[Federal Register Volume 75, Number 50 (Tuesday, March 16, 2010)]
[Rules and Regulations]
[Pages 12441-12445]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-5325]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0953; Directorate Identifier 2009-SW-45-AD;
Amendment 39-16230; AD 2010-06-06]
RIN 2120-AA64
Airworthiness Directives; MD Helicopters, Inc. Model MD-900
Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD) for MD Helicopters, Inc. (MDHI) model MD-900 helicopters that
currently requires applying serial numbers to certain parts, increasing
the life limit for various parts, maintaining a previously established
life limit for a certain vertical stabilizer control system (VSCS)
bellcrank assembly and bellcrank arm, and correcting the part number
for the VSCS bellcrank arm. This amendment requires the same actions as
the existing AD, except it reduces the life limit of the swashplate
spherical slider bearing (slider bearing). It further corrects what was
described as a ``bellcrank arm'' life limit in the current AD and
correctly describes it as another ``bellcrank assembly'' life limit.
This amendment is prompted by two reports of cracks in the slider
bearing that occurred well before the previously increased retirement
life of 2,030 hours time-in-service (TIS) was reached. The actions
specified by this AD are intended to establish appropriate life limits
for various parts, and to prevent fatigue failure of those parts and
subsequent loss of control of the helicopter.
DATES: Effective April 20, 2010.
ADDRESSES: You may get the service information identified in this AD
from MD Helicopters Inc., Attn: Customer Support Division, 4555 E.
McDowell Rd., Mail Stop M615, Mesa, Arizona 85215-9734, telephone 1-
800-388-3378, fax 480-346-6813, or on the Web at http://www.mdhelicopters.com.
Examining the Docket: You may examine the docket that contains this
AD, any comments, and other information on the Internet at http://www.regulations.gov, or at the Docket Operations office, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Roger Durbin, Aviation Safety
Engineer,
[[Page 12442]]
FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960
Paramount Blvd., Lakewood, California 90712, telephone (562) 627-5233,
fax (562) 627-5210.
SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 by
superseding AD 99-16-13, Amendment 39-11248 (64 FR 42824, August 6,
1999), Docket No. 98-SW-42-AD, for the MDHI Model MD-900 helicopters
was published in the Federal Register on October 22, 2009 (74 FR
54495). The action proposed to decrease the life limit of the slider
bearing from 2,030 hours TIS to 700 hours time-in-service (TIS).
Additionally, changing the nomenclature for part number 900F2341712-101
from bellcrank arm to bellcrank assembly was proposed. The action also
proposed to retain the requirements of the existing AD to apply serial
numbers to various parts, and to retain the life limits of various
other parts.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal 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.
The FAA estimates that this AD will affect 27 helicopters of U.S.
registry, and that it will take approximately 2.5 work hours per
helicopter to accomplish the serialization of the affected parts at an
average labor rate of $85 per work hour. Additionally, it is estimated
that 8 of those aircraft will require replacement of the slider
bearing, which will require approximately 7 work hours to accomplish at
an average labor rate of $85 per work hour. Required parts will cost
approximately $11,080 per helicopter for the slider bearing. Based on
these figures, we estimate the total cost impact of the AD on U.S.
operators to be $99,137.
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, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. Section 39.13 is amended by removing Amendment 39-11248 (64 FR
42824, August 6, 1999), and by adding a new airworthiness directive
(AD), Amendment 39-16230, to read as follows:
2010-06-06 MD Helicopters, Inc.: Amendment 39-16230. Docket No. FAA-
2009-0953; Directorate Identifier 2009-SW-45-AD. Supersedes AD 99-
16-13, Amendment 39-11248, Docket No. 98-SW-42-AD.
Applicability: MD-900 helicopters, certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To establish appropriate life limits for various parts, and to
prevent fatigue failure of those parts and subsequent loss of
control of the helicopter, accomplish the following:
(a) Remove from service as follows:
(1) The nonrotating swashplate assembly, part number (P/N)
900C2010192-105, -107, -109, or -111, on or before 1,800 hours time-
in-service (TIS).
(2) The collective drive link assembly, P/N 900C2010207-101, on
or before 3,307 hours TIS.
(3) The swashplate spherical slider bearing, P/N 900C3010042-
103, on or before 700 hours TIS.
(4) The vertical stabilizer control system (VSCS) bellcrank
assembly, P/N 900FP341712-103, and bellcrank assembly, P/N
900F2341712-101, on or before 2,700 hours TIS.
(b) Within 100 hours TIS:
(1) For Model MD-900 helicopters with serial numbers (S/N) 900-
00002 through 900-00012, apply the appropriate S/N to the mid-
forward truss assembly, P/N 900F2401200-102, and the forward and aft
deck-fitting assemblies, P/N 900F2401500-103 and P/N 900F2401600-
103.
(2) For Model MD-900 helicopters with S/N 900-00002 through 900-
00048, apply S/N to the left and right VSCS bellcrank assemblies, P/
N 900F2341712-101 and P/N 900FP341712-103, and the mid-aft truss
strut assembly, P/N 900F2401300-103.
(3) Apply the S/N, as specified in paragraphs (b)(1) and (b)(2)
of this AD, adjacent to the existing P/N, as listed in Appendix A of
this AD, using permanent ink or paint. When dry, apply a clear coat
over the S/N.
(c) This AD revises the Airworthiness Limitations Section of the
MD-900 Maintenance Manual by increasing the life limits for certain
parts and reducing the life limit of the slider bearing.
Note: The Airworthiness Limitations Section of the MD-900
Rotorcraft Maintenance Manual, Reissue 1, Revision 25, dated April
16, 2006, and MD Helicopters Service Bulletin SB900-096, dated
February 28, 2005, pertain 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,
for information about previously approved alternative methods of
compliance.
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(e) This amendment becomes effective on April 20, 2010.
Issued in Fort Worth, Texas, on February 18, 2010.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-5325 Filed 3-15-10; 8:45 am]
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