61722 Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations 

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: 

■ a. Removing airworthiness directives 

(AD) 2001–18–06, Amendment 39– 

12432 (66 FR 47575, September 13, 

2001) (‘‘AD 2001–18–06’’); and AD 

2008–22–16, Amendment 39–15712 (73 

FR 63629, October 27, 2008) (‘‘AD 

2008–22–16’’), and 

■ b. Adding the following new AD: 

2015–20–09 General Electric Company: 

Amendment 39–18288; Docket No. 

FAA–2008–0808; Directorate Identifier 

2008–NE–18–AD. 

(a) Effective Date 

This AD is effective November 18, 2015. 

(b) Affected ADs 

This AD replaces AD 2001–18–06 and AD 

2008–22–16. 

(c) Applicability 

This AD applies to all General Electric 

Company (GE) CT58–100–2, CT58–110–1, 

CT58–110–2, CT58–140–1, and CT58–140–2 

turboshaft engines. 

(d) Unsafe Condition 

This AD was prompted by recalculation of 

life for parts installed on engines used in 

Utility operations, and a reduced life for 

compressor spools in all operations. We are 

issuing this AD to prevent failure of lifelimited rotating parts, uncontained part 

release, damage to the engine, and damage to 

the aircraft. 

(e) Compliance 

Do the actions required by this AD, unless 

already done. 

(1) Calculating Cyclic Life Consumption 

Re-calculate the cycles-since-new for all 

compressor spools, and for life-limited 

rotating parts other than compressor spools 

used in Utility operations. Use paragraphs 

3.A.(1) and 3.B.(1) in the Accomplishment 

Instructions of GE CT58 Alert Service 

Bulletin (ASB) No. SB 72–A0162, Revision 

16, dated January 7, 2015, to perform the 

calculations. 

(2) Removal of Compressor Spools 

After the effective date of this AD, remove 

compressor spools, part numbers (P/Ns) 

5124T94G02, 6010T57G04, 6010T57G07, and 

6010T57G08 from service, before reaching 

the life limits specified in paragraph 4.A., 

Appendix A, in GE CT58 ASB No. SB 72– 

A0162, Revision 16, dated January 7, 2015, 

as re-calculated per paragraph (e)(1) of this 

AD. 

(3) Removal of Rotating Parts Used in Utility 

Operations Other Than Compressor Spools 

After the effective date of this AD, remove 

from service any life-limited rotating part 

used in Utility operations, other than the 

compressor spools with P/Ns listed in 

paragraph (e)(2) of this AD, that exceeds its 

life limit as re-calculated per paragraph (e)(1) 

of this AD. Use Tables I, II, III, and IV in 

paragraphs 3.D. through 3.G. in the 

Accomplishment Instructions in GE CT58 

ASB No. SB 72–A0162, Revision 16, dated 

January 7, 2015, and paragraph 4.D., 

Appendix A of this GE CT58 ASB, to 

determine when to remove these parts. 

(4) Removal of Rotating Parts Not Used in 

Utility Operations Other Than Compressor 

Spools 

After the effective date of this AD, remove 

from service any life-limited rotating part not 

used in Utility operations, other than the 

compressor spools with P/Ns listed in 

paragraph (e)(2) of this AD, that exceeds its 

life limit. Use Tables I, II, III, and IV in 

paragraphs 3.D. through 3.G. in the 

Accomplishment Instructions in GE CT58 

ASB No. SB 72–A0162, Revision 16, dated 

January 7, 2015, and paragraph 4.C., 

Appendix A of this GE CT58 ASB, to 

determine when to remove these parts. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(g) Related Information 

For more information about this AD, 

contact Christopher McGuire, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7120; fax: 781–238– 

7199; email: chris.mcguire@faa.gov. 

(h) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) General Electric Company (GE) CT58 

Alert Service Bulletin No. SB 72–A0162, 

Revision 16, dated January 7, 2015. 

(ii) Reserved. 

(3) For GE service information identified in 

this AD, contact General Electric Company, 

GE Aviation, Room 285, One Neumann Way, 

Cincinnati, OH 45215; phone: 513–552–3272; 

email: aviation.fleetsupport@ge.com. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 12 

New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(5) You may view this service information 

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/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

September 30, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–25719 Filed 10–13–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3224; Directorate 

Identifier 2015–CE–026–AD; Amendment 

39–18290; AD 2015–20–11] 

RIN 2120–AA64 

Airworthiness Directives; SchemppHirth Flugzeugbau GmbH Sailplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Schempp-Hirth Flugzeugbau GmbH 

Models Duo Discus and Duo Discus T 

powered sailplanes. 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 excessive load on the air 

brake system. We are issuing this AD to 

require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective November 

18, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 18, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3224; or in person at 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 service information identified in 

this AD, contact Schempp-Hirth 

Flugzeugbau GmbH, Krebenstrasse 25, 

73230 Kirchheim/Teck, Germany; 

telephone: +49 7021 7298–0; fax: +49 

7021 7298–199; email: info@schempphirth.com; Internet: http:// 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations 61723 

www.schempp-hirth.com. You may 

view this 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

Docket No. FAA–2015–3224. 

FOR FURTHER INFORMATION CONTACT: Jim 

Rutherford, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 

329–4090; email: jim.rutherford@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to add an AD that would apply 

to Schempp-Hirth Flugzeugbau GmbH 

Models Duo Discus and Duo Discus T 

powered sailplanes. The NPRM was 

published in the Federal Register on 

August 4, 2015 (80 FR 46206). The 

NPRM proposed to correct an unsafe 

condition for the specified products and 

was based on mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country. The MCAI states: 

Operational experience shows that 

application of an excessive load on the air 

brake system may induce damage to the drive 

funnels in the fuselage and to the air brake 

bellcrank at the root rips of the wing. 

This condition, if not detected and 

corrected, could lead to an uncontrolled 

actuation of the air brakes (symmetric and 

asymmetric), possibly resulting in reduced 

control of the (powered) sailplane. 

To address this potential unsafe condition, 

Schempp-Hirth Flugzeugbau GmbH issued 

Technical Note (TN) 380–2, 396–17, 868–22 

and 890–14 (published as a single document) 

to provide inspection instructions. 

Consequently EASA issued AD 2015–0139 

to require to repetitive inspections of the air 

brake bellcrank, the air brake drive funnels 

and the airbrake control system, and 

replacement of damaged parts. 

Since that AD was issued, it was found that 

the drawing number of the reinforced air 

brake drive funnel was incorrectly stated in 

the original issue of the Schempp-Hirth TN. 

The wrongly referred drawing S14FB703 

refers to an existing part, different from air 

brake drive funnel and cannot be installed as 

a replacement part for air brake drive funnel. 

Consequently, Schempp-Hirth Flugzeugbau 

GmbH issued Revision 1 of TN 380–2, 396– 

17, 868–22 and 890–14, hearafter referenced 

to as ‘the revised TN’ in this AD. 

For the reasons described above, this AD 

is revised to require using the revised TN. 

The MCAI can be found in the AD 

docket on the Internet at http://

www.regulations.gov/ 

#!documentDetail;D=FAA-2015-3224- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 46206, August 4, 2015) 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 (80 FR 

46206, August 4, 2015) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 46206, 

August 4, 2015). 

Related Service Information Under 1 

CFR Part 51 

We reviewed Schempp-Hirth 

Flugzeugbau GmbH Technical Note No. 

380–2/396–17/868–22/890–14, Revision 

1, issued July 13, 2015 (published as a 

single document), and Working 

instruction for Technical Note No. 380– 

2/396–17/868–22/890–14, Ausgabe 

(English translation: issue) 1, Datum 

(English translation: dated) May 11, 

2015. The service information describes 

procedures for inspecting and replacing 

the airbrake bell crank and the airbrake 

drive funnels and inspecting the 

airbrake control system for proper 

clearance and making necessary 

adjustments. This service information is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

31 products of U.S. registry. We also 

estimate that it will take about 2 workhours per product to comply with the 

basic inspection requirements of this 

AD. The average labor rate is $85 per 

work-hour. 

Based on these figures, we estimate 

the cost of this portion of the AD on 

U.S. operators to be $5,270, or $170 per 

product. 

We estimate that it will take about 4 

work-hours per product to comply with 

the airbrake bell crank replacement 

requirement of this AD. The average 

labor rate is $85 per work-hour. 

Required parts will cost about $500 per 

product. 

Based on these figures, we estimate 

the cost of this portion of the AD on 

U.S. operators to be $26,040, or $840 per 

product. 

We estimate that it will take about 4 

work-hours per product to comply with 

the airbrake drive funnel replacement 

requirement of this AD. The average 

labor rate is $85 per work-hour. 

Required parts will cost about $500 per 

product. 

Based on these figures, we estimate 

the cost of this portion of the AD on 

U.S. operators to be $26,040, or $840 per 

product. 

In addition, we estimate that any 

necessary follow-on actions to make any 

necessary adjustments to the airbrake 

control system will take about 2 workhours for a cost of $170 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 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 


tkelley on DSK3SPTVN1PROD with RULES
61724 Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations 

(4) 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3224; 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 adding 

the following new AD: 

2015–20–11 Schempp-Hirth Flugzeugbau 

GmbH: Amendment 39–18290; Docket 

No. FAA–2015–3224; Directorate 

Identifier 2015–CE–026–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective November 18, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Schempp-Hirth 

Flugzeugbau GmbH Model Duo Discus 

powered sailplanes, serial numbers 1 through 

639, and Model Duo Discus T powered 

sailplanes, serial numbers 1 through 110 and 

112 through 247, certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 27: Flight Controls. 

(e) Reason 

This AD was prompted by 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 excessive 

load on the air brake system. We are issuing 

this AD to prevent uncontrolled actuation of 

the air brakes (symmetric or asymmetric), 

which could result in reduced control. 

(f) Actions and Compliance 

Unless already done, do the actions in 

paragraph (f)(1) through (f)(5) of this AD. 

(1) Within 40 days after November 17, 2015 

(the effective date of this AD) and repetitively 

thereafter at intervals not to exceed 100 hours 

time-in-service until the terminating 

replacement action required in paragraphs 

(f)(2) and (f)(3) of this AD (as applicable) is 

done, inspect the airbrake bell crank, the 

airbrake drive funnels, and the airbrake 

control system. 

(i) Inspect the airbrake bell crank and the 

airbrake drive funnels for cracks and damage 

following Action 1 in Schempp-Hirth 

Flugzeugbau GmbH Technical Note No. 380– 

2/396–17/868–22/890–14, Revision 1, issued 

July 13, 2015 (published as a single 

document). 

(ii) Inspect the airbrake control system for 

proper clearance following Paragraph 2.d. of 

Schempp-Hirth Flugzeugbau GmbH Working 

instruction for Technical Note No. 380–2/

396–17/868–22/890–14, Ausgabe (English 

translation: issue) 1, Datum (English 

translation: dated) May 11, 2015. 

(2) If cracks or damage is found on the 

airbrake bell cranks or the airbrake drive 

funnels during any inspection required in 

paragraph (f)(1) of this AD, before further 

flight, replace each cracked or damaged part 

with a reinforced part. Installing a reinforced 

part terminates the repetitive inspections 

required in paragraph (f)(1) of this AD for 

that part. 

(i) For replacement of the airbrake bell 

cranks, follow Picture 2: Reinforced version 

of airbrake bell crank according to HS 11– 

50.016, Revision a or later, in Schempp-Hirth 

Flugzeugbau GmbH Working instruction for 

Technical Note No. 380–2/396–17/868–22/

890–14, Ausgabe (English translation: issue) 

1, Datum (English translation: dated) May 11, 

2015. 

(ii) For replacement of the airbrake drive 

funnels, follow Picture 5: Airbrake drive 

funnel in fuselage ‘‘Reinforcement of airbrake 

drive funnel according to drawing S14RB703, 

Revision a, in Schempp-Hirth Flugzeugbau 

GmbH Working instruction for Technical 

Note No. 380–2/396–17/868–22/890–14, 

Ausgabe (English translation: issue) 1, Datum 

(English translation: dated) May 11, 2015. 

(3) If no cracks or damage were found on 

the airbrake bell cranks or the airbrake drive 

funnels during any inspection required in 

paragraph (f)(1) of this AD, within 12 months 

after November 17, 2015 (the effective date of 

this AD), replace each of the airbrake bell 

cranks and airbrake drive funnels with a 

reinforced part. These replacements 

terminate the repetitive inspections required 

in paragraph (f)(1) of this AD. 

(i) For replacement of the airbrake bell 

cranks, follow Picture 2: Reinforced version 

of airbrake bell crank according to HS 11– 

50.016, Revision a or later, in Schempp-Hirth 

Flugzeugbau GmbH Working instruction for 

Technical Note No. 380–2/396–17/868–22/

890–14, Ausgabe (English translation: issue) 

1, Datum (English translation: dated) May 11, 

2015. 

(ii) For replacement of the airbrake drive 

funnels, follow Picture 5: Airbrake drive 

funnel in fuselage, ‘‘Reinforcement of 

airbrake drive funnel according to drawing 

S14RB703, Revision a,’’ in Schempp-Hirth 

Flugzeugbau GmbH Working instruction for 

Technical Note No. 380–2/396–17/868–22/

890–14, Ausgabe (English translation: issue) 

1, Datum (English translation: dated) May 11, 

2015. 

(4) If the airbrake control system is found 

to not have proper clearance during the 

inspection required in paragraph (f)(1) of this 

AD, before further flight, make all necessary 

corrective adjustments following Paragraph 

2.d. of Schempp-Hirth Flugzeugbau GmbH 

Working instruction for Technical Note No. 

380–2/396–17/868–22/890–14, Ausgabe 

(English translation: issue) 1, Datum (English 

translation: dated) May 11, 2015. 

(5) As of November 17, 2015 (the effective 

date of this AD), only install an airbrake bell 

crank or an airbrake drive funnel that 

corresponds to Picture 2: Reinforced version 

of airbrake bell crank according to HS 11– 

50.016, Revision a or later, and Picture 5: 

Airbrake drive funnel in fuselage, 

‘‘Reinforcement of airbrake drive funnel 

according to drawing S14RB703, Revision a,’’ 

in Schempp-Hirth Flugzeugbau GmbH 

Working instruction for Technical Note No. 

380–2/396–17/868–22/890–14, Ausgabe 

(English translation: issue) 1, Datum (English 

translation: dated) May 11, 2015, as 

applicable. 

(g) Other FAA AD Provisions 

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: Jim Rutherford, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 329– 

4090; email: jim.rutherford@faa.gov. Before 

using any approved AMOC on any sailplane 

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. 

(h) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No. 2015–0139R1, dated 

July 15, 2015, for related information. You 

may examine the MCAI on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA-2015-3224-0002. 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations 61725 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Schempp-Hirth Flugzeugbau GmbH 

Technical Note No. 380–2/396–17/868–22/

890–14, Revision 1, issued July 13, 2015 

(published as a single document). 

(ii) Schempp-Hirth Flugzeugbau GmbH 

Working instruction for Technical Note No. 

380–2/396–17/868–22/890–14, Ausgabe 

(English translation: issue) 1, Datum (English 

translation: dated) May 11, 2015. 

(3) For Schempp-Hirth Flugzeugbau GmbH 

service information identified in this AD, 

contact Schempp-Hirth Flugzeugbau GmbH, 

Krebenstrasse 25, 73230 Kirchheim/Teck, 

Germany; telephone: +49 7021 7298–0; fax: 

+49 7021 7298–199; email: info@schempphirth.com; Internet: http://www.schempphirth.com. 

(4) You may view this 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. In 

addition, you can access this service 

information on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2015–3224. 

(5) You may view this 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/cfr/ibrlocations.html. 

Issued in Kansas City, Missouri, on 

October 1, 2015. 

Melvin Johnson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–25710 Filed 10–13–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4085; Directorate 

Identifier 2015–CE–033–AD; Amendment 

39–18292; AD 2015–20–13] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Piper Aircraft, Inc. Models PA–28–161, 

PA–28–181, and PA–28R–201 airplanes. 

This AD requires inspecting the right 

wing rib at wing station 140.09 for 

cracks and taking necessary corrective 

action. This AD was prompted by a 

report of cracks found in the wing rib 

bead radius that were formed during 

production. We are issuing this AD to 

correct the unsafe condition on these 

products. 

DATES: This AD is effective October 29, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 29, 2015. 

We must receive comments on this 

AD by November 30, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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. 

For service information identified in 

this AD, contact Piper Aircraft, Inc., 

Customer Service, 2926 Piper Drive, 

Vero Beach, Florida 32960; telephone: 

(877) 879–0275; fax: none; email: 

customer.service@piper.com; Internet: 

www.piper.com. You may review 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. It is also available on the Internet 

at http://www.regulations.gov by 

searching for locating Docket No. FAA– 

2015–4085. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

4085; 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 (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Gregory ‘‘Keith’’ Noles, Aerospace 

Engineer, FAA, Atlanta Aircraft 

Certification Office, 1701 Columbia 

Avenue, College Park, Georgia 30337; 

phone: (404) 474–5551; fax: (404) 474– 

5606; email: gregory.noles@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received a report from Piper 

Aircraft, Inc. of a production quality 

control problem on certain Models PA– 

28–161, PA–28–181, and PA–28R–201 

airplanes. A change in production 

tooling and processes caused cracks to 

form along the edge of rib stiffening 

beads during manufacture. These cracks 

cause reduced structural integrity of the 

wing, which results in the inability of 

the wing rib to carry ultimate load. 

This condition, if not corrected, could 

result in reduced structural integrity of 

the wing with consequent loss of 

control. We are issuing this AD to 

correct the unsafe condition on these 

products. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Piper Aircraft, Inc. 

Service Bulletin No. 1279, dated August 

26, 2015. The service bulletin describes 

procedures for inspecting the right wing 

rib at wing station 140.09 for cracks and 

for obtaining an FAA-approved repair if 

cracks are found. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section of this AD. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires accomplishing the 

actions specified in the service 

information described previously. 

FAA’s Justification and 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 cracks in the wing rib, if 

not detected and corrected immediately, 


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