19716 Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules 

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: 

Airbus: Docket No. FAA–2011–0305; 

Directorate Identifier 2010–NM–186–AD. 

Comments Due Date 

(a) We must receive comments by May 23, 

2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A320– 

214, -232, and -233 airplanes, all 

manufacturer serial numbers on which 

Airbus modification 38310 has been 

accomplished in production; certificated in 

any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight Controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

* * * * * 

Results from a design review done by 

AIRBUS for documentation update have 

revealed that, on post-mod 38310 A320 

aeroplanes only, in case of emergency 

electrical configuration combined with a 

Green and Yellow hydraulic system loss, 

during landing phase (nose landing gear 

extended), the roll control would only be 

provided by the left aileron. 

This condition, if not corrected, could lead 

to an asymmetrical landing configuration, 

resulting in reduced control of the aeroplane. 

* * * * * 

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) Within 24 months after the effective 

date of this AD, modify the electrical 

installation of the elevator aileron computer 

and trimmable horizontal stabilizer motor 1 

power supply, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–27–1199, 

Revision 02, dated September 20, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Modifications done before the effective 

date of this AD in accordance with Airbus 

Service Bulletin A320–27–1199, Revision 01, 

dated March 4, 2010, are acceptable for 

compliance with the requirements of 

paragraph (g) 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 

(i) 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, sent it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; 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 

(j) Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2010–0149, dated July 21, 2010; and Airbus 

Mandatory Service Bulletin A320–27–1199, 

Revision 02, dated September 20, 2010; for 

related information. 

Issued in Renton, Washington, on March 

25, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–8409 Filed 4–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0306; Directorate 

Identifier 2010–NM–176–AD] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

SYSTEMS (Operations) Limited Model 

4101 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: 

* * * BAE Systems (Operations) Ltd has 

issued Revision 33 of the AMM [airplane 

maintenance manual] to amend Chapter 05– 

10–10 by adding one new Structurally 

Significant Item (SSI) and increasing the 

repeat inspection period on another SSI. 

Failure to comply with this revision 

constitutes an unsafe condition. 

The unsafe condition is failure of 

certain structurally significant items, 

including the main landing gear and the 

nose landing gear, which could result in 

reduced structural integrity of the 

airplane; and fuel vapor ignition 

sources, which could result in a fuel 

tank explosion and consequent loss of 

the airplane. 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 23, 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– 

mstockstill on DSKH9S0YB1PROD with PROPOSALS

Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules 19717 

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 BAE 

SYSTEMS (Operations) Limited, 

Customer Information Department, 

Prestwick International Airport, 

Ayrshire, KA9 2RW, Scotland, United 

Kingdom; telephone +44 1292 675207; 

fax +44 1292 675704; e-mail 

RApublications@baesystems.com; 

Internet http://www.baesystems.com/ 

Businesses/RegionalAircraft/index.htm. 

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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1175; 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–2011–0306; Directorate Identifier 

2010–NM–176–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 April 27, 2009, we issued AD 

2009–10–02, Amendment 39–15897 (74 

FR 21246, May 7, 2009). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2009–10–02, we 

have determined that new or more 

restrictive limitations are necessary to 

adequately address the identified unsafe 

condition. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued Airworthiness 

Directive 2010–0098, dated May 27, 

2010 (referred to after this as ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

The Jetstream J41 Aircraft Maintenance 

Manual (AMM), includes the following 

chapters: 

—05–10–10 ‘‘Airworthiness Limitations’’, 

—05–10–20 ‘‘Certification Maintenance 

Requirements’’, and, 

—05–10–30 ‘‘Critical Design Configuration 

Control Limitations (CDCCL)—Fuel 

System’’ 

Compliance with these chapters has been 

identified as mandatory actions for continued 

airworthiness and EASA AD 2009–0052 was 

issued to require operators to comply with 

those instructions. 

Since the issuance of that AD, BAE 

Systems (Operations) Ltd has issued Revision 

33 of the AMM to amend Chapter 05–10–10 

by adding one new Structurally Significant 

Item (SSI) and increasing the repeat 

inspection period on another SSI. Failure to 

comply with this revision constitutes an 

unsafe condition. 

For the reasons described above, this 

[EASA] AD, which supersedes EASA AD 

2009–0052, requires the implementation of 

the new or more restrictive maintenance 

requirements and/or airworthiness 

limitations as specified in the defined parts 

of Chapter 05 of the AMM at Revision 33. 

The unsafe condition is failure of 

certain structurally significant items, 

including the main landing gear and the 

nose landing gear, which could result in 

reduced structural integrity of the 

airplane; and fuel vapor ignition 

sources, which could result in a fuel 

tank explosion and consequent loss of 

the airplane. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

BAE SYSTEMS (Operations) Limited 

has issued Subjects 05–10–00, 05–10– 

10, 05–10–20, and 05–10–30 of Chapter 

05 of Jetstream Series 4100 Aircraft 

Maintenance Manual, Revision 33, 

dated February 15, 2010. 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 3 products of U.S. registry. 

The actions that are required by AD 

2009–10–02 and retained in this 

proposed AD take about 1 work-hour 

per product, at an average labor rate of 

$85 per work hour. Based on these 

figures, the estimated cost of the 

currently required actions is $85 per 

product. 

We estimate that it would take about 

1 additional work-hour 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 $255, or $85 per product. 

mstockstill on DSKH9S0YB1PROD with PROPOSALS

19718 Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules 

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 39–15897 (74 FR 

21246, May 7, 2009) and adding the 

following new AD: 

BAE SYSTEMS (Operations) Limited: Docket 

No. FAA–2011–0306; Directorate 

Identifier 2010–NM–176–AD. 

Comments Due Date 

(a) We must receive comments by May 23, 

2011. 

Affected ADs 

(b) This AD supersedes AD 2009–10–02, 

Amendment 39–15897. 

Applicability 

(c) This AD applies to all BAE SYSTEMS 

(Operations) Limited Model 4101 airplanes, 

certificated in any category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new actions (e.g., inspections) and/ 

or Critical Design Configuration Control 

Limitations (CDCCLs). Compliance with 

these actions and/or CDCCLs is required by 

14 CFR 91.403(c). For airplanes that have 

been previously modified, altered, or 

repaired in the areas addressed by this AD, 

the operator may not be able to accomplish 

the actions described in the revisions. In this 

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

the operator must request approval of an 

alternative method of compliance (AMOC) 

according to paragraph (k) of this AD. The 

request should include a description of 

changes to the required actions that will 

ensure the continued operational safety of 

the airplane. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 05. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

* * * BAE Systems (Operations) Ltd has 

issued Revision 33 of the AMM [airplane 

maintenance manual] to amend Chapter 05– 

10–10 by adding one new Structurally 

Significant Item (SSI) and increasing the 

repeat inspection period on another SSI. 

Failure to comply with this revision 

constitutes an unsafe condition. 

The unsafe condition is failure of certain 

structurally significant items, including the 

main landing gear and the nose landing gear, 

which could result in reduced structural 

integrity of the airplane; and fuel vapor 

ignition sources, which could result in a fuel 

tank explosion and consequent loss of the 

airplane. 

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 2009– 

10–02 

Revise Airworthiness Limitations Section 

(AWL) of Instructions for Continued 

Airworthiness 

(g) Within 90 days after June 11, 2009 (the 

effective date of AD 2009–10–02): Revise the 

AWL section of the Instructions for 

Continued Airworthiness by incorporating 

the instructions of Subjects 05–10–10, 

‘‘Airworthiness Limitations,’’ 05–10–20, 

‘‘Certification Maintenance Requirements,’’ 

and 05–10–30, ‘‘Critical Design Configuration 

Control Limitations (CDCCL)—Fuel System,’’ 

of the BAE Systems (Operations) Limited 

Jetstream Series 4100 Airplane Maintenance 

Manual (AMM), Revision 31, dated February 

15, 2009. Thereafter, except as provided in 

paragraph (k) of this AD, no alternative 

replacement times or inspection intervals 

may be approved for any affected component. 

Doing the actions required by paragraph (i) 

of this AD terminates the requirements of this 

paragraph. 

(h) Where paragraph 2.A.(2) of Subject 05– 

10–10 of the BAE Systems (Operations) 

Limited Jetstream Series 4100 AMM, 

Revision 31, dated February 15, 2009, 

specifies that certain landing gear units ‘‘must 

be removed before 31st March 2008,’’ this AD 

requires compliance within 60 days after 

June 11, 2009. 

New Requirements of This AD 

Maintenance Program Revision 

(i) Within 90 days after the effective date 

of this AD: Revise the maintenance program 

by incorporating Subject 05–10–10, 

‘‘Airworthiness Limitations Description and 

Operation’’; Subject 05–10–20, ‘‘Certification 

Maintenance Requirements Description and 

Operation’’; and Subject 05–10–30, ‘‘Critical 

Design Configuration Control Limitations 

(CDCCL)—Fuel System Description and 

Operation’’; of Chapter 05 of the BAE Systems 

(Operations) Limited Jetstream Series 4100 

AMM, Revision 33, dated February 15, 2010. 

Doing the actions required by this paragraph 

terminates the requirements of paragraph (g) 

of this AD. The initial compliance times for 

the tasks are at the applicable times specified 

in paragraphs (i)(1), (i)(2), and (i)(3) of this 

AD. 

(1) For replacement tasks of life limited 

parts specified in Subject 05–10–10, 

‘‘Airworthiness Limitations Description and 

Operation,’’ of Chapter 05 of the BAE Systems 

(Operations) Limited Jetstream Series 4100 

AMM, Revision 33, dated February 15, 2010: 

Prior to the applicable flight cycles (landings) 

or flight hours (flying hours) on the part 

specified in the ‘‘Mandatory Life Limits’’ 

column in Subject 05–10–10, or within 90 

days after the effective date of this AD, 

whichever occurs later. 

(2) For structurally significant item tasks 

specified in Subject 05–10–10, 

‘‘Airworthiness Limitations Description and 

Operation,’’ of Chapter 05 of the BAE Systems 

(Operations) Limited Jetstream Series 4100 

AMM, Revision 33, dated February 15, 2010: 

Prior to the accumulation of the applicable 

flight cycles specified in the ‘‘Initial 

Inspection’’ column in Subject 05–10–10, or 

within 90 days after the effective date of this 

AD, whichever occurs later. 

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Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules 19719 

(3) For certification maintenance 

requirements tasks specified in Subject 05– 

10–20, ‘‘Certification Maintenance 

Requirements Description and Operation,’’ of 

Chapter 05 of the BAE Systems (Operations) 

Limited Jetstream Series 4100 AMM, 

Revision 33, dated February 15, 2010: Prior 

to the accumulation of the applicable flight 

hours specified in the ‘‘Time Between 

Checks’’ column in Subject 05–10–20, or 

within 90 days after the effective date of this 

AD, whichever occurs later; except for tasks 

that specify ‘‘first flight of the day’’ in the 

‘‘Time Between Checks’’ column in Subject 

05–10–20, the initial compliance time is the 

first flight of the next day after doing the 

revision required by paragraph (i) of this AD, 

or within 90 days after the effective date of 

this AD, whichever occurs later. 

No Alternative Actions, Intervals, and/or 

Critical Design Configuration Control 

Limitations (CDCCLs) 

(j) After accomplishing the revision 

required by paragraph (i) of this AD, no 

alternative actions (e.g., inspections), 

intervals, and/or CDCCLs may be used unless 

the actions, intervals, and/or CDCCLs are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: 

Although EASA Airworthiness Directive 

2010–0098, dated May 27, 2010, specifies 

both revising the maintenance program to 

include limitations, and doing certain 

repetitive actions (e.g., inspections) and/or 

maintaining Critical Design Configuration 

Control Limitations (CDCCLs), this AD only 

requires the revision. Requiring a revision of 

the maintenance program, rather than 

requiring individual repetitive actions and/or 

maintaining CDCCLs, requires operators to 

record AD compliance only at the time the 

revision is made. Repetitive actions and/or 

maintaining CDCCLs specified in the 

airworthiness limitations must be complied 

with in accordance with 14 CFR 91.403(c). 

Other FAA AD Provisions 

(k) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1175; fax (425) 

227–1149. 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 

(l) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2010–0098, dated 

May 27, 2010; Subjects 05–10–10, 

‘‘Airworthiness Limitations,’’ 05–10–20, 

‘‘Certification Maintenance Requirements,’’ 

and 05–10–30, ‘‘Critical Design Configuration 

Control Limitations (CDCCL)—Fuel System,’’ 

of the BAE Systems (Operations) Limited 

Jetstream Series 4100 AMM, Revision 31, 

dated February 15, 2009; and Subjects 05– 

10–00, ‘‘Time Limits Description and 

Operation,’’ 05–10–10, ‘‘Airworthiness 

Limitations Description and Operation,’’ 05– 

10–20, ‘‘Certification Maintenance 

Requirements Description and Operation,’’ 

and 05–10–30, ‘‘Critical Design Configuration 

Control Limitations (CDCCL)—Fuel System 

Description and Operation,’’ of Chapter 05 of 

the BAE Systems (Operations) Limited 

Jetstream Series 4100 AMM, Revision 33, 

dated February 15, 2010; for related 

information. 

Issued in Renton, Washington, on March 

30, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–8410 Filed 4–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0307; Directorate 

Identifier 2010–NM–111–AD] 

RIN 2120–AA64 

Airworthiness Directives; Saab AB, 

Saab Aerosystems Model SAAB 2000 

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: 

* * * * * 

A report has been received of an incident 

where one of the two bolts attaching the 

actuator mounting bracket to the MLG [main 

landing gear] Shock Strut was found loose, 

leading to failure of the other attachment 

bolt, subsequently resulting in failure of the 

bracket. 

This condition, if not detected and 

corrected, could prevent the MLG to extend 

to the full down-and-locked position, 

possibly resulting in MLG collapse upon 

landing or during roll-out, with consequent 

damage to the aeroplane and injury to the 

occupants. 

* * * * * 

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 23, 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 service information identified in 

this proposed AD, contact Saab AB, 

Saab Aerosystems, SE–581 88, 

Linko ̈ping, Sweden; telephone +46 13 

18 5591; fax +46 13 18 4874; e-mail 

saab2000.techsupport@saabgroup.com; 

Internet http://www.saabgroup.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 

mstockstill on DSKH9S0YB1PROD with PROPOSALS