[Federal Register Volume 77, Number 112 (Monday, June 11, 2012)]
[Proposed Rules]
[Pages 34281-34283]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-14037]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0602; Directorate Identifier 2009-SW-061-AD]
RIN 2120-AA64
Airworthiness Directives; Schweizer Aircraft Corporation
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) for Schweizer Aircraft Corporation (Schweizer) Model 269D and
Model 269D Configuration A helicopters. The type certificate for these
models is currently held by Sikorsky Aircraft Corporation (Sikorsky).
This proposal is prompted by reports of loose horizontal stabilizers
and cracks in the stabilizer-support structure for the extruded
tailboom. The AD would require inspecting the aft fuselage assembly in
the area around the attachment point of the horizontal stabilizer,
including the paint, for a crack. This AD also would require inspecting
the tailboom interior support structure, and if necessary, installing
an inspection panel kit in the aft fuselage assembly, and installing
doublers in the stabilizer support brackets. The actions specified by
the proposed AD are intended to prevent separation of the horizontal
stabilizer from the helicopter and subsequent loss of control of the
helicopter.
DATES: We must receive comments on this proposed AD by August 10, 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
Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical
Support, mailstop s581a, 6900 Main Street, Stratford, CT 06614;
telephone (800) 562-4409; email [email protected]; or at http://www.sikorsky.com. You may review copies of the referenced 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: Stephen Kowalski, Aviation Safety
Engineer, New York Aircraft Certification Office, Engine & Propeller
Directorate, 1600 Stewart Ave. suite 410, Westbury, NY 11590; telephone
(516) 228-7327; 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
This document proposes adopting a new AD for the Schweizer Model
269D and Model 269D Configuration A helicopters, serial numbers 0001 to
0062A, with aft fuselage assembly part number (P/N) 269D3300-1
installed. This proposal is prompted by reports of loose horizontal
stabilizers and cracks in the support structure for the extruded
tailboom. The actions specified by the proposed AD are intended to
prevent separation of the horizontal stabilizer from the helicopter and
subsequent loss of control of the helicopter.
FAA's Determination
We are proposing this AD because we evaluated all known relevant
information and determined that an unsafe condition exists and is
likely to exist or develop on other products of the same type design.
Related Service Information
We have reviewed Schweizer Service Bulletin DB-018.3, dated
December 13, 2007 (SB), which specifies inspecting for cracks in the
fuselage assemblies and installing an inspection panel kit and
stabilizer mount doublers. The Type Certificate for these helicopters
transferred from Schweizer to Sikorsky on September 26, 2011.
[[Page 34282]]
Proposed AD Requirements
This proposed AD would require:
Before the first flight of each day, visually inspecting
the aft fuselage assembly in the area around the attachment point of
the horizontal stabilizer for a crack.
If there is a crack in the aft fuselage assembly clip, aft
bulkhead, or adjacent skins, repairing the crack and either performing
a repetitive inspection at intervals not to exceed 200 hours time-in-
service (TIS) or replacing the aft fuselage assembly.
If there is a crack in a longeron, tailboom tube collar or
a forward stabilizer bulkhead, replacing the aft fuselage assembly.
Within 100 hours TIS or three months, whichever occurs
first:
[cir] Removing the horizontal stabilizer, cleaning the horizontal
stabilizer mounting brackets, inspecting the mounting brackets for wear
greater than 0.002-inch deep, and replacing the mounting bracket if the
bracket wear exceeds 0.002-inch deep.
[cir] Modifying the aft fuselage assembly by installing Inspection
Panel kit P/N SA-269DK-035, installing doublers on the forward side of
each mounting bracket, inspecting the horizontal stabilizer forward and
aft spars for wear in the mounting attachment areas, and replacing the
spar if the wear exceeds 0.002-inch deep.
[cir] Inspecting for rivet interference between the rivet heads and
skin on the top surface of the horizontal stabilizer and the tailboom
stiffening web near Station 232.4 and replacing the rivets if
interference exists.
[cir] Installing an airworthy horizontal stabilizer using 4 bolts,
P/N NAS1304-4, and 4 washers, P/N AN960KD416 or NAS1149D0463K.
Removing aft fuselage assembly P/N 269D3300-1, and
replacing it with aft fuselage assembly P/N 269D3300-35, would be
terminating action for the requirements of this AD.
Differences Between This Proposed AD and the Service Information
The Schweizer SB requires contacting the manufacturer if certain
damage is found for repair instructions. This AD does not.
Costs of Compliance
We estimate that this proposed AD would affect 18 helicopters. The
average labor rate is $85 per work hour. Based on these assessments, we
estimate the following costs:
Daily visual inspection. This would take about 10 minutes
for a labor cost of $9. Assuming 365 daily inspections per year, the
annual labor cost per helicopter would be about $3,285. The annual cost
for the U.S. fleet would total $59,130.
Internal inspection. This would take two work-hours for a
labor cost of $170. Assuming 10 inspections a year, the annual labor
cost per helicopter would be $1,700.
Install inspection panel. This would take 16 work-hours
for a labor cost of $1,360. Parts would cost $150 for a cost per
helicopter of $1,510.
Repair damaged longerons, tailboom tube collars, or
forward stabilizer bulkhead as needed. This would take 24 work-hours
for a labor cost of $2,040. Parts would cost $38,000 for a cost per
helicopter of $40,040.
Repair a crack in the aft fuselage assembly clip, aft
bulkhead, or adjacent skins. This would take 24 work-hours for a labor
cost of $2,040. Parts would cost $120 for a cost per helicopter of
$2,160.
Repair interference between the rivet heads and skin .
This would take 10 work-hours for a labor cost of $850. No parts would
be needed.
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 adding the following new
Airworthiness Directive
(AD): SCHWEIZER AIRCRAFT CORPORATION HELICOPTERS: Docket No. FAA-
2012-0602; Directorate Identifier 2009-SW-061-AD.
(a) Applicability
This AD applies to Schweizer Aircraft Corporation (Schweizer)
Model 269D and Model 269D Configuration A helicopters, serial
numbers 0001 to 0062A, with aft fuselage assembly part number (P/N)
269D3300-1 installed, certificated in any category.
Note to Applicability: The type certificate for these models is
currently held by Sikorsky Aircraft Corporation.
(b) Unsafe Condition
This AD defines the unsafe condition as loose horizontal
stabilizers and cracks in the stabilizer support structure for the
extruded tailboom, which could result in separation of the
horizontal stabilizer from the helicopter and subsequent loss of
helicopter control.
(c) 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.
[[Page 34283]]
(d) Required Actions
(1) Before the first flight of each day, visually inspect the
aft fuselage assembly in the area around the attachment point of the
horizontal stabilizer, including the paint, for a crack. If there is
a crack, remove the horizontal stabilizer and perform an interior
inspection in accordance with Part II: Internal Inspection,
paragraphs b. and c., of Schweizer Service Bulletin DB-018.3, dated
December 13, 2007 (SB).
(i) If there is a crack in the aft fuselage assembly clip, in
the aft bulkhead, or in adjacent skins, repair the crack.
Thereafter, at intervals not to exceed 200 hours time-in-service
(TIS), remove the horizontal stabilizer and repeat the interior
inspection in accordance with Part II: Internal Inspection,
paragraphs b. and c., of the SB, or replace the aft fuselage
assembly, P/N 269D3300-1,with an airworthy aft fuselage assembly, P/
N 269D3300-35.
(ii) If there is a crack in a longeron, tailboom tube collar or
a forward stabilizer bulkhead, replace the aft fuselage assembly
with an airworthy aft fuselage assembly, P/N 269D3300-35.
(2) Within 100 hours TIS or three months, whichever occurs
first:
(i) Remove the horizontal stabilizer, clean the horizontal
stabilizer mounting brackets, and inspect the mounting brackets for
wear greater than 0.002-inch deep. If the bracket wear exceeds
0.002-inch deep, replace the mounting bracket with an airworthy
mounting bracket.
(ii) Modify the aft fuselage assembly by installing Inspection
Panel kit P/N SA-269DK-035.
(iii) Install doublers on the forward side of each mounting
bracket in accordance with Part III-2, paragraphs e. through i., of
the SB.
(iv) Inspect the horizontal stabilizer forward and aft spars for
wear in the mounting attachment areas. If the wear exceeds 0.002-
inch deep, replace the spar with an airworthy spar.
(v) Inspect for rivet interference between the rivet heads and
skin on the top surface of the horizontal stabilizer and the
tailboom stiffening web near Station 232.4. If interference exists,
replace with airworthy rivets.
(vi) Install an airworthy horizontal stabilizer using 4 bolts,
P/N NAS1304-4, and 4 washers, P/N AN960KD416 or NAS1149D0463K.
(3) Removing aft fuselage assembly, P/N 269D3300-1, and
replacing it with aft fuselage assembly, P/N 269D3300-35, is
terminating action for the requirements of this AD.
(e) Special Flight Permit
Special flight permits may be issued in accordance with 14 CFR
21.197 and 21.199 provided that before operating the helicopter to a
location to perform the actions in paragraphs (d)(1) through (d)(3)
of this AD, a daily, pre-flight visual inspection is accomplished in
accordance with paragraph (d)(1) of this AD.
(f) Alternative Methods of Compliance (AMOC)
(1) The Manager, NYACO, FAA, may approve AMOCs for this AD. Send
your proposal to: Stephen Kowalski, Aviation Safety Engineer, New
York Aircraft Certification Office, Engine & Propeller Directorate,
1600 Stewart Ave., suite 410, Westbury, NY 11590; telephone (516)
228-7327; 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
For service information identified in this AD, contact Sikorsky
Aircraft Corporation, Attn: Manager, Commercial Technical Support,
mailstop s581a, 6900 Main Street, Stratford, CT 06614; telephone
(800) 562-4409; email [email protected]; or at http://www.sikorsky.com. You may review a copy of information at the FAA,
Office of the Regional Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas 76137.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 5302, Rotorcraft
tailboom.
Issued in Fort Worth, Texas, on May 25, 2012.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-14037 Filed 6-8-12; 8:45 am]
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