with a part number (P/N) 

listed in table 1 of this AD. 

TABLE 1—LIST OF FWC PART

NUMBERS AFFECTED BY THIS AD 

FWC Part No. 

350E017238484 (H1D1) 

350E016187171 (C5) 

350E017248685 (H1D2) 

350E017251414 (H1E1) 

350E017271616 (H1E2) 

350E018291818 (H1E3CJ) 

350E018301919 (H1E3P) 

350E018312020 (H1E3Q) 

350E053020202 (H2E2) 

350E053020303 (H2E3) 

350E053020404 (H2E4) 

350E053020606 (H2F2) 

350E053020707 (H2F3) 

350E053021010 (H2F3P) 

350E053020808 (H2F4) 

Subject 

(d) Air Transport Association (ATA) of 

America Code 31: Indicating and Recording 

Systems. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Following in-service experience, analyses 

of the failure to follow procedure or heed 

existing cockpit cues were conducted to 

assess the consequences of mismanagement 

of thrust levers during landing. 

The investigation results identified the 

need for improvements in the identification 

of throttle mis-positioning and so providing 

further opportunity for the flight crew to 

identify an incorrect thrust lever 

configuration and to correct this. * * * In 

addition, the analysis of the thrust lever 

management issue shows two categories of 

scenarios that could lead to thrust asymmetry 

during landing with controllability and 

deceleration consequences: 

* * * * * 

These thrust asymmetry conditions, if not 

corrected, could result in loss of control of 

the aeroplane during landing. 

* * * * * 

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. 

Restatement of Requirements of AD 2002– 

10–06, Amendment 39–12752 (67 FR 35425, 

May 20, 2002), With New Optional Method 

of Compliance 

Modification 

(g) For Model A319, A320, and A321 series 

airplanes without Airbus modification 26017: 

Within 18 months after June 24, 2002 (the 

effective date of AD 2002–10–06, 

Amendment 39–12752 (67 FR 35425, May 20, 

2002)), replace the flight warning computers 

(FWCs) in accordance with Airbus Service 

Bulletin A320–31–1106, Revision 04, dated 

December 21, 1999; or Revision 05, dated 

September 21, 2000. 

Note 1: FWC replacement accomplished 

prior to June 24, 2002, in accordance with 

Airbus Service Bulletin A320–31–1106, 

dated January 3, 1997; Revision 01, dated 

April 16, 1997; Revision 02, dated January 

20, 1998; or Revision 03, dated July 9, 1999; 

is acceptable for compliance with the 

requirements of paragraph (g) of this AD. 

Optional Method of Compliance 

(h) Installation of a FWC standard in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

31–1141, Revision 04, dated February 14, 

2002, is an acceptable method of compliance 

with the replacement required by paragraph 

(g) of this AD. 

New Requirements of This AD 

Flight Warning Computer Replacement 

(i) Within 48 months after the effective 

date of this AD: Replace both FWC units with 

FWC part number 350E053020909, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

31–1334, Revision 04, including Appendix 

01, dated September 12, 2011. 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 202 / Wednesday, October 19, 2011 / Proposed Rules 64857 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(j) For all airplanes, except for Model A319 

series airplanes on which modifications 

28238, 28162, and 28342 have been 

incorporated, replacing both FWCs in 

accordance with Airbus Service Bulletin 

A320–31–1334, dated July 30, 2009; Revision 

01, dated December 14, 2009; or Revision 02, 

dated September 13, 2010; or Revision 03, 

dated March 15, 2011; before the effective 

date of this AD is acceptable for compliance 

with the corresponding replacement required 

by paragraph (i) of this AD. 

(k) Replacing both FWCs in accordance 

with Airbus Service Bulletin A320–31–1141, 

dated March 6, 2000; Revision 01, dated May 

25, 2000; Revision 02, dated January 22, 

2001; or Revision 03, dated June 12, 2001; 

before the effective date of this AD is 

acceptable for compliance with the 

corresponding installation specified in 

paragraph (h) of this AD. 

Parts Installation 

(l) As of the effective date of this AD, and 

after accomplishing the actions in paragraph 

(i) of this AD, no person may install a FWC 

with a P/N listed in table 1 of this AD on any 

airplane. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(m) 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: 

Tim Dulin, Aerospace Engineer, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

425–227–2141; 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. 

(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 

(n) Refer to MCAI EASA Airworthiness 

Directive 2011–0001, dated January 10, 2011; 

Airbus Service Bulletin A320–31–1106, 

Revision 04, dated December 21, 1999; 

Airbus Mandatory Service Bulletin A320–31– 

1106, Revision 05, dated September 21, 2000; 

Airbus Service Bulletin A320–31–1141, 

Revision 04, dated February 14, 2002; and 

Airbus Service Bulletin A320–31–1334, 

Revision 04, including Appendix 01, dated 

September 12, 2011; for related information. 

Issued in Renton, Washington, on October 

11, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–27026 Filed 10–18–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1089; Directorate 

Identifier 2011–NM–110–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model BD–100–1A10 (Challenger 

300) 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: 

During a routine inspection, deformation 

was found at the neck of the pressure 

regulator body on the oxygen Cylinder and 

Regulator Assemblies (CRA) of a BD–700– 

1A11 aeroplane. 

An investigation by the vendor * * * 

revealed that the deformation was attributed 

to two (2) batches of raw material that did not 

meet the required tensile strength. This may 

cause elongation of the pressure regulator 

neck, which could result in rupture of the 

oxygen cylinder and in the case of cabin 

depressurization, oxygen not being available 

when required. 

* * * * * 

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 December 5, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC, 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.crj@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: 

Cesar Gomez, 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– 

7318; 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–2011–1089; Directorate Identifier 

2011–NM–110–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 


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