Federal Register / Vol. 71, No. 174 / Friday, September 8, 2006 / Rules and Regulations 52983 

DEPARTMENT OF AGRICULTURE 

Animal and Plant Health Inspection 

Service 

9 CFR Parts 55 and 81 

[Docket No. 00–108–4] 

Chronic Wasting Disease Herd 

Certification Program and Interstate 

Movement of Farmed or Captive Deer, 

Elk, and Moose; Delay of Effective Date 

AGENCY: Animal and Plant Health 

Inspection Service, USDA. 

ACTION: Final rule; delay of effective 

date. 

SUMMARY: We recently amended the 

regulations to establish a herd 

certification program and interstate 

movement restrictions for cervids to 

control the spread of chronic wasting 

disease. That final rule had an effective 

date of October 19, 2006. We are 

delaying that effective date until further 

notice, to give the agency time to 

consider several petitions we recently 

received that asked for the rule not to 

take effect as scheduled. This delay is 

needed to allow the agency to consider 

the issues raised in the petitions and 

decide what action to take in response 

to them. 

DATES: The effective date for the final 

rule amending 9 CFR part 55 and adding 

9 CFR part 81, published at 71 FR 

41682, July 21, 2006, is delayed until 

further notice. APHIS will publish a 

document in the Federal Register 

announcing any new effective date or 

other decision. 

FOR FURTHER INFORMATION CONTACT: Dr. 

Dean E. Goeldner, Senior Staff 

Veterinarian, Ruminant Health 

Programs, VS, APHIS, 4700 River Road 

Unit 43, Riverdale, MD 20737–1231; 

(301) 734–4916. 

SUPPLEMENTARY INFORMATION: 

Background 

The Animal and Plant Health 

Inspection Service’s (APHIS’s) 

regulations in 9 CFR subchapter B 

govern cooperative programs to control 

and eradicate communicable diseases of 

livestock. In accordance with the 

Animal Health Protection Act (7 U.S.C. 

8301 et seq.), the Secretary of 

Agriculture has the authority to issue 

orders and promulgate regulations to 

prevent the introduction into the United 

States and the dissemination within the 

United States of any pest or disease of 

livestock, and to pay claims growing out 

of the destruction of animals. 

On July 21, 2006, we published a final 

rule in the Federal Register (71 FR 

41682–41707) amending 9 CFR 

subchapter B by establishing regulations 

in part 55 for a Chronic Wasting Disease 

Herd Certification Program to help 

eliminate chronic wasting disease from 

the farmed or captive cervid herds in 

the United States (the CWD rule). Under 

that rule, owners of deer, elk, and moose 

herds who choose to participate would 

have to follow program requirements for 

animal identification, testing, herd 

management, and movement of animals 

into and from herds. We also amended 

9 CFR subchapter B by establishing a 

new part 81 containing interstate 

movement requirements to prevent the 

spread of CWD. 

Delay in Effective Date 

We recently received several petitions 

requesting a delay in the effective date 

of the CWD rule and reconsideration of 

several requirements of the rule. We are 

currently evaluating the merits of these 

petitions, and will publish a notice in 

the Federal Register in the near future 

making the contents of the petitions 

available to the public for comment. We 

are delaying the effective date of the 

CWD rule while this process is 

underway. 

Authority: 7 U.S.C. 8301–8317; 7 CFR 2.22, 

2.80, and 371.4. 

Done in Washington, DC, this 30th day of 

August 2006. 

W. Ron DeHaven, 

Administrator, Animal and Plant Health 

Inspection Service. 

[FR Doc. E6–14861 Filed 9–7–06; 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25760; Directorate 

Identifier 2006–CE–48–AD; Amendment 39–

14757; AD 2006–18–51] 

RIN 2120–AA64 

Airworthiness Directives; Raytheon 

Aircraft Company Models 1900, 1900C, 

and 1900D Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Raytheon Aircraft Company (RAC) 

Models 1900, 1900C, and 1900D 

airplanes. This AD contains the same 

information as emergency AD 2006–18–

51 and publishes the action in the 

Federal Register. This AD requires you 

to do a one-time visual inspection of 

both the left and right wing rear spar 

lower caps for cracking and other 

damage such as loose or missing 

fasteners; repair any cracks or damage 

found; and report any cracks or damage 

found to the FAA and RAC. This AD 

results from extensive cracks found in 

the wing rear spar lower caps and rear 

spar web of two of the affected 

airplanes. One of the airplanes also had 

missing fasteners. We are issuing this 

AD to detect and correct cracking and 

other damage in the wing rear spar 

lower caps of the affected airplanes 

before the cracks or damage lead to 

failure. Such a wing failure could result 

in the wing separating from the airplane 

with consequent loss of control. 

DATES: This AD becomes effective on 

September 8, 2006. 

We must receive any comments on 

this AD by November 7, 2006. 

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. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.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. 

To view the comments to this AD, go 

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

number is FAA–2006–25760; 

Directorate Identifier 2006–CE–48–AD. 

FOR FURTHER INFORMATION CONTACT: 

Steven E. Potter, FAA, 1801 Airport 

Road, Wichita, Kansas 67209; 

telephone: (316) 946–4124; fax: (316) 

946–4107. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA received recent reports of 

cracks found in the wings of two RAC 

1900D airplanes. During routine 

maintenance, the wing rear spar lower 

caps and rear spar web were found to 

have significant cracks. 

The RAC Structural Inspection 

Manual requires a thorough inspection 

of the wing rear spar at 17,500 hours 

time-in-service (TIS) with repetitive 

inspections at intervals of 3,000 hours 

TIS. 


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52984 Federal Register / Vol. 71, No. 174 / Friday, September 8, 2006 / Rules and Regulations 

One airplane had 19,126 hours TIS 

when cracks were found. The cracks 

were in the lower aft spar cap flange, 

but the cracks extended upward into the 

web and terminated at the lightening 

hole in the spar web. Fasteners were 

also found missing in the spar cap and 

wing cove splice plate. There were no 

discrepancies recorded from the initial 

inspection at 17,500 hours TIS on this 

airplane. 

Early indications show similar 

cracking on the other airplane. We 

continue to gather information on this 

airplane. 

Analysis shows that similar cracks 

could also develop in the wings of the 

Models 1900 and 1900C airplanes. 

Cracking in the wing rear spar lower 

caps, if not corrected, could result in 

wing failure. Such a wing failure could 

result in the wing separating from the 

airplane with consequent loss of 

control. 

On August 31, 2006, FAA issued 

emergency AD 2006–18–51 to require 

you to do a one-time visual inspection 

of both the left and right wing rear spar 

lower caps for cracking and other 

damage such as loose or missing 

fasteners; repair any cracks or damage 

found; and report any cracks or damage 

found to the FAA and RAC. 

FAA’s Determination 

The FAA determined that immediate 

corrective action was required, that 

notice and opportunity for prior public 

comment were impracticable and 

contrary to the public interest, and that 

good cause existed to make the AD 

effective immediately by individual 

letters issued on August 31, 2006, to all 

known U.S. operators of the affected 

RAC Models 1900, 1900C, and 1900D 

airplanes. These conditions still exist, 

and the AD is published in the Federal 

Register as an amendment to section 

39.13 of the Federal Aviation 

Regulations (14 CFR 39.13) to make it 

effective to all persons. 

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 ‘‘FAA–

2006–25760; Directorate Identifier 

2006–CE–48–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, 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 adding 

the following new airworthiness 

directive (AD): 

2006–18–51 Raytheon Aircraft Company 

(RAC): Amendment 39–14757; Docket 

No. FAA–2005–25760; Directorate 

Identifier 2006–CE–48–AD. 

Effective Date 

(a) This AD becomes effective on 

September 8, 2006. 

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 Nos. 

(1) 1900 ..................... UA–3. 

(2) 1900C (C–12J) .... UB–1 through UB– 

74, UC–1 through 

UC–174, and UD– 

1 through UD–6. 

(3) 1900D .................. UE–1 through UE– 

439. 

Unsafe Condition 

(d) This AD is the result of extensive cracks 

found in the wing rear spar lower caps and 

rear spar web of two of the affected airplanes. 

One of the airplanes also had missing 

fasteners. We are issuing this AD to detect 

and correct cracking and other damage in the 

wing rear spar lower caps of the affected 

airplanes before the cracks or damage lead to 

failure. Such a wing failure could result in 

the wing separating from the airplane with 

consequent loss of control. 

Compliance 

(e) To address this problem, you must do 

the following: 


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Federal Register / Vol. 71, No. 174 / Friday, September 8, 2006 / Rules and Regulations 52985 

Actions Compliance Procedures 

(1) A one-time visual inspection of both the left 

and right wing rear spar lower caps for 

cracks and other damage such as loose or 

missing fasteners. 

At whichever occurs later after September 8, 

2006 (the effective date of this AD), except 

to those who received emergency AD 

2006–18–51, which contained the requirements of this amendment and became effective immediately upon receipt: 

(i) Within 24 hours; or 

(ii) Prior to further flight. 

Follow the procedures in the Appendix to this 

AD. 

(2) For the inspection in paragraph (e)(1) of this 

AD, you may return/position the airplane to a 

home base, hangar, maintenance facility, etc. 

For this repositioning, you may operate the 

airplane up to 3 hours time-in-service provided the flight(s) occur(s) no later than 30 

days after September 8, 2006 (the effective 

date of this AD), except to those who received emergency AD 2006–18–51, which 

contained the requirements of this amendment and became effective immediately 

upon receipt. 

The following limitations are imposed for such 

a repositioning flight: 

(i) ONLY THE PILOT AND ANY ADDITIONAL FLIGHT CREW MEMBER REQUIRED FOR SAFE OPERATION IS 

ALLOWED FOR THIS FLIGHT; 

(ii) FLIGHT INTO KNOWN OR FORECAST MODERATE OR SEVERE TURBULENCE IS PROHIBITED; and 

(iii) INDICATED AIRSPEED IS LIMITED 

TO 175 KNOTS MAXIMUM. 

(3) Repair any cracks or other damage such as 

loose or missing fasteners found during the 

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

AD. Do this by obtaining and incorporating an 

FAA-approved repair scheme from RAC. 

Before further flight after the inspection required by paragraph (e)(1) of this AD. Contact RAC at Post Office Box 85, Wichita, 

Kansas 67201–0085; phone: 316–676–

8366; fax: (316) 676–8745; e-mail: 

tom_peay@rac.ray.com. 

(4) Report the inspection results to the FAA 

and RAC. For the reporting requirement in 

this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the 

information collection requirements and has 

assigned OMB Control Number 2120–0056. 

Within 72 hours after completing the inspection required in paragraph (e)(1) of this AD. Send your report to Steven E. Potter, FAA, 

1801 Airport Road, Wichita, Kansas 67209; 

fax: (316) 946–4107; e-mail: steven.potter@faa.gov; and Tom Peay, 

Raytheon Aircraft Company, Post Office 

Box 85, Wichita, Kansas 67201–0085; fax: 

(316) 676–8745; e-mail: tom_peay@

rac.ray.com. Include in your report the following information: 

(i) Aircraft model and serial number; 

(ii) Number of cycles; 

(iii) Aircraft hours TIS; 

(iv) Left and right wing lower spar cap 

hours TIS; 

(v) Hours TIS on the spar cap since last 

inspection; 

(vi) Answer yes or no whether cracking, 

missing fasteners, or other damage 

was found; and 

(vii) If cracking was found, identify size 

and location of cracks. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Wichita Aircraft 

Certification Office, FAA, ATTN: Steven E. 

Potter, FAA, 1801 Airport Road, Wichita, 

Kansas 67209; telephone: (316) 946–4124; 

fax: (316) 946–4107, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures in 14 CFR 39. 

APPENDIX TO AD 2006–18–51 

Inspection Instructions—Raytheon Aircraft 

Company 1900 Series Wing Rear Spar 

Step 1. Lower the wing flaps to provide 

visual access to the wing rear spar cove area. 

Although the pictures show the flaps 

removed, this AD does not require flap 

removal to do the inspection. 

Step 2. Using a strong, high-intensity light 

visually inspect the area of the wing rear spar 

identified in Figure 1. There is ample 

visually visual access from above the upper 

surface of the flap. Look for cracks (like those 

shown in Figures 2 and 3) and loose or 

missing fasteners. 

Step 3. Clean the wing rear spar area 10 

inches inboard and outboard of the buttock 

line (BL) 114 area. 

Step 4. Repeat the Step 2 inspection. 

BILLING CODE 4910–13–U 


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52988 Federal Register / Vol. 71, No. 174 / Friday, September 8, 2006 / Rules and Regulations 

Issued in Kansas City, Missouri, on 

September 1, 2006. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 06–7511 Filed 9–7–06; 8:45 am] 

BILLING CODE 4910–13–C 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25513; Directorate 

Identifier 99–NE–61–AD; Amendment 39–

14753; AD 2006–18–14] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG Tay 650–15 

and Tay 651–54 Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

airworthiness directive (AD) for RollsRoyce Deutschland Ltd & Co KG (RRD) 

Tay 650–15 and Tay 651–54 turbofan 

engines. That AD currently establishes 

cyclic life limits for certain part number 

(P/N) stage 1 high pressure turbine 

(HPT) discs and stage 1 low pressure 

turbine (LPT) discs operating under 

certain flight plan profiles. This AD 

requires calculating and re-establishing 

the achieved cyclic life of stage 1 HPT 

discs, P/N JR32013 or P/N JR33838, and 

stage 1 LPT discs, P/N JR32318A, that 

have been exposed to different flight 

plan profiles. This AD also requires 

removing from service those stage 1 

HPT discs and stage 1 LPT discs 

operated under Tay 650–15 engine flight 

plan profiles A, B, C, and D, and 

operated under Tay 651–54 engine 

datum flight profile, at reduced cyclic 

life limits, using a drawdown schedule. 

This AD results from RRD updating 

their low-cycle-fatigue analysis for stage 

1 HPT discs and stage 1 LPT discs and 

reducing their cyclic life limits. We are 

issuing this AD to prevent cracks 

leading to turbine disc failure, which 

could result in an uncontained engine 

failure and damage to the airplane. 

DATES: This AD becomes effective 

October 13, 2006. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of October 13, 2006. 

ADDRESSES: You can get the service 

information identified in this AD from 

Rolls-Royce Deutschland Ltd & Co KG, 

Eschenweg 11, 15872 BlankenfeldeMahlow, Germany, telephone 49–0–33–

7086–1768; fax 49–0–33–7086–3356. 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

Room PL–401 on the plaza level of the 

Nassif Building, 400 Seventh Street, 

SW., Washington, DC. 


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