Federal Register / Vol. 72, No. 72 / Monday, April 16, 2007 / Proposed Rules 18925 

Services Domain systems, hardware, 

software, and databases from 

unauthorized access. 

2. Protection of field-loadable 

software (FLS) applications and 

databases which are electronically 

transmitted from external sources to the 

on-aircraft networks and storage 

devices, and used within the Aircraft 

Control Domain and Airline Information 

Services Domain. 

Applicability 

As discussed above, these proposed 

special conditions are applicable to the 

787. Should Boeing apply at a later date 

for a change to the type certificate to 

include another model incorporating the 

same novel or unusual design features, 

these proposed special conditions 

would apply to that model as well 

under the provisions of § 21.101. 

Conclusion 

This action affects only certain novel 

or unusual design features of the 787. It 

is not a rule of general applicability, and 

it affects only the applicant that applied 

to the FAA for approval of these features 

on the airplane. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

The authority citation for these 

Special Conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

The Proposed Special Conditions 

Accordingly, the Administrator of the 

Federal Aviation Administration (FAA) 

proposes the following special 

conditions as part of the type 

certification basis for the Boeing Model 

787–8 airplane. 

The applicant shall ensure system security 

protection for the Aircraft Control Domain 

and Airline Information Services Domain 

from unauthorized external access. The 

applicant shall also ensure that security 

threats are identified and risk mitigation 

strategies are implemented to minimize the 

likelihood of occurrence of each of the 

following conditions: 

1. Reduction in airplane safety margins or 

airplane functional capabilities, including 

those possibly caused by maintenance 

activity; 

2. An increase in flightcrew workload or 

conditions impairing flightcrew efficiency, 

and; 

3. Distress or injury to airplane occupants. 

Issued in Renton, Washington, on April 5, 

2007. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 07–1838 Filed 4–13–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27747; Directorate 

Identifier 2007–CE–030–AD] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Models 150 and 152 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Cessna Aircraft Company (Cessna) 

Models 150 and 152 airplanes. This 

proposed AD would require replacing 

the rudder stop, rudder stop bumper, 

and attachment hardware with a new 

rudder stop modification kit. This 

proposed AD also requires replacing the 

safety wire with jamnuts. This proposed 

AD results from two accidents where 

the rudder was found in the over-travel 

position with the stop plate hooked over 

the stop bolt heads. We are proposing 

this AD to prevent the rudder from 

traveling past the normal travel limit 

and becoming jammed in the over-travel 

position. This condition could result in 

loss of control. 

DATES: We must receive comments on 

this proposed AD by June 15, 2007. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

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. 

For service information identified in 

this proposed AD, contact Cessna 

Aircraft Company, Product Support, 

P.O. Box 7706, Wichita, KS 67277; 

telephone: (316) 517–5800; fax: (316) 

942–9006. 

FOR FURTHER INFORMATION CONTACT: Gary 

Park, Aerospace Engineer, 1801 Airport 

Road, Room 100, Wichita, Kansas 

67209; telephone: (316) 946–4123; fax: 

(316) 946–4107. 

SUPPLEMENTARY INFORMATION

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under the 

ADDRESSES section. Include the docket 

number, ‘‘FAA–2007–27747; Directorate 

Identifier 2007–CE–030–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed 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 proposed AD. 

Discussion 

This AD results from two spin 

accidents involving Cessna Model 152 

airplanes where the rudder was found 

in the over-travel position with the stop 

plate hooked over the stop bolt heads. 

In the first accident, which occurred 

in Canada, a flight instructor and 

student pilot were unable to recover 

after performing a spin maneuver. When 

the airplane was inspected, the rudder 

was found jammed. 

In the second accident the rudder 

bumper was found to be installed 

incorrectly, which resulted in a rudder 

jam during an attempted spin recovery. 

Upon recovery of the airplanes after 

the accidents, both accident airplanes 

had their rudder stop plates hooked 

over the stop bolts. After examining the 

accident airplanes and other Cessna 

Models 150 and 152 airplanes, accident 

investigators determined that, under 

certain conditions, it is possible to jam 

the rudder past its normal travel limit. 

The jam occurs when the stop plate is 

forced aft of the stop bolt head. The 

forward edge of the stop plate can then 

become lodged under the head of the 

stop bolt causing the rudder to jam in 

this over-travel position. Recovery from 

a spin may not be possible with the 

rudder jammed beyond the normal 

rudder travel stop limits. 

This condition, if not corrected, could 

result in loss of control. 


cprice-sewell on PROD1PC66 with PROPOSALS
18926 Federal Register / Vol. 72, No. 72 / Monday, April 16, 2007 / Proposed Rules 

Relevant Service Information 

We have reviewed the following 

Cessna Aircraft Company service 

information, dated January 22, 2001: 

• Service Bulletin SEB01–1; 

• Service Kit SK152–25; and 

• Service Kit SK152–24. 

The service information describes 

procedures for replacing the rudder 

stop, rudder stop bumper, and 

attachment hardware with a new rudder 

stop modification kit. The service 

information also describes the 

procedure for replacing the safety wire 

with jamnuts. 

FAA’s Determination and Requirements 

of the Proposed AD 

We are proposing this AD because we 

evaluated all information and 

determined the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. This proposed AD would 

require replacing the rudder stop, 

rudder stop bumper, and attachment 

hardware with a new rudder stop 

modification kit. This proposed AD also 

requires replacing the safety wire with 

jamnuts. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 18,670 airplanes in the 

U.S. registry. 

We estimate the following costs to do 

the proposed modification: 

Labor cost Parts cost Total cost per 

airplane 

Total cost on 

U.S. operators 

4 work-hours × $80 per hour = $320 .......................................................................................... $60 $380 $7,094,600 

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 have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

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); 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 proposed AD and placed it in the 

AD docket. 

Examining the AD Docket 

You may examine the AD docket that 

contains the proposed 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, Safety. 

The Proposed 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 adding 

the following new AD: 

Cessna Aircraft Company: Docket No. FAA–

2007–27747; Directorate Identifier 2007–

CE–030–AD. 

Comments Due Date 

(a) We must receive comments on this 

airworthiness directive (AD) action by June 

15, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the following 

airplane models and serial numbers that are 

certificated in any category: 

Models Serial numbers 

(1) 150F ................................................................................................................ 15061533 through 15064532. 

(2) 150G ............................................................................................................... 15064533 through 15064969 and 15064971 through 15067198. 

(3) 150H ............................................................................................................... 15067199 through 15069308 and 649. 

(4) 150J ................................................................................................................ 15069309 through 15071128. 

(5) 150K ............................................................................................................... 15071129 through 15072003. 

(6) 150L ................................................................................................................ 15072004 through 15075781. 

(7) 150M ............................................................................................................... 15075782 through 15079405. 

(8) A150K ............................................................................................................. A1500001 through A1500226. 

(9) A150L .............................................................................................................. A1500227 through A1500432 and A1500434 through 

A1500523. 

(10) A150M ........................................................................................................... A1500524 through A1500734 and 15064970. 

(11) A–150L .......................................................................................................... A–1501001 through A–1501039. 

(12) A–A150L ....................................................................................................... A–A1500001 through A–A1500009. 


cprice-sewell on PROD1PC66 with PROPOSALS
Federal Register / Vol. 72, No. 72 / Monday, April 16, 2007 / Proposed Rules 18927 

Models Serial numbers 

(13) F150F ............................................................................................................ F150–0001 through F150–0067. 

(14) F150G ........................................................................................................... F150–0068 through F150–0219. 

(15) F150H ........................................................................................................... F150–0220 through F150–0389. 

(16) F150J ............................................................................................................ F150–0390 through F150–0529. 

(17) F150K ........................................................................................................... F15000530 through F15000658. 

(18) F150L ............................................................................................................ F15000659 through F15001143. 

(19) F150M ........................................................................................................... F15001144 through F15001428. 

(20) FA150K ......................................................................................................... FA1500001 through FA1500081. 

(21) FA150L ......................................................................................................... FA1500082 through FA1500261. 

(22) FA150M ........................................................................................................ FA1500262 through FA1500336. 

(23) 152 ................................................................................................................ 15279406 through 15286033. 

(24) A152 .............................................................................................................. A1520735 through A1521049, A1500433, and 681. 

(25) F152 .............................................................................................................. F15201429 through F15201980. 

(26) FA152 ........................................................................................................... FA1520337 through FA1520425. 

Unsafe Condition 

(d) This AD results from two accidents 

where the rudder was found in the overtravel position with the stop plate hooked 

over the stop bolt heads. We are issuing this 

AD to prevent the rudder from traveling past 

the normal travel limit and becoming 

jammed in the over-travel position. This 

condition could result in loss of control. 

Compliance 

(e) To address this problem, you must do 

the following, unless already done: 

Action Compliance Procedures 

(1) For airplanes with a forged bulkhead: Replace the rudder stop, rudder stop bumper, 

and attachment hardware with the new rudder stop modification kit SK152–25; and replace safety wire with jamnuts.

Within the next 100 hours time-in-service 

(TIS) or 12 months after the effective date 

of this AD, whichever occurs first.

Follow Cessna Aircraft Company Service Bulletin SEB01–1, and Cessna Aircraft Company Service Kit SK152–25, both dated 

January 22, 2001. 

(2) For airplanes with a sheet metal bulkhead: 

Replace the rudder stop, rudder stop bumper, and attachment hardware with the new 

rudder stop modification kit SK152–24; and 

replace safety wire with jamnuts.

Within the next 100 hours TIS or 12 months 

after the effective date of this AD, whichever occurs first.

Follow Cessna Aircraft Company Service Bulletin SEB01–1, and Cessna Aircraft Company Service Kit SK152–24, both dated 

January 22, 2001. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, FAA, ATTN: Gary Park, 

Aerospace Engineer, 1801 Airport Road, 

Room 100, Wichita, Kansas 67209; telephone: 

(316) 946–4123; 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. 

Related Information 

(g) To get copies of the service information 

referenced in this AD, contact Cessna Aircraft 

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

Wichita, KS 67277; telephone: (316) 517–

5800; fax: (316) 942–9006. To view the AD 

docket, go to the Docket Management 

Facility; U.S. Department of Transportation, 

400 Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC, or on the 

Internet at http://dms.dot.gov. The docket 

number is Docket No. FAA–2007–27747; 

Directorate Identifier 2007–CE–030–AD. 

Issued in Kansas City, Missouri, on April 

10, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–7180 Filed 4–13–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF DEFENSE 

Office of the Secretary 

[DoD–2007–HA–0015] 

RIN 0720–AB13 

32 CFR Part 199 

TRICARE; Expansion of Geographic 

Scope of the TRICARE Retiree Dental 

Program (TRDP) 

AGENCY: Office of the Secretary, DoD. 

ACTION: Proposed rule. 

SUMMARY: This proposed rule expands 

the geographic scope of the TRICARE 

Retiree Dental Program (TRDP) to 

overseas locations not currently covered 

by the program. At this time, TRDP is 

only applicable in the 50 United States 

and the District of Columbia, Canada, 

Puerto Rico, Guam, American Samoa, 

the Commonwealth of the Northern 

Mariana Islands, and the U.S. Virgin 

Islands. Expanding the geographic scope 

of the program will ensure that all 

TRICARE-eligible retirees are eligible for 

the same dental benefits, regardless of 

their location. There are no additional 

Government costs associated with this 

proposed expansion of TRDP overseas 

as TRDP costs are borne entirely by 

enrollees through premium payments. 

DATES: Written comments received at 

the address indicated below by June 15, 

2007 will be accepted. 

ADDRESSES: You may submit comments, 

identified by docket number and/or RIN 

number and title, by any of the 

following methods: 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

• Mail: Federal Docket Management 

System Office, 1160 Defense Pentagon, 

Washington, DC 20301–1160. 

Instructions: All submissions received 

must include the agency name and 

docket number or Regulatory 

Information Number (RIN) for this 

Federal Register document. The general 

policy for comments and other 

submissions from members of the public 

is to make these submissions available 

for public viewing on the Internet at 

http://regulations.gov as they are 

received without change, including any 

personal identifiers or contact 

information. 

FOR FURTHER INFORMATION CONTACT: 

Debra Hatzel, Program Requirements 

Division, TRICARE Management 

Activity, telephone (303) 676–3572. 


cprice-sewell on PROD1PC66 with PROPOSALS