Airworthiness Directives; MD Helicopters, Inc. Model 600N Helicopters, 60102-60105 [E8-23540]
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Federal Register / Vol. 73, No. 198 / Friday, October 10, 2008 / Rules and Regulations
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:
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PART 77—TUBERCULOSIS
1. The authority citation for part 77
continues to read as follows:
■
6 Meat Animals Production, Distribution and
Income 2007 Summary. April 2008. Agricultural
Statistics Board. NASS, USDA.
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17:42 Oct 09, 2008
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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.
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(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).
*
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■ 3. In § 77.11, paragraphs (a) and (b) are
revised to read as follows:
§ 77.11
zones.
Modified accredited States or
(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.
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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.
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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
Federal Aviation
Administration, DOT.
ACTION: Final rule; request for
comments.
AGENCY:
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
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
https://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 https://
www.mdhelicopters.com.
Examining the Docket: You may
examine the docket that contains the
AD, any comments, and other
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information on the Internet at https://
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,
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60103
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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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 https://
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).
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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
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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:
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(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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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
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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
https://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: https://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]
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60105
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.
Federal Energy Regulatory
Commission.
ACTION: Interim rule.
AGENCY:
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.
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: https://
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.
DATES:
E:\FR\FM\10OCR1.SGM
10OCR1
]]>Agencies
[Federal Register Volume 73, Number 198 (Friday, October 10, 2008)]
[Rules and Regulations]
[Pages 60102-60105]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-23540]
=======================================================================
-----------------------------------------------------------------------
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
[[Page 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 https://
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 https://
www.mdhelicopters.com.
Examining the Docket: You may examine the docket that contains the
AD, any comments, and other information on the Internet at https://
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-in-
service (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
[[Page 60104]]
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 https://
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
0
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
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
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
[[Page 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 https://
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: https://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
