Airworthiness Directives; MD Helicopters, Inc., Model 369, YOH-6A, 369A, OH-6A, 369H, 369HM, 369HS, 369HE, 369D, 369E, 369F, and 369FF Helicopters, 33642-33644 [E7-11409]
Download as PDF
<![CDATA[
33642
Federal Register / Vol. 72, No. 117 / Tuesday, June 19, 2007 / Rules and Regulations
Actions
Compliance
Procedures
(2) Replace the hydraulic pump outlet tube,
part number (P/N) 390–580035 (or FAA-approved equivalent) for the LH engine or P/N
390–580037 (or FAA-approved equivalent)
for the RH engine.
Each and every time any of the following occurs until the kits required in paragraph
(e)(4) of this AD are incorporated
(i) Prior to further flight after any inspection required in paragraph (e)(1) of this AD where
evidence of chafing, excessive vibration,
wear, deterioration, or hydraulic fluid leakage is found; and
(ii) Within 1 hour TIS following identification of
an intended or unintended engine operation
with the hydraulic shutoff valve closed.
Within 5 days after December 28, 2006 (the
effective date of AD 2006–26–08).
Raytheon Aircraft Premier 1 Model 390 Maintenance Manual, P/N 390–590001–0015.
(3) Incorporate Raytheon Aircraft Company
Part
Number
390–590001–0003C3TC6,
dated September 16, 2006 into the airplane
flight manual (AFM).
(4) Incorporate Kits No. 390–5804–0001 and
390–5805–0001.
At whichever of the following that occurs first:
(i) Within the next 25 hours TIS after
June 20, 2007 (the effective date of this
AD); or
(ii) Within the next 45 days after June 20,
2007 (the effective date of this AD.
(f) After the actions required in paragraph
(e)(4) of this AD are done:
(1) the repetitive inspections and
replacement of paragraphs (e)(1) and (e)(2) of
this AD are no longer required.
(2) the requirement in paragraph (e)(3) of
this AD to incorporate Raytheon Aircraft
Company Part Number 390–590001–
0003C3TC6, dated September 16, 2006, into
the AFM remains valid.
5805 (Kit 390–5805–0001 Field Service Kit),
as referenced in Hawker Beechcraft
Mandatory Service Bulletin 29–3800, Issued
May, 2007, to do the actions required by this
AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Raytheon Aircraft Company Kit—Dampener
Support Improvement, Drawing No. 390–
5804 (Kit 390–5804–0001 Field Service Kit)
and Raytheon Aircraft Company Kit—
Hydraulic Pump Pressure Hose Installation
No. 390–5805 (Kit 390–5805–0001 Field
Service Kit), as referenced in Hawker
Beechcraft Mandatory Service Bulletin 29–
3800, Issued May, 2007, under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) On February 2, 2006 (71 FR 5581,
February 2, 2006), the Director of the Federal
Register approved the incorporation by
reference of Raytheon Mandatory Service
Bulletin No. SB 29–3771, dated January,
2006; and Raytheon Safety Communique No.
267, dated January 2006.
(3) For service information identified in
this AD, contact Hawker Beechcraft
Corporation, 9709 East Central, Wichita,
Kansas 67291; telephone: (800) 429–5372 or
(316) 676–3140.
(4) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Kansas City, Missouri
64106; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
pwalker on PROD1PC71 with RULES
Alternative Methods of Compliance
(AMOCs)
(g) The Manager, Wichita Aircraft
Certification Office, FAA, ATTN: James P.
Galstad, Propulsion Aerospace Engineer,
ACE 116W, Wichita Aircraft Certification
Office, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone: (316) 946–
4135; fax: (316) 946–4107, has the authority
to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Before using any approved AMOC on any
airplane to which the AMOC applies, notify
your appropriate principal inspector (PI) in
the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(h) AMOCs approved for AD 2006–26–08
are approved for this AD.
Material Incorporated by Reference
(i) You must use Raytheon Mandatory
Service Bulletin No. SB 29–3771, dated
January, 2006; Raytheon Safety Communique
No. 267, dated January 2006; and Raytheon
Aircraft Company Kit—Dampener Support
Improvement, Drawing No. 390–5804 (Kit
390–5804–0001 Field Service Kit) and
Raytheon Aircraft Company Kit—Hydraulic
Pump Pressure Hose Installation No. 390–
VerDate Aug<31>2005
17:54 Jun 18, 2007
Jkt 211001
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The owner/operator holding at least a private
pilot certificate as authorized by section
43.7 of the Federal Aviation Regulations (14
CFR 43.7) may do the AFM change requirement of this AD. Make an entry into the aircraft records showing compliance with this
portion of the AD in accordance with section
43.9 of the Federal Aviation Regulations (14
CFR 43.9).
Follow the instructions in the documents presented below as referenced in Hawker
Beechcraft Mandatory Service Bulletin 29–
3800, Issued May, 2007:
(i) Raytheon Aircraft Company Kit—
Dampener
Support
Improvement,
Drawing No. 390–5804 (Kit 390–5804–
0001 Field Service Kit).
(ii) Raytheon Aircraft Company Kit—Hydraulic Pump Pressure Hose Installation No. 390–5805 (Kit 390–5805–0001
Field Service Kit).
Issued in Kansas City, Missouri, on June 4,
2007.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–11241 Filed 6–18–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28449; Directorate
Identifier 2007–SW–18–AD; Amendment 39–
15103; AD 2007–09–51]
RIN 2120–AA64
Airworthiness Directives; MD
Helicopters, Inc., Model 369, YOH–6A,
369A, OH–6A, 369H, 369HM, 369HS,
369HE, 369D, 369E, 369F, and 369FF
Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: This document publishes in
the Federal Register an amendment
adopting Airworthiness Directive (AD)
2007–09–51, sent previously to all
known U.S. owners and operators of the
E:\FR\FM\19JNR1.SGM
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pwalker on PROD1PC71 with RULES
Federal Register / Vol. 72, No. 117 / Tuesday, June 19, 2007 / Rules and Regulations
specified MD Helicopters, Inc. (MDHI),
model helicopters by individual letters.
This AD requires, before further flight,
removing each affected tail rotor blade
assembly and inspecting the bore of the
tail rotor blade root fitting. If the blade
assembly does not have a smooth
radius, the AD requires replacing it. The
AD also requires identifying each
airworthy tail rotor blade assembly with
the applicable helicopter model. This
amendment is prompted by a report of
an accident after the loss of a tail rotor
blade. The actions specified by this AD
are intended to prevent the failure of a
tail rotor blade and subsequent loss of
control of the helicopter.
DATES: Effective July 5, 2007, to all
persons except those persons to whom
it was made immediately effective by
Emergency AD 2007–09–51, issued on
April 27, 2007, which contained the
requirements of this amendment.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of July 5, 2007.
Comments for inclusion in the Rules
Docket must be received on or before
August 20, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically;
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically;
• 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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays; or
• Fax: 202–493–2251.
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 web
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://
dms.dot.gov, or in person at the Docket
Management System (DMS) Docket
Offices between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The Docket Office (telephone
VerDate Aug<31>2005
17:54 Jun 18, 2007
Jkt 211001
(800) 647–5527) is located on the plaza
level of the Department of
Transportation Nassif Building at the
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the DMS
receives them.
FOR FURTHER INFORMATION CONTACT: John
Cecil, Aviation Safety Engineer, FAA,
Los Angeles Aircraft Certification
Office, Airframe Branch, 3960
Paramount Blvd., Lakewood, California
90712–4137, telephone (562) 627–5228,
fax (562) 627–5210.
SUPPLEMENTARY INFORMATION: On April
27, 2007, the FAA issued Emergency AD
2007–09–51 (EAD) for the specified
MDHI model helicopters. The EAD
requires, before further flight, removing
each affected tail rotor blade assembly
and, using a bright light, inspecting the
bore of the tail rotor blade root fitting.
If the blade assembly does not have a
smooth radius, the AD requires
replacing it. The AD also requires
identifying each airworthy tail rotor
blade assembly with the applicable
model of helicopter. That action was
prompted by a report of an accident
after the loss of a tail rotor blade. This
condition, if not corrected, could result
in the failure of a tail rotor blade and
subsequent loss of control of the
helicopter.
MDHI has issued Service Bulletin No.
SB369H–247, SB369D–204, SB369E–
099, and SB369F–084, dated April 26,
2007 (SB), which describes procedures
for inspecting the tail rotor blade
assembly. The SB states that reports
from the field have shown that there are
tail rotor blades in operation with a
machining defect. The SB further states
that these blades have a sharp transition
in the tapered end of the root fitting
bore that can cause the tail rotor blade
root fitting to fail.
Since the unsafe condition described
is likely to exist or develop on other
MDHI model helicopters of these same
type designs, the FAA issued EAD
2007–09–51 to prevent the failure of a
tail rotor blade and subsequent loss of
control of the helicopter. This AD
requires the following, before further
flight:
• Remove each affected tail rotor
blade assembly. Using a bright light,
inspect the bore of the tail rotor blade
root fitting.
• Replace each blade assembly that
does not have a smooth radius.
• Identify the airworthy tail rotor
blade assembly with the applicable
model of helicopter.
The actions must be done by following
specified portions of the ASB described
previously. The short compliance time
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33643
involved is required because the
previously described critical unsafe
condition can adversely affect the
controllability and structural integrity of
the helicopter. Therefore, removing each
affected blade assembly, inspecting the
bore of the tail rotor blade root fitting,
and replacing each blade assembly that
does not have a smooth radius are
required before further flight, and this
AD must be issued immediately.
Since it was found that immediate
corrective action was required, notice
and opportunity for prior public
comment thereon were impracticable
and contrary to the public interest. Good
cause existed to make the AD effective
immediately by individual letters issued
on April 27, 2007, to all known U.S.
owners and operators of MD
Helicopters, Inc., Model 369 (Army
YOH–6A), 369A (Army OH–6A), 369H,
369HM, 369HS, 369HE, 369D, 369E,
369F, and 369FF helicopters. These
conditions still exist, and the AD is
hereby published in the Federal
Register as an amendment to 14 CFR
39.13 to make it effective to all persons.
The FAA estimates that this AD will
affect 980 helicopters of U.S. registry
and will require about:
• 0.1 work hour to identify a blade,
• 2 work hours to remove, inspect,
install and balance the tail rotor blade
assemblies on each helicopter,
• $80 per work hour labor rate, and
• $8,862 for each replacement blade
plus hardware.
Based on these figures, we estimate the
total cost impact of the AD on U.S.
operators to be $1,901,592, assuming 1
out of 10 blades are found defective for
an estimated 196 blades that need
replacing.
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–2007–28449;
Directorate Identifier 2007–SW–18–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 https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
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33644
Federal Register / Vol. 72, No. 117 / Tuesday, June 19, 2007 / Rules and Regulations
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), or you may visit
https://dms.dot.gov.
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 DMS to examine the
economic evaluation.
pwalker on PROD1PC71 with RULES
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.
VerDate Aug<31>2005
18:22 Jun 18, 2007
Jkt 211001
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
I
2007–09–51 MD Helicopters, Inc.:
Amendment 39–15103. Docket No.
FAA–2007–28449; Directorate Identifier
2007–SW–28–AD.
Applicability
Model 369, YOH–6A, 369A, OH–6A, 369H,
369HM, 369HS, 369HE, 369D, 369E, 369F,
and 369FF helicopters, with a tail rotor
blade, part number (P/N) 369A1613,
369D21606, 369D21613, 369D21615, or 421–
088, all dash numbers, installed, certificated
in any category.
Compliance
Before further flight, unless accomplished
previously.
To prevent the loss of a tail rotor blade and
subsequent loss of control of the helicopter,
do the following:
(a) Inspect each affected tail rotor blade for
a smooth radius as follows:
(1) Remove the tail rotor blade assembly by
following the Accomplishment Instructions,
paragraphs 2.B.(1) through 2.B.(3), Part 2., of
MD Helicopters, Inc., Service Bulletin
SB369H–247, SB369D–204, SB369E–099, and
SB369F–084 dated April 26, 2007 (SB).
(2) Using a bright light, inspect the bore of
the tail rotor blade root fitting by following
the Accomplishment Instructions, paragraphs
2.B.(4) and 2.B.(5), Part 2, and Figures 1 and
2 of the SB.
(b) Replace each blade assembly that does
not have a smooth radius by following the
Accomplishment Instructions, paragraphs
2.B.(6) and (7), Part 2, and Figure 2 of the SB.
(c) Identify the airworthy tail rotor blade
assembly with the applicable model of
helicopter by following the Identification,
paragraphs 3.(1) through 3.(4) of the SB.
(d) 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, FAA; Attn: John
Cecil, Aviation Safety Engineer, Airframe
Branch, 3960 Paramount Blvd., Lakewood,
California 90712–4137, telephone (562) 627–
5228, fax (562) 627–5210, for information
about previously approved alternative
methods of compliance.
(e) Special flight permits will not be
issued.
(f) Inspecting, replacing, and identifying
the tail rotor blade assembly shall be done by
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
following the specified portions of MD
Helicopters, Inc., Service Bulletin SB369H–
247, SB369D–204, SB369E–099, and
SB369F–084, dated April 26, 2007. The
Director of the Federal Register approved this
incorporation by reference in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Copies 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 Web at https://www.mdhelicopters.com.
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.
(g) This amendment becomes effective on
July 5, 2007, to all persons except those
persons to whom it was made immediately
effective by Emergency AD 2007–09–51,
issued April 27, 2007, which contained the
requirements of this amendment.
Issued in Fort Worth, Texas, on June 5,
2007.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E7–11409 Filed 6–18–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2007–27678; Airspace
Docket No. 07–ACE–3]
Modification of Class E Airspace;
Monticello, IA
Federal Aviation
Administration (FAA), DOT.
ACTION: Direct final rule; confirmation of
effective date.
AGENCY:
SUMMARY: This document confirms the
effective date of the direct final rule
which revises Class E airspace at
Monticello, IA.
DATE: Effective Date: 0901 UTC, July 5,
2007.
FOR FURTHER INFORMATION CONTACT:
Grant Nichols, System Support, DOT
Regional Headquarters Building, Federal
Aviation Administration, 901 Locust,
Kansas City, MO 64106; telephone:
(816) 329–2522.
SUPPLEMENTARY INFORMATION: The FAA
published this direct final rule with a
request for comments in the Federal
Register on May 16, 2007 (72 FR 27415).
The FAA uses the direct final
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]]>Agencies
[Federal Register Volume 72, Number 117 (Tuesday, June 19, 2007)]
[Rules and Regulations]
[Pages 33642-33644]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-11409]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28449; Directorate Identifier 2007-SW-18-AD;
Amendment 39-15103; AD 2007-09-51]
RIN 2120-AA64
Airworthiness Directives; MD Helicopters, Inc., Model 369, YOH-
6A, 369A, OH-6A, 369H, 369HM, 369HS, 369HE, 369D, 369E, 369F, and 369FF
Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This document publishes in the Federal Register an amendment
adopting Airworthiness Directive (AD) 2007-09-51, sent previously to
all known U.S. owners and operators of the
[[Page 33643]]
specified MD Helicopters, Inc. (MDHI), model helicopters by individual
letters. This AD requires, before further flight, removing each
affected tail rotor blade assembly and inspecting the bore of the tail
rotor blade root fitting. If the blade assembly does not have a smooth
radius, the AD requires replacing it. The AD also requires identifying
each airworthy tail rotor blade assembly with the applicable helicopter
model. This amendment is prompted by a report of an accident after the
loss of a tail rotor blade. The actions specified by this AD are
intended to prevent the failure of a tail rotor blade and subsequent
loss of control of the helicopter.
DATES: Effective July 5, 2007, to all persons except those persons to
whom it was made immediately effective by Emergency AD 2007-09-51,
issued on April 27, 2007, which contained the requirements of this
amendment.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 5, 2007.
Comments for inclusion in the Rules Docket must be received on or
before August 20, 2007.
ADDRESSES: Use one of the following addresses to submit comments on
this AD:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically;
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically;
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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays; or
Fax: 202-493-2251.
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 web 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://
dms.dot.gov, or in person at the Docket Management System (DMS) Docket
Offices between 9 a.m. and 5 p.m., Monday through Friday, except
Federal holidays. The Docket Office (telephone (800) 647-5527) is
located on the plaza level of the Department of Transportation Nassif
Building at the street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after the DMS
receives them.
FOR FURTHER INFORMATION CONTACT: John Cecil, Aviation Safety Engineer,
FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960
Paramount Blvd., Lakewood, California 90712-4137, telephone (562) 627-
5228, fax (562) 627-5210.
SUPPLEMENTARY INFORMATION: On April 27, 2007, the FAA issued Emergency
AD 2007-09-51 (EAD) for the specified MDHI model helicopters. The EAD
requires, before further flight, removing each affected tail rotor
blade assembly and, using a bright light, inspecting the bore of the
tail rotor blade root fitting. If the blade assembly does not have a
smooth radius, the AD requires replacing it. The AD also requires
identifying each airworthy tail rotor blade assembly with the
applicable model of helicopter. That action was prompted by a report of
an accident after the loss of a tail rotor blade. This condition, if
not corrected, could result in the failure of a tail rotor blade and
subsequent loss of control of the helicopter.
MDHI has issued Service Bulletin No. SB369H-247, SB369D-204,
SB369E-099, and SB369F-084, dated April 26, 2007 (SB), which describes
procedures for inspecting the tail rotor blade assembly. The SB states
that reports from the field have shown that there are tail rotor blades
in operation with a machining defect. The SB further states that these
blades have a sharp transition in the tapered end of the root fitting
bore that can cause the tail rotor blade root fitting to fail.
Since the unsafe condition described is likely to exist or develop
on other MDHI model helicopters of these same type designs, the FAA
issued EAD 2007-09-51 to prevent the failure of a tail rotor blade and
subsequent loss of control of the helicopter. This AD requires the
following, before further flight:
Remove each affected tail rotor blade assembly. Using a
bright light, inspect the bore of the tail rotor blade root fitting.
Replace each blade assembly that does not have a smooth
radius.
Identify the airworthy tail rotor blade assembly with the
applicable model of helicopter.
The actions must be done by following specified portions of the ASB
described previously. The short compliance time involved is required
because the previously described critical unsafe condition can
adversely affect the controllability and structural integrity of the
helicopter. Therefore, removing each affected blade assembly,
inspecting the bore of the tail rotor blade root fitting, and replacing
each blade assembly that does not have a smooth radius are required
before further flight, and this AD must be issued immediately.
Since it was found that immediate corrective action was required,
notice and opportunity for prior public comment thereon were
impracticable and contrary to the public interest. Good cause existed
to make the AD effective immediately by individual letters issued on
April 27, 2007, to all known U.S. owners and operators of MD
Helicopters, Inc., Model 369 (Army YOH-6A), 369A (Army OH-6A), 369H,
369HM, 369HS, 369HE, 369D, 369E, 369F, and 369FF helicopters. These
conditions still exist, and the AD is hereby published in the Federal
Register as an amendment to 14 CFR 39.13 to make it effective to all
persons.
The FAA estimates that this AD will affect 980 helicopters of U.S.
registry and will require about:
0.1 work hour to identify a blade,
2 work hours to remove, inspect, install and balance the
tail rotor blade assemblies on each helicopter,
$80 per work hour labor rate, and
$8,862 for each replacement blade plus hardware.
Based on these figures, we estimate the total cost impact of the AD on
U.S. operators to be $1,901,592, assuming 1 out of 10 blades are found
defective for an estimated 196 blades that need replacing.
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-2007-28449;
Directorate Identifier 2007-SW-18-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 https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each
[[Page 33644]]
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), or you may visit https://dms.dot.gov.
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 DMS 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 adding a new airworthiness directive to
read as follows:
2007-09-51 MD Helicopters, Inc.: Amendment 39-15103. Docket No. FAA-
2007-28449; Directorate Identifier 2007-SW-28-AD.
Applicability
Model 369, YOH-6A, 369A, OH-6A, 369H, 369HM, 369HS, 369HE, 369D,
369E, 369F, and 369FF helicopters, with a tail rotor blade, part
number (P/N) 369A1613, 369D21606, 369D21613, 369D21615, or 421-088,
all dash numbers, installed, certificated in any category.
Compliance
Before further flight, unless accomplished previously.
To prevent the loss of a tail rotor blade and subsequent loss of
control of the helicopter, do the following:
(a) Inspect each affected tail rotor blade for a smooth radius
as follows:
(1) Remove the tail rotor blade assembly by following the
Accomplishment Instructions, paragraphs 2.B.(1) through 2.B.(3),
Part 2., of MD Helicopters, Inc., Service Bulletin SB369H-247,
SB369D-204, SB369E-099, and SB369F-084 dated April 26, 2007 (SB).
(2) Using a bright light, inspect the bore of the tail rotor
blade root fitting by following the Accomplishment Instructions,
paragraphs 2.B.(4) and 2.B.(5), Part 2, and Figures 1 and 2 of the
SB.
(b) Replace each blade assembly that does not have a smooth
radius by following the Accomplishment Instructions, paragraphs
2.B.(6) and (7), Part 2, and Figure 2 of the SB.
(c) Identify the airworthy tail rotor blade assembly with the
applicable model of helicopter by following the Identification,
paragraphs 3.(1) through 3.(4) of the SB.
(d) 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, FAA;
Attn: John Cecil, Aviation Safety Engineer, Airframe Branch, 3960
Paramount Blvd., Lakewood, California 90712-4137, telephone (562)
627-5228, fax (562) 627-5210, for information about previously
approved alternative methods of compliance.
(e) Special flight permits will not be issued.
(f) Inspecting, replacing, and identifying the tail rotor blade
assembly shall be done by following the specified portions of MD
Helicopters, Inc., Service Bulletin SB369H-247, SB369D-204, SB369E-
099, and SB369F-084, dated April 26, 2007. The Director of the
Federal Register approved this incorporation by reference in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies 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 Web at https://
www.mdhelicopters.com. 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.
(g) This amendment becomes effective on July 5, 2007, to all
persons except those persons to whom it was made immediately
effective by Emergency AD 2007-09-51, issued April 27, 2007, which
contained the requirements of this amendment.
Issued in Fort Worth, Texas, on June 5, 2007.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-11409 Filed 6-18-07; 8:45 am]
BILLING CODE 4910-13-P
