Airworthiness Directives; MD Helicopters, Inc. Model MD900 Helicopters, 78931-78934 [E8-28367]
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Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations
Actions and Compliance
(f) Unless already done, do the following
actions:
(1) Within the next 3 months after January
28, 2009 (the effective date of this AD) and
repetitively thereafter at intervals not to
exceed 12 months, visually inspect the
control bridge in areas of juncture with the
two control sticks for cracks. Do the
inspection following paragraph A of LET
Aircraft Industries, a.s. Mandatory Bulletin
MB No. L23/050a, Revision No. 2, dated
September 12, 2007, except use a 10X
magnifier and do a dye penetrant inspection
following the procedures in chapter 5,
section 5, of FAA Advisory Circular AC
43.13–1B CHG 1, dated September 27, 2001.
(2) If cracks are found in the control bridge
bedding during any inspection required in
paragraph (f)(1) of this AD, before further
flight, replace the defective control bridge
bedding, Dwg. No. A740 371N, in the control
bridge assembly, Dwg. No. A740 370N,
following LET Aircraft Industries, a.s.
Mandatory Bulletin MB No. L23/050a,
Revision No. 2, dated September 12, 2007;
and Appendix No. 1, ‘‘Replacement of
Bearings 608 CSN 024630 at Control Bridge
Dwg. No. A740 370N in a Bedding Dwg. No.
A740 371N,’’ to LET Aircraft Industries, a.s.
Mandatory Bulletin MB No. L23/050a,
Revision No. 2, dated September 12, 2007.
(3) Doing the replacement required in
paragraph (f)(2) of this AD terminates the 12month repetitive inspection required in
paragraph (f)(1) of this AD. After the
replacement required in paragraph (f)(2) of
this AD, perform subsequent inspections on
the new control bridge assembly according to
LET Aircraft Industries, a.s. Documentation
Bulletin No.: L23/020 d, dated August 6,
2007.
FAA AD Differences
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Note: This AD differs from the MCAI and/
or service information as follows:
(1) The service information requires a
visual inspection with a 6X magnifier. We are
requiring a dye penetrant inspection and a
10X magnifier to detect cracks that could go
undetected using only a 6X magnifier.
(2) The MCAI requires updating the
maintenance manuals to add repetitive
inspections of the control bridge. Since the
maintenance manual is only one way of
establishing a maintenance program, the only
way we can mandate these repetitive
inspections is through an AD action. We have
made these repetitive inspections part of this
AD.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Greg Davison, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4130; fax: (816) 329–
4090. Before using any approved AMOC on
any sailplane to which the AMOC applies,
notify your appropriate principal inspector
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19:28 Dec 23, 2008
Jkt 217001
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency (EASA) AD No. 2007–0261,
dated October 2, 2007; LET Aircraft
Industries, a.s. Mandatory Bulletin MB No.
L23/050a, Revision No. 2, dated September
12, 2007; Appendix No. 1, ‘‘Replacement of
Bearings 608 CSN 024630 at Control Bridge
Dwg. No. A740 370N in a Bedding Dwg. No.
A740 371N,’’ to LET Aircraft Industries, a.s.
Mandatory Bulletin MB No. L23/050a,
Revision No. 2, dated September 12, 2007;
LET Aircraft Industries, a.s. Documentation
Bulletin No.: L23/020 d, dated August 6,
2007; and FAA Advisory Circular AC 43.13–
1B CHG 1, dated September 27, 2001, for
related information. FAA Advisory Circular
AC 43.13–1B CHG 1, dated September 27,
2001, can be found on the Internet at
https://rgl.faa.gov/.
Material Incorporated by Reference
(i) You must use LET Aircraft Industries,
a.s. Mandatory Bulletin MB No. L23/050a,
Revision No. 2, dated September 12, 2007;
Appendix No. 1, ‘‘Replacement of Bearings
608 CSN 024630 at Control Bridge Dwg. No.
A740 370N in a Bedding Dwg. No. A740
371N,’’ to LET Aircraft Industries, a.s.
Mandatory Bulletin MB No. L23/050a,
Revision No. 2, dated September 12, 2007;
and LET Aircraft Industries, a.s.
Documentation Bulletin No.: L23/020 d,
dated August 6, 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
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Aircraft Industries, a.s. Na
´
Zahonech 1177, 686 04 Kunovice, Czech
Republic; phone: +420–572816002; fax:
+420–572816006; Internet:
https://www.let.cz/.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, 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/
cfr/ibr-locations.html.
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78931
Issued in Kansas City, Missouri, on
December 16, 2008.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–30405 Filed 12–23–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1250; Directorate
Identifier 2008–SW–49–AD; Amendment 39–
15755; AD 2008–17–51]
RIN 2120–AA64
Airworthiness Directives; MD
Helicopters, Inc. Model MD900
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)
2008–17–51, which was sent previously
to all known U.S. owners and operators
of MD Helicopters, Inc. (MDHI) Model
MD900 helicopters by individual letters.
This AD requires, before further flight,
fluorescent magnetic particle inspecting
the aft threads of the forward directional
control cable (control cable) for a crack
and replacing the control cable with an
airworthy part if you find a crack. If you
do not find a crack, this AD requires
that you demagnetize the cable threads
until you reach a certain gauss level.
This AD also requires visually
inspecting the aft cable attach bracket
for a crack and for interference with
movement of the control cable or for
deformation of the aft cable attach
bracket. If a crack or interference with
movement of the control cable or
deformation of the aft cable attach
bracket exists, this AD requires
replacing the bracket with an airworthy
part. This AD also requires modifying
the control cable conduit and the
rotating cone control rod and
identifying the rotating cone control rod
with a certain part number. This
amendment is prompted by three
reports of in-flight failure of the control
cable and loss of yaw control resulting
in emergency landings and subsequent
damage to the helicopter. The actions
specified by this AD are intended to
prevent loss of yaw control and
subsequent loss of control of the
helicopter.
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78932
Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations
DATES: January 8, 2009, to all persons
except those persons to whom it was
made immediately effective by
Emergency AD 2008–17–51, issued on
August 14, 2008, 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 January 8,
2009.
Comments for inclusion in the Rules
Docket must be received on or before
February 23, 2009.
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 bulletin
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. You
may purchase the American Society for
Testing and Material standard from
ASTM International on the Web at
https://www.astm.org/.
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
D. Schrieber, FAA, Los Angeles Aircraft
Certification Office, Aviation Safety
Engineer, Airframe Branch, 3960
Paramount Blvd., Lakewood, California
90712, telephone 562–627–5348, fax
562–627–5210.
SUPPLEMENTARY INFORMATION: On August
14, 2008, we issued Emergency AD
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19:28 Dec 23, 2008
Jkt 217001
2008–17–51 for the specified MDHI
model helicopters. The Emergency AD
requires fluorescent magnetic particle
inspecting the aft threads of the control
cable for a crack and replacing the
control cable with an airworthy part if
you find a crack. If you do not find a
crack, the Emergency AD requires that
you demagnetize the cable threads until
you reach a certain gauss level. The
Emergency AD also requires visually
inspecting the aft cable attach bracket
for a crack and for interference with
movement of the control cable or for
deformation of the aft cable attach
bracket. If a crack or interference with
movement of the control cable or
deformation of the aft cable attach
bracket exists, the Emergency AD
requires replacing the bracket with an
airworthy part. The Emergency AD also
requires modifying the control cable
conduit and the rotating cone control
rod and identifying the rotating cone
control rod with part number
‘‘900C2010582–105.’’ The Emergency
AD was prompted by three reports of inflight failure of the control cable and
loss of yaw control resulting in
emergency landings and subsequent
damage to the helicopter. This
condition, if not corrected, could result
in loss of yaw control and subsequent
loss of control of the helicopter.
MDHI has issued Service Bulletin
SB900–108R1, dated August 13, 2008,
which describes procedures for
magnetic particle inspecting and
modifying the control cable and rotating
cone control rod installation.
Since the unsafe condition described
is likely to exist or develop on other
MDHI model helicopters of the same
type design, we issued Emergency AD
2008–17–51 to prevent loss of yaw
control and subsequent loss of control of
the helicopter. The Emergency AD
requires the following, before further
flight:
• Remove the rotating cone, the
thruster extension, and the rotating cone
control rod, and NAS1193K4CP lock
device (2 parts).
• Do a fluorescent magnetic particle
inspection for a crack in the aft threads
of the control cable. If you find a crack,
replace the control cable with an
airworthy part. If you do not find a
crack, demagnetize the cable threads
until you reach a gauss level of +/¥3.
• Visually inspect the aft cable attach
bracket for a crack. Inspect for
interference with the movement of the
control cable or for deformation of the
aft cable attach bracket. If a crack or
interference with the movement of the
control cable or deformation of the aft
cable attach bracket exists, replace the
bracket with an airworthy part.
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• Cut and modify the aft end of the
control cable conduit.
• Modify the rotating cone control
rod by drilling lock wire holes. Using
permanent ink, identify the rotating
cone control rod with part number
900C2010582–105.
• Inspect the control cable for proper
adjustment.
• Install the rotating cone control rod.
• Install the thruster extension.
• Install the rotating cone. If you
adjust the control cable at the attach
brackets, inspect for interference with
the movement of the control cable or for
deformation of the aft cable attach
bracket. If interference with the
movement of the control cable or
deformation of the aft cable attach
bracket exists, replace the bracket with
an airworthy part.
• Rerig the antitorque directional
control system.
The actions must be done by
following specified portions of the
service bulletin described previously.
The short compliance time involved is
required because the previously
described critical unsafe condition can
adversely affect the controllability of the
helicopter. Therefore, the actions
described previously 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, and
good cause existed to make the AD
effective immediately by individual
letters issued on August 14, 2008, to all
known U.S. owners and operators of
MDHI Model MD900 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 33 helicopters of U.S. registry. It
will take about 5.5 work hours to
remove, modify, visually inspect, and
install parts, and 2 work hours to
fluorescent magnetic particle inspect the
aft threads in the control cable per
helicopter at an average labor rate of $80
per work hour. The kits required to
modify the control cable cost about
$8,603 for the entire fleet. Based on
these figures, we estimate the total cost
impact of the AD on U.S. operators to
be $28,403.
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
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Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations
written data, views, or arguments
regarding this AD. Send your comments
to an address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2008–1250;
Directorate Identifier 2008–SW–49–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://
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
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19:28 Dec 23, 2008
Jkt 217001
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
■
2008–17–51 MD Helicopters, Inc.:
Amendment 39–15755. Docket No.
FAA–2008–1250; Directorate Identifier
2008–SW–49–AD.
Applicability: Model MD900 helicopters,
serial numbers 900–00008 through 900–
00128, with part number (P/N)
900C3010045–105 forward directional
control cable (control cable), P/N
900C2010582–103 rotating cone control rod,
and P/N 9000F2318021 (all dash numbers)
tailboom assembly, installed, certificated in
any category.
Compliance: Before further flight, unless
done previously.
To prevent loss of yaw control and
subsequent loss of control of the helicopter,
do the following:
(a) Remove the rotating cone, the thruster
extension, the rotating cone control rod, and
the NAS1193K4CP lock device (2 parts). Do
not reinstall the lock device. Use your hand
and turn the telescopic part on the aft end
of the control cable until it is fully forward
on the control cable.
Note: The MDHI maintenance manuals
CSP–900RMM–2, Sections 67–20–00, 29–00–
00, 53–40–00; CSP–SPM, Section 20–30–00;
and CSP–900IPL–4 Illustrated Parts pertain
to the subject of this AD.
(b) Do a fluorescent magnetic particle
inspection for a crack in the aft threads of the
control cable as depicted in Figure 2 and by
following MD Helicopters, Inc. (MDHI)
Service Bulletin SB900–108R1, dated August
13, 2008, Section 2, Accomplishment
Instructions (SB), paragraphs (5)(a) through
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78933
5(j). The inspection must be done by an
inspector qualified under the guidelines
established by MIL–STD–410E, ATA
Specification 105, AIA–NAS–410, or an
FAA-accepted equivalent for qualification
standards of NDT Inspection/Evaluation
Personnel. The inspector that accepts or
rejects the inspected part must be certified to
a Non-Destructive Testing (NDT) UT
minimum Level II. The part must be
inspected to the inspection facilities written
procedure approved by a person certified to
a Level III. For the magnetic particle
examination process and qualifications,
follow the American Society for Testing and
Material (ASTM) E 1444–93 e1.
(1) If you find a crack, replace the control
cable with an airworthy part.
(2) If you do not find a crack, demagnetize
the cable threads by following paragraphs
(6)(a) or (6)(b) of the SB until you reach a
gauss level of +/¥3.
(c) Visually inspect the aft cable attach
bracket, depicted in Figure 3 of the SB, for
a crack. Inspect for interference with the
movement of the control cable or for
deformation of the aft cable attach bracket by
following paragraphs (9)(a) through (9)(c) of
the SB. If a crack or interference with the
movement of the control cable or
deformation of the aft cable attach bracket
exists, replace the bracket with an airworthy
part.
(d) Cut and modify the aft end of the
control cable conduit as depicted in Figure
4 of the SB by following paragraphs (10)(a)
through (10)(g) of the SB.
(e) Modify the rotating cone control rod by
drilling lock wire holes as depicted in Figure
5 of the SB by following paragraphs (11)(a)
through (11)(g) of the SB. Using permanent
ink, mark the rotating cone control rod with
‘‘900C2010582–105.’’
(f) Inspect the control cable for proper
adjustment by following paragraphs (12)(a)
through (12)(c), of the SB.
(g) Install the rotating cone control rod as
depicted in Figure 6 of the SB by following
paragraphs (13)(a) through (13)(c) of the SB.
Make sure the control cable threads are past
the witness hole in the rotating cone control
rod.
(h) Install the thruster extension.
(i) Install the rotating cone. If you adjust
the control cable at the attach brackets,
inspect for interference with the movement
of the control cable or for deformation of the
aft cable attach bracket by following
paragraph (15) of the SB. If interference with
the movement of the control cable or
deformation of the aft cable attach bracket
exists, replace the bracket with an airworthy
part.
(j) Rerig the antitorque directional control
system.
(k) 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:
Eric D. Schrieber, Aviation Safety Engineer,
Airframe Branch, 3960 Paramount Blvd.,
Lakewood, California 90712, telephone 562–
627–5348, fax 562–627–5210, for information
about previously approved alternative
methods of compliance.
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Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations
(l) Special flight permits will not be issued.
(m) The inspections and modification must
be done by following the specified portions
of MD Helicopters, Inc. Service Bulletin
SB900–108R1, dated August 13, 2008. Copies
of this service bulletin 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.
The inspection must also be done by
following the magnetic particle examination
process and qualifications found in American
Society for Testing and Material (ASTM) E
1444–93 e1, approved February 15, 1993,
Standard Practice for Magnetic Particle
Examination. Copies of this information may
be purchased from AMST International on
the Web at https://www.astm.org/. 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 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.
(n) This amendment becomes effective on
January 8, 2009, to all persons except those
persons to whom it was made immediately
effective by Emergency AD 2008–17–51,
issued August 14, 2008, which contained the
requirements of this amendment.
Issued in Fort Worth, Texas, on November
19, 2008.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E8–28367 Filed 12–23–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1085; Directorate
Identifier 2008–CE–057–AD; Amendment
39–15777; AD 2008–26–11]
RIN 2120–AA64
Airworthiness Directives; Piper
Aircraft, Inc. Models PA–46–350P, PA–
46R–350T, and PA–46–500TP Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Piper Aircraft, Inc. (Piper) Models PA–
46–350P, PA–46R–350T, and PA–46–
500TP airplanes. This AD requires you
to install a stall warning heat control
modification kit. This AD results from
ice forming on the stall vane heater
during flights into icing conditions with
the landing gear down. We are issuing
this AD to prevent ice from forming on
the stall vane, which may result in
failure of the stall warning system. This
failure could result in the pilot being
unaware of an approaching stall
situation.
DATES: This AD becomes effective on
January 28, 2009.
On January 28, 2009, the Director of
the Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: For service information
identified in this AD, contact Piper
Aircraft, Inc., 2926 Piper Drive, Vero
Beach, Florida 32960; telephone: (772)
567–4361; fax: (772) 978–6573; Internet:
https://www.newpiper.com/.
To view the AD docket, go to U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590, or on the Internet at https://
www.regulations.gov. The docket
number is FAA–2008–1085; Directorate
Identifier 2008–CE–057–AD.
FOR FURTHER INFORMATION CONTACT: John
Lee, Aerospace Engineer, Federal
Aviation Administration, Aircraft
Certification Office, One Crown Center,
1895 Phoenix Blvd., Suite 450, Atlanta,
Georgia 30349; telephone: (770) 994–
6736; fax: (770) 703–6097.
SUPPLEMENTARY INFORMATION:
Discussion
On October 3, 2008, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an AD that would apply to
certain Piper Models PA–46–350P, PA–
46R–350T, and PA–46–500TP airplanes.
This proposal was published in the
Federal Register as a notice of proposed
rulemaking (NPRM) on October 10, 2008
(73 FR 60201). The NPRM proposed to
require you to install a stall warning
heat control modification kit.
Comments
We provided the public the
opportunity to participate in developing
this AD. We received no comments on
the proposal or on the determination of
the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 803
airplanes in the U.S. registry.
We estimate the following costs to do
the modification:
Labor cost
Parts cost
Total cost per
airplane
Total cost on
U.S.
operators
1.5 work-hours × $80 per hour = $120 .......................................................................................
$95
$215
$172,645
pwalker on PROD1PC71 with RULES
Warranty credit may be given to the
extent noted in the service bulletin.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
VerDate Aug<31>2005
19:28 Dec 23, 2008
Jkt 217001
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,
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
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
E:\FR\FM\24DER1.SGM
24DER1
]]>Agencies
[Federal Register Volume 73, Number 248 (Wednesday, December 24, 2008)]
[Rules and Regulations]
[Pages 78931-78934]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-28367]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1250; Directorate Identifier 2008-SW-49-AD;
Amendment 39-15755; AD 2008-17-51]
RIN 2120-AA64
Airworthiness Directives; MD Helicopters, Inc. Model MD900
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) 2008-17-51, which was sent
previously to all known U.S. owners and operators of MD Helicopters,
Inc. (MDHI) Model MD900 helicopters by individual letters. This AD
requires, before further flight, fluorescent magnetic particle
inspecting the aft threads of the forward directional control cable
(control cable) for a crack and replacing the control cable with an
airworthy part if you find a crack. If you do not find a crack, this AD
requires that you demagnetize the cable threads until you reach a
certain gauss level. This AD also requires visually inspecting the aft
cable attach bracket for a crack and for interference with movement of
the control cable or for deformation of the aft cable attach bracket.
If a crack or interference with movement of the control cable or
deformation of the aft cable attach bracket exists, this AD requires
replacing the bracket with an airworthy part. This AD also requires
modifying the control cable conduit and the rotating cone control rod
and identifying the rotating cone control rod with a certain part
number. This amendment is prompted by three reports of in-flight
failure of the control cable and loss of yaw control resulting in
emergency landings and subsequent damage to the helicopter. The actions
specified by this AD are intended to prevent loss of yaw control and
subsequent loss of control of the helicopter.
[[Page 78932]]
DATES: January 8, 2009, to all persons except those persons to whom it
was made immediately effective by Emergency AD 2008-17-51, issued on
August 14, 2008, 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 January 8, 2009.
Comments for inclusion in the Rules Docket must be received on or
before February 23, 2009.
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 bulletin 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.
You may purchase the American Society for Testing and Material standard
from ASTM International on the Web at https://www.astm.org/.
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 D. Schrieber, FAA, Los Angeles
Aircraft Certification Office, Aviation Safety Engineer, Airframe
Branch, 3960 Paramount Blvd., Lakewood, California 90712, telephone
562-627-5348, fax 562-627-5210.
SUPPLEMENTARY INFORMATION: On August 14, 2008, we issued Emergency AD
2008-17-51 for the specified MDHI model helicopters. The Emergency AD
requires fluorescent magnetic particle inspecting the aft threads of
the control cable for a crack and replacing the control cable with an
airworthy part if you find a crack. If you do not find a crack, the
Emergency AD requires that you demagnetize the cable threads until you
reach a certain gauss level. The Emergency AD also requires visually
inspecting the aft cable attach bracket for a crack and for
interference with movement of the control cable or for deformation of
the aft cable attach bracket. If a crack or interference with movement
of the control cable or deformation of the aft cable attach bracket
exists, the Emergency AD requires replacing the bracket with an
airworthy part. The Emergency AD also requires modifying the control
cable conduit and the rotating cone control rod and identifying the
rotating cone control rod with part number ``900C2010582-105.'' The
Emergency AD was prompted by three reports of in-flight failure of the
control cable and loss of yaw control resulting in emergency landings
and subsequent damage to the helicopter. This condition, if not
corrected, could result in loss of yaw control and subsequent loss of
control of the helicopter.
MDHI has issued Service Bulletin SB900-108R1, dated August 13,
2008, which describes procedures for magnetic particle inspecting and
modifying the control cable and rotating cone control rod installation.
Since the unsafe condition described is likely to exist or develop
on other MDHI model helicopters of the same type design, we issued
Emergency AD 2008-17-51 to prevent loss of yaw control and subsequent
loss of control of the helicopter. The Emergency AD requires the
following, before further flight:
Remove the rotating cone, the thruster extension, and the
rotating cone control rod, and NAS1193K4CP lock device (2 parts).
Do a fluorescent magnetic particle inspection for a crack
in the aft threads of the control cable. If you find a crack, replace
the control cable with an airworthy part. If you do not find a crack,
demagnetize the cable threads until you reach a gauss level of +/-3.
Visually inspect the aft cable attach bracket for a crack.
Inspect for interference with the movement of the control cable or for
deformation of the aft cable attach bracket. If a crack or interference
with the movement of the control cable or deformation of the aft cable
attach bracket exists, replace the bracket with an airworthy part.
Cut and modify the aft end of the control cable conduit.
Modify the rotating cone control rod by drilling lock wire
holes. Using permanent ink, identify the rotating cone control rod with
part number 900C2010582-105.
Inspect the control cable for proper adjustment.
Install the rotating cone control rod.
Install the thruster extension.
Install the rotating cone. If you adjust the control cable
at the attach brackets, inspect for interference with the movement of
the control cable or for deformation of the aft cable attach bracket.
If interference with the movement of the control cable or deformation
of the aft cable attach bracket exists, replace the bracket with an
airworthy part.
Rerig the antitorque directional control system.
The actions must be done by following specified portions of the
service bulletin described previously. The short compliance time
involved is required because the previously described critical unsafe
condition can adversely affect the controllability of the helicopter.
Therefore, the actions described previously 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, and good cause
existed to make the AD effective immediately by individual letters
issued on August 14, 2008, to all known U.S. owners and operators of
MDHI Model MD900 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 33 helicopters of U.S.
registry. It will take about 5.5 work hours to remove, modify, visually
inspect, and install parts, and 2 work hours to fluorescent magnetic
particle inspect the aft threads in the control cable per helicopter at
an average labor rate of $80 per work hour. The kits required to modify
the control cable cost about $8,603 for the entire fleet. Based on
these figures, we estimate the total cost impact of the AD on U.S.
operators to be $28,403.
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
[[Page 78933]]
written data, views, or arguments regarding this AD. Send your comments
to an address listed under ADDRESSES. Include ``Docket No. FAA-2008-
1250; Directorate Identifier 2008-SW-49-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://
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 adding a new airworthiness directive to
read as follows:
2008-17-51 MD Helicopters, Inc.: Amendment 39-15755. Docket No. FAA-
2008-1250; Directorate Identifier 2008-SW-49-AD.
Applicability: Model MD900 helicopters, serial numbers 900-00008
through 900-00128, with part number (P/N) 900C3010045-105 forward
directional control cable (control cable), P/N 900C2010582-103
rotating cone control rod, and P/N 9000F2318021 (all dash numbers)
tailboom assembly, installed, certificated in any category.
Compliance: Before further flight, unless done previously.
To prevent loss of yaw control and subsequent loss of control of
the helicopter, do the following:
(a) Remove the rotating cone, the thruster extension, the
rotating cone control rod, and the NAS1193K4CP lock device (2
parts). Do not reinstall the lock device. Use your hand and turn the
telescopic part on the aft end of the control cable until it is
fully forward on the control cable.
Note: The MDHI maintenance manuals CSP-900RMM-2, Sections 67-20-
00, 29-00-00, 53-40-00; CSP-SPM, Section 20-30-00; and CSP-900IPL-4
Illustrated Parts pertain to the subject of this AD.
(b) Do a fluorescent magnetic particle inspection for a crack in
the aft threads of the control cable as depicted in Figure 2 and by
following MD Helicopters, Inc. (MDHI) Service Bulletin SB900-108R1,
dated August 13, 2008, Section 2, Accomplishment Instructions (SB),
paragraphs (5)(a) through 5(j). The inspection must be done by an
inspector qualified under the guidelines established by MIL-STD-
410E, ATA Specification 105, AIA-NAS-410, or an FAA-accepted
equivalent for qualification standards of NDT Inspection/Evaluation
Personnel. The inspector that accepts or rejects the inspected part
must be certified to a Non-Destructive Testing (NDT) UT minimum
Level II. The part must be inspected to the inspection facilities
written procedure approved by a person certified to a Level III. For
the magnetic particle examination process and qualifications, follow
the American Society for Testing and Material (ASTM) E 1444-93
[egr]1.
(1) If you find a crack, replace the control cable with an
airworthy part.
(2) If you do not find a crack, demagnetize the cable threads by
following paragraphs (6)(a) or (6)(b) of the SB until you reach a
gauss level of +/-3.
(c) Visually inspect the aft cable attach bracket, depicted in
Figure 3 of the SB, for a crack. Inspect for interference with the
movement of the control cable or for deformation of the aft cable
attach bracket by following paragraphs (9)(a) through (9)(c) of the
SB. If a crack or interference with the movement of the control
cable or deformation of the aft cable attach bracket exists, replace
the bracket with an airworthy part.
(d) Cut and modify the aft end of the control cable conduit as
depicted in Figure 4 of the SB by following paragraphs (10)(a)
through (10)(g) of the SB.
(e) Modify the rotating cone control rod by drilling lock wire
holes as depicted in Figure 5 of the SB by following paragraphs
(11)(a) through (11)(g) of the SB. Using permanent ink, mark the
rotating cone control rod with ``900C2010582-105.''
(f) Inspect the control cable for proper adjustment by following
paragraphs (12)(a) through (12)(c), of the SB.
(g) Install the rotating cone control rod as depicted in Figure
6 of the SB by following paragraphs (13)(a) through (13)(c) of the
SB. Make sure the control cable threads are past the witness hole in
the rotating cone control rod.
(h) Install the thruster extension.
(i) Install the rotating cone. If you adjust the control cable
at the attach brackets, inspect for interference with the movement
of the control cable or for deformation of the aft cable attach
bracket by following paragraph (15) of the SB. If interference with
the movement of the control cable or deformation of the aft cable
attach bracket exists, replace the bracket with an airworthy part.
(j) Rerig the antitorque directional control system.
(k) 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: Eric D. Schrieber, Aviation Safety Engineer, Airframe Branch,
3960 Paramount Blvd., Lakewood, California 90712, telephone 562-627-
5348, fax 562-627-5210, for information about previously approved
alternative methods of compliance.
[[Page 78934]]
(l) Special flight permits will not be issued.
(m) The inspections and modification must be done by following
the specified portions of MD Helicopters, Inc. Service Bulletin
SB900-108R1, dated August 13, 2008. Copies of this service bulletin
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. The inspection must also be done by
following the magnetic particle examination process and
qualifications found in American Society for Testing and Material
(ASTM) E 1444-93 [egr]1, approved February 15, 1993,
Standard Practice for Magnetic Particle Examination. Copies of this
information may be purchased from AMST International on the Web at
https://www.astm.org/. 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 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.
(n) This amendment becomes effective on January 8, 2009, to all
persons except those persons to whom it was made immediately
effective by Emergency AD 2008-17-51, issued August 14, 2008, which
contained the requirements of this amendment.
Issued in Fort Worth, Texas, on November 19, 2008.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-28367 Filed 12-23-08; 8:45 am]
BILLING CODE 4910-13-P
