[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: ``9-ad-
[email protected]''. 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

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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