[Federal Register Volume 63, Number 113 (Friday, June 12, 1998)]
[Proposed Rules]
[Pages 32151-32152]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-15621]
[[Page 32151]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-ANE-58-AD]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney R-1340 Series
Reciprocating Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to Pratt & Whitney R-1340 series
reciprocating engines. This proposal would require initial and
repetitive visual and fluorescent penetrant inspections of cylinders,
Part Number 399359, for head cracking. This proposal is prompted by
reports of cylinder head cracking. The actions specified by the
proposed AD are intended to prevent cylinder head cracking, which can
result in engine power loss, forced landing, and damage to the
aircraft.
DATES: Comments must be received by August 11, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, Attention: Rules Docket No. 97-ANE-58-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be sent
via the Internet using the following address: ``engineprop@faa.dot.gov''. Comments sent via the Internet must contain
the docket number in the subject line. Comments may be inspected at
this location between 8:00 a.m. and 4:30 p.m., Monday through Friday,
except Federal holidays.
The service information referenced in the proposed rule may be
obtained from Pratt & Whitney, Publications Department, Supervisor
Technical Publications Distribution, M/S 132-30, 400 Main Street, East
Hartford, CT 06108; telephone (860)565-7700, fax (860)565-4503. This
information may be examined at the FAA, New England Region, Office of
the Regional Counsel, 12 New England Executive Park, Burlington, MA.
FOR FURTHER INFORMATION CONTACT: Wego Wang, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7134, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 97-ANE-58-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, New England Region, Office of the Regional Counsel,
Attention: Rules Docket No. 97-ANE-58-AD, 12 New England Executive
Park, Burlington, MA 01803-5299.
Discussion
The Federal Aviation Administration (FAA) has received reports of
cylinder head cracking on Pratt & Whitney (PW) R-1340 series
reciprocating engines. The investigation has revealed cracking on top
of the engine cylinder head, usually from one spark plug hole to
another. In one case the engine's #1 cylinder head split into two
pieces. One repair station has indicated that at least one or two
cracked cylinder heads will be found on each engine during an engine
repair cycle. An A&P mechanic, specializing in the maintenance of
radial engines, has stated that he has removed at least thirteen
cylinders with cracked cylinder heads from PW R-1340 engines in the
first eight months of 1997. The operator involved in the above-
mentioned accident has experienced one similar in-flight cylinder
failure every year since operating PW R-1340 engines, and has
discovered several cylinders with cracked cylinder heads during daily
pre-flight inspections in 1997. Since the majority of aircraft with
this engine installation are agricultural and fly at very low
altitudes, engine power loss even short of a complete engine failure
can result in a forced landing. This condition, if not corrected, could
result in cylinder head cracking, which can result in engine power
loss, forced landing, and damage to the aircraft.
The FAA has reviewed and approved the technical contents of PW
Service Bulletin (SB) No. 1787, September 7, 1983, that describes
procedures for visual and fluorescent penetrant inspections (FPI) of
cylinders, Part Number 399359, for head cracking.
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would require initial and repetitive visual inspections of
cylinders for head cracking at intervals based upon whether the engines
are cowled and baffled, or unbaffled installations. Cracked cylinder
heads must be replaced with serviceable parts if found cracked. In
addition, this AD would require FPI of each cylinder at overhaul. The
actions would be required to be accomplished in accordance with the SB
described previously.
There are approximately 3,000 engines of the affected design in the
worldwide fleet. The FAA estimates that 2,535 engines installed on
aircraft of U.S. registry would be affected by this proposed AD, that
it would take approximately 1 work hour per engine to accomplish the
visual inspection, and 15 work hours to accomplish the FPI, and that
the average labor rate is $60 per work hour. Required parts would cost
approximately $2,000 per engine. In addition, the FAA estimates that 5%
of the fleet will require replacement parts upon inspection. Based on
these figures, the total cost impact of the proposed AD on U.S.
operators is estimated to be $2,687,100.
The regulations proposed herein would not have substantial direct
effects 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. Therefore, in
accordance with Executive Order 12612, it is determined that this
proposal would not have sufficient
[[Page 32152]]
federalism implications to warrant the preparation of a Federalism
Assessment.
For the reasons discussed above, I certify that this 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);
and (3) if promulgated, 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. A copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
Pratt & Whitney: Docket No. 97-ANE-58-AD.
Applicability: Pratt & Whitney (PW) R-1340 series reciprocating
engines, with cylinders, Part Number 399359, installed. These
engines are installed on but not limited to the following aircraft
Air Tractor AT301, Schweizer G164A, and DeHavilland DHC3 series
aircraft.
Note 1: This airworthiness directive (AD) applies to each engine
identified in the preceding applicability provision, regardless of
whether it has been modified, altered, or repaired in the area
subject to the requirements of this AD. For engines that have been
modified, altered, or repaired so that the performance of the
requirements of this AD is affected, the owner/operator must request
approval for an alternative method of compliance in accordance with
paragraph (c) of this AD. The request should include an assessment
of the effect of the modification, alteration, or repair on the
unsafe condition addressed by this AD; and, if the unsafe condition
has not been eliminated, the request should include specific
proposed actions to address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent cylinder head cracking, which can result in engine
power loss, forced landing, and damage to the aircraft, accomplish
the following:
(a) Perform initial and repetitive visual inspections of
cylinders for head cracking, and replace cracked cylinders with
serviceable parts, in accordance with PW Service Bulletin (SB) No.
1787, dated September 7, 1983, as follows:
(1) For cowled and baffled installations, as follows:
(i) Perform the initial visual inspection within 125 hours TIS
after the effective date of this AD.
(ii) Thereafter, visually inspect at intervals not to exceed 250
hours TIS since last inspection.
(2) For all other installations, as follows:
(i) Perform the initial visual inspection within 50 hours time-
in-service (TIS) after the effective date of this AD.
(ii) Thereafter, visually inspect at intervals not to exceed 100
hours TIS since last inspection.
(b) At the next cylinder overhaul after the effective date of
this AD, and at each subsequent overhaul, perform a fluorescent
penetrant inspection (FPI) of cylinders for head cracking, and
replace cracked cylinders with serviceable parts, in accordance with
PW SB No. 1787, dated September 7, 1983.
(c) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, Engine Certification Office.
Operators shall submit their request through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Engine Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Engine Certification Office.
Issued in Burlington, Massachusetts, on June 4, 1998.
Ronald L. Vavruska,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 98-15621 Filed 6-11-98; 8:45 am]
BILLING CODE 4910-13-U
