22298 Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations 

2, 3, 4, 5, and 7 of BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

167, including Appendix 2, Revision 4, dated 

June 10, 2010, and at intervals not to exceed 

4,600 flight cycles for areas specified in 

Drawings 1, 6, 8, and 9 of BAE Systems 

(Operations) Limited Inspection Service 

Bulletin ISB.53–167, including Appendix 2, 

Revision 4, dated June 10, 2010. Doing the 

inspection required by this paragraph 

terminates the requirements of paragraph (g) 

of this AD for that airplane. 

(1) Before the accumulation of 16,000 total 

flight cycles. 

(2) Within 2,000 flight cycles after the 

effective date of this AD. 

(3) Within the applicable times specified in 

paragraphs (j)(3)(i) and (j)(3)(ii) of this AD. 

(i) For areas specified in Drawings 2, 3, 4, 

5, and 7 of BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

167, including Appendix 2, Revision 4, dated 

June 10, 2010: Within 3,600 flight cycles after 

the last inspection done in accordance with 

paragraph (g) of this AD. 

(ii) For areas specified in Drawings 1, 6, 8, 

and 9 of BAE Systems (Operations) Limited 

Inspection Service Bulletin ISB.53–167, 

including Appendix 2, Revision 4, dated June 

10, 2010: Within 4,600 flight cycles after the 

last inspection done in accordance with 

paragraph (g) of this AD. 

(k) For Model Avro 146–RJ airplanes: At 

the latest of the times specified in paragraph 

(k)(1), (k)(2), and (k)(3) of this AD, do an 

external eddy current inspection of the 

forward fuselage skin to detect cracking, in 

accordance with the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

167, including Appendix 2, Revision 4, dated 

June 10, 2010. Repeat the inspection 

thereafter at intervals not to exceed 2,400 

flight cycles for areas specified in Drawings 

2, 3, 4, 5, and 7 of BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

167, including Appendix 2, Revision 4, dated 

June 10, 2010, and 3,000 flight cycles for 

areas specified in Drawings 1, 6, 8, and 9 of 

BAE Systems (Operations) Limited 

Inspection Service Bulletin ISB.53–167, 

including Appendix 2, Revision 4, dated June 

10, 2010. Doing the inspection required by 

this paragraph terminates the requirements of 

paragraph (g) of this AD for that airplane. 

(1) Before the accumulation of 10,000 total 

flight cycles. 

(2) Within 1,000 flight cycles after the 

effective date of this AD. 

(3) Within the applicable times specified in 

paragraphs (k)(3)(i) and (k)(3)(ii) of this AD. 

(i) For areas specified in Drawings 2, 3, 4, 

5, and 7 of BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

167, including Appendix 2, Revision 4, dated 

June 10, 2010: Within 3,600 flight cycles after 

the last inspection done in accordance with 

paragraph (g) of this AD. 

(ii) For areas specified in Drawings 1, 6, 8, 

and 9 of BAE Systems (Operations) Limited 

Inspection Service Bulletin ISB.53–167, 

including Appendix 2, Revision 4, dated June 

10, 2010: Within 4,600 flight cycles after the 

last inspection done in accordance with 

paragraph (g) of this AD. 

(l) If any cracking is found during any 

inspection required by paragraph (j) or (k) of 

this AD, before further flight, accomplish the 

repair in accordance with a method approved 

by the FAA or EASA (or its delegated agent). 

Repair of an airplane in accordance with the 

requirements of this paragraph of this AD 

does not constitute terminating action for the 

inspection requirements of this AD. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(m) Inspections done before the effective 

date of this AD in accordance with BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.53–167, including 

Appendix 2, Revision 2, dated November 17, 

2008; or Revision 3, dated June 17, 2009; are 

acceptable for compliance with the 

corresponding requirements of paragraphs (j) 

and (k) of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(n) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to Attn: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1175; fax (425) 

227–1149. Information may be e-mailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(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. 

Related Information 

(o) Refer to MCAI EASA Airworthiness 

Directive 2009–0070R1, dated July 2, 2010; 

BAE Systems (Operations) Limited 

Modification Service Bulletin ISB.53–167, 

including Appendix 2, Revision 1, dated May 

18, 2004; and BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

167, including Appendix 2, Revision 4, dated 

June 10, 2010; for related information. 

Material Incorporated by Reference 

(p) You must use BAE Systems 

(Operations) Limited Modification Service 

Bulletin ISB.53–167, including Appendix 2, 

Revision 1, dated May 18, 2004; and BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.53–167, including 

Appendix 2, Revision 4, dated June 10, 2010; 

as applicable; 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 

BAE Systems (Operations) Limited 

Modification Service Bulletin ISB.53–167, 

including Appendix 2, Revision 4, dated June 

10, 2010, under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of BAE Systems (Operations) 

Limited Modification Service Bulletin 

ISB.53–167, including Appendix 2, Revision 

1, dated May 18, 2004, on August 2, 2005 (70 

FR 37022, June 28, 2005). 

(3) For service information identified in 

this AD, contact BAE SYSTEMS 

(OPERATIONS) LIMITED, Customer 

Information Department, Prestwick 

International Airport, Ayrshire, KA9 2RW, 

Scotland, United Kingdom; telephone +44 

1292 675207; fax +44 1292 675704; e-mail 

RApublications@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(5) You may also review copies of the 

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/

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on April 4, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–8667 Filed 4–20–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1243; Directorate 

Identifier 2010–CE–058–AD; Amendment 

39–16626; AD 2011–06–02] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company (Cessna) Model 172 

Airplanes Modified by Supplemental 

Type Certificate (STC) SA01303WI 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

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Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations 22299 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

installing a full authority digital engine 

control (FADEC) backup battery, 

replacing the supplement pilot’s 

operating handbook and FAA approved 

airplane flight manual, and replacing 

the FADEC backup battery every 12 

calendar months. This AD was 

prompted by an incident where an 

airplane experienced an in-flight engine 

shutdown caused by a momentary loss 

of electrical power to the FADEC. We 

are issuing this AD to prevent 

interruption of electrical power to the 

FADEC, which could result in an 

uncommanded engine shutdown. This 

failure could lead to a loss of engine 

power. 

DATES: This AD is effective May 26, 

2011. 

Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of May 26, 2011. 

ADDRESSES: For service information 

identified in this AD, contact Thielert 

Aircraft Engines Service GmbH, 

Platanenstra+e 14, D–09350 

Lichtenstein, Deutschland; telephone: 

+49 (37204) 696–1474; fax: +49 (37204) 

696–1910; Internet: http:// 

www.thielert.com/. You may review 

copies of 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. 

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 address for the 

Docket Office (phone: 800–647–5527) is 

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 FURTHER INFORMATION CONTACT: 

Richard Rejniak, Aerospace Engineer, 

Wichita Aircraft Certification Office 

(ACO), FAA, 1801 Airport Road, Room 

100; phone: (316) 946–4128; fax: (316) 

946–4107; e-mail: 

richard.rejniak@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to the 

specified products. That NPRM 

published in the Federal Register on 

December 15, 2010 (75 FR 78177). That 

NPRM proposed to require installing a 

FADEC backup battery, replacing the 

supplement pilot’s operating handbook 

and FAA approved airplane flight 

manual, and replacing the FADEC 

backup battery every 12 calendar 

months. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the proposal and the FAA’s 

response to the comment. 

Request 

Rob van den Bosch, Thielert Aircraft 

Engines GmbH, when referring to the 

airplane maintenance manual (AMM) 

and airplane flight manual (AFM) 

supplement, recommended adding ‘‘or 

later approved issue or revision.’’ The 

commenter reasoned that future changes 

to the AMM or AFM would require 

additional work by the FAA to update 

the AD. 

We disagree with the 

recommendation. If we would include 

such language, it would violate 

regulation, specifically 1 CFR 51.1, 

paragraph (f), which states 

‘‘Incorporation by reference of a 

publication is limited to the edition of 

the publication that is approved. Future 

amendments or revisions of the 

publication are not included.’’. Service 

information that we incorporate by 

reference in an AD is often revised after 

we issue the AD. We can approve later 

revisions of service information as an 

alternative method of compliance 

(AMOC). 

The FAA is not changing this AD as 

a result of this comment. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, 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 for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Costs of Compliance 

We estimate that this AD affects 14 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

For airplanes with a 14-volt battery system; installation of 

a 14-volt FADEC backup battery.

24 work-hours × $85 per 

hour = $2,040.

$820 $2,860 $14,300 

For airplanes with a 28-volt battery system; installation of 

a 28-volt FADEC backup battery.

24 work-hours × $85 per 

hour = $2,040.

1,160 3,200 28,800 

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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

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22300 Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations 

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), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(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. 

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 airworthiness 

directive (AD): 

2011–06–02 Cessna Aircraft Company: 

Amendment 39–16626; Docket No. 

FAA–2010–1243; Directorate Identifier 

2010–CE–058–AD. 

Effective Date 

(a) This AD is effective May 26, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all serial numbers 

of the following airplanes, certified in any 

category, that are modified by Supplemental 

Type Certificate (STC) SA01303WI, as 

identified in Table 1 of this AD: 

TABLE 1 

Model Engine Group 

(1) 172F, 172G, 172H, 172I, 172K, 172L, 172M, F172F, F172G, F172H, F172K, F172L, and F172M .. TAE 125–01 ................... 1 

(2) 172F, 172G, 172H, 172I, 172K, 172L, 172M, F172F, F172G, F172H, F172K, F172L, and F172M .. TAE 125–02–99 ............. 2 

(3) 172N, 172P, F172N, and F172P .......................................................................................................... TAE 125–01 ................... 3 

(4) 172N, 172P, F172N, and F172P .......................................................................................................... TAE 125–02–99 ............. 4 

(5) 172R and 172S ..................................................................................................................................... TAE 125–01 ................... 5 

(6) 172R and 172S ..................................................................................................................................... TAE 125–02–99 ............. 6 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 72: Engine. 

Unsafe Condition 

(e) This AD was prompted by an incident 

where an airplane experienced an in-flight 

engine shutdown caused by a momentary 

loss of electrical power to the FADEC. We are 

issuing this AD to prevent interruption of 

electrical power to the FADEC, which could 

result in an uncommanded engine shutdown. 

This failure could lead to a loss of engine 

power. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Actions Compliance Procedures 

(1) For all airplanes: Modify the engine electrical system by installing a backup battery 

system and associated wiring and circuitry. 

Within the next 100 hours time-in-service after 

May 26, 2011 (the effective date of this AD) 

or within 30 days after May 26, 2011 (the 

effective date of this AD), whichever occurs 

first. 

(i) For groups 1, 3, and 5 airplanes: Follow 

Thielert Aircraft Engines GmbH Service Bulletin TM TAE 601–0007, Revision 8, dated 

October 14, 2010. 

(ii) For groups 2, 4, and 6 airplanes: Follow 

Thielert Aircraft Engines GmbH Service Bulletin TM TAE 601–1001 P1, Revision 8, 

dated October 14, 2010. 

(2) For all airplanes: Replace the FADEC 

backup battery. 

Within 12 calendar months after doing the 

modification required in paragraph (f)(1) of 

this AD and repetitively thereafter within 12 

calendar months after the previous replacement. 

(i) For groups 1, 3, and 5 airplanes: Follow 

Page 8, Revison 2, dated October 8, 2010, 

from Chapter 24 ‘‘Electrical Power’’ (Chapter 20–AMM–24–01–US) of Thielert Aircraft 

Engines GmbH Supplement Airplane Maintenance Manual Cessna 172 & Reims F172 

TAE 125–01, Doc. No.: AMM–20–01 (US– 

Version) Version: 2/4. 

(ii) For groups 2, 4, and 6 airplanes: Follow 

page 7, Revision 1, dated October 8, 2010, 

from Chapter 24 ‘‘Electrical Power’’ (Chapter 20–AMM–24–02–US) of Thielert Aircraft 

Engines GmbH Supplement Airplane Maintenance Manual Cessna 172 & Reims F172 

CENTURION 2.0 (TAE 125–02–99), Doc. 

No.: AMM–20–02 (US–Version) Version: 1/ 

1. 

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Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations 22301 

Actions Compliance Procedures 

(3) For groups 1 and 2 airplanes: Incorporate 

Thielert Aircraft Engines GmbH ‘‘Supplemental Airplane Flight Manual or Pilot’s Operating Handbook and FAA Approved Airplane 

Flight Manual Supplement (as applicable) for 

the Cessna 172 F, G, H, I, K, L, M, Reims 

Cessna F172 F, G, H, K, L, M, Equipped with 

TAE 125–01 or TAE 125–02–99 Installation,’’ 

Issue 2–1, TAE–Nr.: 20–0310–21042, dated 

October 4, 2010, into the pilot’s operating 

handbook. 

Before further flight after doing the modification required in paragraph (f)(1) of this AD. Not applicable. 

(4) For groups 3 and 4 airplanes: Incorporate 

Thielert Aircraft Engines GmbH ‘‘Supplemental Airplane Flight Manual or Pilot’s Operating Handbook and FAA Approved Airplane 

Flight Manual Supplement (as applicable) for 

the Cessna 172 N & P, Reims Cessna F172 

N & P, Equipped with TAE 125–01 or TAE 

125–02–99 Installation,’’ Issue 2–1, TAE–Nr.: 

20–0310–20042, dated October 4, 2010, into 

the pilot’s operating handbook. 

Before further flight after doing the modification required in paragraph (f)(1) of this AD. Not applicable. 

(5) For groups 5 and 6 airplanes: Incorporate 

Thielert Aircraft Engines GmbH ‘‘Supplemental Pilot’s Operating Handbook and FAA 

Approved Airplane Flight Manual Supplement 

for the Cessna 172 R & S, Equipped with 

TAE 125–01 or TAE 125–02–99 Installation,’’ 

Issue 2–1, TAE–Nr.: 20–0310–22042, dated 

October 4, 2010, into the pilot’s operating 

handbook. 

Before further flight after doing the modification required in paragraph (f)(1) of this AD. Not applicable. 

Alternative Methods of Compliance 

(AMOCs) 

(g)(1) The Manager, Wichita Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your Principal Maintenance Inspector 

or Principal Avionics Inspector, as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

Related Information 

(h) For more information about this AD, 

contact Richard Rejniak, Aerospace Engineer, 

Wichita ACO, FAA, 1801 Airport Road, 

Room 100; phone: (316) 946–4128; fax: (316) 

946–4107; e-mail: richard.rejniak@faa.gov. 

Material Incorporated by Reference 

(i) You must use the following information 

to do the actions required by this AD, unless 

the AD specifies otherwise: 

(1) Thielert Aircraft Engines GmbH Service 

Bulletin TM TAE 601–0007, Revision 8, 

dated October 14, 2010; 

(2) Thielert Aircraft Engines GmbH Service 

Bulletin TM TAE 601–1001 P1, Revision 8, 

dated October 14, 2010; 

(3) Chapter 24 ‘‘Electrical Power’’ (Chapter 

20–AMM–24–01–US), Issue 2, Revision No.: 

2, dated October 8, 2010, of Thielert Aircraft 

Engines GmbH Supplement Airplane 

Maintenance Manual Cessna 172 & Reims 

F172 TAE 125–01, Doc. No.: AMM–20–01 

(US–Version) Version: 2/4; 

(4) Chapter 24 ‘‘Electrical Power’’ (Chapter 

20–AMM–24–02–US), Issue: 1, Rev. No: 1, 

dated October 8, 2010, of Thielert Aircraft 

Engines GmbH Supplement Airplane 

Maintenance Manual Cessna 172 & Reims 

F172 CENTURION 2.0 (TAE 125–02–99), 

Doc. No.: AMM–20–02 (US–Version) 

Version: 1/1; 

(5) Thielert Aircraft Engines GmbH 

‘‘Supplemental Airplane Flight Manual or 

Pilot’s Operating Handbook and FAA 

Approved Airplane Flight Manual 

Supplement (as applicable) for the Cessna 

172 F, G, H, I, K, L, M, Reims Cessna F172 

F, G, H, K, L, M, Equipped with TAE 125– 

01 or TAE 125–02–99 Installation,’’ Issue 2– 

1, TAE–Nr.: 20–0310–21042, dated October 

4, 2010; and 

(6) Thielert Aircraft Engines GmbH 

‘‘Supplemental Airplane Flight Manual or 

Pilot’s Operating Handbook and FAA 

Approved Airplane Flight Manual 

Supplement (as applicable) for the Cessna 

172 N & P, Reims Cessna F172 N & P, 

Equipped with TAE 125–01 or TAE 125–02– 

99 Installation,’’ Issue 2–1, TAE–Nr.: 20– 

0310–20042, dated October 4, 2010; and 

(7) Thielert Aircraft Engines GmbH 

‘‘Supplemental Pilot’s Operating Handbook 

and FAA Approved Airplane Flight Manual 

Supplement for the Cessna 172 R & S, 

Equipped with TAE 125–01 or TAE 125–02– 

99 Installation,’’ Issue 2–1, TAE–Nr.: 20– 

0310–22042, dated October 4, 2010. 

(j) 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. 

(3) For service information identified in 

this AD, contact Thielert Aircraft Engines 

Service GmbH, Platanenstra+e 14, D–09350 

Lichtenstein, Deutschland; telephone: +49 

(37204) 696–1474; fax: +49 (37204) 696– 

1910; Internet: http://www.thielert.com/. 

(4) You may review copies of the 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. 

(5) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, 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 April 

5, 2011. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–8564 Filed 4–20–11; 8:45 am] 

BILLING CODE 4910–13–P 

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