[Federal Register: June 23, 2010 (Volume 75, Number 120)]
[Rules and Regulations]
[Page 35619-35622]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr23jn10-6]
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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.
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:
http://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 http://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: This e-mail address is being protected from spambots. You need JavaScript enabled to view it .
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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.
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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:
$1,768
$714 per V-band clamp.
$714 X 2 = $1,428.
2 work-hours per V-band clamp. 2
clamps per airplane: 4 work-hours X
$85 per hour = $340.
Total Cost Per Model
PA-32R-301T Airplane
Parts Cost
Labor Cost
We estimate the following costs to do the replacement for Model PA-32R-301T airplanes.
These airplanes have two V-band clamps installed:
•
$884
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
3
Labor Cost
Parts Cost
Total Cost Per Model
PA-46-350P Airplane
2 work-hours X $85 per hour = $170
$714

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
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
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. FAA amends § 39.13 by adding a new AD to read as follows:
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(b) None.
(e) To address this problem, you must do the following, unless already done:
Compliance
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.
Unsafe Condition
(d) Air Transport Association of America (ATA) Code 78: Engine Exhaust.
Subject
4622001 through 4622200 and 4636001 through 4636341.
PA–46–350P
AIRWORTHINESS DIRECTIVE
FAA
Aviation Safety
www.faa.gov/aircraft/safety/alerts/
www.gpoaccess.gov/fr/advanced.html
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
5
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.

Remove the spot welded V-band clamp(s) and
discard. Then, do either of the following
actions:
(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:
http://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
Material Incorporated by Reference
(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.
Alternative Methods of Compliance (AMOCs)
Not applicable.
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 time-
in-service (TIS) after
July 28, 2010 (the
effective date of this
AD), whichever occurs
first.
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(i) Install the new riveted clamp(s) and tighten
to an initial torque of 40 in. lbs. Tap the V-
band 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 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/Aeroquip P/N
55677-340M or
Lycoming P/N
40D21162-340M.
As of July 28, 2010
(the effective date of
this AD).

Issued in Kansas City, Missouri, on June 14, 2010.
Sandra J. Campbell,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
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this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_
of_federal_regulations/ibr_locations.html.