Airworthiness Directives; MD Helicopters, Inc. Model 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HS, 369HM, 500N, and OH-6A Helicopters, 32788-32791 [E7-11393]
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32788
Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations
• $6 for hydraulic fluid each time it
is changed.
Based on these figures, we estimate
the total cost impact of the AD on U.S.
operators to be $92,296, assuming two
fluid replacements per year for 50
percent of the helicopter fleet.
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.
Adoption of the Amendment
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the Federal Aviation Administration
I
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17:11 Jun 13, 2007
Jkt 211001
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:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
(e) This amendment becomes effective on
July 19, 2007.
Note: The subject of this AD is addressed
in Direction Generale de l’Aviation Civile
(France) AD Nos. F–2004–055 and F–2004–
056, both dated April 28, 2004.
2. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
2007–12–22 Eurocopter France:
Amendment 39–15100. Docket No.
FAA–2005–20863; Directorate Identifier
2004–SW–36–AD.
Issued in Fort Worth, Texas, on May 25,
2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. E7–11410 Filed 6–13–07; 8:45 am]
BILLING CODE 4910–13–P
§ 39.13
[Amended]
I
Applicability
Model AS350B, BA, B1, B2, B3, D and
AS355E helicopters, certificated in any
category.
Compliance
Required as indicated.
To prevent ice from forming in the
hydraulic system resulting in an unintended
movement of the flight controls and
subsequent loss of control of the helicopter,
do the following:
(a) If the outside air temperature in an FAA
weather briefing is forecast to be below
negative 15 degrees Celsius (5 degrees
Fahrenheit) at or below your planned flight
altitude and the hydraulic fluid has not been
replaced within the past 100 hours time-inservice or within the past 30 days, whichever
occurred first, before further flight, replace
the hydraulic fluid. Replace the hydraulic
fluid by following the Accomplishment
Instructions, paragraphs 2.A. and 2.B., of
Eurocopter Alert Service Bulletin Nos.
05.00.43 or 05.00.45, both dated April 8,
2004, as applicable.
(b) 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 Safety Management Group,
Rotorcraft Directorate, FAA, ATTN: Ed
Cuevas, Aviation Safety Engineer, Fort
Worth, Texas 76193–0111, telephone (817)
222–5355, fax (817) 222–5961, for
information about previously approved
alternative methods of compliance.
(c) Special flight permits will not be
issued.
(d) Replacing the hydraulic fluid must be
done by following Eurocopter Alert Service
Bulletin Nos. 05.00.43 or 05.00.45, both
dated April 8, 2004, as applicable. 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 American
Eurocopter Corporation, 2701 Forum Drive,
Grand Prairie, Texas 75053–4005, telephone
(972) 641–3460, fax (972) 641–3527. You may
review copies at the FAA, Office of the
Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 63, 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://
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003–SW–37–AD; Amendment
39–15101; AD 2007–12–23]
RIN 2120–AA64
Airworthiness Directives; MD
Helicopters, Inc. Model 369A, 369D,
369E, 369F, 369FF, 369H, 369HE,
369HS, 369HM, 500N, and OH–6A
Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This amendment adopts a
new airworthiness directive (AD) for
MD Helicopters, Inc. (MDHI) Model
369A, 369D, 369E, 369F, 369FF, 369H,
369HE, 369HS, 369HM, 500N, and OH–
6A helicopters that requires inspecting
each landing gear fairing support
assembly (support assembly), replacing
or reworking certain forward and aft
landing gear assemblies, and creating an
access hole to facilitate inspections and
a recurring inspection. A terminating
action for the requirements of this AD
is also provided. This amendment is
prompted by five reports of landing gear
strut (strut) failures. The actions
specified by this AD are intended to
detect a crack that could result in the
failure of a strut and subsequent loss of
control of the helicopter during landing.
DATES: Effective July 19, 2007.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of July 19,
2007.
The service information
referenced in this AD may be obtained
from MD Helicopters Inc., Attn:
Customer Support Division, 4555 E.
McDowell Rd., Mail Stop M615, Mesa,
ADDRESSES:
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Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations
Arizona 85215–9734, telephone 1–800–
388–3378, fax 480–346–6813, or on the
Web at https://www.mdhelicopters.com.
This information may be examined at
the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas.
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: A
proposal to amend 14 CFR part 39 to
add an AD for the specified MDHI
model helicopters was published as a
Notice of Proposed Rulemaking (NPRM)
in the Federal Register on August 4,
2004 (69 FR 47040). That NPRM would
have required removing all landing gear
fairings; determining the number and
location of rivets that attach the landing
gear fairing support assembly to the
landing gear strut; and if three rivets
(forward, aft and inboard) are present,
replacing or reworking the landing gear
assembly. If only the forward and aft
rivets are present, no rework would be
required by the proposed AD. That
NPRM was prompted by five reports of
strut failures. Operators of the
helicopters with failed struts do not fall
into any clear category of service. For
example, one was a tour operator in
Niagara Falls, New York, and another
was a police department operator in
Calgary, Canada. In its original design,
the fairing support was attached to the
strut with three rivets (forward, aft, and
outboard). In 1994, the manufacturer
released a design change to attach the
fairing support assembly with only
forward and aft rivets because of the
possibility of reduced service life of the
strut if the third rivet was located on the
inboard side of the strut. Some landing
gear struts entered service with an
additional rivet hole drilled on the
inboard side of the strut. This additional
rivet hole results in decreased fatigue
strength of the strut and subsequent
cracking. That condition, if not
corrected, could result in cracking of the
forward and aft struts, failure of a strut,
and subsequent loss of control of the
helicopter during landing.
After issuing that NPRM, we received
several comments from 2 commenters
and we agreed that we should make
some changes to the NPRM. Because
some of those changes expanded the
scope of the NPRM, we determined that
it was necessary to reopen the comment
period to provide additional
opportunity for public comment.
Therefore, a Supplemental NPRM
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17:11 Jun 13, 2007
Jkt 211001
(SNPRM) was published in the Federal
Register on January 8, 2007 (72 FR 666).
The SNPRM revised the NPRM by
proposing to mandate both the creation
of an access hole to facilitate
inspections and a recurring inspection.
The SNPRM also proposed excluding
from the applicability certain
helicopters modified with a certain
Supplemental Type Certificate (STC)
and provided a terminating action for
the proposed requirements. The SNPRM
also included clarifying changes.
Interested persons have been afforded
an opportunity to participate in the
making of this amendment. No
comments were received on the SNPRM
or the FAA’s determination of the cost
to the public. The FAA has determined
that air safety and the public interest
require the adoption of the rule as
proposed except we have expanded the
contact address in paragraph (d) in the
body of the AD to provide more
information to the public and have
made minor editorial changes. These
changes will neither increase the
economic burden on any operator nor
increase the scope of this AD.
The FAA has reviewed MD
Helicopters Service Bulletin SB369H–
244, SB369E–094, SB500N–022,
SB369D–200, and SB369F–078, dated
April 7, 2000, which describes
procedures for determining the number
and location of rivets attaching the
landing gear fairing support assembly to
the landing gear strut. Where three
rivets are present, instructions are
provided to rework the landing gear
assembly and replace any cracked strut
assembly.
The FAA estimates that this AD will
affect 651 helicopters of U.S. registry.
Determining the number of rivets and
initially inspecting each affected ‘‘3hole’’ strut and fairing will take
approximately 2 work hours, installing
a new strut will take approximately 1.5
work hours, and reworking a strut will
take 1 work hour. Each repetitive
inspection will take 1/4 work hour per
strut (1 hour per helicopter for each of
4 struts). The average labor rate is $80
per work hour. Required parts (new
struts) will cost approximately $2,838
for each forward strut, $2,574 for each
aft strut, and $97 for a modification kit
to install an inspection hole. Assuming
that each helicopter has an initial
inspection, that all 651 helicopters are
modified, that 325 helicopters have two
struts reworked, that 5 helicopters
require 2 new forward struts, and that
2 repetitive inspections are required per
year, the total estimated cost of the AD
on U.S. operators is about $353,047
($248,887 for the initial inspections,
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32789
modification, and parts, and $104,160
for the repetitive inspections).
Regulatory Findings
The regulations adopted herein 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. Therefore, it is
determined that this final rule does not
have federalism implications under
Executive Order 13132.
For the reasons discussed above, I
certify that this action (1) is not a
‘‘significant regulatory action’’ under
Executive Order 12866; (2) is not a
‘‘significant rule’’ under DOT
Regulatory Policies and Procedures (44
FR 11034, February 26, 1979); and (3)
will not have a significant economic
impact, positive or negative, on a
substantial number of small entities
under the criteria of the Regulatory
Flexibility Act. A final evaluation has
been prepared for this action and it is
contained in the Rules Docket. A copy
of it may be obtained from the Rules
Docket at the location provided under
the caption ADDRESSES.
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:
I
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Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations
§ 39.13
PART 39—AIRWORTHINESS
DIRECTIVES
[Amended]
2. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
I
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
2007–12–23 MD Helicopters, Inc.:
Amendment 39–15101. Docket No.
2003–SW–37–AD.
Applicability
Model 369A, 369D, 369E, 369F, 369FF,
369H, 369HE, 369HS, 369HM, 500N, and
OH–6A helicopters, with any of the
components listed in the Applicability Table
installed, excluding any helicopter with
Aerometals strut (part number (P/N)
369XH6001–41, –42, –51, or –52) installed in
accordance with Supplemental Type
Certificate (STC) No. SR00981LA, certificated
in any category:
APPLICABILITY TABLE
Component name
Component part No.
(P/N)
Mid Aft Fairing Assembly ....................................
Aft Support Assembly .........................................
369H6200–61, –62, standard gear.
369H6200–23, –24 (–23 to be reinstalled on the right-hand side and –24 to be reinstalled on
the left-hand side, all configurations).
369H92113–91, –92, extended gear.
369H92113–131, –132, extended gear.
369A6200–45, –46, standard gear.
369H92113–111, –112, extended gear.
369H6200–41, –42, standard gear.
369H92113–81, –82, extended gear.
369H6200–23, –24 (–23 becomes right-hand side and –24 becomes left-hand side).
369H92113–121, –122, extended gear.
369A6200–57, –58, standard gear.
369H92113–101, –102, extended gear.
Aft Fairing Assembly ...........................................
Aft Filler Assembly ..............................................
Aft Fillet Assembly ..............................................
Aft Fillet Assembly ..............................................
Mid Fwd Fairing Assembly .................................
Fwd Fairing Assembly ........................................
Fwd Support Assembly .......................................
Fwd Filler Assembly ...........................................
Fwd Fillet Assembly ............................................
Fwd Fillet Assembly ............................................
pwalker on PROD1PC71 with RULES
Compliance
Required as indicated.
To detect a crack that could result in the
failure of a strut and subsequent loss of
control of the helicopter during landing,
accomplish the following:
(a) Within 4 months, unless accomplished
previously, remove all landing gear fairings
(fairings) and inspect each landing gear
fairing support assembly (support assembly)
to determine the number and location of the
rivets attaching the support assembly to the
landing gear strut assembly (strut assembly).
(1) If three rivets (forward, aft and inboard)
are used to attach the support assembly to the
strut assembly,
(i) For each FORWARD landing gear
assembly, remove the landing gear fillet
assembly (fillet assembly), the three rivets,
and the support assembly, and clean and
dye-penetrant inspect the area in and around
the 0.125 (3.18mm) diameter hole in the
inboard surface of the strut assembly.
(A) If the strut assembly is cracked, replace
the cracked strut assembly with an airworthy
strut assembly and install the other landing
gear components in accordance with steps (6)
through (11) of paragraph C of the
Accomplishment Instructions of MD
Helicopters Service Bulletin SB369H–244,
SB369E–094, SB500N–022, SB369D–200, and
SB369F–078, dated April 7, 2000 (SB).
(B) If the strut assembly is not cracked,
rework the landing gear assembly and install
the other landing gear components in
accordance with steps (5) through (11) of
paragraph C of the Accomplishment
Instructions of the SB.
(ii) For each AFT landing gear assembly,
remove the fillet assembly, the three rivets,
and the support assembly, and clean and
dye-penetrant inspect the area in and around
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Jkt 211001
the 0.125 (3.18mm) diameter hole in the
inboard surface of the strut assembly.
(A) If the strut assembly is cracked, replace
the cracked strut assembly with an airworthy
strut assembly and install the other landing
gear components in accordance with steps (6)
through (13) of paragraph B of the
Accomplishment Instructions of the SB.
(B) If the strut assembly is not cracked,
rework the landing gear assembly and install
the other landing gear components in
accordance with steps (5) through (13) of
Paragraph B of the Accomplishment
Instructions of the SB.
(2) If only two rivets (forward and aft) are
used to attach the support assembly to the
strut assembly and a third rivet hole has not
been drilled in the strut, neither the
inspection of the strut assembly nor the
rework of those landing gear assemblies is
required by this AD.
(b) At intervals not to exceed 100 hours TIS
or during each annual inspection, whichever
occurs first, for any strut assembly that has
a third rivet hole, remove the fairing
inspection button plug and clean and inspect
the area in and around the rivet hole for
cracks using a bright light and a 10x or higher
magnifying glass.
(1) If any FORWARD strut assembly is
cracked, replace the cracked strut with an
airworthy strut assembly.
(2) If any AFT strut assembly is cracked,
replace the cracked strut with an airworthy
strut assembly.
(c) Installing a strut assembly that has only
2 rivet holes is terminating action for the
requirements of this AD.
Note 1: For the Model 369D, 369E, 369F,
369FF, and 500N helicopters, the Handbook
of Maintenance Instruction, Servicing and
Maintenance, HMI, CSP–HMI–2, Chapter 32,
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Section 32–10–00, ‘‘Landing Gear Strut
Inspection’’ pertains to the subject of this AD.
Note 2: For the Model 369A (OH–6A),
369H, 369HE, 369HS, and 369HM
helicopters, the Basic Handbook of
Maintenance Instructions CSP–H–2, Section
6, ‘‘Landing Gear’’ pertains to the subject of
this AD.
(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, FAA,
Los Angeles Aircraft Certification Office,
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) The replacements and installations
shall be done in accordance with the
specified portions of MD Helicopters Service
Bulletin SB369H–244, SB369E–094,
SB500N–022, SB369D–200, and SB369F–078,
dated April 7, 2000. 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/
E:\FR\FM\14JNR1.SGM
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Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations
code_of_federal_regulations/
ibr_locations.html.
(f) This amendment becomes effective on
July 19, 2007.
Issued in Fort Worth, Texas, on June 5,
2007.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E7–11393 Filed 6–13–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 97
[Docket No. 30554; Amdt. No. 3222]
Standard Instrument Approach
Procedures; Miscellaneous
Amendments
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This amendment amends
Standard Instrument Approach
Procedures (SIAPs) for operations at
certain airports. These regulatory
actions are needed because of changes
occurring in the National Airspace
System, such as the commissioning of
new navigational facilities, addition of
new obstacles, or changes in air traffic
requirements. These changes are
designed to provide safe and efficient
use of the navigable airspace and to
promote safe flight operations under
instrument flight rules at the affected
airports.
This rule is effective June 14,
2007. The compliance date for each
SIAP is specified in the amendatory
provisions.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of June 14,
2007.
DATES:
Availability of matter
incorporated by reference in the
amendment is as follows:
For Examination—
1. FAA Rules Docket, FAA
Headquarters Building, 800
Independence Ave., SW., Washington,
DC 20591;
2. The FAA Regional Office of the
region in which affected airport is
located; or
3. The National Flight Procedures
Office, 6500 South MacArthur Blvd.,
Oklahoma City, OK 73169 or,
4. The National Archives and Records
Administration (NARA). For
pwalker on PROD1PC71 with RULES
ADDRESSES:
VerDate Aug<31>2005
17:11 Jun 13, 2007
Jkt 211001
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.
For Purchase—Individual SIAP
copies may be obtained from:
1. FAA Public Inquiry Center (APA–
200), FAA Headquarters Building, 800
Independence Avenue, SW.,
Washington, DC 20591; or
2. The FAA Regional Office of the
region in which the affected airport is
located.
By Subscription—Copies of all SIAPs,
mailed once every 2 weeks, are for sale
by the Superintendent of Documents,
U.S. Government Printing Office,
Washington, DC 20402.
FOR FURTHER INFORMATION CONTACT:
Donald P. Pate, Flight Procedure
Standards Branch (AFS–420), Flight
Technologies and Programs Division,
Flight Standards Service, Federal
Aviation Administration, Mike
Monroney Aeronautical Center, 6500
South MacArthur Blvd. Oklahoma City,
OK 73169 (Mail Address: P.O. Box
25082 Oklahoma City, OK 73125)
telephone: (405) 954–4164.
SUPPLEMENTARY INFORMATION: This
amendment to Title 14, Code of Federal
Regulations, Part 97 (14 CFR part 97)
amends Standard Instrument Approach
Procedures (SIAPs). The complete
regulatory description of each SIAP is
contained in the appropriate FAA Form
8260, as modified by the National Flight
Data Center (FDC)/Permanent Notice to
Airmen (P–NOTAM), which is
incorporated by reference in the
amendment under 5 U.S.C. 552(a), 1
CFR part 51, and § 97.20 of the Code of
Federal Regulations. Materials
incorporated by reference are available
for examination or purchase as stated
above.
The large number of SIAPs, their
complex nature, and the need for a
special format make their verbatim
publication in the Federal Register
expensive and impractical. Further,
airmen do not use the regulatory text of
the SIAPs, but refer to their graphic
depiction on charts printed by
publishers of aeronautical materials.
Thus, the advantages of incorporation
by reference are realized and
publication of the complete description
of each SIAP contained in FAA form
documents is unnecessary. The
provisions of this amendment state the
affected CFR sections, with the types
and effective dates of the SIAPs. This
amendment also identifies the airport,
its location, the procedure identification
and the amendment number.
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32791
The Rule
This amendment to 14 CFR part 97 is
effective upon publication of each
separate SIAP as amended in the
transmittal. For safety and timeliness of
change considerations, this amendment
incorporates only specific changes
contained for each SIAP as modified by
FDC/P–NOTAMs.
The SIAPs, as modified by FDC P–
NOTAM, and contained in this
amendment are based on the criteria
contained in the U.S. Standard for
Terminal Instrument Procedures
(TERPS). In developing these chart
changes to SIAPs, the TERPS criteria
were applied to only these specific
conditions existing at the affected
airports. All SIAP amendments in this
rule have been previously issued by the
FAA in a FDC NOTAM as an emergency
action of immediate flight safety relating
directly to published aeronautical
charts. The circumstances which
created the need for all these SIAP
amendments requires making them
effective in less than 30 days.
Further, the SIAPs contained in this
amendment are based on the criteria
contained in TERPS. Because of the
close and immediate relationship
between these SIAPs and safety in air
commerce, I find that notice and public
procedure before adopting these SIAPs
are impracticable and contrary to the
public interest and, where applicable,
that good cause exists for making these
SIAPs effective in less than 30 days.
Conclusion
The FAA has determined that this
regulation only involves an established
body of technical regulations for which
frequent and routine amendments are
necessary to keep them operationally
current. It, therefore—(1) is not a
‘‘significant regulatory action’’ under
Executive Order 12866; (2) is not a
‘‘significant rule’’ under DOT
Regulatory Policies and Procedures (44
FR 11034; February 26, 1979); and (3)
does not warrant preparation of a
regulatory evaluation as the anticipated
impact is so minimal. For the same
reason, the FAA certifies that this
amendment will not have a significant
economic impact on a substantial
number of small entities under the
criteria of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 97
Air Traffic Control, Airports,
Incorporation by reference, and
Navigation (Air).
E:\FR\FM\14JNR1.SGM
14JNR1
]]>Agencies
[Federal Register Volume 72, Number 114 (Thursday, June 14, 2007)]
[Rules and Regulations]
[Pages 32788-32791]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-11393]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-SW-37-AD; Amendment 39-15101; AD 2007-12-23]
RIN 2120-AA64
Airworthiness Directives; MD Helicopters, Inc. Model 369A, 369D,
369E, 369F, 369FF, 369H, 369HE, 369HS, 369HM, 500N, and OH-6A
Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) for
MD Helicopters, Inc. (MDHI) Model 369A, 369D, 369E, 369F, 369FF, 369H,
369HE, 369HS, 369HM, 500N, and OH-6A helicopters that requires
inspecting each landing gear fairing support assembly (support
assembly), replacing or reworking certain forward and aft landing gear
assemblies, and creating an access hole to facilitate inspections and a
recurring inspection. A terminating action for the requirements of this
AD is also provided. This amendment is prompted by five reports of
landing gear strut (strut) failures. The actions specified by this AD
are intended to detect a crack that could result in the failure of a
strut and subsequent loss of control of the helicopter during landing.
DATES: Effective July 19, 2007.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 19, 2007.
ADDRESSES: The service information referenced in this AD may be
obtained from MD Helicopters Inc., Attn: Customer Support Division,
4555 E. McDowell Rd., Mail Stop M615, Mesa,
[[Page 32789]]
Arizona 85215-9734, telephone 1-800-388-3378, fax 480-346-6813, or on
the Web at https://www.mdhelicopters.com. This information may be
examined at the FAA, Office of the Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort Worth, Texas.
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: A proposal to amend 14 CFR part 39 to add an
AD for the specified MDHI model helicopters was published as a Notice
of Proposed Rulemaking (NPRM) in the Federal Register on August 4, 2004
(69 FR 47040). That NPRM would have required removing all landing gear
fairings; determining the number and location of rivets that attach the
landing gear fairing support assembly to the landing gear strut; and if
three rivets (forward, aft and inboard) are present, replacing or
reworking the landing gear assembly. If only the forward and aft rivets
are present, no rework would be required by the proposed AD. That NPRM
was prompted by five reports of strut failures. Operators of the
helicopters with failed struts do not fall into any clear category of
service. For example, one was a tour operator in Niagara Falls, New
York, and another was a police department operator in Calgary, Canada.
In its original design, the fairing support was attached to the strut
with three rivets (forward, aft, and outboard). In 1994, the
manufacturer released a design change to attach the fairing support
assembly with only forward and aft rivets because of the possibility of
reduced service life of the strut if the third rivet was located on the
inboard side of the strut. Some landing gear struts entered service
with an additional rivet hole drilled on the inboard side of the strut.
This additional rivet hole results in decreased fatigue strength of the
strut and subsequent cracking. That condition, if not corrected, could
result in cracking of the forward and aft struts, failure of a strut,
and subsequent loss of control of the helicopter during landing.
After issuing that NPRM, we received several comments from 2
commenters and we agreed that we should make some changes to the NPRM.
Because some of those changes expanded the scope of the NPRM, we
determined that it was necessary to reopen the comment period to
provide additional opportunity for public comment. Therefore, a
Supplemental NPRM (SNPRM) was published in the Federal Register on
January 8, 2007 (72 FR 666). The SNPRM revised the NPRM by proposing to
mandate both the creation of an access hole to facilitate inspections
and a recurring inspection. The SNPRM also proposed excluding from the
applicability certain helicopters modified with a certain Supplemental
Type Certificate (STC) and provided a terminating action for the
proposed requirements. The SNPRM also included clarifying changes.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the SNPRM
or the FAA's determination of the cost to the public. The FAA has
determined that air safety and the public interest require the adoption
of the rule as proposed except we have expanded the contact address in
paragraph (d) in the body of the AD to provide more information to the
public and have made minor editorial changes. These changes will
neither increase the economic burden on any operator nor increase the
scope of this AD.
The FAA has reviewed MD Helicopters Service Bulletin SB369H-244,
SB369E-094, SB500N-022, SB369D-200, and SB369F-078, dated April 7,
2000, which describes procedures for determining the number and
location of rivets attaching the landing gear fairing support assembly
to the landing gear strut. Where three rivets are present, instructions
are provided to rework the landing gear assembly and replace any
cracked strut assembly.
The FAA estimates that this AD will affect 651 helicopters of U.S.
registry. Determining the number of rivets and initially inspecting
each affected ``3-hole'' strut and fairing will take approximately 2
work hours, installing a new strut will take approximately 1.5 work
hours, and reworking a strut will take 1 work hour. Each repetitive
inspection will take 1/4 work hour per strut (1 hour per helicopter for
each of 4 struts). The average labor rate is $80 per work hour.
Required parts (new struts) will cost approximately $2,838 for each
forward strut, $2,574 for each aft strut, and $97 for a modification
kit to install an inspection hole. Assuming that each helicopter has an
initial inspection, that all 651 helicopters are modified, that 325
helicopters have two struts reworked, that 5 helicopters require 2 new
forward struts, and that 2 repetitive inspections are required per
year, the total estimated cost of the AD on U.S. operators is about
$353,047 ($248,887 for the initial inspections, modification, and
parts, and $104,160 for the repetitive inspections).
Regulatory Findings
The regulations adopted herein 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a
significant economic impact, positive or negative, on a substantial
number of small entities under the criteria of the Regulatory
Flexibility Act. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
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:
[[Page 32790]]
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:
2007-12-23 MD Helicopters, Inc.: Amendment 39-15101. Docket No.
2003-SW-37-AD.
Applicability
Model 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HS, 369HM,
500N, and OH-6A helicopters, with any of the components listed in
the Applicability Table installed, excluding any helicopter with
Aerometals strut (part number (P/N) 369XH6001-41, -42, -51, or -52)
installed in accordance with Supplemental Type Certificate (STC) No.
SR00981LA, certificated in any category:
Applicability Table
------------------------------------------------------------------------
Component name Component part No. (P/N)
------------------------------------------------------------------------
Mid Aft Fairing Assembly..... 369H6200-61, -62, standard gear.
Aft Support Assembly......... 369H6200-23, -24 (-23 to be reinstalled
on the right-hand side and -24 to be
reinstalled on the left-hand side, all
configurations).
Aft Fairing Assembly......... 369H92113-91, -92, extended gear.
Aft Filler Assembly.......... 369H92113-131, -132, extended gear.
Aft Fillet Assembly.......... 369A6200-45, -46, standard gear.
Aft Fillet Assembly.......... 369H92113-111, -112, extended gear.
Mid Fwd Fairing Assembly..... 369H6200-41, -42, standard gear.
Fwd Fairing Assembly......... 369H92113-81, -82, extended gear.
Fwd Support Assembly......... 369H6200-23, -24 (-23 becomes right-hand
side and -24 becomes left-hand side).
Fwd Filler Assembly.......... 369H92113-121, -122, extended gear.
Fwd Fillet Assembly.......... 369A6200-57, -58, standard gear.
Fwd Fillet Assembly.......... 369H92113-101, -102, extended gear.
------------------------------------------------------------------------
Compliance
Required as indicated.
To detect a crack that could result in the failure of a strut
and subsequent loss of control of the helicopter during landing,
accomplish the following:
(a) Within 4 months, unless accomplished previously, remove all
landing gear fairings (fairings) and inspect each landing gear
fairing support assembly (support assembly) to determine the number
and location of the rivets attaching the support assembly to the
landing gear strut assembly (strut assembly).
(1) If three rivets (forward, aft and inboard) are used to
attach the support assembly to the strut assembly,
(i) For each FORWARD landing gear assembly, remove the landing
gear fillet assembly (fillet assembly), the three rivets, and the
support assembly, and clean and dye-penetrant inspect the area in
and around the 0.125 (3.18mm) diameter hole in the inboard surface
of the strut assembly.
(A) If the strut assembly is cracked, replace the cracked strut
assembly with an airworthy strut assembly and install the other
landing gear components in accordance with steps (6) through (11) of
paragraph C of the Accomplishment Instructions of MD Helicopters
Service Bulletin SB369H-244, SB369E-094, SB500N-022, SB369D-200, and
SB369F-078, dated April 7, 2000 (SB).
(B) If the strut assembly is not cracked, rework the landing
gear assembly and install the other landing gear components in
accordance with steps (5) through (11) of paragraph C of the
Accomplishment Instructions of the SB.
(ii) For each AFT landing gear assembly, remove the fillet
assembly, the three rivets, and the support assembly, and clean and
dye-penetrant inspect the area in and around the 0.125 (3.18mm)
diameter hole in the inboard surface of the strut assembly.
(A) If the strut assembly is cracked, replace the cracked strut
assembly with an airworthy strut assembly and install the other
landing gear components in accordance with steps (6) through (13) of
paragraph B of the Accomplishment Instructions of the SB.
(B) If the strut assembly is not cracked, rework the landing
gear assembly and install the other landing gear components in
accordance with steps (5) through (13) of Paragraph B of the
Accomplishment Instructions of the SB.
(2) If only two rivets (forward and aft) are used to attach the
support assembly to the strut assembly and a third rivet hole has
not been drilled in the strut, neither the inspection of the strut
assembly nor the rework of those landing gear assemblies is required
by this AD.
(b) At intervals not to exceed 100 hours TIS or during each
annual inspection, whichever occurs first, for any strut assembly
that has a third rivet hole, remove the fairing inspection button
plug and clean and inspect the area in and around the rivet hole for
cracks using a bright light and a 10x or higher magnifying glass.
(1) If any FORWARD strut assembly is cracked, replace the
cracked strut with an airworthy strut assembly.
(2) If any AFT strut assembly is cracked, replace the cracked
strut with an airworthy strut assembly.
(c) Installing a strut assembly that has only 2 rivet holes is
terminating action for the requirements of this AD.
Note 1: For the Model 369D, 369E, 369F, 369FF, and 500N
helicopters, the Handbook of Maintenance Instruction, Servicing and
Maintenance, HMI, CSP-HMI-2, Chapter 32, Section 32-10-00, ``Landing
Gear Strut Inspection'' pertains to the subject of this AD.
Note 2: For the Model 369A (OH-6A), 369H, 369HE, 369HS, and
369HM helicopters, the Basic Handbook of Maintenance Instructions
CSP-H-2, Section 6, ``Landing Gear'' pertains to the subject of this
AD.
(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, FAA, Los Angeles
Aircraft Certification Office, 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) The replacements and installations shall be done in
accordance with the specified portions of MD Helicopters Service
Bulletin SB369H-244, SB369E-094, SB500N-022, SB369D-200, and SB369F-
078, dated April 7, 2000. 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/
[[Page 32791]]
code--of--federal--regulations/ibr--locations.html.
(f) This amendment becomes effective on July 19, 2007.
Issued in Fort Worth, Texas, on June 5, 2007.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-11393 Filed 6-13-07; 8:45 am]
BILLING CODE 4910-13-P
