AD 2005-10-12

[Federal Register Volume 70, Number 95 (Wednesday, May 18, 2005)]
[Rules and Regulations]
[Pages 28415-28417]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 05-9764]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21217; Directorate Identifier 2005-SW-06-AD; 
Amendment 39-14089; AD 2005-10-12]
RIN 2120-AA64


Airworthiness Directives; Schweizer Aircraft Corporation Model 
269C, C-1, and D 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 
the Schweizer Aircraft Corporation (Schweizer) Model 269C, C-1, and D 
helicopters. This action requires inspecting, modifying, and testing 
the lateral control trim actuator assembly on certain serial-numbered 
helicopters. This amendment is prompted by three reported incidents of 
the inner spring tube separating from the lateral trim control housing 
resulting in a lateral cyclic control restriction. The actions 
specified in this AD are intended to prevent separation of the inner 
spring tube from the lateral trim control housing and the associated 
loss of trim control, increased local resistance to right cyclic stick 
movement, and an emergency landing or subsequent loss of control of the 
helicopter.

DATES: Effective June 2, 2005.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 2, 2005.
    Comments for inclusion in the Rules Docket must be received on or 
before July 18, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
    <bullet> DOT Docket Web site: Go to  <a href="http://dms.dot.gov">http://dms.dot.gov</a> and follow 
the instructions for sending your comments electronically;
    <bullet> Government-wide rulemaking Web site: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a> and follow the instructions for sending your 
comments electronically;
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400

[[Page 28416]]

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 
Schweizer Aircraft Corporation, 1250 Schweizer Road, Horseheads, New 
York 14845.

Examining the Docket

    You may examine the docket that contains the AD, any comments, and 
other information on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a>, 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: Leung Lee, Aviation Safety Engineer, 
FAA, New York Aircraft Certification Office, Systems and Flight Test 
Branch, 1600 Stewart Ave., Suite 410, Westbury, New York 11590, 
telephone (516) 228-7309, fax (516) 794-5531.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for the 
Schweizer Model 269C, C-1, and D helicopters. This action requires 
inspecting, modifying, and testing the lateral control trim actuator 
assembly on certain serial-numbered helicopters. This amendment is 
prompted by three reported incidents of the inner spring tube 
separating from the lateral trim control housing resulting in a lateral 
cyclic control restriction. This condition, if not corrected, could 
result in the loss of trim control, increased local resistance to right 
cyclic stick movement, and an emergency landing or subsequent loss of 
control of the helicopter.
    We have reviewed Schweizer Service Bulletins B-283.1 and C1B-017.1, 
both dated March 4, 2005, and DB-012, dated February 8, 2005, which 
describe procedures for inspecting, modifying, and testing the lateral 
control trim actuator assembly, part number (P/N) 269A7316-13.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type designs. Therefore, we are issuing this AD 
to prevent the separation of the inner spring tube from the lateral 
trim control housing, resulting in the loss of trim control, increased 
local resistance to right cyclic stick movement, and a subsequent 
emergency landing or loss of control of the helicopter. This AD 
requires the following:
    <bullet> For Model 269C, S/N 1865 through 1874, with a prefix of S, 
and Model 269C-1, S/N 0169 through 0191, before further flight, inspect 
the lateral control trim actuator assembly for a scuffmark, 
indentation, or outer spring guide tube deformation. Inspect for 
security of the inner spring tube in the socket of the lateral trim 
control housing by rotating and pulling on the inner spring tube. 
Examine the resin bead around the base of the inner spring tube and 
housing socket. Resin should be translucent dark pink in color to 
indicate a good bond.
    [cir] If a scuffmark, indentation, or deformation exists on the 
outer spring tube, or the inner spring tube is loose or has motion, or 
bonding is separated, before further flight, remove the lateral control 
trim actuator assembly; modify the trim control housing and the inner 
spring tube; and test run the actuator assembly.

    [cir] If no scuffmark, indentation, or deformation exists on the 
outer spring tube, or the inner spring tube is not loose, or the 
bonding is not separated, within the next 25 hours time-in-service 
(TIS), modify the lateral control trim actuator assembly.

    <bullet> For Model 269D, Configuration A, S/N 0044 through 0050 
with an A suffix, within the next 50 hours TIS, modify the lateral 
control trim actuator assembly.

Accomplish the actions by following the service bulletins 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, inspecting, modifying, 
and testing the lateral control trim assembly, P/N 269A7316-13, before 
further flight, for Model 269C and C-1 or no later than 50 hours TIS 
for Model 269D are required, and this AD must be issued immediately.
    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 20 helicopters and will take 
about:
    <bullet> 2\1/4\ work hours to inspect, modify, and test Schweizer 
Model 269C and C-1 helicopters (for 19 helicopters), and
    <bullet> 3\1/2\ work hours to modify and test Schweizer Model 269D 
helicopters (for one helicopter).
    <bullet> The average labor rate is $65 per hour.
    <bullet> The cost is about $30 for adhesive, solvent, sandpaper, 
and nylon or cotton cord.
    Based on these figures, we estimate the total cost impact of the AD 
on U.S. operators to be about $3,606.

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-2005-21217; 
Directorate Identifier 2005-SW-06-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 <a href="http://dms.dot.gov">http://dms.dot.gov</a>, 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 <a href="http://dms.dot.gov">http://dms.dot.gov</a>.

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

[[Page 28417]]

this AD. See the DMS 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

    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:

2005-10-12 Schweizer Aircraft Corporation: Amendment 39-14089. 
Docket No. FAA-2005-21217; Directorate Identifier 2005-SW-06-AD.

    Applicability: Model 269C, serial number (S/N) 1865 through 1874 
with a prefix of S; Model 269C-1, S/N 0169 through 0191; and Model 
269D, Configuration A, S/N 0044 through 0050 with an A suffix, 
helicopters, with a lateral control trim actuator assembly, part 
number (P/N) 269A7316-13, installed, except for an actuator assembly 
containing a <greek-i>30 drilled hole in the lateral trim control 
housing through the wall of the inner spring tube socket, 
certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent separation of the inner spring tube from the lateral 
trim control housing, the associated loss of trim control, increased 
local resistance to right cyclic stick movement, and subsequent 
emergency landing or loss of control of the helicopter, accomplish 
the following:
    (a) For Model 269C, S/N 1865 through 1874, with a prefix of S, 
and Model 269C-1, S/N 0169 through 0191, before further flight, 
inspect the lateral control trim actuator assembly for a scuffmark, 
indentation, or outer spring guide tube deformation. Inspect for 
security of the inner spring tube in the socket of the lateral trim 
control housing by rotating and pulling on the inner spring tube. 
Examine the resin bead around the base of the inner spring tube and 
housing socket. Resin should be translucent dark pink in color to 
indicate a good bond. Conduct the inspection by following the 
Procedures in Part I of Schweizer Service Bulletin B-283.1 or C1B-
017.1, both dated March 4, 2005, respectively, as applicable.
    (1) If a scuffmark, indentation, or deformation exists on the 
outer spring tube, or the inner spring tube is loose or has motion, 
or the bonding is separated, before further flight, remove the 
lateral control trim actuator assembly; modify the trim control 
housing and the inner spring tube; and test run the actuator 
assembly. Modify and test run the actuator assembly by following the 
Procedures in Part II of Schweizer Service Bulletin B-283.1 or C1B-
017.1, both dated March 4, 2005, as applicable.
    (2) If no scuffmark, indentation, or deformation exists on the 
outer spring tube, or the inner spring tube is not loose, or the 
bonding is not separated, within the next 25 hours time-in-service 
(TIS), modify the lateral control trim actuator assembly as required 
by paragraph (a)(1) of this AD.
    (b) For Model 269D, Configuration A, S/N 0044 through 0050 with 
a suffix of A, within the next 50 hours TIS, modify the lateral 
control trim actuator assembly by following the Procedures in 
Schweizer Service Bulletin DB-012, paragraphs a through i, dated 
February 8, 2005.
    (c) 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 New York Aircraft Certification Office, FAA, for 
information about previously approved alternative methods of 
compliance.
    (d) Inspect, modify, and test the affected lateral control trim 
actuator assembly by following Schweizer Service Bulletin DB-012, 
dated February 8, 2005, or B-283.1, or C1B-017.1, both dated March 
4, 2005, 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 Schweizer 
Aircraft Corporation, 1250 Schweizer Road, Horseheads, New York 
14845. 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: <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.
    (e) This amendment becomes effective on June 2, 2005.

    Issued in Fort Worth, Texas, on May 6, 2005.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-9764 Filed 5-17-05; 8:45 am]
BILLING CODE 4910-13-P