[Federal Register: December 24, 2008 (Volume 73, Number 248)]
[Rules and Regulations]
[Page 78931-78934]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr24de08-5]
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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.
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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 http://
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 http://www.mdhelicopters.com.
You may purchase the American Society for Testing and Material standard
from ASTM International on the Web at http://www.astm.org/.
Examining the Docket: You may examine the docket that contains the
AD, any comments, and other information on the Internet at http://
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 http://
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
http://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
http://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: http://
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]
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