[Federal Register Volume 77, Number 181 (Tuesday, September 18, 2012)]
[Proposed Rules]
[Pages 57534-57536]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-22953]
[[Page 57534]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0983; Directorate Identifier 2012-CE-001-AD;]
RIN 2120-AA64
Airworthiness Directives; Piper Aircraft, Inc. Airplanes
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 all Piper Aircraft, Inc. Models PA-31, PA-31-325,
and PA-31-350 airplanes. The existing AD currently requires a detailed
repetitive inspection of the exhaust system downstream of the
turbochargers and repair or replacement of parts as necessary. Since we
issued that AD, forced landings of aircraft have occurred due to
exhaust system failures upstream of aircraft turbochargers and between
recurring detailed inspections. This proposed AD would require both
visual and detailed repetitive inspections, expanding the inspection
scope to include the entirety of each airplane exhaust system. We are
proposing this AD to prevent the possibility of an inflight powerplant
fire due to an exhaust system failure.
DATES: We must receive comments on this proposed AD by November 2,
2012.
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 http://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 proposed AD, contact
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. 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 http://www.regulations.gov; 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: [email protected].
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-2012-0983;
Directorate Identifier 2012-CE-001-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 http://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 April 7, 1986, AD 82-16-05 R1, amendment 39-5278 (51 FR 11707-
01, April 7, 1986), was published in the Federal Register for certain
Piper Aircraft, Inc. Models PA-31, PA-31-325, and PA-31-350 airplanes.
That AD requires a detailed repetitive inspection of the exhaust system
downstream of the turbochargers and repair or replacement of parts as
necessary. That AD resulted from exhaust system failures downstream
from turbochargers. We issued that AD to prevent the possibility of an
inflight powerplant fire due to an exhaust system failure.
Actions Since Existing AD Was Issued
Since we issued AD 82-16-05 R1 (51 FR 11707-01, April 7, 1986),
forced landings of aircraft have occurred due to exhaust system
failures upstream of aircraft turbochargers and between recurring
detailed inspections.
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 these same type
designs.
Proposed AD Requirements
This proposed AD would retain certain requirements of AD 82-16-05
R1 (51 FR 11707-01, April 7, 1986). This proposed AD would require a
detailed repetitive inspection of the entire exhaust systems.
Costs of Compliance
We estimate that this proposed AD affects 1,016 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Visual inspection................ 2 work-hours x $85 per Not applicable..... $170 $172,720
hour = $170.
Disassembled inspection.......... 5 work-hours x $85 per Not applicable..... 425 431,800
hour = $425.
----------------------------------------------------------------------------------------------------------------
The on-condition costs of exhaust system part repairs and
replacement cannot be predicted because the multitude of manner and
environments in which aircraft operate will result in widely varying
exhaust system conditions over time.
[[Page 57535]]
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We 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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing airworthiness directive
(AD) 82-16-05 R1, Amendment 39-5278 (51 FR 11707-01, April 7, 1986),
and adding the following new AD:
Piper Aircraft, Inc.: Docket No. FAA-2012-0983; Directorate
Identifier 2012-CE-001-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by November 2,
2012.
(b) Affected ADs
This AD supersedes AD 82-16-05 R1, Amendment 39-5278.
(c) Applicability
This AD applies to turbocharged Piper Aircraft, Inc. Models PA-
31, PA-31-325, and PA-31-350 airplanes, all serial numbers,
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 the forced landings of aircraft due to
exhaust system failures between recurring detailed inspections. 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) Visual Inspection
Within the next 50 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 50 hours TIS or 6 months,
whichever occurs first, inspect the entirety of each exhaust system
by gaining access to (but not disassembling) each exhaust system.
Using a flashlight and a mirror, visually inspect the entirety of
each exhaust system for bulges, burned areas, corrosion, cracks,
deformation, exhaust stains, and holes and pinholes. Riveted
couplings should be checked for loose rivets and cracks emanating
from rivet holes. Inspection procedure references can be found in
FAA Advisory Circular 43.13-1B, Change 1, dated September 27, 2001,
Acceptable Methods, Techniques, And Practices--Aircraft Inspection
and Repair (http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgAdvisoryCircular.nsf/0/99C827DB9BAAC81B86256B4500596C4E?OpenDocument&Highlight=ac%2043.13-1b).
(h) Detailed Inspection
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, and repetitively thereafter at intervals not
to exceed 100 hours TIS or 12 months, whichever occurs first, do the
following:
(1) Gain access to each exhaust system and remove all exhaust
system v-band couplings.
Note 1 to paragraph (h) of this AD: During removal, we
recommend not opening the v-band couplings more than the MINIMUM
diameter necessary to clear coupled flanges.
(2) Using either a dye-penetrant inspection method or a light
and a 10-power magnifying glass (inspection procedure references can
be found in FAA Advisory Circular 43.13-1B, Change 1, dated
September 27, 2001, Acceptable Methods, Techniques, and Practices-
Aircraft Inspection and Repair (http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgAdvisoryCircular.nsf/0/99C827DB9BAAC81B86256B4500596C4E?OpenDocument&Highlight=ac%2043.13-1b), accomplish the following:
(i) Inspect the tailpipe assembly for damage including bulges,
burned areas, corrosion, cracks, deformation, exhaust stains, and
holes and pinholes.
(ii) Inspect each v-band coupling for damage including bending,
cracks (those emanating from rivets, too), failed spot welds,
indications of exhaust flanges bottoming in couplings, loose rivets,
overstress, and spreading of v-band segments. Inspect the bolt and
nut of each coupling for thread damage.
(iii) Inspect the flanges of the exhaust system (which mate with
the transition), the transition, the tail pipe, and the turbocharger
(uncoupled) for cracks, distortion, and evidence indicative of
improper surface mating.
(3) Inspect the three exhaust system slip joints between each
turbocharger and its closest riser for seizure.
Note 2 to paragraph (h) of this AD: We established the
repetitive inspection compliance times of this AD so they may
coincide with scheduled oil changes and annual inspections.
(i) Corrective Actions
(1) If any damage is found as a result of the inspections
required in paragraph (g) of this AD, before further flight, do the
following corrective actions:
(i) Replace loose or damaged v-band couplings following the
instructions in paragraph (k) of this AD.
(ii) Repair or replace loose fasteners and damaged exhaust
system parts with airworthy parts.
(2) If any damage is found as a result of the inspections listed
in paragraph (h) of this AD, before further flight, do the following
corrective actions:
(i) Replace any loose or damaged v-band couplings following the
instructions in paragraph (k) of this AD.
(ii) Repair or replace loose fasteners, seized slip joints, and
damaged exhaust system parts with airworthy parts.
(iii) Replace any part exhibiting flange cracking or distortion,
and remove any carbon deposits from mating flange surfaces.
(j) Mandatory Replacement
(1) Initially replace the v-band coupling following the
procedures in paragraph (k) of
[[Page 57536]]
this AD at whichever of the following occurs later:
(i) The v-band coupling reaches a total of 1,000 hours time-in-
service (TIS); or
(ii) 50 hours TIS after the effective date of this AD, or 6
months after the effective date of this AD, whichever occurs
earlier.
(2) After the initial replacement required in paragraph (j)(1)
of this AD, repetitively thereafter replace the v-band coupling
every 1,000 hours TIS.
(k) Flange and V-Band Coupling
(1) Install serviceable and replacement v-band couplings
following the applicable instructions contained in Piper Aircraft
Corporation Service Bulletin No. 644E, dated May 9, 2012 and/or
Lycoming Service Instruction No. 1238B, dated January 6, 2010.
(2) Use the applicable torque values specified within Piper
Aircraft Corporation Service Bulletin No. 644E, dated May 9, 2012,
for Piper v-band couplings; and within Lycoming Service Instruction
No. 1238B, dated January 6, 2010, for Lycoming v-band couplings;
making sure the torque indicator wrench socket is properly aligned
to prevent side loads upon the (v-band coupling) bolt.
(3) Align each flange couple so that mating flange surfaces are
flat against each other (do not use a v-band coupling to pull
flanges into alignment).
(4) Verify that the locknuts exhibit a prevailing torque, and
replace any locknuts and/or mating couplings with airworthy parts
when locknuts are not exhibiting a prevailing torque.
Note 1 to paragraph (k) of this AD: During installation, we
recommend not opening the v-band coupling more than the MINIMUM
diameter necessary to clear coupled flanges.
(l) 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.
(m) 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: [email protected].
(2) For service information identified in this AD, contact 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. 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.
Issued in Kansas City, Missouri, on September 11, 2012.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2012-22953 Filed 9-17-12; 8:45 am]
BILLING CODE 4910-13-P