[Federal Register: November 26, 2008 (Volume 73, Number 229)]
[Proposed Rules]
[Page 71952-71955]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26no08-28]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1243; Directorate Identifier 2007-SW-03-AD]
RIN 2120-AA64
Airworthiness Directives; Erickson Air-Crane Incorporated
(Erickson) 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 Model S-64F helicopters. The AD would require
inspections for cracking or working rivets in each left and right
splice fitting (transition fitting), the pylon bulkhead assembly--
canted (bulkhead assembly), the pylon steel strap (strap), and the
attaching rotary rudder boom and pylon structure. This proposal is
prompted by several reports of cracking in the transition fittings, the
bulkhead assembly, and pylon. The actions specified by the proposed AD
are intended to detect cracking in the rotary rudder boom or pylon due
to fatigue, and to prevent failure from static overload and subsequent
loss of control of the helicopter.
DATES: Comments must be received on or before January 26, 2009.
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, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-
[[Page 71953]]
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, ATTN: Chris Erickson/Compliance
Officer, 3100 Willow Springs Rd., PO Box 3247, Central Point, OR 97502,
telephone (541) 664-5544, fax (541) 664-2312, e-mail address
cerickson@ericksonaircrane.com.
FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office,
Fort Worth, Texas 76193-0170, 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-2008-1243,
Directorate Identifier 2007-SW-03-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).
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 Model S-64F
helicopters with a transition fitting, part number (P/N) 6420-66341-
101, -102, -103, or -104, a bulkhead assembly, P/N 6420-66340-041, -
043, or -044, or a strap, P/N 6420-66301-119 or -127, installed. The AD
would require inspections for cracking or working rivets in each
transition fitting, the bulkhead assembly, the strap, and the attaching
rotary rudder boom and pylon structure, and replacing or repairing any
cracked or damaged part with an airworthy part. This proposal is
prompted by several reports of cracking in the transition fittings, the
bulkhead assembly, and the pylon. The cracks were discovered during
inspections. The actions specified by the proposed AD are intended to
detect cracking in the rotary rudder boom or pylon due to fatigue, and
to prevent failure from static overload and subsequent loss of control
of the helicopter.
We have reviewed Erickson Service Bulletin (SB) No. 64B20-6,
Revision A, dated December 12, 2007, which describes procedures for
inspecting the transition fittings, the bulkhead assembly, the strap,
and the attaching rotary rudder boom and pylon structure for cracking
or working rivets. We have also reviewed Erickson SB No. 64F General-3,
Revision C, dated December 12, 2007, which summarizes a listing of a
portion of the Model S-64F helicopter components, their part numbers,
and the corresponding service bulletins to use when performing the
structural inspections.
The unsafe condition associated with the fatigue cracking and
working rivets is likely to exist or develop on other helicopters of
the same type design. Therefore, the proposed AD would require, within
20 hours time-in-service (TIS), and thereafter at intervals not to
exceed 20 hours TIS:
Visually inspecting each transition fitting for a crack or
working rivets on the inboard face of the rotary rudder boom and pylon;
Visually inspecting the outboard face of each rotary
rudder boom and pylon skin panel (skin panel) that attaches to the
transition fittings for a crack or working rivets in the transition
fitting attachment areas;
Visually inspecting the forward and aft sides of the
bulkhead assembly for a crack;
Visually inspecting the upper 12 inches of the strap for a
crack or for working rivets; and
Visually inspecting the pylon on each side of the upper 12
inches of the strap, and also 6 inches above the strap, for a crack or
working rivets.
For any pylon with a strap installed, the proposed AD would
require, within 155 hours TIS, and thereafter at intervals not to
exceed 155 hours TIS, removing the inspection panels, P/N 6420-66304-
109 and 6420-66303-125, on the forward and aft sides of the pylon, and
visually inspecting the left-hand cap angle (longeron), P/N 6420-66304-
136, and the interior area of the pylon that is adjacent to the upper
12 inches of the strap, as well as 6 inches above the end of the strap,
for a crack or working rivets. At each 8,300 hours TIS transition
fitting replacement, the proposed AD would require:
With the transition fitting removed, visually inspecting
both sides of each skin panel for a crack in the areas to which the
transition fitting attaches; and
Performing a fluorescent penetrant inspection of the skin
panels for a crack in the area around the fastener holes attaching the
transition fittings to the rotary rudder boom and pylon.
The proposed AD would also require, before further flight:
Inspecting any part and the surrounding area using a 10-
power or higher magnifying glass if you cannot visually determine that
a crack does not exist in that part;
Performing a fluorescent penetrant inspection of any part,
other than a strap, if you cannot determine that a crack does not exist
in the part after inspecting it with a 10-power or higher magnifying
glass;
Performing a magnetic particle inspection of any strap if
you cannot determine that a crack does not exist in the strap after
inspecting it with a 10-power or higher magnifying glass;
If a crack is found, replacing any cracked part with an
airworthy part or repairing that part if it is within the maximum
repair damage limits; and
If any loose or working rivets are found, removing the
rivets, visually inspecting the fastener holes and surrounding area for
a crack or any other damage, and replacing any cracked part with an
airworthy part or replacing any damaged part with an airworthy part if
the damage exceeds the maximum repair damage limits or repairing any
damaged part, if the part is within the maximum repair damage limits.
Finally, replacing any loose or working rivet would be required.
The actions would be required to be accomplished by following specified
portions of the service bulletin described previously.
We estimate that this proposed AD would affect 7 helicopters of
U.S.
[[Page 71954]]
registry, and the proposed actions would take approximately:
0.75 work hour for the visual inspection of the transition
fittings, skin panels, the bulkhead assembly, strap, and pylon exterior
in the strap area with 30 inspections per year;
0.50 work hour for the visual inspection of the pylon
interior in the strap area with 4 inspections per year;
0.75 work hour for the visual and fluorescent penetrant
inspections of the skin panels at the transition fitting with 1
inspection per year; and
40 work hours per helicopter to repair a pylon structural
assembly.
The average labor rate is $80 per work hour. Required parts would
cost approximately $50,000 per helicopter to repair a pylon structural
assembly, if needed. The estimated cost of labor for the inspections of
7 helicopters would be $14,140. The estimated cost to repair the pylon
structural assembly on a helicopter, including the cost of the
replacement parts and labor, would be $53,200. Based on these figures,
the total cost impact of the proposed AD on U.S. operators is estimated
to be $67,340 per year for the fleet, assuming a pylon structural
assembly on one helicopter would need to be repaired.
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 an economic evaluation of the estimated costs to comply
with this proposed AD and placed it in the AD docket.
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.
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-2008-1243;
Directorate Identifier 2007-SW-03-AD.
Applicability: Model S-64F helicopters, with any of the parts
listed in Table 1 of this AD installed, certificated in any
category.
Table 1
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Installed part Part number (P/N)
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Left or right splice fitting 6420-66341-101, -102, -103, or -104
(transition fitting).
Pylon bulkhead assembly--canted 6420-66340-041, -043, or -044
(bulkhead assembly).
Pylon steel strap (strap).............. 6420-66301-119 or -127
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Compliance: Required as indicated.
To detect cracking in the rotary rudder boom or pylon due to
fatigue, and to prevent failure from static overload and subsequent
loss of control of the helicopter, accomplish the following:
(a) Within 20 hours time-in-service (TIS), unless accomplished
previously, and thereafter at intervals not to exceed 20 hours TIS:
(1) Visually inspect each transition fitting, P/N 6420-66341-
101, -102, -103, or -104, for a crack or working rivets on the
inboard face of the rotary rudder boom and pylon, paying particular
attention to the fastener attachment holes, as depicted in Figure 1,
Detail A, of the Accomplishment Instructions in Erickson Air-Crane
Incorporated Service Bulletin No. 64B20-6, Revision A, dated
December 12, 2007 (SB).
(2) Visually inspect the outboard face of each rotary rudder
boom and pylon skin panel (skin panel) that attaches to the
transition fittings for a crack or working rivets in the transition
fitting attachment areas, paying particular attention to the
fastener attachment holes, as shown in Figure 1, Detail B, of the
Accomplishment Instructions in the SB.
(3) Visually inspect the forward and aft sides of each bulkhead
assembly, P/N 6420-66340-041, -043, or -044, for a crack. Pay
particular attention to the circled areas shown in Figure 2 of the
Accomplishment Instructions in the SB.
(4) Visually inspect the upper 12 inches of each strap, P/N
6420-66301-119 or -127, for a crack or for working rivets as shown
in Figure 3 of the Accomplishment Instructions in the SB.
(5) Visually inspect the pylon for a crack or working rivets on
each side of the upper 12 inches of the strap, and also 6 inches
above the end of the strap as shown in Figure 3 of the
Accomplishment Instructions in the SB.
(b) For any pylon with a strap installed, within 155 hours TIS,
unless previously accomplished, and thereafter at intervals not to
exceed 155 hours TIS, remove the inspection access covers, P/N 6420-
66304-109 and P/N 6420-66303-125, on the forward and aft sides of
the pylon and visually inspect the left-hand cap angle (longeron),
P/N 6420-66304-136, and the interior area of the pylon adjacent to
the upper 12 inches of the strap, as well as 6 inches above the end
of the strap, for a crack or working rivets, as shown in Figure 3 of
the Accomplishment Instructions in the SB.
(c) At each transition fitting replacement, which is required at
intervals not to exceed 8,300 hours TIS:
(1) With each transition fitting removed, visually inspect both
sides of each skin panel for a crack in the areas to which the
transition fitting attaches, paying particular attention to the
fastener attachment holes, as
[[Page 71955]]
depicted in Details A and B, Figure 1, of the Accomplishment
Instructions in the SB.
(2) Perform a fluorescent penetrant inspection of each skin
panel for a crack in the areas around the fastener holes where the
transition fittings attach to the rotary rudder boom and pylon.
(d) Before further flight, accomplish the following:
(1) If you cannot visually determine that a crack does not exist
in a part, inspect the part and the surrounding area using a 10-
power or higher magnifying glass.
(2) If you cannot determine that a crack does not exist in a
part other than a strap after inspecting it with a 10-power or
higher magnifying glass, perform a fluorescent penetrant inspection
of the part.
(3) If you cannot determine that a crack does not exist in a
strap after inspecting it with a 10-power or higher magnifying
glass, perform a magnetic particle inspection of the strap.
(e) If a crack is found, before further flight, replace any
cracked part with an airworthy part, or repair the cracked part if
the damage is within the maximum repair damage limits.
Note: The maximum repair damage limitations are stated in the
applicable Component and Repair Overhaul Manual.
(f) If any loose or working rivets are found, before further
flight, remove the rivets and visually inspect the fastener holes
and surrounding area for a crack or any other damage. Replace any
part that is cracked with an airworthy part; replace any damaged
part with damage exceeding the maximum repair damage limits with an
airworthy part or repair any damaged part that is within the maximum
repair damage limits. Also, replace any loose or working rivets.
(g) 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, FAA, ATTN:
Michael Kohner, Aviation Safety Engineer, FAA, Rotorcraft
Directorate, Rotorcraft Certification Office, Fort Worth, Texas
76193-0170, telephone (817) 222-5170, fax (817) 222-5783, for
information about previously approved alternative methods of
compliance.
(h) Special flight permits may be issued in accordance with 14
CFR 21.197 and 21.199 to operate the helicopter to a location where
the inspection requirements of this AD can be accomplished. No
special flight permits will be issued to accomplish replacements or
repairs, or if a crack is suspected.
Issued in Fort Worth, Texas, on November 14, 2008.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-28109 Filed 11-25-08; 8:45 am]
BILLING CODE 4910-13-P