Airworthiness Directives; Piper Aircraft, Inc., 38806-38809 [2014-16003]
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Federal Register / Vol. 79, No. 131 / Wednesday, July 9, 2014 / Proposed Rules
(p) New Requirement of This AD: Inspection,
Corrective Action and Replacement of
Fittings Replaced in Accordance With
Paragraph (l) of This AD
For airplanes on which a new carriage
attach fitting with the original part number
on the outboard foreflap was installed in
accordance with paragraph (l) of this AD: Do
the actions specified in paragraphs (p)(1) and
(p)(2) of this AD.
(1) Within 1,000 flight cycles after the
effective date of this AD, do a detailed
inspection for cracks and surface deviation
on all edges surfaces, and lug attachment
fastener holes, and a HFEC inspection for
cracks at the lug attachment fastener holes,
on the carriage attach fittings for the outboard
foreflaps, and do all applicable corrective
actions, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 727–57A0135, Revision 4,
dated September 26, 2012. Repeat the
inspection at intervals not to exceed 200
flight cycles. Do all applicable corrective
actions before further flight.
(2) Within 3,000 flight cycles or 3 years
after the effective date of this AD, replace the
fitting with a new, improved fitting in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
727–57A0135, Revision 4, dated September
26, 2012. Accomplishing the requirements of
this paragraph terminates the requirements of
paragraphs (g), (m), and (p)(1) of this AD for
that outboard foreflap only.
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(q) New Requirement of This AD: Inspection
and Corrective Actions on Fittings Replaced
According to Paragraph (k), (o), or (p) of
This AD on Outboard Foreflaps
For airplanes on which a new, improved
carriage attach fitting on the outboard
foreflap was replaced in accordance with the
requirements of paragraph (k), (o), or (p) of
this AD: Within 20,000 flight cycles after
installing that fitting, do a detailed
inspection for cracks and surface deviation
on all edges surfaces, and lug attachment
fastener holes, and a HFEC inspection for
cracks at the lug attachment fastener holes,
on the carriage attach fittings for the outboard
foreflaps, and do all applicable corrective
actions, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 727–57A0135, Revision 4,
dated September 26, 2012. Do all applicable
corrective actions before further flight.
Repeat the inspection thereafter at intervals
not to exceed 1,400 flight cycles.
Accomplishing the requirements of this
paragraph terminates the requirements of
paragraph (g) of this AD for outboard
foreflaps only.
(r) Retained Credit for Previously
Accomplished Service Bulletins
(1) This paragraph restates the credit
provided by paragraph (p) of AD 2005–14–
07, Amendment 39–14184 (70 FR 39647, July
11, 2005), with no changes. Installations
accomplished before August 15, 2005 (the
effective date of AD 2005–14–07), in
accordance with Boeing 727 Service Bulletin
57–59, dated September 2, 1965, are
acceptable for compliance with the
requirements of paragraph (j)(1) of this AD.
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(2) This paragraph restates the credit
provided by paragraph (q) of AD 2005–14–07,
Amendment 39–14184 (70 FR 39647, July 11,
2005), with no changes. Inspections and
modifications accomplished before August
15, 2005 (the effective date of AD 2005–14–
07), in accordance with Boeing Service
Bulletin 727–27–133, dated October 7, 1971,
are acceptable for compliance with the
requirements of paragraph (j)(2) of this AD.
DEPARTMENT OF TRANSPORTATION
(s) Alternative Methods of Compliance
(AMOCs)
Airworthiness Directives; Piper
Aircraft, Inc.
(1) The Manager, Los Angeles 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. 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 manager of the ACO, send it to the
attention of the person identified in
paragraph (u) of this AD. Information may be
emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov.
(2) 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2005–14–07,
Amendment 39–14184 (70 FR 39647, July 11,
2005), are approved as AMOCs for the
corresponding provisions of this AD.
AGENCY:
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0437; Directorate
Identifier: 2012–CE–036–AD]
RIN 2120–AA64
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
We propose to supersede an
existing airworthiness directive (AD)
that applies to certain Piper Aircraft,
Inc. Models PA–31P airplanes. AD 76–
06–09 currently requires repetitive
inspection of certain exhaust system
parts with replacement of parts mating
with the turbocharger, as necessary, and
allows installation of a certain tailpipe
v-band coupling as terminating action.
Since we issued AD 76–06–09, there
have been reports of exhaust system
failures, the manufacturer issued new
service information, and the tailpipe vband coupling used for terminating
action is obsolete. This proposed AD
would require the use of the new service
information and expand the scope of the
inspections of the turbocharger exhaust
system. We are proposing this AD to
correct the unsafe condition on these
products.
SUMMARY:
We must receive comments on
this proposed AD by August 25, 2014.
(t) Related Information
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
(1) For more information about this AD,
contact Chandraduth Ramdoss, Aerospace
11.43 and 11.45, by any of the following
Engineer, Airframe Branch, ANM–120L,
methods:
FAA, Los Angeles Aircraft Certification
• Federal eRulemaking Portal: Go to
Office, 3960 Paramount Boulevard,
https://www.regulations.gov. Follow the
Lakewood, CA 90712–4137; phone: 562–627–
instructions for submitting comments.
5239; fax: 562–627–5210; email
• Fax: 202–493–2251.
chandraduth.ramdoss@faa.gov.
• Mail: U.S. Department of
(2) For service information identified in
Transportation, Docket Operations, M–
this AD, contact Boeing Commercial
30, West Building Ground Floor, Room
Airplanes, Attention: Data & Services
W12–140, 1200 New Jersey Avenue SE.,
Management, P.O. Box 3707, MC 2H–65,
Washington, DC 20590.
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
• Hand Delivery: Deliver to Mail
Internet https://www.myboeingfleet.com. You address above between 9 a.m. and 5
may view this referenced service information p.m., Monday through Friday, except
at the FAA, Transport Aircraft Directorate,
Federal holidays.
1601 Lind Avenue SW., Renton, WA. For
For service information identified in
information on the availability of this
this AD, use the following contact
material at the FAA, call 425–227–1221.
information, as applicable, Piper
Issued in Renton, Washington, on June 27,
Aircraft, Inc., 2926 Piper Drive, Vero
2014.
Beach, Florida 32960; telephone: (772)
John P. Piccola,
567–4361; fax: (772) 978–6573; Internet:
Acting Manager, Transport Aircraft
www.piper.com/home/pages/
Directorate, Aircraft Certification Service.
Publications.cfm; or Lycoming Engines,
[FR Doc. 2014–15986 Filed 7–8–14; 8:45 am]
652 Oliver Street, Williamsport,
Pennsylvania 17701; telephone: (570)
BILLING CODE 4910–13–P
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Federal Register / Vol. 79, No. 131 / Wednesday, July 9, 2014 / Proposed Rules
323–6181; Internet: https://
www.lycoming.textron.com/support/
publications/. You may
review copies of the referenced service
information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA,
call (816) 329–4148.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0437; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Gary
Wechsler, Aerospace Engineer, Atlanta
Aircraft Certification Office, FAA, 1701
Columbia Avenue, College Park, Georgia
30337; telephone: (404) 474–5575; fax:
(404) 474–5606; email: gary.wechsler@
faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2014–0437; Directorate Identifier
2012–CE–036–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On October 17, 1978, we issued AD
76–06–09, Amendment 39–3325 (43 FR
50417, October 30, 1978), for certain
Piper Aircraft, Inc. Model PA–31P
airplanes. AD 76–06–09 requires
repetitive inspection of certain exhaust
system parts with replacement of parts
mating with the turbocharger, as
necessary, and allows installation of a
certain tailpipe v-band coupling as
terminating action. AD 76–06–09
resulted from reports of exhaust system
failure. We issued AD 76–06–09 to
preclude failure of the engine exhaust
system.
Actions Since Existing AD Was Issued
Since we issued AD 76–06–09,
Amendment 39–3325 (43 FR 50417,
October 30, 1978), there have been
exhaust system failures, the
manufacturer issued new service
information, and the tailpipe v-band
coupling used for terminating action is
obsolete.
Relevant Service Information
We reviewed Textron Lycoming
Mandatory Service Bulletin No. 393C,
dated November 26, 1976; Piper Aircraft
Corporation Service Bulletin No. 462A,
dated November 3, 1975; Piper Aircraft,
Inc. Service Bulletin No. 492A, dated
May 29, 2012; Piper Aircraft, Inc.
Service Bulletin No. 644E, dated May 9,
2012; Piper Aircraft Corporation kit part
number (P/N) 760 974, dated February
19, 1976; Piper Aircraft Corporation kit
P/N 761 045, dated February 19, 1976;
and Piper Aircraft Corporation kit P/N
761 047, dated February 19, 1976. The
service information describes
procedures for inspecting and replacing
parts of the turbocharger exhaust v-band
couplings, vibration isolators, and
support brackets.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would retain
certain requirements of AD 76–06–09,
Amendment 39–3325 (43 FR 50417,
October 30, 1978). This proposed AD
would require the use of the new service
information and expand the scope of the
inspections of the turbocharger exhaust
system.
Costs of Compliance
We estimate that this proposed AD
affects 85 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Cost per
product
Labor cost
Parts cost
Visual inspection .............................................
Review of maintenance records .....................
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Action
3 work-hours × $85 per hour = $255 .............
.5 work-hour × $85 per hour = $42.50 ...........
Not applicable .......
Not applicable .......
We have no way of determining how
much damage may be found on each
airplane during the proposed
inspection. The scope of damage on the
exhaust system could vary from airplane
to airplane due to the manner and
environments the airplane may operate.
We estimate the following costs to do
any necessary modification/installation/
replacement that would be required
based on the results of the proposed
inspection. We have no way of
$255
42.50
Cost on
U.S.
operators
$21,675
3,612.50
determining what damage may be found
or the number of airplanes that might
need these modification/installation/
replacements:
ON-CONDITION COSTS
Action
Labor cost
Modification of the exhaust pipe slip joint ....................
Installation of the bracket and clamp assembly ...........
5 work-hours × $85 per hour = $425 ...........................
5 work-hours × $85 per hour = $425 ...........................
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Parts cost
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$2,841
5,000
Cost per
product
$3,266
5,425
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Federal Register / Vol. 79, No. 131 / Wednesday, July 9, 2014 / Proposed Rules
ON-CONDITION COSTS—Continued
Action
Labor cost
Replacement of v-band coupling ..................................
2 work-hours × $85 per hour = $170 ...........................
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 proposed
regulation is within the scope of that
authority because it addresses an unsafe
condition that is likely to exist or
develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
76–06–09, Amendment 39–3325 (43 FR
50417, October 30, 1978), and adding
the following new AD:
■
Piper Aircraft, Inc.: Docket No. FAA–2014–
0437; Directorate Identifier 2012–CE–
036–AD.
Parts cost
Cost per
product
780
950
(a) Comments Due Date
The FAA must receive comments on this
AD action by August 25, 2014.
(b) Affected Ads
This AD supersedes AD 76–06–09,
Amendment 39–3325 (43 FR 50417, October
30, 1978).
(c) Applicability
This AD applies to Piper Aircraft, Inc.
Models PA–31P airplanes, serial numbers
31P–1 through 31P–80 and 31P–7300110
through 31P–7730012, that are certificated in
any category.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 78, Engine Exhaust.
(e) Unsafe Condition
This AD was prompted by reports of
exhaust system failures, new service
information issued by the manufacturer, and
the tailpipe v-band coupling used for
terminating action is obsolete. We are issuing
this AD to prevent the possibility of an inflight powerplant fire due to an exhaust
system failure.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection of Exhaust System
(1) Within the next 60 hours time-inservice (TIS) after the effective date of this
AD or within the next 6 months after the
effective date of this AD, whichever occurs
first, and repetitively thereafter at intervals
not to exceed 60 hours TIS or 6 months,
whichever occurs first, inspect the parts as
specified in table 1 of paragraph (g)(1) of this
AD, if installed.
TABLE 1 OF PARAGRAPH (g)(1) OF THIS AD: INSPECTION FOR PIPER AND LYCOMING EXHAUST SYSTEM PARTS
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Product/part nomenclature
Make
Model/part No.
Airplane ............................................................
Engine ..............................................................
Pipe, exhaust, right-rear ..................................
Pipe, exhaust, left-rear ....................................
Pipe, rear exhaust adapter ..............................
Tail pipe assembly, upper ...............................
Tail pipe assembly, lower ................................
V-band coupling ...............................................
V-band coupling ...............................................
Isolator (CA–3383–1) .......................................
Bracket—isolator, upper ..................................
Bracket—isolator, lower ...................................
Piper ...........................
Lycoming ....................
Lycoming ....................
Lycoming ....................
Lycoming ....................
Piper ...........................
Piper ...........................
Lycoming ....................
Piper ...........................
Piper ...........................
Piper ...........................
Piper ...........................
PA–31P ......................
TIGO–541–E series ...
78012 .........................
78008 .........................
LW–13027 ..................
46323–05 ...................
48788–05 ...................
LW–12093–5 ..............
555–366 or 557–369 ..
467–442 .....................
47014–02 ...................
47013–02 ...................
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With a light and mirror or other method
capable of achieving an equivalent visual
resolution, inspect for
the following conditions
Bulges, cracks, and exhaust leak stains.
Bulges, cracks, and exhaust leak stains.
Bulges, cracks, and exhaust leak stains.
Bulges, cracks, and exhaust leak stains.
Bulges, cracks, and exhaust leak stains.
Bulges, cracks, and exhaust leak stains.
Bulges, cracks, and exhaust leak stains.
Cracks and exhaust leak stains.
Cracks and exhaust leak stains.
Cracks, looseness, and distortion.
Cracks, looseness, and distortion.
Cracks, looseness, and distortion.
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Federal Register / Vol. 79, No. 131 / Wednesday, July 9, 2014 / Proposed Rules
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(2) If any damage is found in any
inspection required in paragraph (g)(1) of this
AD, before further fight, do the corrective
actions, as applicable, in paragraphs (g)(2)(i)
through (g)(2)(iv).
(i) Replace Piper v-band couplings
exhibiting cracks and/or exhaust leak stains
with airworthy parts following Piper Aircraft,
Inc. Mandatory Service Bulletin No. 644E,
dated May 9, 2012. Replace Lycoming v-band
couplings exhibiting cracks and/or exhaust
leak stains with airworthy parts following
Lycoming Service Instruction No. 1238B,
Revision B, dated January 6, 2010.
Note to paragraphs (g)(2)(i) and (h)(2)(iii):
During replacement of v-band couplings, we
recommend not opening the v-band coupling
more than the MINIMUM diameter necessary
to clear coupled flanges. It is recommended
to replace any locknuts and/or mating
couplings with airworthy parts when
locknuts do not exhibit a prevailing torque
when installed.
(ii) Replace Lycoming exhaust system parts
exhibiting bulges, cracks, and/or exhaust leak
stains with airworthy parts following
Lycoming Service Instruction No. 1320,
dated March 7, 1975; or Lycoming Service
Instruction No. 1391, dated October 5, 1979,
as applicable.
(iii) Replace Piper tail pipe assembly parts
exhibiting bulges, cracks, and/or exhaust leak
stains with airworthy parts following Piper
Aircraft, Inc. Mandatory Service Bulletin No.
644E, dated May 9, 2012.
(iv) Replace Piper isolators and brackets
exhibiting cracks, looseness and/or distortion
following Piper Aircraft, Inc. Service Bulletin
No. 462A, dated November 3, 1975; and
Service Bulletin No. 492A, dated May 29,
2012.
(h) Exhaust System Modifications
(1) Within the next 100 hours TIS after the
effective date of this AD or within the next
12 months after the effective date of this AD,
whichever occurs first, review the airplane
maintenance records to positively identify
whether the modifications described in
paragraphs (h)(1)(i) through (h)(1)(iii) of this
AD have been done.
(i) Exhaust pipe slip joint modification
following Piper Aircraft, Inc. Service Bulletin
No. 492A, dated May 29, 2012; and Lycoming
Service Bulletin No. 393C, dated November
26, 1976.
(ii) Installation of bracket and clamp
assembly following Piper Kit No. 760–974 as
specified in Piper Aircraft, Inc. Service
Bulletin No. 492A, dated May 29, 2012; or
Piper Aircraft, Inc. Service Bulletin 462A,
dated November 3, 1975.
(iii) Replacement of Piper v-band coupling,
part number 556–053, with Piper v-band
coupling, part number 557–369, following
Piper Aircraft, Inc. Mandatory Service
Bulletin No. 644E, dated May 9, 2012.
(2) If you cannot positively identify that
the modifications described in paragraphs
(h)(1)(i) through (h)(1)(iii) of this AD have
been done, before further flight, you must do
the modifications described in paragraphs
(h)(2)(i) through (h)(2)(ii), as applicable.
(i) Exhaust pipe slip joint modification
following Piper Aircraft, Inc. Service Bulletin
No. 492A, dated May 29, 2012, and Lycoming
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Service Bulletin SB 393C, dated November
26, 1976.
(ii) Installation of bracket and clamp
assembly following Piper Kit No. 760–974 as
specified in Piper Aircraft, Inc. Service
Bulletin No. 492A, dated May 29, 2012; or
Piper Aircraft, Inc. Service Bulletin 462A,
dated November 3, 1975.
(iii) Replacement of Piper v-band coupling,
part number 556–053, with Piper v-band
coupling, part number 557–369, following
Piper Aircraft, Inc. Mandatory Service
Bulletin No. 644E, dated May 9, 2012.
(i) Alternative Methods of Compliance
(AMOCs)
(1) 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. 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 manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
(2) 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.
(j) Related Information
(1) For more information about this AD,
contact Gary Wechsler, Aerospace Engineer,
Atlanta ACO, FAA, 1701 Columbia Avenue,
College Park, Georgia 30337; telephone: (404)
474–5575; fax: (404) 474–5606; email:
gary.wechsler@faa.gov.
(2) For service information identified in
this AD, contact FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA, call
(816) 329–4148.
Issued in Kansas City, Missouri, on June
24, 2014.
Timothy Smyth,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–16003 Filed 7–8–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF THE TREASURY
Internal Revenue Service
26 CFR Part 1
[REG–150760–13]
RIN 1545–BM05
Definition of Real Estate Investment
True Real Property; Correction
Internal Revenue Service (IRS),
Treasury.
ACTION: Correction to notice of proposed
rulemaking.
AGENCY:
This document contains
corrections to a notice of proposed
SUMMARY:
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38809
rulemaking and notice of public hearing
(REG–150760–13) that was published in
the Federal Register on Wednesday,
May 14, 2014 (79 FR 27508), that clarify
the definition of real property for
purposes of the real estate investment
trust provisions of the Internal Revenue
Code.
DATES: Written or electronic comments
and request for a public hearing for the
notice of proposed rulemaking and
notice of public hearing published at 79
FR 27508, May 14, 2014, are still being
accepted and must be received by
August 12, 2014.
FOR FURTHER INFORMATION CONTACT:
Andrea M. Hoffenson, at (202) 317–7053
(not a toll-free number).
SUPPLEMENTARY INFORMATION:
Background
The notice of proposed rulemaking
and notice of public hearing that is the
subject of this document is under
section 856 of the Internal Revenue
Code.
Need for Correction
As published, the notice of proposed
rulemaking and notice of public hearing
(REG–150760–13) contains errors that
are misleading and are in need of
clarification.
Correction to Publication
Accordingly, notice of proposed
rulemaking and notice of public
hearing, that is the subject of FR Doc.
2014–11115, is corrected as follows:
1. On page 27508, in the preamble,
first column, under the caption FOR
FURTHER INFORMATION CONTACT, second
line, the language ‘‘Andrea Hoffenson,
(202) 317–6842, or’’ is corrected to read
‘‘Andrea M. Hoffenson, (202) 317–7053,
or’’.
2. On page 27510, in the preamble,
second column, sixteenth line of the
second full paragraph, the language
‘‘investment credit contexts, this’’ is
corrected to read ‘‘investment tax credit
contexts, this’’.
3. On page 27510, in the preamble,
third column, eighth and ninth lines of
the first full paragraph, the language
‘‘depreciation, (prior) investment tax
credit, and FIRPTA contexts. In
drafting’’ is corrected to read
‘‘depreciation and (prior) investment tax
credit contexts. In drafting’’.
§ 1.856–10
[Corrected]
4. On page 27512, second column,
fourth line of paragraph (e)(2), the
language ‘‘is a distinct asset is based on
all of the’’ is corrected to read ‘‘is a
distinct asset is based on all the’’.
5. On page 27512, third column,
eighth line of paragraph (g) Example 1.
E:\FR\FM\09JYP1.SGM
09JYP1
]]>Agencies
[Federal Register Volume 79, Number 131 (Wednesday, July 9, 2014)]
[Proposed Rules]
[Pages 38806-38809]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-16003]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0437; Directorate Identifier: 2012-CE-036-AD]
RIN 2120-AA64
Airworthiness Directives; Piper Aircraft, Inc.
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to certain Piper Aircraft, Inc. Models PA-31P
airplanes. AD 76-06-09 currently requires repetitive inspection of
certain exhaust system parts with replacement of parts mating with the
turbocharger, as necessary, and allows installation of a certain
tailpipe v-band coupling as terminating action. Since we issued AD 76-
06-09, there have been reports of exhaust system failures, the
manufacturer issued new service information, and the tailpipe v-band
coupling used for terminating action is obsolete. This proposed AD
would require the use of the new service information and expand the
scope of the inspections of the turbocharger exhaust system. We are
proposing this AD to correct the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by August 25, 2014.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this AD, use the following
contact information, as applicable, Piper Aircraft, Inc., 2926 Piper
Drive, Vero Beach, Florida 32960; telephone: (772) 567-4361; fax: (772)
978-6573; Internet: www.piper.com/home/pages/Publications.cfm; or
Lycoming Engines, 652 Oliver Street, Williamsport, Pennsylvania 17701;
telephone: (570)
[[Page 38807]]
323-6181; Internet: https://www.lycoming.textron.com/support/publications/. You may review copies of the referenced
service information at the FAA, Small Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For information on the availability of
this material at the FAA, call (816) 329-4148.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0437; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Gary Wechsler, Aerospace Engineer,
Atlanta Aircraft Certification Office, FAA, 1701 Columbia Avenue,
College Park, Georgia 30337; telephone: (404) 474-5575; fax: (404) 474-
5606; email: gary.wechsler@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0437;
Directorate Identifier 2012-CE-036-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On October 17, 1978, we issued AD 76-06-09, Amendment 39-3325 (43
FR 50417, October 30, 1978), for certain Piper Aircraft, Inc. Model PA-
31P airplanes. AD 76-06-09 requires repetitive inspection of certain
exhaust system parts with replacement of parts mating with the
turbocharger, as necessary, and allows installation of a certain
tailpipe v-band coupling as terminating action. AD 76-06-09 resulted
from reports of exhaust system failure. We issued AD 76-06-09 to
preclude failure of the engine exhaust system.
Actions Since Existing AD Was Issued
Since we issued AD 76-06-09, Amendment 39-3325 (43 FR 50417,
October 30, 1978), there have been exhaust system failures, the
manufacturer issued new service information, and the tailpipe v-band
coupling used for terminating action is obsolete.
Relevant Service Information
We reviewed Textron Lycoming Mandatory Service Bulletin No. 393C,
dated November 26, 1976; Piper Aircraft Corporation Service Bulletin
No. 462A, dated November 3, 1975; Piper Aircraft, Inc. Service Bulletin
No. 492A, dated May 29, 2012; Piper Aircraft, Inc. Service Bulletin No.
644E, dated May 9, 2012; Piper Aircraft Corporation kit part number (P/
N) 760 974, dated February 19, 1976; Piper Aircraft Corporation kit P/N
761 045, dated February 19, 1976; and Piper Aircraft Corporation kit P/
N 761 047, dated February 19, 1976. The service information describes
procedures for inspecting and replacing parts of the turbocharger
exhaust v-band couplings, vibration isolators, and support brackets.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would retain certain requirements of AD 76-06-09,
Amendment 39-3325 (43 FR 50417, October 30, 1978). This proposed AD
would require the use of the new service information and expand the
scope of the inspections of the turbocharger exhaust system.
Costs of Compliance
We estimate that this proposed AD affects 85 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on
Action Labor cost Parts cost Cost per U.S.
product operators
----------------------------------------------------------------------------------------------------------------
Visual inspection................. 3 work-hours x $85 Not applicable.............. $255 $21,675
per hour = $255.
Review of maintenance records..... .5 work-hour x $85 Not applicable.............. 42.50 3,612.50
per hour = $42.50.
----------------------------------------------------------------------------------------------------------------
We have no way of determining how much damage may be found on each
airplane during the proposed inspection. The scope of damage on the
exhaust system could vary from airplane to airplane due to the manner
and environments the airplane may operate. We estimate the following
costs to do any necessary modification/installation/replacement that
would be required based on the results of the proposed inspection. We
have no way of determining what damage may be found or the number of
airplanes that might need these modification/installation/replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Modification of the exhaust pipe slip joint... 5 work-hours x $85 per hour = $2,841 $3,266
$425.
Installation of the bracket and clamp assembly 5 work-hours x $85 per hour = 5,000 5,425
$425.
[[Page 38808]]
Replacement of v-band coupling................ 2 work-hours x $85 per hour = 780 950
$170.
----------------------------------------------------------------------------------------------------------------
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 proposed regulation is
within the scope of that authority because it addresses an unsafe
condition that is likely to exist or develop on products identified in
this rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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 removing airworthiness directive (AD)
76-06-09, Amendment 39-3325 (43 FR 50417, October 30, 1978), and adding
the following new AD:
Piper Aircraft, Inc.: Docket No. FAA-2014-0437; Directorate
Identifier 2012-CE-036-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by August 25,
2014.
(b) Affected Ads
This AD supersedes AD 76-06-09, Amendment 39-3325 (43 FR 50417,
October 30, 1978).
(c) Applicability
This AD applies to Piper Aircraft, Inc. Models PA-31P airplanes,
serial numbers 31P-1 through 31P-80 and 31P-7300110 through 31P-
7730012, that are certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 78, Engine Exhaust.
(e) Unsafe Condition
This AD was prompted by reports of exhaust system failures, new
service information issued by the manufacturer, and the tailpipe v-
band coupling used for terminating action is obsolete. We are
issuing this AD to prevent the possibility of an in-flight
powerplant fire due to an exhaust system failure.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection of Exhaust System
(1) Within the next 60 hours time-in-service (TIS) after the
effective date of this AD or within the next 6 months after the
effective date of this AD, whichever occurs first, and repetitively
thereafter at intervals not to exceed 60 hours TIS or 6 months,
whichever occurs first, inspect the parts as specified in table 1 of
paragraph (g)(1) of this AD, if installed.
Table 1 of Paragraph (g)(1) of This AD: Inspection for Piper and Lycoming Exhaust System Parts
--------------------------------------------------------------------------------------------------------------------------------------------------------
With a light and mirror or other method capable of achieving
Product/part nomenclature Make Model/part No. an equivalent visual resolution, inspect for the following
conditions
--------------------------------------------------------------------------------------------------------------------------------------------------------
Airplane............................. Piper.................. PA-31P................. Bulges, cracks, and exhaust leak stains.
Engine............................... Lycoming............... TIGO-541-E series...... Bulges, cracks, and exhaust leak stains.
Pipe, exhaust, right-rear............ Lycoming............... 78012.................. Bulges, cracks, and exhaust leak stains.
Pipe, exhaust, left-rear............. Lycoming............... 78008.................. Bulges, cracks, and exhaust leak stains.
Pipe, rear exhaust adapter........... Lycoming............... LW-13027............... Bulges, cracks, and exhaust leak stains.
Tail pipe assembly, upper............ Piper.................. 46323-05............... Bulges, cracks, and exhaust leak stains.
Tail pipe assembly, lower............ Piper.................. 48788-05............... Bulges, cracks, and exhaust leak stains.
V-band coupling...................... Lycoming............... LW-12093-5............. Cracks and exhaust leak stains.
V-band coupling...................... Piper.................. 555-366 or 557-369..... Cracks and exhaust leak stains.
Isolator (CA-3383-1)................. Piper.................. 467-442................ Cracks, looseness, and distortion.
Bracket--isolator, upper............. Piper.................. 47014-02............... Cracks, looseness, and distortion.
Bracket--isolator, lower............. Piper.................. 47013-02............... Cracks, looseness, and distortion.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 38809]]
(2) If any damage is found in any inspection required in
paragraph (g)(1) of this AD, before further fight, do the corrective
actions, as applicable, in paragraphs (g)(2)(i) through (g)(2)(iv).
(i) Replace Piper v-band couplings exhibiting cracks and/or
exhaust leak stains with airworthy parts following Piper Aircraft,
Inc. Mandatory Service Bulletin No. 644E, dated May 9, 2012. Replace
Lycoming v-band couplings exhibiting cracks and/or exhaust leak
stains with airworthy parts following Lycoming Service Instruction
No. 1238B, Revision B, dated January 6, 2010.
Note to paragraphs (g)(2)(i) and (h)(2)(iii): During replacement
of v-band couplings, we recommend not opening the v-band coupling
more than the MINIMUM diameter necessary to clear coupled flanges.
It is recommended to replace any locknuts and/or mating couplings
with airworthy parts when locknuts do not exhibit a prevailing
torque when installed.
(ii) Replace Lycoming exhaust system parts exhibiting bulges,
cracks, and/or exhaust leak stains with airworthy parts following
Lycoming Service Instruction No. 1320, dated March 7, 1975; or
Lycoming Service Instruction No. 1391, dated October 5, 1979, as
applicable.
(iii) Replace Piper tail pipe assembly parts exhibiting bulges,
cracks, and/or exhaust leak stains with airworthy parts following
Piper Aircraft, Inc. Mandatory Service Bulletin No. 644E, dated May
9, 2012.
(iv) Replace Piper isolators and brackets exhibiting cracks,
looseness and/or distortion following Piper Aircraft, Inc. Service
Bulletin No. 462A, dated November 3, 1975; and Service Bulletin No.
492A, dated May 29, 2012.
(h) Exhaust System Modifications
(1) Within the next 100 hours TIS after the effective date of
this AD or within the next 12 months after the effective date of
this AD, whichever occurs first, review the airplane maintenance
records to positively identify whether the modifications described
in paragraphs (h)(1)(i) through (h)(1)(iii) of this AD have been
done.
(i) Exhaust pipe slip joint modification following Piper
Aircraft, Inc. Service Bulletin No. 492A, dated May 29, 2012; and
Lycoming Service Bulletin No. 393C, dated November 26, 1976.
(ii) Installation of bracket and clamp assembly following Piper
Kit No. 760-974 as specified in Piper Aircraft, Inc. Service
Bulletin No. 492A, dated May 29, 2012; or Piper Aircraft, Inc.
Service Bulletin 462A, dated November 3, 1975.
(iii) Replacement of Piper v-band coupling, part number 556-053,
with Piper v-band coupling, part number 557-369, following Piper
Aircraft, Inc. Mandatory Service Bulletin No. 644E, dated May 9,
2012.
(2) If you cannot positively identify that the modifications
described in paragraphs (h)(1)(i) through (h)(1)(iii) of this AD
have been done, before further flight, you must do the modifications
described in paragraphs (h)(2)(i) through (h)(2)(ii), as applicable.
(i) Exhaust pipe slip joint modification following Piper
Aircraft, Inc. Service Bulletin No. 492A, dated May 29, 2012, and
Lycoming Service Bulletin SB 393C, dated November 26, 1976.
(ii) Installation of bracket and clamp assembly following Piper
Kit No. 760-974 as specified in Piper Aircraft, Inc. Service
Bulletin No. 492A, dated May 29, 2012; or Piper Aircraft, Inc.
Service Bulletin 462A, dated November 3, 1975.
(iii) Replacement of Piper v-band coupling, part number 556-053,
with Piper v-band coupling, part number 557-369, following Piper
Aircraft, Inc. Mandatory Service Bulletin No. 644E, dated May 9,
2012.
(i) Alternative Methods of Compliance (AMOCs)
(1) 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. 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 manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD.
(2) 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.
(j) Related Information
(1) For more information about this AD, contact Gary Wechsler,
Aerospace Engineer, Atlanta ACO, FAA, 1701 Columbia Avenue, College
Park, Georgia 30337; telephone: (404) 474-5575; fax: (404) 474-5606;
email: gary.wechsler@faa.gov.
(2) For service information identified in this AD, contact FAA,
Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106.
For information on the availability of this material at the FAA,
call (816) 329-4148.
Issued in Kansas City, Missouri, on June 24, 2014.
Timothy Smyth,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-16003 Filed 7-8-14; 8:45 am]
BILLING CODE 4910-13-P
