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 


emcdonald on DSK2BSOYB1PROD with RULES
Federal Register / Vol. 75, No. 170 / Thursday, September 2, 2010 / Rules and Regulations 53847 

use of diagrams and photographs, it is no 

longer appropriate or practical to write the 

requirements of the service bulletin out in 

full in this AD. All requirements, 

accomplishment instructions and 

illustrations are contained in the service 

bulletin. 

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 FAA policies. 

Any such differences are highlighted in 

a note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

25 products of U.S. registry. We also 

estimate that it will take about 1 workhour 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 $0 per 

product. 

Based on these figures, we estimate 

the cost of this AD to the U.S. operators 

to be $2,125 or $85 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 5 work-hours and require parts 

costing $200, for a cost of $625 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 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 

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 Management Facility 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 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 

removing Amendment 39–16280 (75 FR 

23577, May 4, 2010) and adding the 

following new AD: 

2010–10–01 R1 GA 8 Airvan (Pty) Ltd.: 

Amendment 39–16425; Docket No. 

FAA–2010–0463; Directorate Identifier 

2010–CE–021–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 7, 2010. 

Affected ADs 

(b) This AD revises AD 2010–10–01, 

Amendment 39–16280. 

Applicability 

(c) This AD applies to the following model 

and serial number airplanes, certificated in 

any category: 

(i) Group 1 Airplanes (retains the actions 

and applicability from AD 2009–05–01): 

Model GA8 airplanes, serial numbers GA8– 

00–004 and up; and 

(ii) Group 2 Airplanes: Model GA8–TC320 

airplanes, all serial numbers. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 55: Stabilizers. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

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 

use of diagrams and photographs, it is no 

longer appropriate or practical to write the 

requirements of the service bulletin out in 

full in this AD. All requirements, 

accomplishment instructions and 

illustrations are contained in the service 

bulletin. 

The FAA is revising AD 2010–10–01 to allow 

the use of issue 6 or issue 5 of the service 

bulletin. An operator is in compliance if the 

operator chooses to only accomplish issue 5 


emcdonald on DSK2BSOYB1PROD with RULES
53848 Federal Register / Vol. 75, No. 170 / Thursday, September 2, 2010 / Rules and Regulations 

of the SB. This proposed revision of the 

FAA’s AD will make the FAA AD more 

consistent with the latest version of the 

MCAI. 

Actions and Compliance 

(f) For Group 1 Airplanes: Unless already 

done, do the following actions: 

(1) Within the next 10 hours time-inservice (TIS) after March 2, 2009 (the 

effective date retained from AD 2009–05–01): 

(i) For all aircraft not incorporating 

computer numeric control (CNC) machined 

elevator hinges, inspect and repair the left 

and right horizontal stabilizer rear pivot 

attachment installation following instruction 

‘‘3. Rear Pivot Attachment Inspection,’’ of 

Gippsland Aeronautics Mandatory Service 

Bulletin SB–GA8–2002–02, Issue 5, dated 

November 13, 2008; or Gippsland 

Aeronautics Mandatory Service Bulletin SB– 

GA8–2002–02, Issue 6, dated April 21, 2010; 

and 

(ii) For all aircraft, inspect the left and right 

rear attach bolt mating surfaces for damage or 

an out of square condition and replace the 

left and right rear attach bolts following 

instruction ‘‘5. Rear Attach Bolt 

Replacement,’’ of Gippsland Aeronautics 

Mandatory Service Bulletin SB–GA8–2002– 

02, Issue 5, dated November 13, 2008; or 

Gippsland Aeronautics Mandatory Service 

Bulletin SB–GA8–2002–02, Issue 6, dated 

April 21, 2010. Reworking the mating 

surfaces by spotfacing is no longer 

acceptable. If the mating surfaces are 

damaged, not square, or were previously 

reworked by spotfacing the surface, replace 

the parts as specified in Gippsland 

Aeronautics Mandatory Service Bulletin SB– 

GA8–2002–02, Issue 5, dated November 13, 

2008; or Gippsland Aeronautics Mandatory 

Service Bulletin SB–GA8–2002–02, Issue 6, 

dated April 21, 2010. 

(2) Within the next 10 hours TIS after 

March 2, 2009 (the effective date retained 

from AD 2009–05–01) and repetitively 

thereafter at intervals not to exceed 100 hours 

TIS or 12 months, whichever occurs first, for 

all aircraft: 

(i) Inspect the horizontal stabilizer 

externally following instruction ‘‘2. External 

Inspection (Lower flange, Stabilizer rear 

spar),’’ of Gippsland Aeronautics Mandatory 

Service Bulletin SB–GA8–2002–02, Issue 5, 

dated November 13, 2008; or Gippsland 

Aeronautics Mandatory Service Bulletin SB– 

GA8–2002–02, Issue 6, dated April 21, 2010; 

and 

(ii) Inspect the horizontal stabilizer 

internally following instruction ‘‘4. Internal 

Inspection,’’ of Gippsland Aeronautics 

Mandatory Service Bulletin SB–GA8–2002– 

02, Issue 5, dated November 13, 2008; or 

Gippsland Aeronautics Mandatory Service 

Bulletin SB–GA8–2002–02, Issue 6, dated 

April 21, 2010. 

(3) If during the inspection required by 

paragraph (f)(2) of this AD any excessive 

local deflection or movement of the lower 

skin surrounding the lower pivot attachment, 

cracking, or working (loose) rivet is found, 

before further flight, obtain an FAA-approved 

repair scheme from the manufacturer and 

incorporate this repair scheme. Due to FAA 

policy, the repair scheme/modification for 

crack damage must include an immediate 

repair of the crack. The repair scheme cannot 

be by repetitive inspection only. The repair 

scheme/modification may incorporate 

repetitive inspections in addition to the 

repetitive inspections required in paragraph 

(f)(2) of this AD. Continued operational flight 

with un-repaired crack damage is not 

permitted. 

(g) For Group 2 Airplanes: Unless already 

done, do the following actions: 

(1) Within the next 10 hours TIS after May 

10, 2010 (the effective date retained from AD 

2010–10–01): 

(i) For all aircraft not incorporating 

computer numeric control (CNC) machined 

elevator hinges, inspect and repair the left 

and right horizontal stabilizer rear pivot 

attachment installation following instruction 

‘‘3. Rear Pivot Attachment Inspection,’’ of 

Gippsland Aeronautics Mandatory Service 

Bulletin SB–GA8–2002–02, Issue 5, dated 

November 13, 2008; or Gippsland 

Aeronautics Mandatory Service Bulletin SB– 

GA8–2002–02, Issue 6, dated April 21, 2010; 

and, 

(ii) For all aircraft, inspect the left and right 

rear attach bolt mating surfaces for damage or 

an out of square condition and replace the 

left and right rear attach bolts following 

instruction ‘‘5. Rear Attach Bolt 

Replacement,’’ of Gippsland Aeronautics 

Mandatory Service Bulletin SB–GA8–2002– 

02, Issue 5, dated November 13, 2008; or 

Gippsland Aeronautics Mandatory Service 

Bulletin SB–GA8–2002–02, Issue 6, dated 

April 21, 2010. Reworking the mating 

surfaces by spotfacing is no longer 

acceptable. If the mating surfaces are 

damaged, not square, or were previously 

reworked by spotfacing the surface, before 

further flight, replace the parts as specified 

in Gippsland Aeronautics Mandatory Service 

Bulletin SB–GA8–2002–02, Issue 5, dated 

November 13, 2008; or Gippsland 

Aeronautics Mandatory Service Bulletin SB– 

GA8–2002–02, Issue 6, dated April 21, 2010. 

(2) Within the next 10 hours TIS after May 

10, 2010 (the effective date retained from AD 

2010–10–01) and repetitively thereafter at 

intervals not to exceed 100 hours TIS or 12 

months, whichever occurs first, for all 

aircraft: 

(i) Inspect the horizontal stabilizer 

externally following instruction ‘‘2. External 

Inspection (Lower flange, Stabilizer rear 

spar),’’ of Gippsland Aeronautics Mandatory 

Service Bulletin SB–GA8–2002–02, Issue 5, 

dated November 13, 2008; or Gippsland 

Aeronautics Mandatory Service Bulletin SB– 

GA8–2002–02, Issue 6, dated April 21, 2010; 

and 

(ii) Inspect the horizontal stabilizer 

internally following instruction ‘‘4. Internal 

Inspection,’’ of Gippsland Aeronautics 

Mandatory Service Bulletin SB–GA8–2002– 

02, Issue 5, dated November 13, 2008; or 

Gippsland Aeronautics Mandatory Service 

Bulletin SB–GA8–2002–02, Issue 6, dated 

April 21, 2010. 

(3) If during the inspection required by 

paragraph (g)(2) of this AD any excessive 

local deflection or movement of the lower 

skin surrounding the lower pivot attachment, 

cracking, or working (loose) rivet is found, 

before further flight, obtain an FAA-approved 

repair scheme from the manufacturer and 

incorporate this repair scheme. Due to FAA 

policy, the repair scheme/modification for 

crack damage must include an immediate 

repair of the crack. The repair scheme cannot 

be by repetitive inspection only. The repair 

scheme/modification may incorporate 

repetitive inspections in addition to the 

repetitive inspections required in paragraph 

(g)(2) of this AD. Continued operational flight 

with un-repaired crack damage is not 

permitted. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: 

(1) ‘‘Requirement: 1. Daily Inspection 

(Stabilizer attach bolt)’’ of the service 

information requires a daily inspection of the 

stabilizer attach bolt. The daily inspection is 

not a requirement of this AD. Instead of the 

daily inspection, we require you to perform, 

within 10 hours TIS, ‘‘Requirement 3. Rear 

Pivot Attachment Inspection’’ and 

‘‘Requirement 5. Rear Attachment Bolt 

Replacement’’ of the service information. 

Compliance with requirement 3. and 5. is a 

terminating action for the daily inspection, 

and we are requiring these within 10 hours 

TIS after the effective date of AD 2009–05– 

01 for Group 1 airplanes and AD 2010–10– 

01 for Group 2 airplanes. 

(2) ‘‘Requirement: 2. External Inspection 

(Lower flange, Stabilizer rear spar)’’ of the 

service information does not specify any 

action if excessive local deflection or 

movement of lower skin, cracking, or 

working (loose) rivet is found. We require 

obtaining and incorporating an FAAapproved repair scheme from the 

manufacturer before further flight. 

(3) The MCAI does not state if further flight 

with known cracks is allowed. FAA policy is 

to not allow further flight with known cracks 

in critical structure. We require that if any 

cracks are found when accomplishing the 

inspection required in paragraphs (f)(2) and 

(g)(2) of this AD, you must repair the cracks 

before further flight. 

(4) The service information does not state 

that parts with spotfaced nut and bolt mating 

surfaces require replacement. However, the 

service information no longer allows 

reworking of the mating surfaces by 

spotfacing. We require that if any nut and 

bolt surfaces were previously reworked by 

spotfacing, you must replace the parts. 

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. 


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Federal Register / Vol. 75, No. 170 / Thursday, September 2, 2010 / Rules and Regulations 53849 

(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. 

(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/GA8/5, Amdt 4, dated 

May 11, 2010; Gippsland Aeronautics 

Mandatory Service Bulletin SB–GA8–2002– 

02, Issue 5, dated November 13, 2008; and 

Gippsland Aeronautics Mandatory Service 

Bulletin SB–GA8–2002–02, Issue 6, dated 

April 21, 2010, for related information. 

Material Incorporated by Reference 

(h) You must use Gippsland Aeronautics 

Mandatory Service Bulletin SB–GA8–2002– 

02, Issue 5, dated November 13, 2008; and 

Gippsland Aeronautics Mandatory Service 

Bulletin SB–GA8–2002–02, Issue 6, dated 

April 21, 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 

Gippsland Aeronautics Mandatory Service 

Bulletin SB–GA8–2002–02, Issue 6, dated 

April 21, 2010, under 5 U.S.C. 552(a) and 1 

CFR part 51. 

(2) On March 2, 2009 (74 FR 8159; 

February 24, 2009), the Director of the 

Federal Register previously approved the 

incorporation by reference of Gippsland 

Aeronautics Mandatory Service Bulletin SB– 

GA8–2002–02, Issue 5, dated November 13, 

2008. 

(3) For service information identified in 

this AD, contact Gippsland Aeronautics, 

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. 

(4) 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. 

(5) 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 

25, 2010. 

John R. Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–21725 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–2010–0851; Directorate 

Identifier 2010–NM–171–AD; Amendment 

39–16424; AD 2010–18–11] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2C10 (Regional Jet 

Series 700, 701, & 702); Model CL–600– 

2D15 (Regional Jet Series 705); and 

Model CL–600–2D24 (Regional Jet 

Series 900) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

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: 

During maintenance at the vendor’s 

facility, some HSTAs [horizontal stabilizer 

trim actuators] were assembled with the 

incorrect load bearing balls. The material of 

these discrepant balls has lower wear 

characteristics and as such, has a shorter 

expected life. If not corrected, this condition 

can result in the HSTA jam leading to 

difficulties in controlling the aircraft. 

* * * * * 

The unsafe condition is possible loss of 

controllability of the airplane. This AD 

requires actions that are intended to 

address the unsafe condition described 

in the MCAI. 

DATES: This AD becomes effective 

September 17, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of September 17, 2010. 

We must receive comments on this 

AD by October 18, 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 W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, 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 Operations office 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 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: 

Christopher Alfano, Aerospace 

Engineer, Airframe and Mechanical 

Systems Branch, ANE–171, FAA, New 

York Aircraft Certification Office (ACO), 

1600 Stewart Avenue, Suite 410, 

Westbury, New York 11590; telephone 

(516) 228–7340; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2010–20, 

dated July 19, 2010 (referred to after this 

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

condition for the specified products. 

The MCAI states: 

During maintenance at the vendor’s 

facility, some HSTAs were assembled with 

the incorrect load bearing balls. The material 

of these discrepant balls has lower wear 

characteristics and as such, has a shorter 

expected life. If not corrected, this condition 

can result in the HSTA jam leading to 

difficulties in controlling the aircraft. 

This directive mandates incorporation of 

the HSTA with the correct load bearing balls. 

The unsafe condition is possible loss of 

controllability of the airplane. The 

corrective action requires inspecting to 

determine the serial number of the 

HSTAs. You may obtain further 

information by examining the MCAI in 

the AD docket. 


emcdonald on DSK2BSOYB1PROD with RULES