Airworthiness Directives; Schweizer Aircraft Corporation, 9789-9791 [2013-02583]
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Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations
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 a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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 the NPRM (77 FR 62182,
October 12, 2012), the regulatory
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.
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2013–03–05 Airbus: Amendment 39–17340.
Docket No. FAA–2012–1070; Directorate
Identifier 2012–NM–099–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective March 19, 2013.
pmangrum on DSK3VPTVN1PROD with RULES
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1) and (c)(2) of this AD,
certificated in any category.
(1) All Airbus Model A300 B4–601, B4–
603, B4–620, and B4–622 airplanes; Model
A300 B4–605R and B4–622R airplanes;
Model A300 F4–605R and F4–622R
airplanes; and Model A300 C4–605R Variant
F airplanes.
(2) All Airbus Model A310–203, –204,
–221, –222, –304, –322, –324, and –325
airplanes.
VerDate Mar<15>2010
15:05 Feb 11, 2013
Jkt 229001
(d) Subject
Air Transport Association (ATA) of
America Code 28; Fuel.
(e) Reason
This AD was prompted by fuel system
reviews conducted by the European Aviation
Safety Agency (EASA). We are issuing this
AD to reduce the potential of ignition sources
inside fuel tanks, which, in combination with
flammable fuel vapors, could result in fuel
tank explosions and consequent loss of the
airplane.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Actions
Within 48 months after the effective date
of this AD, accomplish the actions specified
in paragraph (g)(1) or (g)(2) of this AD, as
applicable.
(1) For Model A310 series airplanes:
Modify the electrical control circuits of the
inner, center, and trim tank pumps, as
applicable, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A310–28–2170,
dated February 28, 2012.
(2) For Model A300–600 airplanes: Modify
the electrical control circuits of the inner,
center, and trim tank pumps, as applicable,
in accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A300–28–6104, dated February 28,
2012.
(h) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227–2125; fax (425) 227–
1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
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9789
(i) Related Information
Refer to MCAI EASA Airworthiness
Directive 2012–0091, dated May 25, 2012,
and the service information identified in
paragraphs (i)(1) and (i)(2) of this AD, for
related information.
(1) Airbus Mandatory Service Bulletin
A310–28–2170, dated February 28, 2012.
(2) Airbus Mandatory Service Bulletin
A300–28–6104, dated February 28, 2012.
(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) Airbus Mandatory Service Bulletin
A310–28–2170, dated February 28, 2012.
(ii) Airbus Mandatory Service Bulletin
A300–28–6104, dated February 28, 2012.
(3) For service information identified in
this AD, contact Airbus SAS—EAW
(Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airwortheas@airbus.com; Internet https://
www.airbus.com.
(4) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on January
28, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–02723 Filed 2–11–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0602; Directorate
Identifier 2009–SW–061–AD; Amendment
39–17338; AD 2013–03–04]
RIN 2120–AA64
Airworthiness Directives; Schweizer
Aircraft Corporation
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
SUMMARY:
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Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations
pmangrum on DSK3VPTVN1PROD with RULES
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 AD
requires 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 requires 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. This AD is
prompted by reports of loose horizontal
stabilizers and cracks in the stabilizer
support structure for the extruded
tailboom. The actions are intended to
prevent separation of the horizontal
stabilizer from the helicopter and
subsequent loss of control of the
helicopter.
DATES: This AD is effective March 19,
2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of March 19, 2013.
ADDRESSES: 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
tsslibrary@sikorsky.com; or at https://
www.sikorsky.com. You may review a
copy of 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 https://
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:
Stephen Kowalski, Aviation Safety
Engineer, New York Aircraft
Certification Office, Engine & Propeller
Directorate, 1600 Stewart Ave., suite
VerDate Mar<15>2010
15:05 Feb 11, 2013
Jkt 229001
410, Westbury, NY 11590; telephone
(516) 228–7327; email
stephen.kowalski@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On June 11, 2012, at 77 FR 34281, 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
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. That NPRM
proposed to require inspecting the aft
fuselage assembly in the area around the
attachment point of the horizontal
stabilizer, including the paint, for a
crack. That AD also proposed 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
proposed requirements were prompted
by reports of loose horizontal stabilizers
and cracks in the support structure of
the extruded tailboom. The proposed
requirements were intended to prevent
separation of the horizontal stabilizer
from the helicopter and subsequent loss
of control of the helicopter.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we received no comments on the NPRM
(77 FR 34281, June 11, 2012).
FAA’s Determination
We have reviewed the relevant
information and determined that an
unsafe condition exists and is likely to
exist or develop on other products of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed.
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.
Differences Between This AD and the
Service Information
The Schweizer SB requires contacting
the manufacturer if certain damage is
found for repair instructions. This AD
does not.
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Fmt 4700
Sfmt 4700
Costs of Compliance
We estimate that this AD affects 18
helicopters, and that the average labor
rate is $85 per work hour. Based on
these assessments, we estimate the
following costs:
• Daily visual inspection. This takes
about 10 minutes for a labor cost of $9.
Assuming 365 daily inspections per
year, the annual labor cost per
helicopter will be about $3,285. The
annual cost for the U.S. fleet will total
$59,130.
• Internal inspection. This takes two
work-hours for a labor cost of $170.
Assuming 10 inspections a year, the
annual labor cost per helicopter is
$1,700.
• Install inspection panel. This takes
16 work-hours for a labor cost of $1,360.
Parts cost $150 for a cost per helicopter
of $1,510.
• Repair damaged longerons,
tailboom tube collars, or forward
stabilizer bulkhead as needed. This
takes 24 work-hours for a labor cost of
$2,040. Parts 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 takes 24 work-hours for a
labor cost of $2,040. Parts cost $120 for
a cost per helicopter of $2,160.
• Repair interference between the
rivet heads and skin. This takes 10
work-hours for a labor cost of $850. No
parts are 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
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
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Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
pmangrum on DSK3VPTVN1PROD with RULES
2013–03–04 SCHWEIZER AIRCRAFT
CORPORATION HELICOPTERS:
Amendment 39–17338; 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.
VerDate Mar<15>2010
15:05 Feb 11, 2013
Jkt 229001
(c) Effective Date
This AD becomes effective March 19, 2013.
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has been
accomplished previously.
(e) 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-inservice (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.
(f) Special Flight Permits
Special flight permits may be issued in
accordance with 14 CFR 21.197 and 21.199
provided that before operating the helicopter
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9791
to a location to perform the actions in
paragraphs (e)(1) through (e)(3) of this AD, a
daily, pre-flight visual inspection is
accomplished in accordance with paragraph
(e)(1) of this AD.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, NY ACO, 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 stephen.kowalski@faa.gov.
(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) Subject
Joint Aircraft Service Component (JASC)
Code: 5302, Rotorcraft tailboom.
(i) 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) Schweizer Service Bulletin DB–018.3,
dated December 13, 2007.
(ii) Reserved.
(3) For Schweizer Aircraft Corporation
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
tsslibrary@sikorsky.com; or at https://
www.sikorsky.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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on January 29,
2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2013–02583 Filed 2–11–13; 8:45 am]
BILLING CODE 4910–13–P
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]]>Agencies
[Federal Register Volume 78, Number 29 (Tuesday, February 12, 2013)]
[Rules and Regulations]
[Pages 9789-9791]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-02583]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0602; Directorate Identifier 2009-SW-061-AD;
Amendment 39-17338; AD 2013-03-04]
RIN 2120-AA64
Airworthiness Directives; Schweizer Aircraft Corporation
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
[[Page 9790]]
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 AD
requires 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 requires 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. This AD is prompted by reports of loose horizontal
stabilizers and cracks in the stabilizer support structure for the
extruded tailboom. The actions are intended to prevent separation of
the horizontal stabilizer from the helicopter and subsequent loss of
control of the helicopter.
DATES: This AD is effective March 19, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of March 19, 2013.
ADDRESSES: 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 tsslibrary@sikorsky.com; or at https://www.sikorsky.com. You may review a copy of 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 https://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: 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 stephen.kowalski@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On June 11, 2012, at 77 FR 34281, 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 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. That NPRM proposed to require inspecting the aft fuselage
assembly in the area around the attachment point of the horizontal
stabilizer, including the paint, for a crack. That AD also proposed
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 proposed
requirements were prompted by reports of loose horizontal stabilizers
and cracks in the support structure of the extruded tailboom. The
proposed requirements were intended to prevent separation of the
horizontal stabilizer from the helicopter and subsequent loss of
control of the helicopter.
Comments
We gave the public the opportunity to participate in developing
this AD, but we received no comments on the NPRM (77 FR 34281, June 11,
2012).
FAA's Determination
We have reviewed the relevant information and determined that an
unsafe condition exists and is likely to exist or develop on other
products of these same type designs and that air safety and the public
interest require adopting the AD requirements as proposed.
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.
Differences Between This 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 AD affects 18 helicopters, and that the
average labor rate is $85 per work hour. Based on these assessments, we
estimate the following costs:
Daily visual inspection. This takes about 10 minutes for a
labor cost of $9. Assuming 365 daily inspections per year, the annual
labor cost per helicopter will be about $3,285. The annual cost for the
U.S. fleet will total $59,130.
Internal inspection. This takes two work-hours for a labor
cost of $170. Assuming 10 inspections a year, the annual labor cost per
helicopter is $1,700.
Install inspection panel. This takes 16 work-hours for a
labor cost of $1,360. Parts cost $150 for a cost per helicopter of
$1,510.
Repair damaged longerons, tailboom tube collars, or
forward stabilizer bulkhead as needed. This takes 24 work-hours for a
labor cost of $2,040. Parts 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 takes 24 work-hours for a labor cost
of $2,040. Parts cost $120 for a cost per helicopter of $2,160.
Repair interference between the rivet heads and skin. This
takes 10 work-hours for a labor cost of $850. No parts are 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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on
[[Page 9791]]
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):
2013-03-04 SCHWEIZER AIRCRAFT CORPORATION HELICOPTERS: Amendment 39-
17338; 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) Effective Date
This AD becomes effective March 19, 2013.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has been
accomplished previously.
(e) 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.
(f) Special Flight Permits
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 (e)(1) through (e)(3)
of this AD, a daily, pre-flight visual inspection is accomplished in
accordance with paragraph (e)(1) of this AD.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, NY ACO, 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 stephen.kowalski@faa.gov.
(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) Subject
Joint Aircraft Service Component (JASC) Code: 5302, Rotorcraft
tailboom.
(i) 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) Schweizer Service Bulletin DB-018.3, dated December 13,
2007.
(ii) Reserved.
(3) For Schweizer Aircraft Corporation 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
tsslibrary@sikorsky.com; or at https://www.sikorsky.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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on January 29, 2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2013-02583 Filed 2-11-13; 8:45 am]
BILLING CODE 4910-13-P
