Federal Register / Vol. 72, No. 161 / Tuesday, August 21, 2007 / Rules and Regulations 46551 

(1) Inspect the nose landing gear leg for 

cracks as follows. 

(i) Initially within the next 12 months after 

September 25, 2007 (the effective date of this 

AD) or within the next 200 hours time-inservice (TIS) after September 25, 2007 (the 

effective date of this AD), whichever occurs 

later. 

(ii) Repetitively inspect thereafter at 

intervals not to exceed 12 months or 200 

hours TIS, whichever occurs later. 

(2) Replace the nose landing gear leg before 

further flight after any inspection required by 

paragraph (f)(1) of this AD in which cracks 

are found. 

(3) After doing the replacement required in 

paragraph (f)(2) of this AD, repetitively 

inspect at intervals not to exceed 12 months 

or 200 hours TIS, whichever occurs later. 

(4) Do the actions required in paragraphs 

(f)(1), (f)(2), and (f)(3) of this AD following 

Diamond Aircraft Industries GmbH 

Mandatory Service Bulletin No. MSB40–046/ 

1, No. MSBD4–046/1, dated April 25, 2007, 

and the applicable maintenance manual. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

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: Sarjapur Nagarajan, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4145; 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 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 Austro Control AD No. 

A–2005–005, dated November 15, 2005; and 

Diamond Aircraft Industries GmbH 

Mandatory Service Bulletin No. MSB40–046/ 

1, No. MSBD4–046/1, dated April 25, 2007, 

for related information. 

Material Incorporated by Reference 

(i) You must use Diamond Aircraft 

Industries GmbH Mandatory Service Bulletin 

No. MSB40–046/1, No. MSBD4–046/1, dated 

April 25, 2007, 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 Diamond Aircraft Industries 

GmbH, N.A. Otto-Strabe 5, A–2700 Wiener 

Neustadt; Fax: **43–2622–26620; or e-mail: 

support@diamond-air.at. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Room 506, Kansas City, 

Missouri 64106; or 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/ 

cfr/ibr-locations.html. 

Issued in Kansas City, Missouri, on August 

10, 2007. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–16098 Filed 8–20–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28610; Directorate 

Identifier 2007–CE–058–AD; Amendment 

39–15166; AD 2007–17–08] 

RIN 2120–AA64 

Airworthiness Directives; DG 

Flugzeugbau GmbH Model DG–500MB 

Gliders and Glaser-Dirks Flugzeugbau 

GmbH Model DG–800B Gliders 

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. 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: 

Instead of the hub normally used which 

carries the starter ring gear and the hub for 

the tooth belt a slip-clutch can be mounted. 

The unit contains the hub for the tooth belt 

and the starter ring gear. Occurrences during 

service have shown that under bad 

conditions excessive wear on several parts of 

the clutch can occur. 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

September 10, 2007. 

On September 10, 2007, 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 September 20, 2007. 

ADDRESSES: You may send comments by 

any of the following methods: 

• DOT Docket Web Site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• 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. 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.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: 

Gregory Davison, Aerospace Engineer, 

FAA, Small Airplanes Directorate, 901 

Locust St., Room 301, Kansas City, 

Missouri 64016; telephone: (816) 329–

4130; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued Emergency AD 

No. 2007–0001R1–E, dated January 10, 

2007, (referred to after this as ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Instead of the hub normally used which 

carries the starter ring gear and the hub for 


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46552 Federal Register / Vol. 72, No. 161 / Tuesday, August 21, 2007 / Rules and Regulations 

the tooth belt a slip-clutch can be mounted. 

The unit contains the hub for the tooth belt 

and the starter ring gear. Occurrences during 

service have shown that under bad 

conditions excessive wear on several parts of 

the clutch can occur. In order to avoid further 

damages the affected parts of the slip clutch 

on the engines SOLO 2 625 01 and SOLO 2 

652 02 have to be inspected and replaced, if 

necessary. In order to check the condition of 

the clutch on all engines SOLO 2 625 in 

future, additional procedures are installed 

and additional inspection terms are 

introduced. The cover place in front of the 

slip clutch has to be replaced by a stronger 

plate with the No. 2042888. 

The original Emergency AD has now been 

revised to indicate that the initial inspection 

of the installed slip-clutch is required when 

12.5 hours in operation have been 

accumulated. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

SOLO Kleinmotoren GmbH has issued 

Service Bulletin Nr. 4600–2–2, dated 

December 27, 2006. 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 occurrences during service 

have shown that under certain 

conditions, excessive wear on several 

parts of the clutch can occur. Excessive 

wear could cause the slip clutch to 

disengage at an undesired torque, which 

could result in reduced power during 

critical phases of flight. 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 

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–2007–28610; 

Directorate Identifier 2007–CE–058–

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:// 

dms.dot.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 adding 

the following new AD: 

2007–17–08 DG Flugzeugbau GmbH and 

Glaser-Dirks Flugzeugbau GmbH: 

Amendment 39–15166; Docket No. 

FAA–2007–28610; Directorate Identifier 

2007–CE–058–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 10, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Models DG–500MB 

and DG–800B gliders, all serial numbers, 

that: 

(1) Have SOLO engine 2 625 01 equipped 

with optional slip-clutch sets, SOLO part 

number (P/N) 29 00 202, installed; or 


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Federal Register / Vol. 72, No. 161 / Tuesday, August 21, 2007 / Rules and Regulations 46553 

(2) Have SOLO engine 2 625 02 equipped 

with optional slip-clutch sets, SOLO P/N 29 

00 202, installed; and 

(3) Are certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 61: Propellers. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Instead of the hub normally used which 

carries the starter ring gear and the hub for 

the tooth belt a slip-clutch can be mounted. 

The unit contains the hub for the tooth belt 

and the starter ring gear. Occurrences during 

service have shown that under bad 

conditions excessive wear on several parts of 

the clutch can occur. In order to avoid further 

damages the affected parts of the slip clutch 

on the engines SOLO 2 625 01 and SOLO 2 

652 02 have to be inspected and replaced, if 

necessary. In order to check the condition of 

the clutch on all engines SOLO 2 625 in 

future, additional procedures are installed 

and additional inspection terms are 

introduced. The cover place in front of the 

slip clutch has to be replaced by a stronger 

plate with the No. 2042888. 

The original Emergency AD has now been 

revised to indicate that the initial inspection 

of the installed slip-clutch is required when 

12.5 hours in operation have been 

accumulated. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Before further flight after September 10, 

2007 (the effective date of this AD): 

(i) Remove the cover plate of the slipclutch; 

(ii) Inspect the friction pads for wear. 

Dimension in new condition is .335 inches 

(8.5 mm), the wear limit is .256 inches (6.5 

mm); 

(iii) Inspect the slip-clutch shoes on the 

contact surface to the hub for wear. The wear 

limit is .039 inches (1 mm); 

(iv) Replace any parts found to be outside 

the wear limit; and 

(v) Assemble the slip-clutch with a new 

cover plate, P/N 2042888. 

(2) Every 12.5 hours time-in-service (TIS) 

after doing the actions required by paragraph 

(f)(1) of this AD, repetitively inspect the slipclutch and replace any parts found to be 

outside the wear limit before further flight 

after the inspection in which the part(s) 

exceeds the specified limit. 

(3) Every 25 hours TIS after September 10, 

2007 (the effective date of this AD), inspect 

the tiltplay of the clutch drum on the hub for 

excessive play. 

(i) With the tooth belt released, measure 

the play in the axial direction on the starter 

gear. The play limit is .024 inches (0.6 mm); 

and 

(ii) Before further flight after any 

inspection in which excessive play is found, 

replace with an FAA-approved part that is 

new or overhauled by the manufacturer. 

(4) Every 50 hours TIS after September 10, 

2007 (the effective date of this AD), replace 

the slip-clutch with an FAA-approved part 

that is new or overhauled by the 

manufacturer. 

(5) As of September 10, 2007 (the effective 

date of this AD), only install slip-clutch cover 

plate P/N 2042888. 

(6) Each time before the slip-clutch is 

mounted, degrease the taper of the crankshaft 

and the hub of the clutch with thinner 

following the instructions in the service 

bulletin specified in paragraph (f)(7) of this 

AD. The pound inches equivalent to 120 Nm 

is 1062.1. 

(7) Do all actions required by this AD 

following SOLO Kleinmotoren GmbH Service 

Bulletin Nr. 4600–2–2, dated December 27, 

2006. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

FAA, ATTN: Gregory Davison, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4130; fax: (816) 

329–4090, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 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 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 2120π0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency (EASA) Emergency AD No. 

2007–0001R1–E, dated January 10, 2007, and 

SOLO Kleinmotoren GmbH Service Bulletin 

Nr. 4600–2–2, dated December 27, 2006, for 

related information. 

Material Incorporated by Reference 

(i) You must use SOLO Kleinmotoren 

GmbH Service Bulletin Nr. 4600–2–2, dated 

December 27, 2006, 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 SOLO Kleinmotoren GmbH, 

Customer Support, 71050 Sindelfingen, 

Germany; telephone: +49–(0) 7031–301–210; 

fax: +49–(0) 7031–301–136; e-mail: 

wolfgang.emmerich@solo-germany.com. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust St., Room 506, Kansas 

City, Missouri 64016; or 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/federalπ

register/cfr/ibr-locations.html. 

Issued in Kansas City, Missouri on August 

14, 2007. 

Terry L. Chasteen, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 07–4090 Filed 8–20–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28971; Directorate 

Identifier 2007–SW–32–AD; Amendment 39–

15163; AD 2007–17–05] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Model S92–A 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for 

Sikorsky Aircraft Corporation (Sikorsky) 

Model S92–A helicopters. This action 

requires, within a specified time, 

borescope inspecting a certain partnumbered tail rotor pitch change shaft 

and bearing assembly (shaft and bearing 

assembly) and also inspecting after any 

installation. This amendment is 

prompted by an incident involving 

failure of a shaft and bearing assembly 

and servo clevis shaft resulting in loss 

of tail rotor control. The actions 

specified in this AD are intended to 

prevent failure of a shaft and bearing 

assembly, loss of tail rotor pitch and 

yaw control, and subsequent loss of 

control of a helicopter. 

DATES: Effective August 21, 2007. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of August 21, 

2007. 

Comments for inclusion in the Rules 

Docket must be received on or before 

October 22, 2007. 


rmajette on PROD1PC64 with RULES