[Federal Register Volume 75, Number 179 (Thursday, September 16, 2010)]
[Proposed Rules]
[Pages 56487-56489]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-23097]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0909; Directorate Identifier 2010-SW-026-AD]
RIN 2120-AA64
Airworthiness Directives; Erickson Air-Crane Incorporated Model
S-64F Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes adopting a new airworthiness directive
(AD) for Erickson Air-Crane Incorporated (Erickson Air-Crane) Model S-
64F helicopters. The AD would require, at specified intervals, certain
inspections of the rotating swashplate assembly (swashplate) for a
crack. If a crack is found, this AD would also require, before further
flight, replacing the swashplate with an airworthy swashplate. This
proposal is prompted by a report from the manufacturer of a swashplate
cracking during fatigue testing. The actions specified by the proposed
AD are intended to prevent loss of a swashplate due to a fatigue crack,
loss of control of the main rotor system, and subsequent loss of
control of the helicopter.
DATES: Comments must be received on or before November 15, 2010.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed 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,
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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 proposed AD
from Erickson Air-Crane Incorporated, 3100 Willow Springs Road, P.O.
Box 3247, Central Point, OR 97502, telephone (541) 664-5544, fax (541)
664-2312.
You may examine the comments to this proposed AD in the AD docket
on the Internet at http://regulations.gov.
FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Michael
Kohner, ASW-170, Aviation Safety Engineer, Rotorcraft Directorate,
Rotorcraft Certification Office, Fort Worth, Texas 76137, telephone
(817) 222-5170, fax (817) 222-5783.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written data, views, or arguments
regarding this proposed AD. Send your comments to the address listed
under the caption ADDRESSES. Include the docket number ``FAA-2010-0909,
Directorate Identifier 2010-SW-026-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this proposed rulemaking. Using the
search function of the docket Web site, you can find and read the
comments to any of our dockets, including the name of the individual
who sent or signed 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).
Examining the Docket
You may examine the docket that contains the proposed AD, any
comments, and other information 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.
Discussion
This document proposes adopting a new AD for Erickson Air-Crane
Model S-64F helicopters. The AD would require, at specified intervals,
certain visual inspections of the swashplate for a crack. Also, the AD
would require, at specified intervals, a fluorescent-penetrant
inspection (FPI) of the swashplate for a crack. If a crack is found,
this AD would also require, before further flight, replacing the
swashplate with an airworthy swashplate. This proposal is prompted by a
report from the manufacturer of a swashplate cracking during fatigue
testing. This condition, if not corrected, could result in loss of a
swashplate due to a fatigue crack, loss of control of the main rotor
system, and subsequent loss of control of the helicopter.
We have reviewed Erickson Air-Crane Service Bulletin (SB) 64B10-10,
Revision 2, dated April 1, 2008 (SB 64B10-10) and SB 64F General-3,
Revision C, dated December 12, 2007 (SB 64F General-3). SB 64F General-
3 summarizes a listing of the Model S-64F helicopter components, their
part number, and the corresponding service bulletins that the
manufacturer suggests using when performing the structural inspections
of the listed components to maintain the continued airworthiness of the
helicopters. Adherence to some or all of these structural limitations
may be subsequently required by an AD. SB 64B10-10 listed in SB 64F
General-3 and the subject of this proposal describes certain repetitive
inspections of the swashplate for a crack to maintain the continued
airworthiness of the helicopters.
This unsafe condition is likely to exist or develop on other
helicopters of the same type design. Therefore, the proposed AD would
require the following:
Within 15 hours time-in-service (TIS) and thereafter at
intervals not to exceed 15 hours TIS, clean and visually inspect the
swashplate for a crack.
Within 150 hours TIS and thereafter at intervals not to
exceed 150 hours TIS, clean the swashplate and, using a 10-power or
higher magnifying glass, visually inspect the swashplate for a crack.
Within 1,000 hours TIS since the last FPI and thereafter
at intervals not to exceed 1,000 hours TIS, removing the swashplate
from the helicopter and conducting an FPI of the swashplate for a
crack.
If a crack is found after any inspection, before further
flight, replace the swashplate with an airworthy swashplate.
We estimate that this proposed AD would affect 7 helicopters of
U.S. registry and would take about:
.5 hour for the visual inspection;
1 hour for the 10-power or higher magnifying glass
inspection;
35 hours for the 1,000-hour FPI; and
32 hours to replace a swashplate at an average labor rate
of $85 per work hour. Required parts would cost about $25,000 per
helicopter. Based on these figures, the total cost impact of the
proposed AD on U.S. operators would be $229,145, assuming 40 15-hour
visual inspections; 4 150-hour 10-power magnifying glass inspections; 1
1000-hour FPI and 1 swashplate replacement for each helicopter for the
entire fleet of S-64F helicopters for each year.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. Additionally, this proposed
AD would 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 proposed
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 a draft economic evaluation of the estimated costs to
comply with this proposed AD. See the AD docket to examine the draft
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
[[Page 56489]]
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.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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]
2. Section 39.13 is amended by adding a new airworthiness directive
to read as follows:
Erickson Air-Crane Incorporated: Docket No. FAA-2010-0909;
Directorate Identifier 2010-SW-026-AD.
Applicability
Model S-64F helicopters, with rotating swashplate assembly
(swashplate), part number (P/N) 65104-11001-051, installed,
certificated in any category.
Compliance
Required as indicated.
To prevent loss of a swashplate due to a fatigue crack, loss of
control of the main rotor system, and subsequent loss of control of
the helicopter, do the following:
(a) Within 15 hours time-in-service (TIS), unless accomplished
previously, and thereafter at intervals not to exceed 15 hours TIS,
clean and visually inspect the swashplate for a crack in areas A
through F as depicted in Figure 1 of Erickson Air-Crane Incorporated
Service Bulletin 64B10-10, Revision 2, dated April 1, 2008 (SB).
(b) Within 150 hours TIS, unless accomplished previously, and
thereafter at intervals not to exceed 150 hours TIS, clean the
swashplate and, using a 10-power or higher magnifying glass,
visually inspect for a crack in areas A through F as depicted in
Figure 1 of the SB.
(c) Within 1,000 hours TIS since the last fluorescent-penetrant
inspection (FPI) and thereafter at intervals not to exceed 1,000
hours TIS, remove the swashplate from the rotor head, disassemble
and remove the paint from the swashplate, and FPI the swashplate for
a crack in accordance with ATSM E1417, Type I, Methods A or C.
(d) If a crack is found in the swashplate, before further
flight, replace the swashplate with an airworthy swashplate.
(e) 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, Rotorcraft Certification Office, Rotorcraft
Directorate, ATTN: DOT/FAA Southwest Region, Michael Kohner, ASW-
170, Aviation Safety Engineer, Fort Worth, Texas 76137, telephone
(817) 222-5170, fax (817) 222-5783, for information about previously
approved alternative methods of compliance.
(f) The Joint Aircraft System/Component (JASC) Code is 6230:
Main Rotor Mast/Swashplate.
Issued in Fort Worth, Texas, on September 3, 2010.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-23097 Filed 9-15-10; 8:45 am]
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