18380 Federal Register / Vol. 72, No. 70 / Thursday, April 12, 2007 / Rules and Regulations 

Installation of Cockpit Placard for RPM 

Restriction 

(f) Within 10 hours time-in-service (TIS) 

after the effective date of this AD, install a 

placard on the instrument panel as close to 

the tachometer as possible, that states, in 1⁄8

inch-high or higher characters, ‘‘Continuous 

operation between 2,350–2,450 RPM at or 

above 24′′ manifold pressure is prohibited’’. 

The placard shall have red letters, on a 

white contrasting background with a red 

border. For example: 

Continuous operation 

between 2,350–2,450 RPM 

at or above 24′′ manifold 

pressure is prohibited 

Propellers With Unknown Total Hours TIS, 

or 10,000 or More Hours Total TIS on the 

Effective Date of This AD 

(g) For propellers that the total TIS is 

unknown, or that have 10,000 or more hours 

total TIS on the effective date of this AD, 

remove the propeller from service within 50 

hours TIS after the effective date of this AD. 

Propellers With Fewer Than 10,000 Hours 

Total TIS on the Effective Date of This AD 

(h) For propellers with fewer than 10,000 

total hours TIS on the effective date of this 

AD, do the following: 

(1) Perform an inspection of the propeller 

blades and repair if necessary, within 100 

hours after the effective date of this AD, 

using paragraphs 2.B. through 2.F. of 

Accomplishment Instructions of McCauley 

Propeller Systems Alert Service Bulletin 

(ASB) No. ASB248, dated April 19, 2005. 

(2) At the next propeller overhaul or next 

major propeller disassembly, life-limit-stamp 

the letter ‘‘L’’ on the propeller hub and 

blades, using paragraph 3 of 

Accomplishment Instructions of McCauley 

Propeller Systems ASB No. ASB248, dated 

April 19, 2005. 

(3) Thereafter, within every 100 hours TIS 

or at next annual inspection, whichever 

occurs first, inspect, and repair if necessary, 

the propeller blades using paragraphs 2.B. 

through 2.F. of Accomplishment Instructions 

of McCauley Propeller Systems ASB No. 

ASB248, dated April 19, 2005. 

(4) Remove the propeller from service upon 

reaching the life limit of 10,000 hours total 

TIS. 

Alternative Methods of Compliance 

(i) The Manager, Wichita Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(j) Contact Jeff D. Janusz, Aerospace 

Engineer, Wichita Aircraft Certification 

Office, Small Airplane Directorate, 1801 

Airport Road, Room 100, Wichita, KS 67209; 

telephone: 316–946–4148, fax: 316–946– 

4107, for more information about this AD. 

Material Incorporated by Reference 

(k) You must use McCauley Propeller 

Systems Alert Service Bulletin No. ASB248, 

dated April 19, 2005, to perform the actions 

required by this AD. The Director of the 

Federal Register approved the incorporation 

by reference of this service bulletin in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Contact McCauley Propeller Systems, 

P.O. Box 7704, Wichita, Kansas; telephone 

(800) 621–7767, for a copy of this service 

information. You may review copies at the 

FAA, New England Region, Office of the 

Regional Counsel, 12 New England Executive 

Park, Burlington, MA; or 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/federalregister/cfr/ibr-locations.html. 

Issued in Burlington, Massachusetts, on 

April 4, 2007. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–6831 Filed 4–11–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27709; Directorate 

Identifier 2007–CE–028–AD; Amendment 

39–15020; AD 2007–08–03] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Models 172R, 172S, 

182T, T182T, 206H, and T206H 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) to 

supersede AD 2006–17–04, which 

applies to certain Cessna Aircraft 

Company (Cessna) Models 172R, 172S, 

182T, T182T, 206H, and T206H 

airplanes. AD 2006–17–04 currently 

requires you to inspect the two end 

fittings on each of the flexible fuel hoses 

located in the engine compartment for 

the correct torque values, and, if any 

incorrect torque values are found during 

the inspection, tighten the hose end 

fittings to the correct torque values. This 

AD results from four reports of loose 

fuel lines connected to the fuel servo or 

fuel flow transducer. Two reports were 

of in-flight engine failure on a Model 

T182T airplane. A third report was of 

in-flight engine failure on a Model 206H 

airplane. A fourth report was of a Model 

172S airplane losing engine power on 

final approach. Consequently, this AD 

would require you to establish the 

correct torque values of the end fittings 

on fuel hoses for certain Cessna Models 

172R, 172S, 182T, T182T, 206H, and 

T206H airplanes. This AD clarifies that 

the torque values need to be physically 

established and visual inspection only 

is not sufficient. We are issuing this AD 

to detect and correct potential loss of 

fuel flow, which may result in partial or 

complete loss of engine power and/or 

uncontrolled engine compartment fire 

due to fuel leakage forward of the 

firewall. 

DATES: This AD becomes effective on 

May 2, 2007. 

On May 2, 2007 the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

We must receive any comments on 

this AD by June 11, 2007. 

ADDRESSES: Use one of the following 

addresses to comment on this AD. 

• DOT Docket Web site: Go to http:// 

dms.dot.gov and follow the instructions 

for sending your comments 

electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590– 

0001. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

To get the service information 

identified in this AD, contact The 

Cessna Aircraft Company, Product 

Support, P.O. Box 7706, Wichita, 

Kansas 67277–7706; telephone: (316) 

517–5800; facsimile: (316) 942–9006. 

To view the comments to this AD, go 

to http://dms.dot.gov. The docket 

number is FAA–2007–27709; 

Directorate Identifier 2007–CE–028–AD. 

FOR FURTHER INFORMATION CONTACT: 

Trenton Shepherd, Aerospace Engineer, 

Wichita ACO, 1801 Airport Road, Room 

100, Wichita, Kansas 67209; telephone: 

(316) 946–4143; fax: (316) 946–4107. 

SUPPLEMENTARY INFORMATION: 

Discussion 

One report of loose fuel hose 

connections to the fuel injector servo on 

a Cessna Model 172S airplane caused us 

to issue AD 2006–17–04, Amendment 

39–14725 (71 FR 47711, August 18, 

2006). AD 2006–17–04 on certain 

Cessna Models 172R, 172S, 182T, 

T182T, 206H, and T206H airplanes, 

currently requires you to: 

• Inspect the two end fittings on each 

of the flexible fuel hoses located in the 


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Federal Register / Vol. 72, No. 70 / Thursday, April 12, 2007 / Rules and Regulations 18381 

engine compartment for the correct 

torque values; and 

• Tighten the hose end fittings to the 

correct torque values, if any incorrect 

torque values are found during the 

inspection. 

Since issuing AD 2006–17–04, we 

have received four additional reports of 

loose fuel lines connected to the fuel 

servo or fuel flow transducer. Two 

reports were of in-flight engine failure 

on a Model T182T airplane. A third 

report was of in-flight engine failure on 

a Model 206H airplane. A fourth report 

was of a Model 172S airplane that lost 

engine power on final approach. 

In issuing AD 2006–17–04, our intent 

was for the torque values provided in 

Table 4 of the AD to be verified. 

However, the actions we specified in 

AD 2006–17–04 resulted in visual-only 

inspections being accomplished in some 

cases. Visual inspection of torque paint 

or putty is not sufficient to address the 

unsafe condition. This AD clarifies that 

the torque values need to be physically 

established. 

This condition, if not corrected, could 

result in loss of fuel flow resulting in 

partial or complete loss of engine power 

and/or uncontrolled engine 

compartment fire due to fuel leakage 

forward of the firewall. 

Relevant Service Information 

We reviewed Cessna Service Bulletin 

No. SB07–71–01, original issue dated 

March 2, 2007, Revision 1, dated March 

16, 2007. The service information 

describes procedures for a physical 

inspection of the fuel hose connections 

on each of the hoses by loosening each 

connection and then reapplying the 

correct torque value to make sure that 

they are correctly torqued. 

FAA’s Determination and Requirements 

of This AD 

We are issuing this AD because we 

evaluated all the information and 

determined the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. This AD requires you to 

establish the correct torque values of the 

end fittings on fuel hoses for certain 

Cessna Models 172R, 172S, 182T, 

T182T, 206H, and T206H airplanes. 

This AD clarifies that the torque values 

need to be physically established and 

visual inspection only is not sufficient. 

In preparing this rule, we contacted 

type clubs and aircraft operators to get 

technical information and information 

on operational and economic impacts. 

We did not receive any information 

through these contacts. If received, we 

would have included a discussion of 

any information that may have 

influenced this action in the rulemaking 

docket. 

FAA’s Determination of the Effective 

Date 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, 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 an 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments regarding this 

AD. Send your comments to an address 

listed under the ADDRESSES section. 

Include the docket number ‘‘Docket No. 

FAA–2007–27709; Directorate Identifier 

2007–CE–028–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD. We will consider all 

comments received by the closing date 

and may amend the AD in light 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 

concerning 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. 

Examining the AD Docket 

You may examine the AD docket that 

contains the AD, the regulatory 

evaluation, any comments received, and 

other information 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 

Docket Office (telephone (800) 647–

5227) is located at the street address 

stated 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 proposes to amend 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 Airworthiness Directive (AD) 

2006–17–04, Amendment 39–14725 (71 

FR 47711, August 18, 2006), and by 

adding a new AD to read as follows: 

2007–08–03 Cessna Aircraft Company: 

Amendment 39–15020; Docket No. 

FAA–2007–27709; Directorate Identifier 

2007–CE–028–AD. 

Effective Date 

(a) This AD becomes effective on May 2, 

2007. 


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18382 Federal Register / Vol. 72, No. 70 / Thursday, April 12, 2007 / Rules and Regulations 

Affected ADs 

(b) This AD supersedes AD 2006–17–04; 

Amendment 39–14725. 

Applicability 

(c) This AD applies to the following 

airplane models and serial numbers that are 

certificated in any category: 

TABLE 1.—APPLICABILITY

Model Serial Nos. 

(i) 172R .............. 17281244 through 17281364, 17281366 through 17281372, 17281374 through 17281376, and 17281379. 

(ii) 172S ............. 172S9809 through 172S10349, 172S10351 through 172S10374, 172S10376 through 172S10423, 172S10425 through 

172S10426, 172S10428 through 172S10430, 172S10432 through 172S10444, 172S10446 through 172S10450, and 

172S10452 through 172S10454. 

(iii) 182T ............ 18281527 through 18281889, 18281892, 18281895, 18281897, 18281899, 18281901, and 18281904. 

(iv) T182T .......... T18208381 through T18208659, T18208661, T18208663 through T18208678, T18208680 through T18208686, T18208689, 

and T18208690. 

(v) 206H ............. 20608231 through 20608285. 

(vi) T206H .......... T20608515 through T20608662, T20608664 through T20608697, T20608699 through T20608714, and T20608717. 

Unsafe Condition 

(d) This AD is the result of four reports of 

loose fuel lines connected to the fuel servo 

or fuel flow transducer. Two reports were of 

in-flight engine failure on a Model T182T 

airplane. A third report was of in flightengine failure on a Model 206H airplane. A 

fourth report was of a Model 172S airplane 

that lost engine power on final approach. We 

are issuing this AD to detect and correct 

potential loss of fuel flow, which may result 

in partial or complete loss of engine power 

and/or uncontrolled engine compartment fire 

due to fuel leakage forward of the firewall. 

Compliance 

(e) To address this problem, you must do 

the following, unless already done: 

TABLE 2.—ACTIONS, COMPLIANCE, AND PROCEDURES

Actions Compliance Procedures 

(1) For all airplanes not equipped with the 

Garmin G1000 System: Establish the correct 

torque values of the end fittings on each of 

the following hoses in the engine compartment: 

(i) Fuel strainer to engine fuel pump. 

(ii) Engine fuel pump to fuel injector servo 

(except T206H). 

Within the next 5 hours time-in-service (TIS) 

after May 2, 2007 (the effective date of this 

AD). 

Follow Cessna Service Bulletin No. SB07–71–

01, Revision 1, dated March 16, 2007; the 

procedures of the appendix to this AD; and 

the torque values from the table Torque 

Values for Hose End Fittings in the appendix to this AD. 

(iii) T206H only: Engine fuel pump to the 

union at the aft vertical cooling baffle. 

(iv) T206H only: Union at the aft vertical 

cooling baffle to the fuel injector servo. 

(v) Fuel injector servo to fuel manifold 

valve (except turbo models). 

(vi) Turbo models only: Fuel injector servo 

to fuel flow transducer. 

(vii) Turbo models only: Fuel flow transducer to fuel manifold valve. 

(viii) Fuel injector servo fuel return to firewall fitting. 

(2) For all airplanes equipped with the Garmin 

G1000 System: Establish the correct torque 

values of the end fittings on each of the following hoses in the engine compartment: 

(i) Fuel strainer to engine fuel pump. 

(ii) Engine fuel pump to fuel injector servo 

(except T206H). 

Within the next 5 hours TIS after May 2, 2007 

(the effective date of this AD). 

Follow Cessna Service Bulletin No. SB07–71–

01, Revision 1, dated March 16, 2007; the 

procedures of the appendix to this AD; and 

the torque values from the table Torque 

Values for Hose End Fittings in the appendix to this AD. 

(iii) T206H only: Engine fuel pump to the 

union at the aft vertical cooling baffle. 

(iv) T206H only: Union at the aft vertical 

cooling baffle to the fuel injector servo. 

(v) Fuel injector servo to fuel flow transducer. 

(vi) Fuel flow transducer to fuel manifold 

valve. 

(vii) Fuel injector servo fuel return to firewall fitting. 


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Federal Register / Vol. 72, No. 70 / Thursday, April 12, 2007 / Rules and Regulations 18383 

Special Flight Permit 

(f) Under 14 CFR 39.23, we are allowing 

special flight permits for the purpose of 

compliance with this AD under the following 

conditions: Only operate under day visual 

flight rules (VFR). 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, Wichita Aircraft 

Certification Office (ACO), FAA, ATTN: 

Trenton Shepherd, Aerospace Engineer, 

Wichita ACO, 1801 Airport Road, Room 100, 

Wichita, Kansas 67209; telephone: (316) 946–

4143; fax: (316) 946–4107, 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. 

(h) AMOCs approved for AD 2006–17–04 

are not approved for this AD. 

Material Incorporated by Reference 

(i) You must use Cessna Service Bulletin 

No. SB07–71–01, Revision 1, dated March 16, 

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 The Cessna Aircraft 

Company, Product Support, P.O. Box 7706, 

Wichita, Kansas 67277–7706; telephone: 

(316) 517–5800; facsimile: (316) 942–9006. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Appendix to AD 2007–08–03—

Inspection Instructions—Cessna 

Aircraft Company Models 172R, 172S, 

182T, T182T, 206H, and T206H 

Airplanes 

1. Remove upper and side cowlings to 

perform torque procedure. 

2. Remove all signs of old torque putty or 

paint. 

3. Using a suitable tool loosen the hose end 

fitting of each joint, while using a suitable 

tool to restrain the other end fitting of the 

joint to preclude rotation. 

4. Using the applicable fitting torque from 

the table Torque Values for Hose End Fittings 

of this appendix to AD 2007–08–03, torque 

the hose end fitting to the proper torque, 

while using a suitable tool to restrain the 

other end fitting of the joint to preclude 

rotation. 

5. After proper torque has been applied to 

the hose end fitting, apply the applicable 

torque paint or putty to the hose end fitting 

joint. 

6. If during any torque procedure any of 

the non-hose end fittings rotate, stop the 

torque procedure. Totally disconnect the 

hose end joint and remove any fitting that 

has rotated. After the cleaning, visual 

examination, and/or replacement of the 

fitting and/or any seals or sealant, reinstall 

the fitting and torque it to the applicable 

requirement. Then reconnect the hose end 

fitting and repeat Step 4. of this appendix to 

AD 2007–08–03. 

7. Use the table below Torque Values for 

Hose End Fittings for the correct torque 

values to tighten the hose end fittings as 

required in paragraphs (e)(1) and (e)(2) of this 

AD: 

TORQUE VALUES FOR HOSE END FITTINGS

Flare hex sizes in fractions of an inch Hose size 

Correct torque in inch-pounds 

Minimum Maximum 

9⁄16 ................................................................................................................................................ ¥4 135 150 11⁄16 .............................................................................................................................................. ¥6 270 300 7⁄8 ................................................................................................................................................. ¥8 450 500 

Issued in Kansas City, Missouri, on April 

5, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–6826 Filed 4–11–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2007–27110; Airspace 

Docket No. 07–AGL–1] 

Modification of Class E Airspace; Peru, 

IL 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Direct final rule; confirmation 

of effective date. 

SUMMARY: This document confirms the 

effective date of the direct final rule 

which revises Class E airspace at Peru, 

IL. 

EFFECTIVE DATE: 0901 UTC, May 10, 

2007. 

FOR FURTHER INFORMATION CONTACT: 

Grant Nichols, System Support, DOT 

Regional Headquarters Building, Federal 

Aviation Administration, 901 Locust, 

Kansas City, MO 64106; telephone (816) 

329–2522. 

SUPPLEMENTARY INFORMATION: The FAA 

published this direct final rule with a 

request for comments in the Federal 

Register on February 26, 2007 (72 FR 

8266). The FAA uses the direct final 

rulemaking procedures for a noncontroversial rule where the FAA 

believes that there will be no adverse 

public comment. This direct final rule 

advised the public that no adverse 

comments were anticipated, and that 

unless a written adverse comment, or a 

written notice of intent to submit such 

an adverse comment, were received 

within the comment period, the 

regulation would become effective on 

May 10, 2007. No adverse comments 

were received, and thus this notice 

confirms that this direct final rule will 

become effective on that date. 

Issued in Forth Worth, Texas, on March 21, 

2007. 

Ronnie L. Uhlenhaker, 

Manager, System Support Group, ATO 

Central Service Area. 

[FR Doc. 07–1803 Filed 4–11–07; 8:45 am] 

BILLING CODE 4910–13–M 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2006–25997; Airspace 

Docket No. 06–ANM–5] 

Revision of Class E Airspace; 

Redmond, OR 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action will revise the 

Class E airspace at Redmond, OR. 

Additional Class E airspace is necessary 

to accommodate aircraft using a new 

Area Navigation (RNAV) Global 

Positioning System (GPS) Standard 


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