[Federal Register Volume 69, Number 193 (Wednesday, October 6, 2004)]
[Rules and Regulations]
[Pages 59788-59790]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-22264]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19223; Directorate Identifier 2004-SW-20-AD; 
Amendment 39-13813; AD 2004-20-08]
RIN 2120-AA64


Airworthiness Directives; MD Helicopters, Inc. (MDHI) Model 500N 
and 600N Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
MD Helicopters, Inc. (MDHI) Model 500N and 600N helicopters. This 
action requires using a bright light and a 10x or higher magnifying 
glass to inspect each forward and center thruster control cable 
assembly connector (connector) for corrosion pitting or cracking. If 
you find corrosion pitting or cracking, this AD also requires replacing 
the cable assembly with an airworthy cable assembly before further 
flight. This amendment is prompted by a report of a failure of the 
forward thruster cable assembly due to stress corrosion. The actions 
specified in this AD are intended to detect a corrosion-pitted or 
cracked connector and prevent failure of the cable assembly and 
subsequent loss of control of the helicopter.

DATES: Effective October 21, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 21, 2004.
    Comments for inclusion in the Rules Docket must be received on or 
before December 6, 2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically;
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically;
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590;
    <bullet> Fax: (202) 493-2251; or
    <bullet> Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    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-GO48, Mesa, Arizona 85215-9734, telephone 1-800-
388-3378, fax 480-891-6782, or on the Web at http://www.mdhelicopters.com.

Examining the Dockets

    You may examine the docket that contains the AD, any comments, and 
any other information on the Internet at http://dms.dot.gov, or in 
person at the Docket Management System (DMS) Docket Offices between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The 
Docket Office (telephone (800) 647-5227) is located on the plaza level 
of the Department of Transportation Nassif Building at the street 
address stated in the ADDRESSES section. Comments will be available in 
the AD docket shortly after the DMS receives them.

FOR FURTHER INFORMATION CONTACT: John Cecil, Aviation Safety Engineer, 
FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960 
Paramount Blvd., Lakewood, California 90712-4137, telephone (562) 627-
5228, fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for the MDHI 
Model 500N and 600N helicopters. This action requires using a bright 
light and a 10x or higher magnifying glass to inspect each connector 
for corrosion pitting or cracking. If corrosion pitting or cracking is 
found, this AD also requires replacing the cable assembly with an 
airworthy

[[Page 59789]]

cable assembly before further flight. This amendment is prompted by a 
report of a failure of a cable assembly due to a stress corrosion 
crack. The actions specified in this AD are intended to detect a 
corrosion-pitted or cracked connector and to prevent failure of a cable 
assembly and subsequent loss of control of the helicopter.
    We have reviewed MDHI Service Bulletin SB500N-027, SB600N-042, 
dated May 3, 2004 (SB). The SB describes procedures for inspecting the 
connectors on the forward and center cable assemblies for corrosion 
pitting or cracking. Also, the SB specifies replacing the cable 
assembly if corrosion pitting or cracking is found on the connectors.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, this AD is being issued 
to detect a corrosion-pitted or cracked connector on a cable assembly 
and to prevent failure of the cable assembly, and subsequent loss of 
control of the helicopter. This AD requires a one-time inspection of 
the connectors on the cable assemblies for corrosion pitting or 
cracking. If corrosion pitting or cracking is found, this AD also 
requires replacing the cable assembly with an airworthy cable assembly 
before further flight. Accomplish the actions by following the SB 
described previously.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability or structural integrity of the helicopter. Therefore, 
within the next 10 hours time-in-service or 30 days, whichever comes 
first, using a bright light and a 10X or higher magnifying glass, 
inspect each connector for corrosion pitting or cracking. If corrosion 
pitting or cracking is found, replacing the cable assembly with an 
airworthy cable assembly is required before further flight and this AD 
must be issued immediately. Inspecting each connector and replacing the 
cable assembly if corrosion pitting or cracking is found is terminating 
action for the requirements of this AD.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.
    We estimate that this AD will affect 66 helicopters. The 
inspections will take about 1 work hour at an average labor rate of $65 
per work hour. Required parts will cost about $4520 per helicopter. 
Based on these figures, we estimate the total cost impact of the AD on 
U.S. operators to be $4,290 assuming no parts will need to be replaced.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any written data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2004-19223; 
Directorate Identifier 2004-SW-20-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://dms.dot.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), or you may visit http://dms.dot.gov.
    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.

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

    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:

2004-20-08 MD Helicopters, Inc.: Amendment 39-13813. Docket No. FAA-
2004-19223; Directorate Identifier 2004-SW-20-AD.
    Applicability: The following model and serial number (S/N) 
helicopters, with forward thruster cable (cable) assembly and center 
cable assembly part number (P/N), installed, certificated in any 
category:

------------------------------------------------------------------------
                                      Forward cable       Center cable
     Model              S/N            assembly P/N       assembly P/N
------------------------------------------------------------------------
500N..........  With a prefix of          500N7201-55        500N7201-57
                 ``LN'' and 001
                 through 099.
600N..........  With a prefix of          500N7201-55        500N7201-59
                 ``RN'' and 003
                 through 068.
------------------------------------------------------------------------

    Compliance: Required as indicated, unless accomplished 
previously.
    To detect a corrosion-pitted or cracked forward or center cable 
assembly connector (connector) and to prevent failure of the cable 
assembly and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Within the next 10 hours time-in-service or 30 days, 
whichever comes first, using a bright light and a 10X or higher 
magnifying glass, inspect each connector for corrosion pitting or 
cracking by following the Accomplishment Instructions, paragraph 2., 
of MD Helicopter, Inc. Service Bulletin SB500N-027, SB600N-042, 
dated May 3, 2004. If you find

[[Page 59790]]

corrosion pitting or cracking, replace the cable assembly with an 
airworthy cable assembly before further flight. Replacing the cable 
assembly with an airworthy cable assembly is terminating action for 
the requirements of this AD.
    (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 Los Angeles Aircraft Certification Office, FAA, for 
information about previously approved alternative methods of 
compliance.
    (c) Do the inspection by following MD Helicopters, Inc. Service 
Bulletin SB500N-027, SB600N-042, dated May 3, 2004. 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-GO48, Mesa, Arizona 85215-9734, 
telephone 1-800-388-3378, fax 480-891-6782, or on the Web at http://www.mdhelicopters.com. Copies may be inspected 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.
    (d) This amendment becomes effective on October 21, 2004.

    Issued in Fort Worth, Texas, on September 22, 2004.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-22264 Filed 10-5-04; 8:45 am]
BILLING CODE 4910-13-P