53846 Federal Register / Vol. 75, No. 170 / Thursday, September 2, 2010 / Rules and Regulations 

Issued in Renton, Washington, on August 

11, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–20491 Filed 9–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0201; Directorate 

Identifier 2008–NE–47–AD; Amendment 39– 

16314; AD 2010–11–09] 

RIN 2120–AA64 

Airworthiness Directives; Thielert 

Aircraft Engines GmbH (TAE) Models 

TAE 125–01 and TAE 125–02–99 

Reciprocating Engines Installed In, But 

Not Limited To, Diamond Aircraft 

Industries Model DA 42 Airplanes; 

Correction 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting 

airworthiness directive (AD) 2010–11– 

09, which published in the Federal 

Register. That AD applies to TAE 

models TAE 125–01 and TAE 125–02– 

99 reciprocating engines, installed in, 

but not limited to, Diamond Aircraft 

Industries model DA 42 airplanes. The 

part number for engine model TAE 125– 

01 is missing a digit in paragraph (c) 

and in paragraph (e)(3). This document 

corrects those part numbers. In all other 

respects, the original document remains 

the same. 

DATES: This correction is effective 

September 2, 2010. The compliance 

times of AD 2010–11–09 remain 

unchanged. 

FOR FURTHER INFORMATION CONTACT: Tara 

Chaidez, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: tara.chaidez@faa.gov; telephone 

(781) 238–7773; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: On June 8, 

2010 (75 FR 32253), we published a 

final rule AD, FR Doc. 2010–12540, in 

the Federal Register. That AD applies to 

TAE models TAE 125–01 and TAE 125– 

02–99 reciprocating engines, installed 

in, but not limited to, Diamond Aircraft 

Industries model DA 42 airplanes. We 

need to make the following corrections: 

§ 39.13 [Corrected] 

On page 32254, in the second column, 

in paragraph (c), in the fifth line, ‘‘or 02– 

7200–1401R1’’ is corrected to read ‘‘or 

02–7200–14017R1’’. 

On page 32254, in the second column, 

in paragraph (e)(3), in the second line, 

‘‘engine P/N 02–7200–1401R1’’ is 

corrected to read ‘‘engine P/N 02–7200– 

14017R1’’ 

Issued in Burlington, Massachusetts, on 

August 26, 2010. 

Thomas A. Boudreau, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. C1–2010–21870 Filed 9–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0463; Directorate 

Identifier 2010–CE–021–AD; Amendment 

39–16425; AD 2010–10–01 R1] 

RIN 2120–AA64 

Airworthiness Directives; GA 8 Airvan 

(Pty) Ltd Models GA8 and GA8–TC320 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are revising an existing 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued 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: 

Inspection of a high time aircraft has 

revealed cracks in the Horizontal Stabiliser 

rear spar splice plate and inboard main ribs 

around the area of the Horizontal Stabiliser 

rear pivot attachment. Additionally, failure of 

some attach bolts in service may be due to 

improper assembly. 

This amendment is issued to include an 

applicability matrix (Table 1, page 2) in the 

compliance section of the service bulletin for 

improved clarity. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

October 7, 2010. 

On October 7, 2010, the Director of 

the Federal Register approved the 

incorporation by reference of Gippsland 

Aeronautics Mandatory Service Bulletin 

SB–GA8–2002–02, Issue 6, dated April 

21, 2010, listed in this AD. 

As of March 2, 2009 (74 FR 8159; 

February 24, 2009), the Director of the 

Federal Register approved the 

incorporation by reference of Gippsland 

Aeronautics Mandatory Service Bulletin 

SB–GA8–2002–02, Issue 5, dated 

November 13, 2008, listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

Docket 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: 

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 

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 June 21, 2010 (75 FR 34953), 

and proposed to revise AD 2010–10–01, 

Amendment 39–16280 (75 FR 23577, 

May 4, 2010). 

Since we issued AD 2010–10–01, the 

foreign authority has issued an 

amendment to include an applicability 

matrix in the compliance section of the 

manufacturer’s service bulletin for 

improved clarity. The FAA is revising 

this AD to allow the use of issue 6 or 

issue 5 of the service bulletin. An 

operator would be in compliance if the 

operator chose to only accomplish issue 

5 of the service bulletin. This revision 

of the FAA’s AD will make the FAA AD 

more in line with the latest version of 

the received MCAI. 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states that: 

Inspection of a high time aircraft has 

revealed cracks in the Horizontal Stabiliser 

rear spar splice plate and inboard main ribs 

around the area of the Horizontal Stabiliser 

rear pivot attachment. Additionally, failure of 

some attach bolts in service may be due to 

improper assembly. 

This amendment is issued to include an 

applicability matrix (Table 1, page 2) in the 

compliance section of the service bulletin for 

improved clarity. 

The previous amendment included 

reference to the GA8–TC 320 variant in the 

applicability section. 

Amendment 2 was issued because the 

requirement document now contains an 

inspection for cracking in horizontal 

stabilisers which have load transferring 

fittings installed. 

Previous amendments of this AD listed the 

AD requirements in full. Due to the extensive 


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