Airworthiness Directives; Schweizer Aircraft Corporation (Schweizer) Model 269A, A-1, B, C, C-1, and TH-55 Series Helicopters

[Federal Register Volume 76, Number 129 (Wednesday, July 6, 2011)]
[Rules and Regulations]
[Pages 39254-39256]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-16571]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0593; Directorate Identifier 2011-SW-002-AD; 
Amendment 39-16723; AD 2011-12-16]
RIN 2120-AA64


Airworthiness Directives; Schweizer Aircraft Corporation 
(Schweizer) Model 269A, A-1, B, C, C-1, and TH-55 Series Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are superseding an existing emergency airworthiness 
directive (EAD) for the specified Schweizer model helicopters that was 
previously sent to all known U.S. owners and operators. That EAD 
currently requires removing each locknut and verifying sufficient drag 
torque and retorquing, or if the locknut does not have sufficient drag 
torque, replacing the locknut with an airworthy locknut. This AD 
retains the existing EAD requirements but also requires within a 
specified time, modifying the expandable bolts and installing a cotter 
pin. This AD is prompted by a locknut working loose from a bolt 
attaching the tailboom support strut at the aft cluster fitting because 
the locknut installed on the expandable bolt did not have the proper 
threads. We are issuing this AD to modify each expandable bolt to allow 
adding a cotter pin to prevent the strut and driveshaft separating from 
the helicopter and subsequent loss of control of the helicopter.

DATES: This AD is effective July 21, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of July 21, 2011.
    We must receive any comments on this AD by September 6, 2011.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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.
    For service information identified in this AD, contact Schweizer 
Aircraft Corporation, Elmira/Corning Regional Airport, 1250 Schweizer 
Road, Horseheads, NY 14845, telephone (607) 739-3821, fax: (607) 796-
2488, e-mail address [email protected], or at http://www.sacusa.com/support.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Office (telephone: 800-647-

[[Page 39255]]

5527) is in the ADDRESSES section. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Stephen Kowalski, Aviation Safety 
Engineer, FAA, Airframe and Propulsion Branch, ANE-171, 1600 Stewart 
Ave., Suite 410, Westbury, New York 11590, telephone (516) 228-7327, 
fax (516) 794-5531.

SUPPLEMENTARY INFORMATION:

Discussion

    On December 20, 2010, we issued EAD 2011-01-52, Directorate 
Identifier 2010-SW-111-AD, for the specified Schweizer model 
helicopters. That EAD requires, before further flight, removing the 
locknut and reinstalling the locknut while determining the locknut drag 
torque. If the drag torque is a minimum of 2 in-lbs, retorquing the 
locknut to 23 in-lbs is required. If the drag torque is not at least 2 
in-lbs, replacing the locknut with an airworthy locknut is required. 
That AD resulted from a locknut working loose from a bolt attaching the 
tailboom support strut at the aft cluster fitting. Further 
investigation revealed that the locknut installed on the expandable 
bolt did not have the proper threads. We issued that EAD to prevent the 
strut and driveshaft separating from the helicopter and subsequent loss 
of control of the helicopter.

Actions Since AD Was Issued

    Since we issued AD 2011-01-52, the manufacturer has introduced a 
modification of the expandable bolts to allow the addition of a cotter 
pin.

Relevant Service Information

    We reviewed Schweizer Service Bulletins No. B-295 for Model 269A, 
A-1, B, and C helicopters, and No. C1B-032 for Model 269C-1 
helicopters, both dated December 21, 2010. The service information 
specifies verifying sufficient drag torque on each locknut and applying 
the proper torque to each locknut. The service information also 
specifies modifying both expandable bolts to allow the addition of a 
cotter pin.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop on other helicopters of these same type 
designs.

AD Requirements

    This AD retains the requirements in the existing EAD. This AD also 
requires, within 10 hours time-in-service (TIS), modifying both 
expandable bolts by drilling a hole through each bolt to allow the 
addition of a cotter pin. Thereafter, you may not install an expandable 
bolt unless that bolt has been modified in accordance with this AD. 
Modifying both expandable bolts in accordance with this AD is 
terminating action for the requirements of paragraphs (e)(1) and (e)(2) 
of this AD.

Differences Between the AD and the Service Information

    We refer to flight hours as hours TIS.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because this 
condition, if not corrected, could result in the strut and driveshaft 
separating from the helicopter and subsequent loss of control of the 
helicopter. Therefore, we find that notice and opportunity for prior 
public comment are impracticable because of the short compliance time 
and that good cause exists for making this amendment effective in less 
than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide notice and an opportunity to comment 
before it becomes effective. However, we invite you to send any written 
data, views, or arguments about this AD. Send your comments to an 
address listed under the ADDRESSES section. Include the Docket Number 
FAA-2011-0593 and Directorate Identifier 2011-SW-002-AD at the 
beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
AD. We will consider all comments received by the closing date and may 
amend this AD because 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 we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 585 helicopters of U.S. registry. 
We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
              Action                      Labor cost             Parts cost         helicopter       operators
----------------------------------------------------------------------------------------------------------------
Inspection........................  .5 work-hour x $85     negligible...........             $43         $25,155
                                     per hour = $43.
Modification......................  1.5 work-hours x $85   negligible...........             128          74,880
                                     per hour = $128.
----------------------------------------------------------------------------------------------------------------

    We estimate the total cost impact of this AD to be $100,035.

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.

Regulatory Findings

    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.

[[Page 39256]]

    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making any regulatory distinctions, and
    (4) 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA 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. The FAA amends Sec.  39.13 by adding the following new AD:

2011-12-16 Schweizer Aircraft Corporation (Schweizer): Amendment 39-
16723; Docket No. FAA-2011-0593; Directorate Identifier 2011-SW-002-
AD.

Effective Date

    (a) This AD is effective July 21, 2011.

Affected ADs

    (b) This AD supersedes Emergency AD 2011-01-52, issued December 
20, 2010; Directorate Identifier 2010-SW-111-AD.

Applicability

    (c) Schweizer Model 269A, A-1, B, C helicopters (serial number 
(S/N) 1846 and larger); C-1 helicopters (S/N 0156 and larger); and 
TH-55 series helicopters with an Aft Cluster Fitting Modification 
Kit, part number (P/N) SA-269K-106, installed; certificated in any 
category.

Unsafe Condition

    (d) This AD was prompted by a locknut working loose on the 
tailboom aft cluster fitting strut because the locknut installed on 
one expandable bolt did not have the proper threads. This AD 
contains terminating action to require modifying each expandable 
bolt to allow installing a cotter pin to prevent the strut and 
driveshaft separating from the helicopter and subsequent loss of 
control of the helicopter.

Compliance

    (e) Required as indicated, unless already done.
    (1) Before further flight, remove both the left-hand and right-
hand locknuts, P/N MS21043-3. Reinstall the locknuts while 
determining the locknut drag torque. If the drag torque is a minimum 
of 2 in-lbs., retorque the locknut to 23 in-lbs. If the drag torque 
is not at least 2 in-lbs, replace the locknut with an airworthy 
locknut.
    (2) Within 10 hours time-in-service, modify each expandable 
bolt, P/N ADB221-1A, torque locknut, P/N MS21043-3, and install 
cotter pin, P/N MS24665-132 or MS24665-151, in accordance with the 
Procedure Section, Part II, of Schweizer Service Bulletin (SB) No. 
B-295, dated December 21, 2010, for Model 269A, A-1, B, C, and TH-55 
series helicopters or SB No. C1B-032, dated December 21, 2010, for 
Model 269C-1 helicopters.
    (3) Before installing an expandable bolt, P/N ADB221-1A, to 
secure the tailboom support strut to the tailboom aft cluster 
fitting, modify the expandable bolt in accordance with paragraph 
(e)(2) of this AD.
    (f) Modifying both expandable bolts by torquing the locknuts and 
installing the cotter pins as required by this AD is terminating 
action for the requirements of paragraph (e)(1) and (e)(2) of this 
AD.

Special Flight Permit

    (g) Special flight permits will not be issued.

Alternative Methods of Compliance (AMOCs)

    (h) The Manager, New York Aircraft Certification Office (NYACO), 
FAA, has the authority to approve AMOCs for this AD if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the NYACO, send it to the 
attention of the Program Manager, Continuing Operational Safety.

    Note: Before using any approved AMOC, we request that you notify 
your appropriate principal inspector, or lacking a principal 
inspector, the manager of the local flight standards district office 
or certificate holding district office.

Related Information

    (i) For more information about this AD, contact Stephen 
Kowalski, Aviation Safety Engineer, FAA, Airframe and Propulsion 
Branch, ANE-171, 1600 Stewart Ave., Suite 410, Westbury, New York 
11590, telephone (516) 228-7327, fax (516) 794-5531.

Subject

    (j) Joint Aircraft System Component (JASC)/Air Transport 
Association (ATA) of America Code 5302: Rotorcraft Tailboom.

Material Incorporated by Reference

    (k) You must use the specified portions of the service 
information contained in Schweizer Service Bulletins B-295 or C1B-
032, both dated December 21, 2010, for your model helicopter to do 
the actions required by this AD.
    (2) For service information identified in this AD, contact 
Schweizer Aircraft Corporation, Elmira/Corning Regional Airport, 
1250 Schweizer Road, Horseheads, NY 14845, telephone (607) 739-3821, 
fax: (607) 796-2488, e-mail address [email protected], or at 
http://www.sacusa.com/support.
    (3) You may also review copies of the service information that 
is incorporated by reference at the FAA, Office of the Regional 
Counsel, 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 an NARA facility, call 202-
741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Fort Worth, Texas, on June 3, 2011.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-16571 Filed 7-5-11; 8:45 am]
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