[Federal Register: December 31, 2007 (Volume 72, Number 249)]
[Proposed Rules]
[Page 74210-74213]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr31de07-14]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0373; Directorate Identifier 2006-SW-14-AD]
RIN 2120-AA64
Airworthiness Directives; Erickson Air-Crane Incorporated Model
S-64E and 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 the specified Erickson Air-Crane Incorporated (Erickson) model
helicopters. The AD would require determining whether each specified
tail rotor blade assembly (blade assembly) has an affected serial
number or part marking. If a blade assembly has a certain serial number
or part marking, the AD would also require initially and repetitively
inspecting the tail rotor blade for a crack in the strap and pocket
areas. If a crack is found, this AD would also require, before further
flight, replacing the blade assembly with an airworthy blade assembly
that does not have an affected serial number or part marking. This
proposal is prompted by several reports of cracking in the strap and
pocket areas of the tail rotor blade. The actions specified by the
proposed AD are intended to prevent failure of the tail rotor blade and
subsequent loss of control of the helicopter.
DATES: Comments must be received on or before February 29, 2008.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
[[Page 74211]]
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 proposed AD
from Erickson Air-Crane Incorporated, P. O. Box 3247, Central Point, OR
97502, telephone 541-664-5544, fax 541-664-2312, or at http://www.ericksonaircrane.com
.
You may examine the comments to this proposed AD in the AD docket
on the Internet at http://www.regulations.gov.
FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office,
Fort Worth, Texas 76193-0170, telephone (817) 222-5447, 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-2007-0373,
Directorate Identifier 2006-SW-14-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://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 proposed rulemaking. 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 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) or you may visit http://dms.dot.gov.
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 the specified Erickson
model helicopters. The AD would require determining whether certain
tail rotor blade assemblies have an affected serial number or part
marking. If a blade assembly has a certain serial number or part
marking, the AD would also require initially and repetitively
inspecting the tail rotor blade for a crack in the strap and pocket
areas. If a crack is found, this AD would also require, before further
flight, replacing the blade assembly with an airworthy blade assembly
that does not have an affected serial number or part marking. This
proposal is prompted by several reports of cracking in the strap or
pocket areas of the tail rotor blade. This condition, if not corrected,
could result in failure of the tail rotor blade and subsequent loss of
control of the helicopter.
We have reviewed Erickson Alert Service Bulletin 64B15-9, Revision
B, dated October 6, 2006 (ASB), which describes procedures for
determining and inspecting certain marked or serial numbered tail rotor
blades. The ASB specifies repetitive inspections not to exceed 6 flight
hours for the S-64F model and not to exceed 15 flight hours for the S-
64E model. Alternate inspection schedules are also included for ``ferry
flights'' used for delivering the helicopter from one area of operation
to another. The ``ferry flight'' time would be the flight time
beginning at the end of the last operation in one area to the beginning
of the first operation in another area. If a crack is found in the
strap or pocket, the ASB specifies removing and replacing the blade.
We propose to depart from the language of the ASB and propose to
use the terms hours time-in-service (TIS) instead of maximum ground-
air-ground (GAG) cycles. We propose to define a ``ferry flight'' as a
helicopter flight used for delivering the helicopter from one area of
operation to another. During the ``ferry flight'' the helicopter would
not drop off an external load or pick up an external load. A GAG cycle
as defined in the ASB for the purposes of these inspections is any
maneuver that results in a climb-out similar to one following takeoff.
The proposed inspection intervals for the ferry flights were also
modified to accommodate a new range of values based on specifications
supplied by Erickson. The proposed inspection intervals were determined
by multiplying the maximum GAG cycles in the ASB for the given takeoff
weight by the flight endurance of 2.5 hours TIS for the Model S-64E and
2.2 hours TIS for the Model S-64F helicopters and rounding the result
to a near whole number as deemed appropriate.
This unsafe condition is likely to exist or develop on other
helicopters of these same type designs. Therefore, the proposed AD
would require for each blade assembly, part number (P/N) 65161-00001-
042 or -043, the following actions:
Within 25 hours TIS, unless done previously, determine if
the blade assembly has a serial number listed in the ASB. Also,
determine if the blade assembly is marked with an ``RS503'' near the
part number.
If the blade assembly serial number is not listed in the
ASB and does not have ``RS503'' marked near the part number, no further
action would be required by this AD.
If a blade assembly has either an affected serial number
or part marking, before further flight, using a 10-power or higher
magnifying glass, inspect both sides of the blade assembly for a crack
in the strap and pocket areas paying particular attention to the
circled area as depicted in Figure 1 of the ASB.
If no crack is found, inspect the blade assembly at
intervals not to exceed those TIS intervals specified in Table 1 of the
AD.
If a crack is found, before further flight, replace the
unairworthy blade assembly with an airworthy FAA approved blade
assembly that does not have a serial number listed in the ASB and does
not have ``RS503'' marked near the part number.
The actions would be required to be done by following the specified
portions of the ASB described previously.
We estimate that this proposed AD would:
Affect 20 helicopters of U.S. registry; 13 Model S-64E and
7 Model S-64F;
Require about 1 work hour to determine whether an affected
blade is installed;
Require about 1 work hour to inspect the blade assembly,
assuming about 40 inspections a year for each Model S-64E (total 520)
and about 100
[[Page 74212]]
inspections a year for each Model S-64F (total 700);
Require about 4 work hours to replace each tail rotor
blade, assuming 10 tail rotor blade assemblies are replaced;
Cost about $80 per work hour; and
Cost about $60,000 per blade assembly.
Based on these figures, the estimated total cost impact of the
proposed AD on U.S. operators would be $702,400, based on the stated
assumptions.
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 DMS 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
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, 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-2007-0373;
Directorate Identifier 2006-SW-14-AD.
Applicability
Model S-64E and S-64F helicopters, with tail rotor blade
assembly (blade assembly), part number (P/N) 65161-00001-042 or -
043, installed, certificated in any category.
Compliance
Required as indicated.
To prevent failure of the tail rotor blade and subsequent loss
of control of the helicopter, do the following:
(a) Within 25 hours time-in-service (TIS), unless accomplished
previously:
(1) Determine if the blade assembly has a serial number listed
in the Accomplishment Instructions, paragraph 2.A., of Erickson Air-
Crane Incorporated Alert Service Bulletin No. 64B15-9, Revision B,
dated October 6, 2006 (ASB). Also, determine if the blade assembly
has ``RS503'' marked near the P/N.
(2) If the blade assembly serial number is not listed in the ASB
and does not have ``RS503'' marked near the P/N, no further action
is required by this AD.
(3) If a blade assembly has either a serial number listed in
paragraph 2.A of the ASB or has ``RS503'' marked near the part
number, before further flight, using a 10-power or higher magnifying
glass, inspect both sides of the blade assembly for a crack in the
strap and pocket areas paying particular attention to the circled
area as depicted in Figure 1 of the ASB.
(i) If no crack is found, inspect the blade assembly as
specified in paragraph (a)(3) of this AD at intervals not to exceed
those shown in the following table:
Table 1
------------------------------------------------------------------------
Maximum time
Gross takeoff weight between
Mission type (lbs) inspections
(hours TIS)
------------------------------------------------------------------------
Model S-64E Tail Rotor Blade Strap Inspection Intervals
------------------------------------------------------------------------
Ferry Only..................... Above 35,000........... 30
Ferry Only..................... Above 30,000 and less 35
than or equal to
35,000.
Ferry Only..................... Below or equal to 40
30,000.
All Others..................... All.................... 15
------------------------------------------------------------------------
Model S-64F Tail Rotor Blade Strap Inspection Intervals
------------------------------------------------------------------------
Ferry Only..................... Above 35,000........... 8
Ferry Only..................... Above 30,000 and less 15
than or equal to
35,000.
Ferry Only..................... Below or equal to 17
30,000.
All Others..................... All.................... 6
------------------------------------------------------------------------
Note: For the purposes of this AD, a ferry flight is defined as
a helicopter flight used for delivering the helicopter from one area
of operation to another. During the ferry flight, the helicopter
would not drop off an external load or pick up an external load.
(ii) If a crack is found, before further flight, replace the
unairworthy blade assembly with an airworthy FAA approved blade
assembly that does not have a serial number listed in paragraph 2.A
of the ASB and does not have ``RS503'' marked near the P/N.
[[Page 74213]]
(b) Installing an airworthy blade assembly that does not have a
serial number listed in paragraph 2.A of the ASB and does not have
``RS503'' marked near the P/N is terminating action for the
requirements of this AD.
(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, Rotorcraft Directorate, Rotorcraft
Certification Office, FAA, ATTN: Michael Kohner, Aviation Safety
Engineer, Fort Worth, Texas 76193-0170, telephone (817) 222-5447,
fax (817) 222-5783.
Issued in Fort Worth, Texas, on November 28, 2007.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-25411 Filed 12-28-07; 8:45 am]
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