60102 Federal Register / Vol. 73, No. 198 / Friday, October 10, 2008 / Rules and Regulations 

6Meat Animals Production, Distribution and 

Income 2007 Summary. April 2008. Agricultural 

Statistics Board. NASS, USDA. 

in pre-movement tuberculosis testing 

requirements as a result of this interim 

rule, and will therefore benefit from 

reduced costs associated with that 

tuberculosis testing. However, 

tuberculosis testing costs are very small 

when compared to value of the cattle 

tested, and the expected savings, 

therefore, are also relatively small. On 

January 1, 2007, beef cattle in Minnesota 

had an average per animal value of 

$960.6 The average value of dairy cattle 

is considerably higher, given the value 

of milk produced. The savings in 

tuberculosis testing costs represent no 

more than about 1.6 percent of the 

average per-head value of beef cattle 

($15/$960) and an even smaller 

percentage of the average value of dairy 

cattle. 

Under these circumstances, the 

Administrator of the Animal and Plant 

Health Inspection Service has 

determined that this action will not 

have a significant economic impact on 

a substantial number of small entities. 

Executive Order 12372 

This program/activity is listed in the 

Catalog of Federal Domestic Assistance 

under No. 10.025 and is subject to 

Executive Order 12372, which requires 

intergovernmental consultation with 

State and local officials. (See 7 CFR part 

3015, subpart V.) 

Executive Order 12988 

This rule has been reviewed under 

Executive Order 12988, Civil Justice 

Reform. This rule: (1) Preempts all State 

and local laws and regulations that are 

in conflict with this rule; (2) has no 

retroactive effect; and (3) does not 

require administrative proceedings 

before parties may file suit in court 

challenging this rule. 

Paperwork Reduction Act 

This rule contains no new 

information collection or recordkeeping 

requirements under the Paperwork 

Reduction Act of 1995 (44 U.S.C. 3501 

et seq.). 

List of Subjects in 9 CFR Part 77 

Animal diseases, Bison, Cattle, 

Reporting and recordkeeping 

requirements, Transportation, 

Tuberculosis. 

■ Accordingly, we are amending 9 CFR 

part 77 as follows: 

PART 77—TUBERCULOSIS 

■ 1. The authority citation for part 77 

continues to read as follows: 

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

2.80, and 371.4. 

■ 2. In § 77.9, paragraph (b) is revised to 

read as follows: 

§ 77.9 Modified accredited advanced 

States or zones. 

* * * * * 

(b) The following are modified 

accredited advanced zones: All of the 

State of Michigan except for the zones 

that comprise those counties or portions 

of counties in Michigan described in 

§ 77.7(b)(1) and § 77.11(b)(1); and all of 

the State of Minnesota except for the 

zones that comprise those counties or 

portions of counties in Minnesota 

described in § 77.11(b)(2). 

* * * * * 

■ 3. In § 77.11, paragraphs (a) and (b) are 

revised to read as follows: 

§ 77.11 Modified accredited States or 

zones. 

(a) The following are modified 

accredited States: None. 

(b) The following are modified 

accredited zones: 

(1) A zone in Michigan that comprises 

Alcona, Alpena, Antrim, Charlevoix, 

Cheboygan, Crawford, Emmet, 

Montmorency, Oscoda, Otsego, and 

Presque Isle Counties and those portions 

of Iosco and Ogemaw Counties that are 

north of the southernmost boundary of 

the Huron National Forest and the Au 

Sable State Forest. 

(2) Those portions of the Minnesota 

Counties of Lake of the Woods, Roseau, 

Marshall, and Beltrami bounded by a 

line as follows: Beginning in Lake of the 

Woods County at the intersection of the 

U.S./Canadian border and the western 

shoreline of Lake of the Woods; then 

west along the U.S./Canadian border 

(crossing into Roseau County) to Roseau 

County Road 115; then south along 

Roseau County Road 115 to State 

Highway 11; then southwest along State 

Highway 11 to State Highway 32; then 

south along State Highway 32 (crossing 

into Marshall County) to Marshall 

County Road 47/124; then east along 

Marshall County Road 47/124 to 210th 

Avenue Northeast; then south along 

210th Avenue Northeast and southwest 

to where the name changes to 200th 

Avenue Northeast; then south along 

200th Avenue Northeast to County Road 

121; then south along the western 

boundary of Agassiz National Wildlife 

Reserve and along the western boundary 

of the Elm Lake State Wildlife 

Management Area to the southwest 

corner of sec. 21 in T. 155 N., R. 42 W. 

of the Fifth Prime Meridian; then east 

along the southern boundary of secs. 21, 

22, 23, and 24 in T. 155 N., R. 42 W. 

and secs. 19 and 20 in T. 155 N., R. 41 

W.; then south along the western 

boundary of secs. 28 and 33 in T. 155 

N., R. 41 W.; then continuing south 

along Marshall County Road 52 to the 

southern boundary of Marshall County; 

then east along the southern boundary 

of Marshall County to the western 

boundary of Beltrami County (also the 

boundary of the Red Lake Indian 

Reservation); then north along the 

Beltrami County boundary (also the 

boundary of the Red Lake Indian 

Reservation) to the northern boundary 

of the Red Lake Indian Reservation; then 

east along the northern boundary of the 

Red Lake Indian Reservation to the 

southeast corner of sec. 36 in T. 155 N., 

R. 34 W.; then north along the eastern 

boundary of Townships 155, 156, 157 

(crossing into Lake of the Woods 

County), 158, 159, 160, and 161 N., R. 

34 W., to State Highway 11; then 

northwest and north along State 

Highway 11 to County Road 74; then 

east along County Road 74 to Main 

Avenue Northeast; then north along 

Main Avenue Northeast to the northern 

city limits of Warroad; then east along 

the Warroad city limits to the shore of 

Lake of the Woods; then along the shore 

of Lake of the Woods to the point of 

beginning. 

* * * * * 

Done in Washington, DC, this 7th day of 

October 2008. 

Cindy Smith, 

Administrator, Animal and Plant Health 

Inspection Service. 

[FR Doc. E8–24223 Filed 10–9–08; 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0835; Directorate 

Identifier 2008–SW–34–AD; Amendment 39– 

15684; AD 2008–20–05] 

RIN 2120–AA64 

Airworthiness Directives; MD 

Helicopters, Inc. Model 600N 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD) 

for MD Helicopters, Inc. (MDHI) Model 

600N helicopters. The AD currently 

requires modifying the fuselage aft 

section within the next 24 months to 


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Federal Register / Vol. 73, No. 198 / Friday, October 10, 2008 / Rules and Regulations 60103 

strengthen the tailboom attachment 

fittings and upper longerons. This 

amendment retains the current required 

modification and adds the following 

requirements: Repetitively inspecting 

the tailboom attachment fittings; 

installing inspection holes and 

attachment bolt washers; modifying 

both access covers; and replacing 

broken attachment bolts. These 

additional requirements were 

inadvertently omitted from the current 

AD. This amendment is prompted by 

the need to correct our mistake and 

continue the repetitive inspections of 

the tailboom attachment fittings until 

the fuselage aft section is modified. This 

series of ADs is prompted by an 

accident due to failure of the tailboom 

attach points resulting in loss of control 

of the helicopter. The actions specified 

by this AD are intended to prevent 

failure of the tailboom attachment 

fittings, separation of the tailboom from 

the helicopter, and subsequent loss of 

control of the helicopter. 

DATES: Effective October 27, 2008. 

The incorporation by reference of 

certain publications was approved by 

the Director of the Federal Register as of 

April 29, 2002 (67 FR 17934, April 12, 

2002); April 27, 2006 (71 FR 24808, 

April 27, 2006); and April 16, 2008 (73 

FR 13096, March 12, 2008). 

Comments for inclusion in the Rules 

Docket must be received on or before 

December 9, 2008. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

You may get the service information 

identified in this AD from MD 

Helicopters Inc., Attn: Customer 

Support Division, 4555 E. McDowell 

Rd., Mail Stop M615, Mesa, Arizona 

85215–9734, telephone 1–800–388– 

3378, fax 480–346–6813, or on the 

Internet at http:// 

www.mdhelicopters.com. 

Examining the Docket: You may 

examine the docket that contains the 

AD, any comments, and other 

information on the Internet at http:// 

www.regulations.gov, or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The Docket 

Operations office (telephone (800) 647– 

5527) is located in Room W12–140 on 

the ground floor of the West Building at 

the street address stated in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Eric 

Schrieber, Aviation Safety Engineer, 

FAA, Los Angeles Aircraft Certification 

Office, Airframe Branch, 3960 

Paramount Blvd., Lakewood, California 

90712, telephone 562–627–5348, fax 

(562) 627–5210. 

SUPPLEMENTARY INFORMATION: On 

February 27, 2008, we issued AD 2008– 

05–17, Amendment 39–15411 (73 FR 

13096, March 12, 2008), to supersede 

AD 2006–08–12, Amendment 39–14569 

(71 FR 24808, April 27, 2006), which 

superseded AD 2001–24–51, 

Amendment 39–12706 (67 FR 17934, 

April 12, 2002), for the MDHI Model 

600N helicopters. AD 2008–05–17 

required modifying the fuselage aft 

section within the next 24 months to 

strengthen the tailboom attachment 

fittings and upper longerons. AD 2001– 

24–51 was prompted by the discovery of 

a cracked bolt. AD 2006–08–12 was 

prompted by an accident due to failure 

of the tail boom attach points resulting 

in loss of control of the helicopter. That 

condition, if not corrected, could result 

in failure of the tailboom attachment 

fittings, separation of the tailboom from 

the helicopter, and subsequent loss of 

control of the helicopter. 

Since issuing AD 2008–05–17, we 

discovered that we inadvertently 

omitted the requirements from AD 

2006–08–12 to repetitively inspect the 

tailboom attachment fittings; install 

inspection holes and attachment bolt 

washers; modify both access covers; and 

replace broken attachment bolts. Since 

the compliance time in AD 2008–05–17 

for modifying the fuselage aft section is 

24 months, this results in a 24-month 

period of time for which the helicopters 

would not be subject to the actions 

contained in AD 2006–08–12, which 

was not our intention. The accident that 

prompted these ADs may have resulted 

from failure of the thread engagement 

between the nut plate and bolt or by 

cracking in the attachment bathtub ring. 

Therefore, the tailboom attachment 

fittings and upper longerons must be 

inspected at 25- and 100-hour time-inservice (TIS) intervals to detect any 

unairworthy parts and prevent failure of 

the tailboom attachment fittings, 

separation of the tailboom from the 

helicopter, and subsequent loss of 

control of the helicopter. 

Since an unsafe condition has been 

identified that is likely to exist or 

develop on other MDHI Model 600N 

helicopters of the same type design, this 

AD supersedes AD 2008–05–17 to 

reinstate certain actions related to the 

tailboom attachment fittings 

inadvertently omitted from the current 

AD and to continue to require the 

modification of the fuselage aft section 

within 24 months. The inspections and 

modification must be accomplished by 

following the specified portions of the 

service bulletins. 

The short compliance time involved 

is required because the previously 

described critical unsafe condition can 

adversely affect the structural integrity 

and the controllability of the helicopter. 

The inspections are required at 25 and 

100-hours time-in-service (TIS). We 

consider that the 100-hour TIS 

inspection is a relatively short interval 

because some of the affected helicopters 

may reach those hours within 2 months. 

Therefore, this AD must be issued 

immediately to reinstate the previous 

requirements related to the tailboom 

attachment fittings. 

Since a situation exists that requires 

the immediate adoption of this 

regulation, it is found that notice and 

opportunity for prior public comment 

hereon are impracticable, and that good 

cause exists for making this amendment 

effective in less than 30 days. 

We estimate that this AD will affect 

18 helicopters and will take about 322 

work hours to modify each helicopter 

and will require about 1 work hour to 

do a repetitive inspection with 24 

inspections per helicopter per year at an 

average labor rate of $80 per work hour. 

Required parts will cost about $14,960 

per helicopter. Based on these figures 

and assuming 24 repetitive inspections 

per helicopter per year for 2 years until 

the modification is required, we 

estimate the total cost impact of the AD 

on U.S. operators to be $802,080. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2008–0834; 

Directorate Identifier 2008–SW–34–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 


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60104 Federal Register / Vol. 73, No. 198 / Friday, October 10, 2008 / Rules and Regulations 

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:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of our docket Web site, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

Regulatory Findings 

We have 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 the 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 an economic evaluation 

of the estimated costs to comply with 

this AD. See the AD docket to examine 

the economic evaluation. 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by 

removing Amendment 39–15411 (73 FR 

13096, March 12, 2008), and by adding 

a new airworthiness directive (AD), 

Amendment 39–15684, to read as 

follows: 

2008–20–08 MD Helicopters, Inc.: 

Amendment 39–15684. Docket No. 

FAA–2008–0834; Directorate Identifier 

2008–SW–34–AD. Supersedes AD 2008– 

05–17, Amendment 39–15411, Docket 

No. FAA–2007–29342, Directorate 

Identifier 2007–SW–08–AD. 

Applicability: Model 600N helicopters, 

serial numbers with a prefix ‘‘RN’’ and 003 

through 058, that have not been modified in 

the fuselage aft section to strengthen the 

tailboom attachments and longerons per MD 

Helicopters (MDHI) Technical Bulletin (TB) 

TB600N–007, dated January 12, 2004; 

TB600N–007, Revision 1, dated April 13, 

2006; or TB600N–007, Revision 2, dated 

October 5, 2006, certificated in any category. 

Compliance: Required as indicated. 

To prevent failure of the tailboom 

attachment fittings, separation of the 

tailboom from the helicopter, and subsequent 

loss of control of the helicopter, do the 

following: 

Note 1: There is a slight discrepancy 

between MD Helicopters, Inc. Service 

Bulletin SB600N–036, dated November 2, 

2001 (SB600N–036) and MD Helicopters 

Service Bulletin SB600N–039, dated 

December 9, 2003 (SB600N–039) on the 

vertical location of the upper left inspection 

hole. Either location is acceptable for this 

AD. 

(a) Within 5 hours time-in-service (TIS), 

unless accomplished previously: 

(1) Remove the tailboom fairing and 

tailboom. Remove both upper tailboom 

attachment access covers in accordance with 

the Accomplishment Instructions, paragraph 

2.B.(2) of SB600N–036. 

Note 2: MDHI CSP–HMI–2, Section 53–40– 

30, pertains to the subject of this AD. 

(2) Using a light and a 10x or higher 

magnifying glass: 

(i) Inspect the right and left upper tailboom 

attachment fittings, part number (P/N) 

500N3422 and 500N3422–3, respectively, for 

a crack as shown in Figure 1 of SB600N–036. 

If a crack is found, replace any cracked 

attachment fitting with an airworthy 

attachment fitting before further flight. 

(ii) Inspect both upper tailboom attachment 

nut plates for thread damage or a crack. 

Replace any damaged or cracked nut plate 

with an airworthy nut plate before further 

flight. 

(iii) Inspect both angles for a crack. If a 

crack is found on a right-hand angle, P/N 

500N3429–6, before further flight, install a 

new clip in accordance with the 

Accomplishment Instructions, paragraph 

2.B.(5)(c) of SB600N–036. If a crack is found 

on the left-hand angle, P/N 500N3429–7, 

before further flight, replace the angle with 

an airworthy angle, or repair the angle in 

accordance with FAA-approved procedures. 

(3) Replace the upper right (pilot side) 

tailboom attachment bolt (bolt) with a new 

bolt. 

(4) If the removed upper right pilot-side 

bolt is broken, replace the remaining three 

bolts with airworthy bolts before further 

flight. 

(5) Add one washer, P/N AN960C516 

(NAS1149C0563R) or AN960C616 

(NAS1149C0663R), as appropriate, to each 

tailboom bolt between the tailboom and the 

NAS1587 countersunk washer. A minimum 

of two threads must extend past the nut 

plate. 

(6) Modify both access covers in 

accordance with the Accomplishment 

Instructions, paragraph 2.B.(6), of SB600N– 

036. 

(b) Within 5 hours TIS, unless 

accomplished previously: 

(1) Drill four additional inspection holes in 

the fuselage as shown for the left side of the 

fuselage in Figure 1 of SB600N–039, by 

following the Accomplishment Instruction 

paragraphs of SB600N–039 as follows: 

(i) Paragraphs 2.A.(1)(a), (b), and (d) for 

inspection holes at L166 and R166. 

(ii) Paragraphs 2.A.(2)(a), (b), and (d) for 

inspection holes at L153 and R153. 

(2) Thoroughly clean the attachment 

fittings and surrounding area. If the 

attachment fittings and surrounding area 

cannot be satisfactorily cleaned to 

accomplish a borescope inspection, then 

accomplish the actions in paragraph (c) of 

this AD. 

(3) Using a lighted borescope, inspect all 

four attachment fittings and the surrounding 

area for cracking. 

(i) If a crack is found in the upper right 

attachment fitting, accomplish the actions in 

paragraph (c) of this AD. 

(ii) If a crack is found in any of the other 

three attachment fittings, before further 

flight, accomplish the actions described in 

paragraph (f) of this AD. 

(4) Visually inspect the upper longerons for 

cracking in accordance with the 

Accomplishment Instructions, paragraph 

2.C., of SB600N–039. If a crack is found in 

the upper longeron, accomplish the actions 

in paragraph (e) of this AD. 

Note 3: The reference in Figure 1 of 

SB600N–039 to the inspection hole at L167 


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Federal Register / Vol. 73, No. 198 / Friday, October 10, 2008 / Rules and Regulations 60105 

mistakenly states that it was ‘‘Added by 

SB900–036.’’ Inspection holes at L167 and 

R167 were originally specified by SB600N– 

036. 

(c) Within 25 hours TIS, unless 

accomplished previously: 

(1) Thoroughly clean all attachment fittings 

and the surrounding areas, inspect the area 

for cracking, replace the upper right 

attachment fitting and all four nut plates, and 

paint the area inside of the attachment 

fittings in accordance with the 

Accomplishment Instructions, paragraph 

2.B., of MD Helicopters Service Bulletin 

SB600N–043, dated April 13, 2006 (SB600N– 

043). If a crack is found in any of the other 

three attachment fittings, before further 

flight, accomplish the actions described in 

paragraph (f) of this AD. 

(2) Using a 10x magnifying glass, inspect 

the attachment bolts’ threads and shanks for 

wear or damage in accordance with 

paragraph 2.B., of SB600N–043. If wear or 

damage is present, replace the attachment 

bolts with airworthy bolts. 

(d) Thereafter, at the specified intervals, 

remove the plug buttons from the inspection 

holes, and using a bright light, inspect the 

upper and lower left and upper and lower 

right attachment fittings, angles, and nut 

plates for a crack by following the 

Accomplishment Instruction paragraphs of 

SB600N–039, as follows, except you are not 

required to contact MDHI to meet the 

requirements of this AD. 

(1) At intervals not to exceed 25 hours TIS, 

through inspection holes at L167 and R167, 

inspect the upper left and upper right 

attachment fittings, angles, and nut plates by 

following the Accomplishment Instructions, 

paragraphs 2.B.(2) through 2.B.(4), of 

SB600N–039. 

(2) At intervals not to exceed 100 hours 

TIS, through inspection holes at L166 and 

R166, inspect the lower left and lower right 

attachment fittings, angles, and nut plates by 

following the Accomplishment Instructions, 

paragraphs 2.B.(2) through 2.B.(4), of 

SB600N–039. 

(e) If a crack is found in the upper right 

attachment fitting, or in any angle, nut plate, 

longeron, or if thread wear or damage is 

found on any nut plate or bolt, before further 

flight, replace the cracked or worn or 

damaged part with an appropriate airworthy 

part, or accomplish the actions in paragraph 

(f) of this AD. If cracking is found in any of 

the other three attachment fittings, before 

further flight, accomplish the actions 

described in paragraph (f) of this AD. 

(f) If required by paragraph (c)(1) of this 

AD, or if you make this modification to 

comply with paragraph (e) of this AD, modify 

the fuselage aft section to strengthen the 

tailboom attachments and the upper 

longerons by following paragraph 2, 

Accomplishment Instructions, of MDHI 

TB600N–007, dated January 12, 2004; 

TB600N–007, Revision 1, dated April 13, 

2006; or TB600N–007, Revision 2, dated 

October 5, 2006; except you are not required 

to contact the manufacturer. This 

modification to the fuselage aft section is 

terminating action for the requirements of 

this AD. 

(g) Within 24 months, modify the fuselage 

aft section to strengthen the tailboom 

attachments and upper longerons by 

following paragraph 2, Accomplishment 

Instructions, of MDHI TB600N–007, Revision 

2, dated October 5, 2006, except you are not 

required to contact the manufacturer. This 

modification to the fuselage aft section is 

terminating action for the requirements of 

this AD. 

(h) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Los Angeles 

Aircraft Certification Office, Airframe 

Branch, FAA, ATTN: Eric Schrieber, 

Aviation Safety Engineer, 3960 Paramount 

Blvd., Lakewood, California 90712, telephone 

(562) 627–5348, fax (562) 627–5210, for 

information about previously approved 

alternative methods of compliance. 

(i) Inspect, replace, and modify the 

fuselage aft section according to the specified 

portions of the following MD Helicopters 

service information, as applicable. 

(1) Service Bulletin SB600N–036, dated 

November 2, 2001; incorporated by reference 

as of April 29, 2002 (67 FR 17934, April 12, 

2002). 

(2) Service Bulletin SB600N–039, dated 

December 9, 2003; Service SB600N–043, 

dated April 13, 2006; and Technical Bulletin 

TB600N–007, Revision 1, dated April 13, 

2006; incorporated by reference as of April 

27, 2006 (71 FR 24808, April 27, 2006). 

(3) Technical Bulletin TB600N–007, 

Revision 2, dated October 5, 2006; 

incorporated by reference as of April 16, 

2008 (73 FR 13096, March 12, 2008). 

(4) The incorporation by reference of these 

documents was approved previously by the 

Director of the Federal Register in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

(5) Copies of this service information may 

be obtained from MD Helicopters Inc., Attn: 

Customer Support Division, 4555 E. 

McDowell Rd., Mail Stop M615, Mesa, 

Arizona 85215–9734, telephone 1–800–388– 

3378, fax 480–346–6813, or on the Internet at 

http://www.mdhelicopters.com. 

(6) Copies may be inspected at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas, 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. 

(j) This amendment becomes effective 

on October 27, 2008. 

Issued in Fort Worth, Texas, on September 

25, 2008. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–23540 Filed 10–9–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Part 301 

[Docket Nos. EF08–2011–000 and RM08–20– 

000] 

Sales of Electric Power to the 

Bonneville Power Administration; 

Revisions to Average System Cost 

Methodology 

September 30, 2008. 

AGENCY: Federal Energy Regulatory 

Commission. 

ACTION: Interim rule. 

SUMMARY: The Bonneville Power 

Administration (Bonneville) has 

submitted for the Federal Energy 

Regulatory Commission (Commission)’s 

approval a new methodology for 

determining the average system cost 

(ASC) of a utility’s resources under the 

Pacific Northwest Electric Power 

Planning and Conservation Act 

(Northwest Power Act). Bonneville 

requested that the Commission revise its 

regulations to incorporate the new 

methodology and to make the revised 

regulations effective October 1, 2008. 

On an interim basis, the Commission is 

conditionally revising its regulations 

governing the ASC methodology used 

by Bonneville in its Residential 

Exchange Program. The Commission 

also is requesting comments on 

whether, on a final basis, the 

Commission should approve the new 

ASC methodology proposed by 

Bonneville. 

DATES: Effective date: This interim rule 

is effective October 10, 2008. 

Applicability date: The initial 

exchange period begins October 1, 2008 

Comment date: Comments on the 

interim rule are due November 10, 2008. 

ADDRESSES: You may submit comments 

on the interim rule, identified by Docket 

Nos. EF08–2011–000 and RM08–20– 

000, by one of the following methods: 

• Agency Web site: http:// 

www.ferc.gov. Follow instructions for 

submitting comments via the eFiling 

link found in the Comment Procedures 

Section of the preamble. 

• Mail: Commenters unable to file 

comments electronically must mail or 

hand deliver an original and 14 copies 

of their comments to the Federal Energy 

Regulatory Commission, Secretary of the 

Commission, 888 First Street, NE., 

Washington, DC 20426. Please refer to 

the Comment Procedures Section of the 

preamble for additional information on 

how to file paper comments. 


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