[Federal Register Volume 76, Number 208 (Thursday, October 27, 2011)]
[Rules and Regulations]
[Pages 66615-66617]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-27773]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0792; Directorate Identifier 2009-SW-19-AD; 
Amendment 39-16762; AD 2011-16-04]
RIN 2120-AA64


Airworthiness Directives; Sikorsky Aircraft Corporation 
(Sikorsky) Model S-92A Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
Sikorsky Model S-92A helicopters. This action requires making pen and 
ink changes, inserting a copy of this AD, or inserting specified 
temporary revisions into the Limitations section of the Rotorcraft 
Flight Manual (RFM) limiting the maximum rolling groundspeed for a 
normal landing or takeoff from 65 knots to 50 knots for helicopters 
with a certain serial-numbered landing gear retract actuator 
(actuator). Instead of limiting the groundspeed, replacing the affected 
actuator with a modified actuator is terminating action for the 
requirements of this AD. This amendment is prompted by a report of a 
main landing gear that would not retract. The manufacturer reports that 
certain actuators were manufactured with down-lock keys that did not 
meet the specified minimum hardness requirements. This condition, if 
not corrected, could lead to a landing gear collapse following a roll-
on landing that exceeds 50 knots groundspeed. These actions are 
intended to prevent collapse of a landing gear and subsequent loss of 
control of the helicopter.

DATES: Effective November 14, 2011.
    Comments for inclusion in the Rules Docket must be received on or 
before December 27, 2011.

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 information identified in this AD from 
Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical 
Support, mailstop s581a, 6900 Main Street, Stratford, CT, telephone 
(203) 383-4866, e-mail address [email protected], or at http://www.sikorsky.com.
    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: Michael Schwetz, Aviation Safety 
Engineer, Boston Aircraft Certification Office, 12 New England 
Executive Park, Burlington, MA 01803, telephone (781) 238-7761, fax 
(781) 238-7170.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for Sikorsky 
Model S-92A helicopters. This action requires making pen and ink 
changes, inserting a copy of this AD, or inserting certain temporary 
revisions into the Limitations section of the RFM limiting the maximum 
groundspeed for a normal landing or takeoff to 50 knots for helicopters 
with a certain serial-numbered actuator installed. The temporary 
revisions to the Limitations section of the RFM also require replacing 
the actuators if the landing exceeds the 50 knot rolling groundspeed 
before further flight or before towing the helicopter; rolling ground 
taxi operations are permitted. Replacing the affected actuator with a 
modified actuator is terminating action for the requirements of this 
AD. The manufacturer states that it anticipates retrofitting the fleet 
with a modified actuator within 3 years. This amendment is prompted by 
a report that certain actuators were manufactured

[[Page 66616]]

with a down-lock pin that does not meet the specified minimum hardness 
requirements, which could lead to a landing gear collapse following a 
roll-on landing that exceeds 50 knots. These actions are intended to 
prevent a landing gear collapse and subsequent loss of control of the 
helicopter.
    We have reviewed Sikorsky Alert Service Bulletin No. 92-32-001, 
dated May 2, 2008 (ASB), which describes the unsafe condition, its 
cause, and the temporary operating restrictions intended to mitigate 
the unsafe condition until modified actuators are available. The ASB 
references and includes Embraer Liebherr Eqiupamentos do Brasil Service 
Bulletin No. 2392-0850-32-02 Change No. 1, dated May 15, 2008, which 
specifies procedures for replacing the down-lock key in the affected 
actuators.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, this AD is being issued 
to limit the maximum rolling groundspeed for a normal landing or 
takeoff to 50 knots rolling groundspeed. If the limitation is exceeded 
on landing, the actuator must be replaced with a modified actuator 
before further flight or towing operation; rolling ground taxi 
operations are permitted. This AD requires making pen and ink changes, 
inserting a copy of this AD, or inserting the following temporary 
revisions into the Limitations section of the RFM: SA S92A-RFM-000, 
Revision 2; SA S92A-RFM-002, Revision 6; SA S92A-RFM-003, Revision 5; 
SA S92A-RFM-004, Revision 5; SA S92A-RFM-005, Revision 4; or SA S92A-
RFM-006, Revision 3; all approved on January 7, 2011. Instead of 
limiting the groundspeed, replacing each actuator without the 
modification letter ``B'' stamped on the nameplate with an airworthy 
modified actuator with a letter ``B'' stamped on the nameplate 
constitutes terminating action for the requirements of this AD.
    The short compliance time of before further flight is required 
because the previously described critical unsafe condition can 
adversely affect the structural integrity and controllability of the 
helicopter. Therefore, limiting the maximum groundspeed for normal 
landing or takeoff to 50 knots to reduce the likelihood of a landing 
gear collapse is required before further flight 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 42 helicopters. It will take a 
minimal amount of time to make the limitation changes. If the operator 
replaces an affected actuator with a modified actuator, it will take 
about 8 work hours at an average labor rate of $85 per work hour. 
Required parts will cost about $7,841 per helicopter. Based on these 
figures, we estimate the total cost impact of the AD on U.S. operators 
to be $357,882, assuming all the helicopter operators install modified 
actuators.

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-2011-0792; Directorate 
Identifier 2009-SW-19-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

    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:

2011-16-04 Sikorsky Aircraft Corporation: Amendment 39-16762. Docket 
No. FAA-2011-0792; Directorate Identifier 2009-SW-19-AD.

    Applicability: Model S-92A helicopters with landing gear retract 
actuator (actuator), part number (P/N) 92250-00800-103, with a 
serial number (S/N) 101-00026 through 101-00237, without the 
modification letter ``B''

[[Page 66617]]

stamped on the nameplate, certificated in any category.
    Compliance: Before further flight, unless previously 
accomplished.
    To prevent a landing gear collapse and subsequent loss of 
control of the helicopter, do the following:
    (a) Revise the operating limitations, ``Airspeed Limits'' 
section of the rotorcraft Flight Manual (RFM) by one of the 
following methods:
    (1) Insert Sikorsky ``Temporary Revisions'' SA S92A-RFM-000, 
Revision 2; SA S92A-RFM-002, Revision 6; SA S92A-RFM-003, Revision 
5; SA S92A-RFM-004, Revision 5; SA S92A-RFM-005, Revision 4; or SA 
S92A-RFM-006, Revision 3; all approved January 7, 2011; or
    (2) Insert a copy of this AD; or
    (3) Make pen and ink changes with the following limitations:
    ``Maximum rolling groundspeed for normal takeoff or normal 
landing is 50 knots.''
    ``After a landing with a rolling groundspeed in excess of 50 
knots, any further takeoffs or towing operation is prohibited. 
Rolling ground taxi operations of less than 50 knots are 
permitted.''
    (b) Following a landing with a rolling groundspeed in excess of 
50 knots, or as an alternative to revising the operating limitations 
section of the RFM in compliance with this AD, before further 
flight, replace each affected actuator that does not have the 
modification letter ``B'' stamped on the nameplate with an airworthy 
actuator that has the modification letter ``B'' stamped on the 
nameplate.
    (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 Manager, Boston Aircraft Certification Office, FAA, 
ATTN: Michael Schwetz, Aviation Safety Engineer, 12 New England 
Executive Park, Burlington, MA 01803, telephone (781) 238-7761, fax 
(781) 238-7170, for information about previously approved 
alternative methods of compliance.

    Note: Sikorsky Alert Service Bulletin No. 92-32-001, dated May 
2, 2008, which is not incorporated by reference, contains additional 
information about the subject of this AD.

    (d) The Joint Aircraft System/Component (JASC) Code is 3233: 
Landing Gear Actuator.
    (e) This amendment becomes effective on November 14, 2011.

    Issued in Fort Worth, Texas, on July 14, 2011.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-27773 Filed 10-26-11; 8:45 am]
BILLING CODE 4910-13-P