Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 41665 

14, 2011. The Director of the Federal Register 

approved the incorporation by reference of 

the service information, under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact MD Helicopters Inc., Attn: 

Customer Support Division, 4555 E. 

McDowell Rd., Mail Stop M615, Mesa, AZ 

85215–9734, telephone 1–800–388–3378, fax 

480–346–6813, or at http:// 

www.mdhelicopters.com. 

(3) Copies may be inspected at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas, or at the National Archives 

and Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. 

Subject 

(j) The Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code is 6220: Main Rotor Head. 

Issued in Fort Worth, Texas, on June 21, 

2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–17421 Filed 7–14–11; 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; Amendment 

39–16747; AD 2011–14–12] 

RIN 2120–AA64 

Airworthiness Directives; Saab AB, 

Saab Aerosystems Model SAAB 2000 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This 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. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

August 19, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 1, 2011. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on April 8, 2011 (76 FR 19719). 

That NPRM proposed 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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 required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 8 products of U.S. registry. We 

also estimate that it will take about 1 

work-hour per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will 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 

this AD to the 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 

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41666 Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 AD: 

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 AD and placed it in the AD docket. 

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 the NPRM, 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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: 

2011–14–12 Saab AB, Saab Aerosystems: 

Amendment 39–16747. Docket No. 

FAA–2011–0307; Directorate Identifier 

2010–NM–111–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 19, 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 Actions 

(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 of 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 Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, 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, 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– 

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Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 41667 

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 FAAapproved 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. 

Material Incorporated by Reference 

(m) You must use Saab Service Bulletin 

2000–32–073, Revision 01, dated October 20, 

2009, to do the actions required by this AD, 

unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this 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. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on July 1, 

2011. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–17576 Filed 7–14–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0436; Directorate 

Identifier 2011–CE–009–AD; Amendment 

39–16752; AD 2011–15–05] 

RIN 2120–AA64 

Airworthiness Directives; Hawker 

Beechcraft Corporation Models B300 

and B300C (C–12W) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Hawker Beechcraft Corporation Models 

B300 and B300C (C–12W) airplanes. 

This AD was prompted by an error 

found in the take-off speeds and field 

lengths published in the FAA-approved 

airplane flight manual. This AD requires 

a correction to the published data in the 

airplane flight manual and the pilot’s 

operating handbook to ensure it 

corresponds with the published data in 

the pilot’s checklist. This condition, if 

not corrected, could result in a pilot 

taking off from shorter runways than 

required by the airplane if the airplane 

loses an engine after takeoff decision 

speed (V1). This could result in the 

airplane running out of runway before 

take-off can be accomplished. We are 

issuing this AD to correct the unsafe 

condition on these products. 

DATES: This AD is effective August 19, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 19, 2011. 

ADDRESSES: For service information 

identified in this AD, contact Hawker 

Beechcraft Corporation, 9709 East 

Central, Wichita, Kansas 67201; 

telephone: (316) 676–5034; fax: (316) 

676–6614; Internet: https:// 

www.hawkerbeechcraft.com/ 

service_support/pubs/. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 

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

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Jason Brys, Flight Test Engineer, FAA, 

Wichita Aircraft Certification Office, 

1801 S. Airport Road, Room 100, 

Wichita, Kansas 67209; telephone: (316) 

946–4100; fax: (316) 946–4107. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on April 29, 2011 (76 FR 

23921). That NPRM proposed to require 

inserting an update to the performance 

charts in the FAA-approved Airplane 

Flight Manual and the Pilot’s Operating 

Handbook, part number (P/N) 130– 

590031–245. The required runway 

distances published in the current 

manual could be up to 320 feet shorter 

than what is necessary. Hawker 

Beechcraft Corporation determined data 

in the pilot’s checklist (P/N 130– 

590031–273) was correct. This 

condition, if not corrected, could result 

in taking off from shorter runways than 

required by the airplane if the airplane 

loses an engine after takeoff decision 

speed (V1). This could result in the 

airplane running out of runway before 

take-off can be accomplished. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Costs of Compliance 

We estimate that this proposed AD 

affects 46 airplanes of U.S. registry. 

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