Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations 52253 

Issued in Kansas City, Missouri, on August 

17, 2010. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–20877 Filed 8–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0847; Directorate 

Identifier 2010–CE–046–AD; Amendment 

39–16419; AD 2010–18–06] 

RIN 2120–AA64 

Airworthiness Directives; GA 8 Airvan 

(Pty) Ltd Models GA8 and GA8–TC320 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above that will 

supersede an existing AD. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued by the aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Inspections have revealed cases of 

excessive wear in the forward slide of the 

cargo door. Excessive wear in the door slide 

may result in the door becoming detached 

from the aircraft in flight, with potentially 

catastrophic results. 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

August 30, 2010. 

On August 30, 2010, the Director of 

the Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

We must receive comments on this 

AD by October 12, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

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 street address for 

the Docket 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: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On October 18, 2005, we issued AD 

2005–22–02, Amendment 39–14346 (70 

FR 61547; October 25, 2005). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2005–22–02, 

there has been another report of an inflight cargo door separation. 

Consequently, GA 8 Airvan (Pty) Ltd 

has revised the service information by 

improving the inspection method and 

making a minor design change to the 

door slide. 

The Civil Aviation Safety Authority 

(CASA), which is the aviation authority 

for Australia, has issued AD/GA8/3, 

Amdt 2, dated August 11, 2010 (referred 

to after this as ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Inspections have revealed cases of 

excessive wear in the forward slide of the 

cargo door. Excessive wear in the door slide 

may result in the door becoming detached 

from the aircraft in flight, with potentially 

catastrophic results. 

Following a recent in-flight door 

separation, this amendment is issued to 

update the service bulletin to remove any 

ambiguities that could have existed in the 

previous revision to the referenced service 

bulletin. It also provides an improved 

inspection method and a minor design 

change to the cargo door slide (inclusion of 

slide backing plate, castellated nut and spilt 

[sic] pin). 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

GippsAero Pty. Ltd. has issued 

Mandatory Service Bulletin SB–GA8– 

2005–23, Issue 3, dated August 5, 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 the 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 this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all 

information provided by the State of 

Design Authority and determined the 

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 have also required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are described in a 

separate paragraph of the AD. These 

requirements take precedence over 

those copied from the MCAI. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because an in-flight separation of 

the door could potentially strike the 

horizontal stabilizer structure, which 

could lead to failure of the tailplane 

assembly. Therefore, we determined 

that notice and opportunity for public 

comment before issuing this AD are 

impracticable and that good cause exists 

for making this amendment effective in 

fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

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52254 Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2010–0847; 

Directorate Identifier 2010–CE–046–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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. 

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 

removing Amendment 39–14346 (70 FR 

61547; October 25, 2005), and adding 

the following new AD: 

2010–18–06 GA 8 AIRVAN (PTY) LTD: 

Amendment 39–16419; Docket No. 

FAA–2010–0847; Directorate Identifier 

2010–CE–046–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 30, 2010. 

Affected ADs 

(b) This AD supersedes AD 2005–22–02, 

Amendment 39–14346. 

Applicability 

(c) This AD applies to GA 8 Airvan (Pty) 

Ltd Models GA8 and GA8–TC320 airplanes, 

all serial numbers, certificated in any 

category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 52: Doors. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Inspections have revealed cases of 

excessive wear in the forward slide of the 

cargo door. Excessive wear in the door slide 

may result in the door becoming detached 

from the aircraft in flight, with potentially 

catastrophic results. 

Following a recent in-flight door 

separation, this amendment is issued to 

update the service bulletin to remove any 

ambiguities that could have existed in the 

previous revision to the referenced service 

bulletin. It also provides an improved 

inspection method and a minor design 

change to the cargo door slide (inclusion of 

slide backing plate, castellated nut and spilt 

[sic] pin). 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within 500 hours total time-in-service 

(TIS) of the airplane or within the next 10 

hours TIS after August 30, 2010 (the effective 

date of this AD), whichever occurs later, do 

all of Action 1: of GippsAero Pty. Ltd. 

Mandatory Service Bulletin SB–GA8–2005– 

23, Issue 3, dated August 5, 2010. 

(2) Within 100 hours TIS after doing the 

actions in paragraph (f)(1) of this AD or 

within 12 calendar months after doing the 

actions in paragraph (f)(1) of this AD, 

whichever occurs first, and repetitively 

thereafter at intervals not to exceed 100 hours 

TIS or 12 calendar months, whichever occurs 

first, do all of Action 2: of GippsAero Pty. 

Ltd. Mandatory Service Bulletin SB–GA8– 

2005–23, Issue 3, dated August 5, 2010. 

(3) If a cracked or excessively worn slider 

is found during any inspection required in 

paragraph (f)(1) or (f)(2) of this AD, before 

further flight replace the slider. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: The MCAI 

and service information only list the Model 

GA8 in the applicability. The cargo door for 

the Model GA8–TC320 has the same design 

and this AD also applies to the Model GA8– 

TC320. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4059; fax: (816) 329– 

4090. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

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

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI Civil Aviation Safety 

Authority AD No. AD/GA8/3, Amdt 2, dated 

August 11, 2010, and GippsAero Pty. Ltd. 

Mandatory Service Bulletin SB–GA8–2005– 

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Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations 52255 

23, Issue 3, dated August 5, 2010, for related 

information. 

Material Incorporated by Reference 

(i) You must use GippsAero Pty. Ltd. 

Mandatory Service Bulletin SB–GA8–2005– 

23, Issue 3, dated August 5, 2010, 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 GippsAero Pty. Ltd., Attn: 

Technical Services, P.O. Box 881, Morwell, 

Victoria 3840, Australia; telephone: + 61 03 

5172 1200; fax: +61 03 5172 1201; Internet: 

http://www.gippsaero.com. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri, on August 

18, 2010. 

John R. Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–21063 Filed 8–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0827; Directorate 

Identifier 2010–CE–029–AD; Amendment 

39–16412; AD 2010–17–18] 

RIN 2120–AA64 

Airworthiness Directives; Air Tractor, 

Inc. Models AT–802 and AT–802A 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) to 

supersede AD 2010–13–08, which 

applies to all Air Tractor, Inc. (Air 

Tractor) Models AT–802 and AT–802A 

airplanes. AD 2010–13–08 currently 

requires you to repetitively inspect 

(using the eddy current method) the two 

outboard fastener holes in both of the 

wing main spar lower caps at the center 

splice joint for cracks and repair or 

replace any cracked spar cap. Since we 

issued 2010–13–08, we evaluated 

service information issued by Air 

Tractor and determined we need to add 

inspections, add modifications, and 

change the safe life for certain serial 

number (SN) ranges. Consequently, this 

AD would retain the actions of AD 

2010–13–08 and would add inspections, 

add modifications, and change the safe 

life for certain SN ranges. We are issuing 

this AD to detect and correct cracks in 

the wing main spar lower cap at the 

center splice joint, which could result in 

failure of the spar cap and lead to wing 

separation and loss of control of the 

airplane. 

DATES: This AD becomes effective on 

September 9, 2010. 

On September 9, 2010, the Director of 

the Federal Register approved the 

incorporation by reference of Snow 

Engineering Co. Service Letter #80GG, 

revised December 21, 2005; Snow 

Engineering Co. Service Letter #284, 

dated October 4, 2009; Snow 

Engineering Co. Service Letter #281, 

dated August 1, 2009; Snow Engineering 

Co. Service Letter #245, dated April 25, 

2005; Snow Engineering Co. Drawing 

Number 20995, Sheet 3, dated 

November 25, 2005; Snow Engineering 

Co. Drawing Number 20995, Sheet 2, 

Rev. D., dated November 25, 2005; and 

Snow Engineering Co. Drawing Number 

20975, Sheet 4, Rev. A., dated January 

7, 2009, listed in this AD. 

As of April 21, 2006 (71 FR 19994, 

April 19, 2006), the Director of the 

Federal Register approved the 

incorporation by reference of Snow 

Engineering Co. Service Letter #240, 

dated September 30, 2004; and Snow 

Engineering Co. Process Specification 

#197, page 1, revised June 4, 2002; pages 

2 through 4, dated February 23, 2001; 

and page 5, dated May 3, 2002, listed in 

this AD. 

We must receive any comments on 

this AD by October 12, 2010. 

ADDRESSES: Use one of the following 

addresses to comment on this AD. 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

To get the service information 

identified in this AD, contact Air 

Tractor, Inc., P.O. Box 485, Olney, Texas 

76374; telephone: (940) 564–5616; fax: 

(940) 564–5612; E-mail: 

airmail@airtractor.com; Internet: http:// 

www.airtractor.com. 

To view the comments to this AD, go 

to http://www.regulations.gov. The 

docket number is FAA–2010–0827; 

Directorate Identifier 2010–CE–029–AD. 

FOR FURTHER INFORMATION CONTACT: 

Andrew McAnaul, Aerospace Engineer, 

ASW–150 (c/o MIDO–43), 10100 

Reunion Place, Suite 650, San Antonio, 

Texas 78216; telephone: (210) 308– 

3365; facsimile: (210) 308–3370. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Since 2000, we have issued several 

ADs related to the wing spar inspection 

and safe life on Air Tractor AT–400, 

AT–500, AT–600, and AT–800 series 

airplanes. 

In 2001, we issued AD 2001–10–04, 

Amendment 39–12230 (66 FR 27014, 

May 16, 2001) to lower the safe life for 

the wing lower spar cap on Air Tractor 

AT–400, AT–500, and AT–800 series 

airplanes. This AD allowed for 

inspection (using eddy current methods) 

of the wing lower spar cap for airplanes 

that were at or over the lower safe life 

and for which parts were not available. 

Later that same year, we revised that AD 

to remove AT–800 series airplanes from 

the applicability that were equipped 

with the factory-supplied computerized 

fire gate (part number 80540) and 

engaged in full-time firefighting. 

In 2002, we issued AD 2002–11–05, 

Amendment 39–12766 (67 FR 37967, 

May 31, 2002) that retained the actions 

for the AT–802 series airplanes and 

further reduced the safe life for certain 

AT–400 series airplanes and certain 

AT–500 series airplanes that either 

incorporate or have incorporated 

Marburger winglets. 

After receiving reports of fatigue 

cracking found on three Model AT– 

802A airplanes that were below the 

reduced safe life established in AD 

2001–10–04, we issued AD 2006–08–09, 

Amendment 39–14565 (71 FR 27794, 

May 12, 2006). AD 2006–08–09 required 

repetitively inspecting the two outboard 

fastener holes in both of the wing main 

spar lower caps at the center splice joint 

for cracks and repairing or replacing any 

cracked spar cap. 

After issuing AD 2006–08–09, we 

determined the need to clarify the 

affected SN applicability. Models AT– 

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