Airworthiness Directives; Piper Aircraft, Inc. Models PA-32R-301T and PA-46-350P Airplanes, 35619-35622 [2010-14991]
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Federal Register / Vol. 75, No. 120 / Wednesday, June 23, 2010 / Rules and Regulations
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lower spar caps following paragraph (j)(2) of
this AD to terminate the repetitive eddy
current inspections required in paragraph
(j)(4)(i) of this AD.
(5) If you have modified your airplane
following paragraph (j)(1) of this AD prior to
3,200 hours TIS, you must do the following
to reach the extended 8,000-hour TIS safe
life:
(i) If you did not cold work the outboard
two fastener holes in both the left and right
hand lower spar caps following paragraph
(j)(2) of this AD, you must do the repetitive
eddy current inspections following paragraph
(j)(4)(i) of this AD until you accumulate 4,800
hours TIS after the modification on the wing
spar lower cap. Upon accumulation of 4,800
hours TIS after the modification on the wing
spar lower cap, do the repetitive eddy current
inspections at intervals not to exceed every
600 hours TIS until you reach the extended
safe life of 8,000-hour TIS.
(ii) If you did cold work the outboard two
fastener holes in both the left and right hand
lower spar caps following paragraph (j)(2) of
this AD, upon accumulation of 4,800 hours
TIS after the modification on the wing spar
lower cap do the repetitive eddy current
inspections at intervals not to exceed every
600 hours TIS until you reach the 8,000-hour
TIS safe life.
(6) For the initial and repetitive eddy
current inspections required in paragraphs
(j)(3), (j)(4)(i), (j)(5)(i) and (j)(5)(ii) of this AD,
follow the instructions as specified in Snow
Engineering Co. Process Specification #197,
page 1, revised June 4, 2002; pages 2 through
4, dated February 23, 2001; and page 5, dated
May 3, 2002. For any cracks found, follow
the instructions for repair or replacement as
specified in paragraph (g) of this AD.
(k) If any cracks are found as a result of any
inspection required in paragraphs (e)(2),
(j)(3), (j)4)(i), (j)(5)(i), and (j)(5)(ii) of this AD,
report any cracks you find within 10 days
after the cracks are found or within 10 days
after April 21, 2006 (the effective date of AD
2006–08–09), whichever occurs later.
(1) Include in your report the aircraft SN,
aircraft hours TIS, wing spar cap hours TIS,
crack location and size, corrective action
taken, and a point of contact name and phone
number. Send your report to Andy McAnaul,
Aerospace Engineer, ASW–150 (c/o MIDO–
43), 10100 Reunion Place, Suite 650, San
Antonio, Texas 78216; telephone: (210) 308–
3365; facsimile: (210) 308–3370.
(2) The Office of Management and Budget
(OMB) approved the information collection
requirements contained in this regulation
under the provisions of the Paperwork
Reduction Act and assigned OMB Control
Number 2120–0056.
Special Permit Flight
(l) Under 14 CFR part 39.23, we are
allowing special flight permits for the
purpose of compliance with this AD under
the following conditions:
(1) Only operate in day visual flight rules
(VFR).
(2) Ensure that the hopper is empty.
(3) Limit airspeed to 135 miles per hour
(mph) indicated airspeed (IAS).
(4) Avoid any unnecessary g-forces.
(5) Avoid areas of turbulence.
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16:08 Jun 22, 2010
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(6) Plan the flight to follow the most direct
route.
Alternative Methods of Compliance
(AMOCs)
(m) The Manager, Fort Worth Airplane
Certification Office, ASW–150, FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN: Andy
McAnaul, Aerospace Engineer, ASW–150,
FAA San Antonio MIDO–43, 10100 Reunion
Pl., Ste. 650, San Antonio, Texas 78216;
telephone: (210) 308–3365; fax: (210) 308–
3370. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(n) AMOCs approved for AD 2006–08–09
are not approved for this AD.
Related Information
(o) To get copies of the service information
referenced in this AD, contact Air Tractor,
Inc., P.O. Box 485, Olney, Texas 76374;
telephone: (940) 564–5616; fax: (940) 564–
5612; E-mail: airmail@airtractor.com;
Internet: https://www.airtractor.com. To view
the AD docket, go to U.S. Department of
Transportation, Docket Operations, M–30,
West Building Ground Floor, Room W12–
140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, or on the Internet at
https://www.regulations.gov.
Material Incorporated by Reference
(p) You must use Snow Engineering Co.
Process Specification #197, page 1, revised
June 4, 2002; pages 2 through 4, dated
February 23, 2001; and page 5, dated May 3,
2002; Snow Engineering Co. Process
Specification #204, Rev. C, dated November
16, 2004; Snow Engineering Co. Service
Letter #215, page 5, titled ‘‘802 Spar
Inspection Holes and Vent Tube Mod,’’ dated
November 19, 2003; Snow Engineering Co.
Service Letter #240, dated September 30,
2004; Snow Engineering Co. Drawing
Number 20975, Sheet 2, Rev. A, dated
September 1, 2004; Snow Engineering Co.
Drawing Number 20975, Sheet 3, dated
January 6, 2005; and Snow Engineering Co.
Drawing 20995, Sheet 2, Rev. C, dated
September 28, 2004, to do the actions
required by this AD, unless the AD specifies
otherwise.
(1) On April 21, 2006 (71 FR 19994, April
19, 2006), the Director of the Federal Register
approved the incorporation by reference of
Snow Engineering Co. Process Specification
#197, page 1, revised June 4, 2002; pages 2
through 4, dated February 23, 2001; and page
5, dated May 3, 2002; Snow Engineering Co.
Process Specification #204, Rev. C, dated
November 16, 2004; Snow Engineering Co.
Service Letter #215, page 5, titled ‘‘802 Spar
Inspection Holes and Vent Tube Mod,’’ dated
November 19, 2003; Snow Engineering Co.
Service Letter #240, dated September 30,
2004; Snow Engineering Co. Drawing
Number 20975, Sheet 2, Rev. A, dated
September 1, 2004; Snow Engineering Co.
Drawing Number 20975, Sheet 3, dated
January 6, 2005; and Snow Engineering Co.
Drawing 20995, Sheet 2, Rev. C, dated
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35619
September 28, 2004, under 5 U.S.C. 552(a)
and 1 CFR part 51.
(2) For service information identified in
this AD, contact Air Tractor, Inc., P.O. Box
485, Olney, Texas 76374; telephone: (940)
564–5616; fax: (940) 564–5612; E-mail:
airmail@airtractor.com; Internet: https://
www.airtractor.com.
(3) You may review copies of the service
information incorporated by reference for
this AD at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas
City, Missouri 64106. For information on the
availability of this material at the Central
Region, call (816) 329–3768.
(4) You may also review copies of the
service information incorporated by reference
for this AD 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/
code_of_federal_regulations/
ibr_locations.html.
Issued in Kansas City, Missouri on June 15,
2010.
Sandra J. Campbell,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–14990 Filed 6–22–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0122; Directorate
Identifier 2009–CE–067–AD; Amendment
39–16338; AD 2010–13–07]
RIN 2120–AA64
Airworthiness Directives; Piper
Aircraft, Inc. Models PA–32R–301T and
PA–46–350P Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Piper Aircraft, Inc. Models PA–32R–
301T and PA–46–350P airplanes. This
AD requires you to replace any spotwelded, V-band exhaust coupling with
a riveted, V-band exhaust coupling. This
AD results from reports that spotwelded, V-band exhaust couplings are
failing. We are issuing this AD to
prevent failure of the V-band exhaust
coupling, which could cause the
exhaust pipe to detach from the
turbocharger. This failure could result
in release of high-temperature gases
inside the engine compartment and
possibly cause an in-flight fire. An inflight fire could lead to loss of control.
DATES: This AD becomes effective on
July 28, 2010.
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Federal Register / Vol. 75, No. 120 / Wednesday, June 23, 2010 / Rules and Regulations
On July 28, 2010, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: To get the service
information identified in this AD,
contact Lycoming, 652 Oliver Street,
Williamsport, PA 17701; telephone:
(570) 323–6181; fax: (570) 327–7101;
Internet: https://www.lycoming.com.
To view the AD docket, go to U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590, or on the Internet at https://
www.regulations.gov. The docket
number is FAA–2010–0122; Directorate
Identifier; 2009–CE–067–AD.
FOR FURTHER INFORMATION CONTACT:
Darby Mirocha, Aerospace Engineer,
FAA, Atlanta Aircraft Certification
Office (ACO), 1701 Columbia Avenue,
College Park, Georgia 30337; telephone:
(404) 474–5573; fax: (404) 474–5606; email: darby.mirocha@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On February 9, 2010, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an AD that would apply to
Piper Aircraft, Inc. Models PA–32R–
301T and PA–46–350P airplanes. This
proposal was published in the Federal
Register as a notice of proposed
rulemaking (NPRM) on February 19,
2010 (75 FR 7407). The NPRM proposed
to require replacing any spot-welded, Vband exhaust coupling with a riveted,
V-band exhaust coupling.
Comments
We provided the public the
opportunity to participate in developing
this AD. We received one comment in
support of the AD. The following
presents the additional comments
received on the proposal and FAA’s
response to each comment:
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Comment Issue No. 1: Incorporate
Additional Lycoming Service
Instructions
Gerald Stroum and Gerald Blank
suggest that Lycoming Service
Instructions 1448 and 1238B be
incorporated into the AD because they
contain helpful instructions and
procedures for the proper installation of
exhaust components.
Mr. Stroum also suggests that adding
a requirement to free all slip joints when
replacing the clamp will assist in
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16:08 Jun 22, 2010
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enabling the exhaust system to be
installed and aligned correctly.
The commenters state that these types
of clamps (spot welded) have been used
with a long history of success in the
automotive diesel industry, and the
issue is more readily solved by proper
installation than by a change in clamp
design. Their experience shows proper
installation, torque techniques, and pretorque alignments of components go a
long way in preventing clamp failures
down the road.
We agree with the commenters that
proper installation and maintenance,
which includes freeing the slip joint to
ensure proper operation, plays a key
role in the longevity and proper
function of the exhaust system.
The data in Lycoming Service
Instruction 1448 contains references to
part numbers that are not the subject of
this AD; therefore, we have determined
including reference to that service
instruction would provide confusing
and contradictory information.
However, we agree Lycoming Service
Instruction 1238B provides beneficial
information about the proper assembly
and torque procedures of V-band
clamps.
We will change the final rule AD
action to incorporate by reference
Lycoming Service Instruction 1238B.
We will not change the final rule AD
action to incorporate reference to
Lycoming Service Instruction 1448.
Comment Issue No. 2: Correct the Cost
of Compliance
Gerald Blank, Ed Novak, and
Shoreline Aviation, Inc. state that the
Cost of Compliance section in the
proposed AD incorrectly reflects the
number of V-band clamps installed on
the airplanes affected by this AD.
All three commenters suggest
changing the Cost of Compliance section
to accurately reflect the number of Vband clamps installed on each affected
model airplane.
We agree with the commenters. After
further research, we determined that
Model PA–32R–301T (Saratoga II TC)
has two of the affected V–Band clamps
installed, and Model PA–46–350P
(Mirage) has one. We will change the
final rule AD action to incorporate this
change.
Comment Issue No. 3: The AD Should
Be Written Against the V-Band Clamp
Instead of the Airplanes
Ed Novak and Shoreline Aviation,
Inc. both suggest that since identical
clamps have failed on other airplane
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models that prompted two previous ADs
(AD 2000–11–04 for Commander
Aircraft Company (Commander) Model
114TC airplanes and AD 2004–23–17 for
Mooney Airplane Company, Inc.,
(Mooney) Model M20M airplanes), this
AD should be written against the
Lycoming engine/clamp combination
restricting its use on any exhaust
system.
Shoreline Aviation, Inc. states the
incident that prompted this AD would
not have happened if the previous ADs
had been written against the clamp and
not the airplanes.
Based on the specific reports the FAA
has received to date regarding Piper
Aircraft, Inc. Models PA–32R–301T and
PA–46–350P airplanes and with the
subsequent issuance of Piper Service
Bulletin 1180A, the FAA initiated this
AD action against certain Piper
airplanes only.
We will continue to collect and
analyze all available data to determine
whether the condition exists in any
other airplane configurations. We may
take additional rulemaking action in the
future to address either additional
airplane configurations or the engine
design depending on the FAA’s
determination of all existing and future
information received.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed except for
incorporating reference to Lycoming
Service Instruction 1238B and updating
the Cost of Compliance section to
accurately reflect how many V-band
clamps each model of the airplanes
affected by this AD has installed, and
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 596
airplanes in the U.S. registry provided
they have the affected V-band exhaust
coupling installed.
We estimate the following costs to do
the replacement for Model PA–46–350P
airplanes. These airplanes have one Vband clamp installed:
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Federal Register / Vol. 75, No. 120 / Wednesday, June 23, 2010 / Rules and Regulations
Labor cost
Parts cost
2 work-hours × $85 per hour = $170 ......................................................................................................................
We estimate the following costs to do
the replacement for Model PA–32R–
Total cost
per model PA–
32R–301T
airplane
2 work-hours per V-band clamp. 2 clamps per airplane: 4 work-hours × $85
per hour = $340.
$714 per V-band clamp. $714 × 2 = $1,428. .....
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We have determined that 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;
VerDate Mar<15>2010
16:08 Jun 22, 2010
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 a summary of the costs
to comply with this AD (and other
information as included in the
Regulatory Evaluation) and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2010–0122;
Directorate Identifier 2009–CE–067–AD’’
in your request.
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 Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
■
Regulatory Findings
Jkt 220001
$884
301T airplanes. These airplanes have
two V-band clamps installed:
Parts cost
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 AD.
Total cost
per model
PA–46–350P
airplane
$714
Labor cost
Authority for This Rulemaking
35621
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]
Frm 00017
Fmt 4700
2010–13–07 Piper Aircraft, Inc.:
Amendment 39–16338; Docket No.
FAA–2010–0122; Directorate Identifier
2009–CE–067–AD.
Effective Date
(a) This AD becomes effective on July 28,
2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following
airplane models and serial numbers that are
certificated in any category:
Model
Serial numbers
PA–32R–301T
PA–46–350P ....
3257001 through 3257311.
4622001 through 4622200
and 4636001 through
4636341.
Subject
(d) Air Transport Association of America
(ATA) Code 78: Engine Exhaust.
Unsafe Condition
This AD is the result of reports that spotwelded, V-band exhaust couplings are
failing. We are issuing this AD to prevent
failure of the V-band exhaust coupling,
which could cause the exhaust pipe to detach
from the turbocharger. This failure could
result in release of high-temperature gases
inside the engine compartment and possibly
cause an in-flight fire. An in-flight fire could
lead to loss of control.
Compliance
2. FAA amends § 39.13 by adding a
new AD to read as follows:
■
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$1,768
Sfmt 4700
(e) To address this problem, you must do
the following, unless already done:
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35622
Federal Register / Vol. 75, No. 120 / Wednesday, June 23, 2010 / Rules and Regulations
Actions
Compliance
Procedures
(1) Replace V-band exhaust couplings, part
number (P/N) Lycoming 40D21162–340M or
Eaton/Aeroquip 55677–340M with an improved
design
Eaton/Aeroquip
P/N
NH1009399–10 or Lycoming P/N 40D23255–
340M.
At the next regularly scheduled maintenance
event after July 28, 2010 (the effective date
of this AD) or within the next 25 hours timein-service (TIS) after July 28, 2010 (the effective date of this AD), whichever occurs
first.
(2) Do not install any Eaton/Aeroquip P/N
55677–340M or Lycoming P/N 40D21162–
340M.
As of July 28, 2010 (the effective date of this
AD).
Remove the spot welded V-band clamp(s)
and discard. Then, do either of the following
actions:
(i) Install the new riveted clamp(s) and tighten
to an initial torque of 40 in. lbs. Tap the Vband clamp(s) around its circumference
with a rubber mallet to equalize band tension. Retorque the clamp(s) to 60 in. lbs.
and again tap the clamp(s) around its circumference. Retorque the clamp(s) to a 60
in. lbs. final torque and re-safety wire the Vband coupling(s); or
(ii) Install the new riveted clamp(s) follow
Lycoming Service Instruction No. 1238B,
dated January 6, 2010, and re-safety wire
the V-band coupling(s).
Not applicable.
Alternative Methods of Compliance
(AMOCs)
(f) The Manager, Atlanta Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN: Darby
Mirocha, Aerospace Engineer, FAA, Atlanta
ACO, 1701 Columbia Avenue, College Park,
Georgia 30337; telephone: (404) 474–5573;
fax: (404) 474–5606. Before using any
approved AMOC on any airplane to which
the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking
a PI, your local FSDO.
jlentini on DSKJ8SOYB1PROD with RULES
Material Incorporated by Reference
(g) You must use Lycoming Service
Instruction No. 1238B, dated January 6, 2010,
or the procedures specified in paragraph
(e)(1) of this AD to do the actions required
by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Lycoming, 652 Oliver Street,
Williamsport, PA 17701; telephone: (570)
323–6181; fax: (570) 327–7101; Internet:
https://www.lycoming.com.
(3) You may review copies of the service
information incorporated by reference for
this AD at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas
City, Missouri 64106. For information on the
availability of this material at the Central
Region, call (816) 329–3768.
(4) You may also review copies of the
service information incorporated by reference
for this AD 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/
code_of_federal_regulations/
ibr_locations.html.
VerDate Mar<15>2010
16:08 Jun 22, 2010
Jkt 220001
Issued in Kansas City, Missouri, on June
14, 2010.
Sandra J. Campbell,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–14991 Filed 6–22–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0273; Directorate
Identifier 2009–NM–134–AD; Amendment
39–16335; AD 2010–13–04]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Model DHC–8–400 Series
Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
Two in-service incidents have been
reported on DHC–8 Series 400 aircraft in
which the nose landing gear (NLG) trailing
arm pivot pin retention bolt (part number
NAS6204–13D) was damaged. One incident
involved the left hand NLG tire which
ruptured on take-off. Investigation
determined that the retention bolt failure was
due to repeated contact of the castellated nut
with the towing device including both the
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Fmt 4700
Sfmt 4700
towbar and the towbarless rigs. The loss of
the retention bolt allowed the pivot pin to
migrate from its normal position and resulted
in contact with and rupture of the tire. The
loss of the pivot pin could compromise
retention of the trailing arm and could result
in a loss of directional control due to loss of
nose wheel steering. The loss of an NLG tire
or the loss of directional control could
adversely affect the aircraft during take off or
landing.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective July
28, 2010.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 28, 2010.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Richard Beckwith, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
New York 11590; telephone (516) 228–
7302; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on March 23, 2010 (75 FR
13682). That NPRM proposed to correct
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]]>Agencies
[Federal Register Volume 75, Number 120 (Wednesday, June 23, 2010)]
[Rules and Regulations]
[Pages 35619-35622]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-14991]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0122; Directorate Identifier 2009-CE-067-AD;
Amendment 39-16338; AD 2010-13-07]
RIN 2120-AA64
Airworthiness Directives; Piper Aircraft, Inc. Models PA-32R-301T
and PA-46-350P Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Piper Aircraft, Inc. Models PA-32R-301T and PA-46-350P airplanes. This
AD requires you to replace any spot-welded, V-band exhaust coupling
with a riveted, V-band exhaust coupling. This AD results from reports
that spot-welded, V-band exhaust couplings are failing. We are issuing
this AD to prevent failure of the V-band exhaust coupling, which could
cause the exhaust pipe to detach from the turbocharger. This failure
could result in release of high-temperature gases inside the engine
compartment and possibly cause an in-flight fire. An in-flight fire
could lead to loss of control.
DATES: This AD becomes effective on July 28, 2010.
[[Page 35620]]
On July 28, 2010, the Director of the Federal Register approved the
incorporation by reference of certain publications listed in this AD.
ADDRESSES: To get the service information identified in this AD,
contact Lycoming, 652 Oliver Street, Williamsport, PA 17701; telephone:
(570) 323-6181; fax: (570) 327-7101; Internet: https://www.lycoming.com.
To view the AD docket, go to U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue, SE., Washington, DC 20590, or on the Internet at
https://www.regulations.gov. The docket number is FAA-2010-0122;
Directorate Identifier; 2009-CE-067-AD.
FOR FURTHER INFORMATION CONTACT: Darby Mirocha, Aerospace Engineer,
FAA, Atlanta Aircraft Certification Office (ACO), 1701 Columbia Avenue,
College Park, Georgia 30337; telephone: (404) 474-5573; fax: (404) 474-
5606; e-mail: darby.mirocha@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On February 9, 2010, we issued a proposal to amend part 39 of the
Federal Aviation Regulations (14 CFR part 39) to include an AD that
would apply to Piper Aircraft, Inc. Models PA-32R-301T and PA-46-350P
airplanes. This proposal was published in the Federal Register as a
notice of proposed rulemaking (NPRM) on February 19, 2010 (75 FR 7407).
The NPRM proposed to require replacing any spot-welded, V-band exhaust
coupling with a riveted, V-band exhaust coupling.
Comments
We provided the public the opportunity to participate in developing
this AD. We received one comment in support of the AD. The following
presents the additional comments received on the proposal and FAA's
response to each comment:
Comment Issue No. 1: Incorporate Additional Lycoming Service
Instructions
Gerald Stroum and Gerald Blank suggest that Lycoming Service
Instructions 1448 and 1238B be incorporated into the AD because they
contain helpful instructions and procedures for the proper installation
of exhaust components.
Mr. Stroum also suggests that adding a requirement to free all slip
joints when replacing the clamp will assist in enabling the exhaust
system to be installed and aligned correctly.
The commenters state that these types of clamps (spot welded) have
been used with a long history of success in the automotive diesel
industry, and the issue is more readily solved by proper installation
than by a change in clamp design. Their experience shows proper
installation, torque techniques, and pre-torque alignments of
components go a long way in preventing clamp failures down the road.
We agree with the commenters that proper installation and
maintenance, which includes freeing the slip joint to ensure proper
operation, plays a key role in the longevity and proper function of the
exhaust system.
The data in Lycoming Service Instruction 1448 contains references
to part numbers that are not the subject of this AD; therefore, we have
determined including reference to that service instruction would
provide confusing and contradictory information. However, we agree
Lycoming Service Instruction 1238B provides beneficial information
about the proper assembly and torque procedures of V-band clamps.
We will change the final rule AD action to incorporate by reference
Lycoming Service Instruction 1238B. We will not change the final rule
AD action to incorporate reference to Lycoming Service Instruction
1448.
Comment Issue No. 2: Correct the Cost of Compliance
Gerald Blank, Ed Novak, and Shoreline Aviation, Inc. state that the
Cost of Compliance section in the proposed AD incorrectly reflects the
number of V-band clamps installed on the airplanes affected by this AD.
All three commenters suggest changing the Cost of Compliance
section to accurately reflect the number of V-band clamps installed on
each affected model airplane.
We agree with the commenters. After further research, we determined
that Model PA-32R-301T (Saratoga II TC) has two of the affected V-Band
clamps installed, and Model PA-46-350P (Mirage) has one. We will change
the final rule AD action to incorporate this change.
Comment Issue No. 3: The AD Should Be Written Against the V-Band Clamp
Instead of the Airplanes
Ed Novak and Shoreline Aviation, Inc. both suggest that since
identical clamps have failed on other airplane models that prompted two
previous ADs (AD 2000-11-04 for Commander Aircraft Company (Commander)
Model 114TC airplanes and AD 2004-23-17 for Mooney Airplane Company,
Inc., (Mooney) Model M20M airplanes), this AD should be written against
the Lycoming engine/clamp combination restricting its use on any
exhaust system.
Shoreline Aviation, Inc. states the incident that prompted this AD
would not have happened if the previous ADs had been written against
the clamp and not the airplanes.
Based on the specific reports the FAA has received to date
regarding Piper Aircraft, Inc. Models PA-32R-301T and PA-46-350P
airplanes and with the subsequent issuance of Piper Service Bulletin
1180A, the FAA initiated this AD action against certain Piper airplanes
only.
We will continue to collect and analyze all available data to
determine whether the condition exists in any other airplane
configurations. We may take additional rulemaking action in the future
to address either additional airplane configurations or the engine
design depending on the FAA's determination of all existing and future
information received.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed
except for incorporating reference to Lycoming Service Instruction
1238B and updating the Cost of Compliance section to accurately reflect
how many V-band clamps each model of the airplanes affected by this AD
has installed, and minor editorial corrections. We have determined that
these minor corrections:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 596 airplanes in the U.S. registry
provided they have the affected V-band exhaust coupling installed.
We estimate the following costs to do the replacement for Model PA-
46-350P airplanes. These airplanes have one V-band clamp installed:
[[Page 35621]]
------------------------------------------------------------------------
Total cost per
model PA-46-
Labor cost Parts cost 350P airplane
------------------------------------------------------------------------
2 work-hours x $85 per hour = $170...... $714 $884
------------------------------------------------------------------------
We estimate the following costs to do the replacement for Model
PA-32R-301T airplanes. These airplanes have two V-band clamps
installed:
----------------------------------------------------------------------------------------------------------------
Total cost per
model PA-32R-
Labor cost Parts cost 301T airplane
----------------------------------------------------------------------------------------------------------------
2 work-hours per V-band clamp. 2 clamps per airplane: 4 $714 per V-band clamp. $714 x 2 = $1,768
work-hours x $85 per hour = $340. $1,428..
----------------------------------------------------------------------------------------------------------------
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 AD.
Regulatory Findings
We have determined that 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 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 a summary of the costs to comply with this AD (and
other information as included in the Regulatory Evaluation) and placed
it in the AD Docket. You may get a copy of this summary by sending a
request to us at the address listed under ADDRESSES. Include ``Docket
No. FAA-2010-0122; Directorate Identifier 2009-CE-067-AD'' in your
request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (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. FAA amends Sec. 39.13 by adding a new AD to read as follows:
2010-13-07 Piper Aircraft, Inc.: Amendment 39-16338; Docket No. FAA-
2010-0122; Directorate Identifier 2009-CE-067-AD.
Effective Date
(a) This AD becomes effective on July 28, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following airplane models and serial
numbers that are certificated in any category:
------------------------------------------------------------------------
Model Serial numbers
------------------------------------------------------------------------
PA-32R-301T...................... 3257001 through 3257311.
PA-46-350P....................... 4622001 through 4622200 and 4636001
through 4636341.
------------------------------------------------------------------------
Subject
(d) Air Transport Association of America (ATA) Code 78: Engine
Exhaust.
Unsafe Condition
This AD is the result of reports that spot-welded, V-band
exhaust couplings are failing. We are issuing this AD to prevent
failure of the V-band exhaust coupling, which could cause the
exhaust pipe to detach from the turbocharger. This failure could
result in release of high-temperature gases inside the engine
compartment and possibly cause an in-flight fire. An in-flight fire
could lead to loss of control.
Compliance
(e) To address this problem, you must do the following, unless
already done:
[[Page 35622]]
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Replace V-band exhaust At the next Remove the spot
couplings, part number (P/ regularly scheduled welded V-band
N) Lycoming 40D21162-340M maintenance event clamp(s) and
or Eaton/Aeroquip 55677- after July 28, 2010 discard. Then, do
340M with an improved (the effective date either of the
design Eaton/Aeroquip P/N of this AD) or following actions:
NH1009399-10 or Lycoming P/ within the next 25 (i) Install the new
N 40D23255-340M. hours time-in- riveted clamp(s)
service (TIS) after and tighten to an
July 28, 2010 (the initial torque of
effective date of 40 in. lbs. Tap the
this AD), whichever V-band clamp(s)
occurs first. around its
circumference with
a rubber mallet to
equalize band
tension. Retorque
the clamp(s) to 60
in. lbs. and again
tap the clamp(s)
around its
circumference.
Retorque the
clamp(s) to a 60
in. lbs. final
torque and re-
safety wire the V-
band coupling(s);
or
(ii) Install the new
riveted clamp(s)
follow Lycoming
Service Instruction
No. 1238B, dated
January 6, 2010,
and re-safety wire
the V-band
coupling(s).
(2) Do not install any Eaton/ As of July 28, 2010 Not applicable.
Aeroquip P/N 55677-340M or (the effective date
Lycoming P/N 40D21162-340M. of this AD).
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Atlanta Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. Send information to
ATTN: Darby Mirocha, Aerospace Engineer, FAA, Atlanta ACO, 1701
Columbia Avenue, College Park, Georgia 30337; telephone: (404) 474-
5573; fax: (404) 474-5606. Before using any approved AMOC on any
airplane to which the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
Material Incorporated by Reference
(g) You must use Lycoming Service Instruction No. 1238B, dated
January 6, 2010, or the procedures specified in paragraph (e)(1) of
this AD to do the actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Lycoming, 652 Oliver Street, Williamsport, PA 17701; telephone:
(570) 323-6181; fax: (570) 327-7101; Internet: https://www.lycoming.com.
(3) You may review copies of the service information
incorporated by reference for this AD at the FAA, Central Region,
Office of the Regional Counsel, 901 Locust, Kansas City, Missouri
64106. For information on the availability of this material at the
Central Region, call (816) 329-3768.
(4) You may also review copies of the service information
incorporated by reference for this AD 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/code_of_federal_regulations/ibr_locations.html.
Issued in Kansas City, Missouri, on June 14, 2010.
Sandra J. Campbell,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-14991 Filed 6-22-10; 8:45 am]
BILLING CODE 4910-13-P
