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

19720 Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Shahram Daneshmandi, Aerospace 

Engineer, International Branch, ANM– 

116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1112; 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–2011–0307; Directorate Identifier 

2010–NM–111–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0069, 

dated April 14, 2010 (referred to after 

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

condition for the specified products. 

The MCAI states: 

A report has been received of an incident 

where one of the two bolts attaching the 

actuator mounting bracket to the MLG 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. 

To correct this potentially unsafe 

condition, SAAB has published Service 

Bulletin (SB) 2000–32–073, describing a 

[detailed] inspection of the attachment bolts 

[and nuts] to detect any loose bolts [and 

nuts], follow-up corrective action(s), 

depending on findings, and the installation 

of the correct number of washers. 

For the reasons described above, this EASA 

AD requires the accomplishment of the 

actions described in SAAB SB 2000–32–073. 

Required actions, if any loose parts are 

found, include replacing the bolt with a 

new bolt, and then doing a detailed 

inspection of the bolts for uniform or 

fretting corrosion; a detailed inspection 

of the actuator mounting bracket and 

shock struts for damage, cracks, and 

signs of corrosion; and doing corrective 

actions if necessary. Corrective actions 

include removing corrosion, replacing 

affected bolts with new bolts, tightening 

loose nuts, repairing, and installing the 

correct number of washers. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Relevant Service Information 

Saab has issued Service Bulletin 

2000–32–073, Revision 01, dated 

October 20, 2009. 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 8 products of U.S. registry. 

We also estimate that it would take 

about 1 work-hour 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 $1,039 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, we estimate the cost of the 

proposed AD on U.S. operators to be 

$8,992, or $1,124 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 10 work-hours and require parts 

costing $1,039, for a cost of $1,889 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 

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Federal Register / Vol. 76, No. 68 / Friday, April 8, 2011 / Proposed Rules 19721 

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: 

Saab AB, Saab Aerosystems: Docket No. 

FAA–2011–0307; Directorate Identifier 

2010–NM–111–AD. 

Comments Due Date 

(a) We must receive comments by May 23, 

2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Saab AB, Saab 

Aerosystems Model SAAB 2000 airplanes, 

certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

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. 

* * * * * 

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. 

Inspection 

(g) Within 12 months after the effective 

date of this AD, do a detailed inspection for 

any loose top bolt and nut of the shock strut 

actuator mounting bracket of both the lefthand and right-hand main landing gear 

(MLG), in accordance with paragraph 2.B. of 

the Accomplishment Instructions of Saab 

Service Bulletin 2000–32–073, Revision 01, 

dated October 20, 2009. 

Corrective Action 

(h) If any loose bolt or nut is found during 

the inspection required by paragraph (g) of 

this AD, before further flight, replace the bolt 

with a new bolt and accomplish paragraphs 

(h)(1) and (h)(2) of this AD, in accordance 

with paragraph 2.C. of the Accomplishment 

Instructions Saab Service Bulletin 2000–32– 

073, Revision 01, dated October 20, 2009. 

(1) Do a detailed inspection of the bottom 

bolts for uniform or fretting corrosion. If any 

corrosion is found, before further flight, 

accomplish all applicable corrective actions, 

in accordance with the Accomplishment 

Instructions of Saab Service Bulletin 2000– 

32–073, Revision 01, dated October 20, 2009. 

(2) Do a detailed inspection for damage, 

cracks, and other signs of deterioration of the 

actuator mounting bracket and shock strut. If 

signs of damage, cracks, or other signs of 

deterioration are found on the actuator 

mounting bracket or the shock strut, before 

further flight, repair in accordance with a 

method approved by the FAA or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

(i) Within 12 months after the effective 

date of this AD, unless already accomplished 

in accordance with paragraph (h) of this AD, 

install the correct number of washers for both 

the top and bottom bolts of the shock strut 

actuator mounting bracket of both MLG, in 

accordance with paragraph 2.C.of the 

Accomplishment Instructions of Saab Service 

Bulletin 2000–32–073, Revision 01, dated 

October 20, 2009. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(j) Actions accomplished before the 

effective date of this AD in accordance with 

Saab Service Bulletin 2000–32–073, dated 

June 26, 2009, are considered acceptable for 

compliance with the corresponding actions 

specified in 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 

(k) 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: 

Shahram Daneshmandi, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1112; 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 

(l) Refer to MCAI EASA Airworthiness 

Directive 2010–0069, dated April 14, 2010; 

and Saab Service Bulletin 2000–32–073, 

Revision 01, dated October 20, 2009; for 

related information. 

Issued in Renton, Washington, on March 

31, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–8412 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–2011–0308; Directorate 

Identifier 2010–NM–233–AD] 

RIN 2120–AA64 

Airworthiness Directives; 328 Support 

Services GmbH (Type Certificate 

Previously Held by AvCraft Aerospace 

GmbH; Fairchild Dornier GmbH; 

Dornier Luftfahrt GmbH) Model 328– 

100 and –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 maintenance, it has been 

discovered that at the installation of the 

fixation brackets for rudder spring tabs and 

trim tabs an incorrect installation of the 

fixation brackets may have occurred. * * * 

mstockstill on DSKH9S0YB1PROD with PROPOSALS