[Federal Register Volume 77, Number 126 (Friday, June 29, 2012)]
[Proposed Rules]
[Pages 38744-38747]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-15978]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0689; Directorate Identifier 2009-SW-065-AD]
RIN 2120-AA64
Airworthiness Directives; Sikorsky Aircraft-Manufactured Model S-
64F Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) for the Sikorsky Aircraft Corporation-manufactured Model S-64F
helicopters, now under the Erickson Air-Crane Incorporated (Erickson)
Model S-64F type certificate. That AD currently requires inspections,
rework, and replacement, if necessary, of the main gearbox (MGB) second
stage lower planetary plate (plate). Since we issued that AD, the
manufacturer has conducted a configuration review and analysis, and a
review of the service history of certain components. The proposed
actions are intended to establish life limits for certain components,
remove various parts from service, and require consistency in the part
numbers of certain four bladed tail rotor (T/R) assemblies to prevent
fatigue cracking, failure from static overload, and subsequent loss of
control of the helicopter.
DATES: We must receive comments on this proposed AD by August 28, 2012.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
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 proposed AD, the economic
evaluation, any comments received and other information. The street
address for the Docket Operations Office (telephone 800-647-5527) is in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
For service information identified in this proposed 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 address
[email protected]. You may review a copy of this service
information at the FAA, Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office,
Fort Worth, Texas 76137, telephone (817) 222-5170, email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this rulemaking by submitting
written comments, data, or views. We also invite comments relating to
the economic, environmental, energy, or federalism impacts that might
result from adopting the proposals in this document. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. To
ensure the docket does not contain duplicate comments, commenters
should send only one copy of written comments, or if comments are filed
electronically, commenters should submit only one time.
We will file in the docket all comments that we receive, as well as
a report summarizing each substantive public contact with FAA personnel
concerning this proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.
Discussion
On May 9, 1997, we issued AD 97-10-15, Amendment 39-10028 (62 FR
28321, May 23, 1997), for the Sikorsky Aircraft-manufactured Model S-
64F helicopters (now under the Erickson Model S-64F helicopter type
certificate) with a plate, P/N 6435-20516-101, with 2,000 or more hours
time-in-service (TIS). That AD requires, before the first flight of
each day, inspecting the MGB main oil filter for magnesium
contamination, and if magnesium contamination is present, replacing the
MGB assembly. That AD also requires inspecting the MGB assembly within
100 hours TIS, and thereafter at intervals not to exceed 500 hours TIS,
and if necessary, replacing the MGB assembly. Finally, that AD
requires, at the next overhaul of the MGB assembly, inspecting and
reworking the plate. That action was prompted by two incidents in which
the plate was found cracked. The requirements of that AD are intended
to prevent failure of the plate due to fatigue cracking, which could
lead to failure of the MGB and subsequent loss of control of the
helicopter.
Actions Since Existing AD Was Issued
Since we issued AD 97-10-15, Erickson has performed additional
analysis as a part of a configuration review and has also reviewed the
service history of certain components. Erickson determined that certain
life-limits and other maintenance requirements need to be revised, and
released Erickson Service Bulletin (SB) No. 64F General-1, Revision 17,
dated August 17, 2010 (SB No. 64F General-1, Rev. 17). We have reviewed
this SB and have determined that the retirement lives of certain parts
need to be revised. We have also determined that certain parts,
including the plate, P/N 6435-20516-101, which is the subject of the
existing AD, should be removed from service and should no longer be
eligible for installation on these helicopters.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or
[[Page 38745]]
develop in other products of the same type design.
Related Service Information
SB No. 64F General-1, Rev. 17, contains the Airworthiness
Limitations Schedule for the Model S-64F helicopter and lists the parts
and assemblies with their specified retirement lives.
Proposed AD Requirements
This AD proposes to reduce or establish the life limits for certain
flight-critical components, remove other parts with service
difficulties from service, and require that T/R blade assembly P/N
65160-00001-048 be installed only as a set of four and not be installed
with another part-numbered blade. The requirements in current AD 97-10-
15 would be superseded and the part-numbered planetary plate, which is
the subject of that AD, would be removed from service. This proposed AD
would require, before further flight, a change in the life-limit for
the following components:
Main Rotor (M/R) Blade Assembly, P/N 6415-20601-045;
Main Transmission Support Beam Assembly, LH, P/N 6420-
62363-045;
Main Transmission Support Beam Assembly, RH, P/N 6420-
62363-046;
Left Splice Fitting (Transition Fitting), Rotary, Rudder
Boom, P/N 6420-66341-101;
Right Splice Fitting (Transition Fitting), Rotary, Rudder
Boom, P/N 6420-66341 102;
M/R Drive Shaft, P/N 6435-20536-101;
Pressure Plate Assembly, Rotary Wing Head, P/N 65101-
11016-042;
Horn and Liner Assembly, P/N 65102-11047-041;
Lower Hub Plate Assembly, P/N 65103-11009-041;
Horizontal Hinge Pin, Rotary Wing Head, P/N 65103-11020-
103;
Damper Bracket Assembly, Rotary Wing Head, P/N 65103-
11032-043;
Hub Subassembly, Rotary Wing, P/N 65103-11310-043;
Shaft Assembly, Pitch Control Tail Gearbox, P/N 65358-
07035-043; and
Rod End Assembly, Primary Servo Assembly, P/N 65652-11212-
041.
In addition to proposing new or revised life limits for certain
flight-critical components, this AD also proposes to remove the
following components from service due to service difficulties:
Spindle Assembly, Rotary Rudder, P/N 6410-30302-041;
MGB Second Stage Lower Planetary Plate, P/N 6435-20516-101
or 6435-20516-102;
Bracket Assembly, Main Servo, P/N 6435-20527-041 or 6435-
20527-042;
Primary Servo Link Assembly, Tandem Servo, M/R, P/N 6465-
62161-042;
Shoulder Bolt, T/R, P/N 65111-07001-102; and
T/R Blade Assembly, P/N 65161-00001-041.
This proposed AD contains only a portion of the life-limited parts
for this model helicopter, and is not an all-inclusive list.
Costs of Compliance
We estimate that this proposed AD would affect 7 helicopters of
U.S. Registry and estimate, at an average labor rate of $85 per hour,
the following costs for removing from service the parts listed in Table
2 of this proposed AD action:
Reviewing helicopter records to determine if an affected
part is installed will require approximately 2 work-hours, for a cost
per helicopter of $170 and a fleet cost of $1,190.
Replacing the rotary rudder spindle assembly will require
10 work-hours and a parts cost of $2,787, for a cost per helicopter of
$3,637 and a fleet cost of $25,459.
Replacing the plate will require 40 work-hours and a parts
cost of $43,750, for a cost per helicopter of $47,150 and a fleet cost
of $330,050.
Replacing the main servo bracket assembly will require 2
work-hours and a parts cost of $5,223, for a cost per helicopter of
$5,393 and a fleet cost of $37,751.
Replacing the primary servo link assembly of the M/R
tandem servo will require 10 work-hours and a parts cost of $14,533,
for a cost per helicopter of $15,383 and a fleet cost of $107,681.
Replacing the T/R shoulder bolt will require 10 work-hours
and a parts cost of $571, for a cost per helicopter of $1,421 and a
fleet cost of $9,947.
Replacing the T/R Blade Assembly will require 8 work-hours
and a parts cost of $125,765 for a cost per helicopter of $126,445 and
a fleet cost of $885,115.
The total cost to replace the parts that are proposed to
be removed from service is estimated to be $199,599 per helicopter and
a fleet cost of $1,397,193.
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
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. 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, I certify this 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);
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 proposed 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The FAA amends Sec. 39.13 by removing Amendment 39-10028 (62 FR
28321, May 23, 1997), and adding the following new AD:
[[Page 38746]]
ERICKSON AIR-CRANE INCORPORATED: Docket No. FAA-2012-0689;
Directorate Identifier 2009-SW-065-AD.
(a) Applicability
This AD applies to Sikorsky Aircraft Corporation-manufactured
Model S-64F helicopters, now under the Erickson Air-Crane
Incorporated Model S-64F type certificate, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as a fatigue crack in a
flight critical component. This condition could result in component
failure from static overload and subsequent loss of control of the
helicopter.
(c) Other Affected ADs
This AD supersedes AD 97-10-15, Amendment 39-10028 (62 FR 28321,
May 23, 1997).
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless accomplished
previously.
(e) Required Actions
(1) Before further flight:
(i) Remove from service any part with a number of hours time-in-
service (TIS) equal to or greater than the part's retirement life as
stated in following Table 1 of this AD.
Table 1--Parts With New or Revised Life Limits
------------------------------------------------------------------------
Part name Part No. (P/N) Retirement life
------------------------------------------------------------------------
Main Rotor (M/R) Blade Assembly.. 6415-20601-045 13,280 hours TIS.
Main Transmission Support Beam 6420-62363-045 9,300 hours TIS.
Assembly, LH.
Main Transmission Support Beam 6420-62363-046 9,300 hours TIS.
Assembly, RH.
Left Splice Fitting (Transition 6420-66341-101 8,300 hours TIS.
Fitting), Rotary, Rudder Boom.
Right Splice Fitting (Transition 6420-66341-102 8,300 hours TIS.
Fitting), Rotary, Rudder Boom.
M/R Drive Shaft.................. 6435-20536-101 2,200 hours TIS.
Pressure Plate Assembly, Rotary 65101-11016-042 8,800 hours TIS.
Wing Head.
Horn and Liner Assembly.......... 65102-11047-041 1,140 hours TIS.
Lower Hub Plate Assembly......... 65103-11009-041 15,500 hours TIS.
Horizontal Hinge Pin, Rotary Wing 65103-11020-103 5,100 hours TIS.
Head.
Damper Bracket Assembly, Rotary 65103-11032-043 20,000 hours TIS.
Wing Head.
Hub Subassembly, Rotary Wing..... 65103-11310-043 21,600 hours TIS.
Shaft Assembly, Pitch Control 65358-07035-043 9,400 hours TIS.
Tail Gearbox.
Rod End Assembly, Primary Servo 65652-11212-041 20,800 hours TIS.
Assembly.
------------------------------------------------------------------------
Note to Table 1: The list of parts in Table 1 of this AD
contains only a portion of the life-limited parts for this model
helicopter and is not an all-inclusive list.
(ii) Revise the retirement life of each part as shown in Table 1
of this AD by making pen and ink changes or by inserting a copy of
this AD into the Airworthiness Limitations section of the
maintenance manual.
(iii) Record on the component history card or equivalent record
the retirement life for each part as shown in Table 1 of this AD.
(2) Before further flight, remove from service any part with a
P/N listed in the following Table 2 of this AD, regardless of the
part's TIS. The P/Ns listed in Table 2 of this AD are not eligible
for installation on any helicopter.
Table 2--Parts To Be Removed From Service
------------------------------------------------------------------------
Part name P/N
------------------------------------------------------------------------
Spindle Assembly, Rotary Rudder........ 6410-30302-041.
Main Gearbox Second Stage Lower 6435-20516-101 or 6435-20516-
Planetary Plate. 102.
Bracket Assembly, Main Servo........... 6435-20527-041 or 6435-20527-
042.
Primary Servo Link, Tandem Servo, M/R.. 6465-62161-042.
Shoulder Bolt, Tail Rotor (T/R)........ 65111-07001-102.
T/R Blade Assembly..................... 65161-00001-041.
------------------------------------------------------------------------
(3) Before further flight, if a T/R blade assembly, P/N 65160-
00001-048, is installed, remove any of the other three T/R blade
assemblies that have a different P/N and replace it with a T/R blade
assembly, P/N 65160-00001-048. The T/R blade assembly, P/N 65160-
00001-048, must be installed in sets of four only.
(f) 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, FAA, Rotorcraft Directorate, Rotorcraft
Certification Office, Fort Worth, Texas, 76137, telephone (817) 222-
5170, email [email protected].
(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.
(g) Additional Information
Erickson Service Bulletin No. 64F General-1, Revision 17, dated
August 17, 2010, which is not incorporated by reference, contains
additional information about the subject of this AD. For service
information identified in this AD, contact 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, email address
[email protected]. You may review a copy of this
information at the FAA,
[[Page 38747]]
Office of the Regional Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas 76137.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6300: Main Rotor
Drive System and 6400: Tail Rotor System.
Issued in Fort Worth, Texas, on June 21, 2012.
M. Monica Merritt,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-15978 Filed 6-28-12; 8:45 am]
BILLING CODE 4910-13-P