Document ID: FAA-2008-1243-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Erickson Air-Crane Incorporated Helicopters
Posted Date: 2012-12-10T05:00Z

[Federal Register Volume 77, Number 237 (Monday, December 10, 2012)]
[Rules and Regulations]
[Pages 73265-73268]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-28434]

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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; 
Amendment 39-17267; AD 2012-23-11]
RIN 2120-AA64

Airworthiness Directives; Erickson Air-Crane Incorporated 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for 
Erickson Air-Crane Incorporated (Erickson) Model S-64F helicopters. 
This AD requires inspecting for cracking or working rivets in each left 
and right splice fitting (transition fitting), the pylon bulkhead 
assembly-canted (bulkhead assembly), and the pylon steel strap (strap). 
This AD was prompted by several reports of cracking in the transition 
fittings, the bulkhead assembly, and the pylon. The actions specified 
by this 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: This AD is effective January 14, 2013.

[[Page 73266]]

    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of January 14, 
2013.

ADDRESSES: For service information identified in this AD, contact 
Erickson Air-Crane Incorporated, ATTN: Chris Erickson/Compliance 
Officer, 3100 Willow Springs Rd., P.O. Box 3247, Central Point, OR 
97502; telephone (541) 664-5544; fax (541) 664-2312; email 
cerickson@ericksonaircrane.com. You may review the referenced service 
information at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

Examining the AD Docket

    You may examine the AD docket 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 AD docket contains this AD, any incorporated-by-reference 
service information, the economic evaluation, any comments received, 
and other information. The street address for the Docket Operations 
Office (phone: 800-647-5527) is U.S. Department of Transportation, 
Docket Operations Office, M-30, West Building Ground Floor, Room W12-
140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety 
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5170; 
email 7-avs-asw-170@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    On November 26, 2008, at 73 FR 71952, the Federal Register 
published our notice of proposed rulemaking (NPRM), which proposed to 
amend 14 CFR part 39 to include an AD that would apply to Erickson 
Model S-64F helicopters with a transition fitting, part number (P/N) 
6420-66341-101, -102, -103, or -104; bulkhead assembly, P/N 6420-66340-
041, -043, or -044; or a strap, P/N 6420-66301-119 or -127, installed. 
That NPRM proposed to require inspecting for cracking or working rivets 
in each transition fitting, the bulkhead assembly, the strap, and the 
attaching rotary rudder boom and pylon structure, and repairing or 
replacing any cracked or damaged part with an airworthy part. The NPRM 
also proposed to require, for any part where you could not visually 
determine that a crack does not exist, inspecting using a 10-power or 
higher magnifying glass. If you could not determine that a crack does 
not exist in the part after inspecting it with a 10-power or higher 
magnifying glass, the NPRM proposed to require performing a fluorescent 
particle inspection (FPI) of any part other than a strap, and 
performing a magnetic particle inspection (MPI) of any strap. The NPRM 
also proposed to require replacing any loose or working rivet. The 
proposed requirements were 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.

Comments

    After our NPRM (73 FR 71952, November 26, 2008) was published, we 
received comments from one commenter.

Request

    A commenter from Erickson Air-Crane asked that we delete the 
bulkhead assembly, P/N 6420-66340-041, from the applicability and 
compliance section of the NPRM (73 FR 71952, November 26, 2008) since 
that P/N is not used on Erickson Model S-64F helicopters. We agree and 
have revised this AD accordingly.
    The commenter also asked that we delete the words ``other than a 
strap'' from the requirement to perform an FPI on a part other than a 
strap if you cannot determine that a crack does not exist, and delete 
the entire requirement to perform an MPI of the strap if you cannot 
determine that a crack does not exist. The commenter states that an MPI 
cannot be performed on the strap when it is installed on a helicopter; 
instead an FPI of the strap would need to be performed with the other 
parts. We partially agree. We agree that an MPI cannot be performed on 
the strap while it is installed on the helicopter because the strap is 
attached to the aluminum pylon section. An MPI for the strap was 
initially proposed in the NPRM (73 FR 71952, November 26, 2008) because 
this would be the type of inspection normally used for a steel part. 
Instead of changing the MPI on the strap to an FPI as requested, after 
further review, we determined that deleting this inspection, as well as 
the magnifying glass inspection and certain FPIs that were proposed in 
the NPRM, will not impact the overall level of safety. These 
inspections were included in the event a visual inspection was 
insufficient to determine whether a crack exists. If any additional 
inspections are necessary to determine if a crack exists, a qualified 
individual performing the inspection must make this determination.

FAA's Determination

    We have reviewed the relevant information, considered the comments 
received, and determined that an unsafe condition exists and is likely 
to exist or develop on other products of the same type design and that 
air safety and the public interest require adopting the AD requirements 
as proposed with the changes described previously and minor editorial 
changes. We have also revised the estimated costs of complying with 
this AD to reflect an average labor rate of $85 per work-hour instead 
of $80 per work-hour. These changes are consistent with the intent of 
the proposals in the NPRM (73 FR 71952, November 26, 2008) and will not 
increase the economic burden on any operator nor increase the scope of 
the AD.

Related Service Information

    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 SBs to use when performing the structural 
inspections.

Costs of Compliance

    We estimate that this AD will affect 7 helicopters of U.S. 
Registry. We estimate that operators may incur the following costs in 
order to comply with this AD. It will take about 0.75 work-hour to 
visually inspect the transition fittings, skin panels, the bulkhead 
assembly, strap, and pylon exterior in the strap area; we estimate 30 
of these visual inspections per year. It will take about 0.50 work-hour 
to visually inspect the pylon interior in the strap area; we estimate 4 
of these visual inspections per year. It will take about 0.75 work-hour 
to visually and fluorescent penetrant inspect the skin panels at the 
transition fitting; we estimate performing these inspections 1 time per 
year. It will take about 40 work-hours to repair a pylon structural 
assembly. The average labor rate is $85 per work-hour and the cost for 
required parts to repair a pylon structural assembly is approximately 
$50,000. Based on these figures, we estimate the annual cost of the 
inspections will be $2,146 per helicopter and $15,024 for the fleet on

[[Page 73267]]

U.S. operators. The estimated cost to repair a pylon structural 
assembly, including the cost for replacement parts and labor, is 
$53,400.

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.
    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 a regulatory distinction; 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.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD and placed it in the AD docket.

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 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 airworthiness 
directive (AD):

2012-23-11 Erickson Air-Crane Incorporated: Amendment 39-17267; 
Docket No. FAA-2008-1243; Directorate Identifier 2007-SW-03-AD.

(a) Applicability

    This AD applies to Erickson Air-Crane Incorporated (Erickson) 
Model S-64F helicopters with a left or right splice fitting 
(transition fitting), part number (P/N) 6420-66341-101, -102, -103, 
or -104; pylon bulkhead assembly-canted (bulkhead assembly), P/N 
6420-66340-043 or -044; or a pylon steel strap (strap), P/N 6420-
66301-119 or -127, installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as cracking in the rotary 
rudder boom or pylon due to fatigue, failure from static overload, 
and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective January 14, 2013.

(d) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(e) Required Actions

    (1) Within 20 hours time-in-service (TIS), and thereafter at 
intervals not to exceed 20 hours (TIS):
    (i) 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).
    (ii) 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.
    (iii) Visually inspect the forward and aft sides of each 
bulkhead assembly, P/N 6420-66340-043 or -044, for a crack. Pay 
particular attention to the circled areas shown in Figure 2 of the 
Accomplishment Instructions in the SB.
    (iv) 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.
    (v) 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.
    (2) For any pylon with a strap installed, within 155 hours TIS, 
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.
    (3) At each transition fitting replacement, which is required at 
intervals not to exceed 8,300 hours TIS:
    (i) 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 depicted in Details A and B, Figure 1, 
of the Accomplishment Instructions in the SB.
    (ii) 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.
    (4) If there is a crack, 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 to paragraph (e)(4) of this AD:  The maximum repair damage 
limitations are stated in the applicable Component and Repair 
Overhaul Manual.

    (5) 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.

(f) Special Flight Permits

    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.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Rotorcraft Certification Office, FAA, may 
approve AMOCs for this AD. Send your proposal to: Michael Kohner, 
Aviation Safety Engineer, Rotorcraft Certification Office, 
Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 
76137; telephone (817) 222-5170; email 7-avs-asw-170@faa.gov.

[[Page 73268]]

    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office or 
certificate holding district office before operating any aircraft 
complying with this AD through an AMOC.

(h) Additional Information

    Erickson Air-Crane Service Bulletin No. 64F General-3, Revision 
C, dated December 12, 2007, which is not incorporated by reference, 
contains additional information about the subject of this AD. For 
this service information, contact Erickson Air-Crane Incorporated, 
ATTN: Chris Erickson/Compliance Officer, 3100 Willow Springs Rd., 
P.O. Box 3247, Central Point, OR 97502; telephone (541) 664-5544; 
fax (541) 664-2312; email cerickson@ericksonaircrane.com. You may 
also review this service information at the FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 5302, Rotorcraft 
Tail Boom.

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Erickson Air-Crane Incorporated Service Bulletin No. 64B20-
6, Revision A, dated December 12, 2007.
    (ii) Reserved.
    (3) For Erickson Air-Crane Incorporated service information 
identified in this AD, contact Erickson Air-Crane Incorporated, 
ATTN: Chris Erickson/Compliance Officer, 3100 Willow Springs Rd., 
P.O. Box 3247, Central Point, OR 97502; telephone (541) 664-5544; 
fax (541) 664-2312; email cerickson@ericksonaircrane.com.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. For information on the availability of this 
material at the FAA, call (817) 222-5110.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on November 13, 2012.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-28434 Filed 12-7-12; 8:45 am]
BILLING CODE 4910-13-P