[Federal Register Volume 61, Number 111 (Friday, June 7, 1996)]
[Rules and Regulations]
[Pages 29003-29006]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-14220]
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Rules and Regulations
Federal Register
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Federal Register / Vol. 61, No. 111 / Friday, June 7, 1996 / Rules
and Regulations
[[Page 29003]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 91-ANE-29; Amendment 39-9470; AD 91-21-01 R1]
RIN 2120-AA64
Airworthiness Directives; Textron Lycoming Model TIO-540-S1AD
Reciprocating Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment revises an existing airworthiness directive
(AD), applicable to Textron Lycoming Model TIO-540-S1AD reciprocating
engines, that currently requires the upgrade of the engine exhaust
system to a new design configuration; and also establishes inspection
intervals for engines incorporating the new design configuration, for
engines incorporating the design configuration required by a previous
AD, and for engines not yet incorporating either design configuration.
This amendment clarifies that an exhaust system disassembly is not
necessary when inspecting the exhaust system after the installation of
the new design One-piece Exhaust Riser Kit, and Manifold Retaining Kit.
This amendment is prompted by reports from operators requesting
clarification of two paragraphs in the compliance section. The actions
specified by this AD are intended to prevent cracking or distortion of
engine exhaust system flanges, V-band coupling, and pipes, which could
result in engine compartment fire and smoke entering the cabin with
possible loss to the aircraft.
DATES: Effective June 27, 1996.
The incorporation by reference of certain publications listed in
the regulations was approved by the Director of the Federal Register as
of November 4, 1991.
Comments for inclusion in the Rules Docket must be received on or
before August 6, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 91-ANE-29, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be
submitted to the Rules Docket by using the following Internet address:
``[email protected]''.
The service information referenced in this AD may be obtained from
Textron Lycoming/Subsidiary of Textron Inc., Williamsport, PA 17701;
(717) 327-7278, fax (717) 327-7022. This information may be examined at
the FAA, New England Region, Office of the Assistant Chief Counsel, 12
New England Executive Park, Burlington, MA; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700, Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Richard Fiesel, Aerospace Engineer,
New York Aircraft Certification Office, FAA, Engine and Propeller
Directorate, 10 Fifth St., 3rd Floor, Valley Stream, MY 11581-1200;
telephone (516) 256-7504, fax (516) 568-2716.
SUPPLEMENTARY INFORMATION: On September 18, 1991, the Federal Aviation
Administration (FAA) issued airworthiness directive (AD) 91-21-01,
Amendment 39-8048 (56 FR 51646, October 15, 1991), to require the
modification of all affected Textron Lycoming Model TIO-540-S1AD
reciprocating engines by upgrading the engine exhaust system; and
repetitive inspections of the exhaust system for engines incorporating
the new design configuration, for engines incorporating the design
configuration required by the existing AD, and for engines not yet
incorporating either design configuration. That action was prompted by
reports of failures of exhaust systems due to exhaust pipes that were
misaligned and misassembled, or both. That condition, if not corrected,
could result in cracking or distortion of engine exhaust system
flanges, V-band coupling, and pipes, which could result in engine
compartment fire and smoke entering the cabin with possible loss to the
aircraft.
Since the issuance of that AD, the FAA has received reports from
operators requesting clarification of two paragraphs in the compliance
section. Operators have incorrectly interpreted these compliance
paragraphs, (b)(2)(i) and (b)(2)(ii), as requiring disassembly of the
exhaust system after installation of the new design One-piece exhaust
Riser and Manifold Retaining Kits. This revised AD adds
paragraph.(b)(2)(iii) to clarify that disassembly and re-inspection are
not required after compliance with paragraph (b)(2)(i) of this AD.
The FAA has reviewed and approved the technical contents of Textron
Lycoming Service Bulletin (SB) No. 484, dated January 30, 1989, that
describes the inspection, alignment, and modification of the original
exhaust assembly, and Textron Lycoming No. SB 499A, dated June 14,
1991, that describes the installation of the redesigned one-piece
exhaust pipe configuration.
Since an unsafe condition has been identified that is likely to
exist or develop on other engines of this same type design, this AD
revises AD 91-21-01 to clarify that an exhaust system disassembly is
not necessary when inspecting the exhaust system after the installation
of the new design One-piece Exhaust Riser Kit, and Manifold Retaining
Kit. The actions are required to be accomplished in accordance with the
SB's described previously.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All
communications received on or before
[[Page 29004]]
the closing date for comments will be considered, and this rule may be
amended in light of the comments received. Factual information that
supports the commenter's ideas and suggestions is extremely helpful in
evaluating the effectiveness of the AD action and determining whether
additional rulemaking action would be needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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 that
summarizes each FAA-public contact concerned with the substance of this
AD 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 91-ANE-29.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and is not a ``significant regulatory action''
under Executive Order 12866. It has been determined further that this
action involves an emergency regulation under DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979). If it is determined
that this emergency regulation otherwise would be significant under DOT
Regulatory Policies and Procedures, a final regulatory evaluation will
be prepared and placed in the Rules Docket. A copy of it, if filed, may
be obtained from the Rules Docket at the location provided under the
caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to 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), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-8048 (56 FR
51646, October 15, 1991) and by adding a new airworthiness directive,
Amendment 39-9470, to read as follows:
91-21-01 R1 Textron Lycoming: Amendment 39-9470. Docket 91-ANE-29.
Revises AD 91-21-01, Amendment 39-8048.
Applicability: Textron Lycoming Model TIO-540-S1AD reciprocating
engines installed on but not limited to Piper PA-32 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 use the
authority provided in paragraph (c) to request approval from the
Federal Aviation Administration (FAA). This approval may address
either no action, if the current configuration eliminates the unsafe
condition, or different actions necessary to address the unsafe
condition described in this AD. Such a request should include an
assessment of the effect of the changed configuration on the unsafe
condition addressed by this AD. In no case does the presence of any
modification, alteration, or repair remove any engine from the
applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent cracking or distortion of engine exhaust system
flanges, V-band coupling, and pipes, which could result in engine
compartment fire and smoke entering the cabin with possible loss to
the aircraft, accomplish the following:
(a) For engines which have not complied with AD 89-12-04,
paragraph (d), or Textron Lycoming Service Bulletin (SB) No. 484,
Part II, dated January 30, 1989, on the effective date of this AD,
accomplish the following:
(1) Within 25 hours time in service (TIS) after the effective
date of this AD, install Crossover Exhaust Pipe Kit (05K21125) in
accordance with Textron Lycoming SB No. 484, Part II, dated January
30, 1989, and also install new design One-piece Exhaust Riser Kit
(05K21503) and Manifold Retainer Kit (05K19650-S) in accordance with
Textron Lycoming SB No. 499A, dated June 14, 1991.
Note 2: Instructions and notes relating to marking the slip
joints, rotating the exhaust pipes for alignment, and maintaining
clearances at critical locations during the above installation are
contained in Textron Lycoming SB No. 499A, dated June 14, 1991.
(2) Thereafter, at intervals not to exceed 100 hours TIS,
accomplish the following:
(i) Inspect the exhaust system for heat damage, distortion,
cracks or excessive wear in accordance with Textron Lycoming SB No.
484, Part II, dated January 30, 1989.
(ii) Inspect the exhaust system for clearance dimensions, proper
fastener torque and slip joint engagement in accordance with
paragraphs 10, 11, and 12 of Textron Lycoming SB No. 499A, dated
June 14, 1991.
(iii) Repair or replace damaged parts with serviceable parts
prior to further flight.
(b) For engines that have complied with all portions of AD 89-
12-04, or Textron Lycoming SB No. 484, dated January 30, 1989, on
the effective date of this AD, accomplish the following:
(1) Within 25 hours TIS after the effective date of this AD, and
thereafter, at intervals not to exceed 25 hours TIS until the new
design One-piece Exhaust Riser Kit (05K21503) has been installed in
accordance with paragraph (b)(2)(i) of this AD, accomplish the
following;
(i) Inspect all exhaust system joints, flanges, couplings and
brackets for heat damage, distortion, cracks or excessive wear, in
accordance with Textron Lycoming SB No. 484, dated January 30, 1989.
(ii) Inspect the exhaust system for proper slip joint engagement
by measuring distances between pipe end points in accordance with
Appendix 1 of this AD.
(iii) If damage is observed in the exhaust system or
measurements exceed allowable dimensions, repair or replace parts
with serviceable parts, as necessary, prior to further flight.
(iv) Reassemble and align exhaust system in accordance with
Textron Lycoming SB No. 484, dated January 30, 1989, and Appendix 1
of this AD.
(2) Within 75 hours TIS after the effective date of this AD,
accomplish the following:
(i) Install new design One-piece Exhaust Riser Kit (05K21503)
and manifold retainer kit (05K19650-S) in accordance with Textron
Lycoming SB No. 499A, dated June 14, 1991.
(ii) Thereafter, at intervals not to exceed 100 TIS, perform
exhaust system inspections specified in paragraph (a)(2)(i) and
(a)(2)(ii) of this AD. Operators need determine the minimum
engagement of only exhaust pipes LW-16102 and LW-16103 by referring
to Appendix 1 of this AD.
(iii) The repetitive 25 hours TIS inspections required by
paragraph (b)(1) of this AD are not required after installation of
the new design One-piece Exhaust Riser Kit (05K21503) and the
Manifold Retainer Kit (05K19650-S) in accordance with paragraph
(b)(2)(i) of this AD.
(c) An alternative method of compliance or adjustment of the
initial compliance time that provides an acceptable level of safety
may be used if approved by the Manager,
[[Page 29005]]
New York Aircraft Certification Office. The request should be
forwarded through an appropriate FAA Maintenance Inspector, who may
add comments and then send it to the Manager, New York Aircraft
Certification Office.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from.
(d) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the aircraft to a location where
the inspection may be performed.
(e) The actions required by this AD shall be done in accordance
with the following Textron Lycoming SB's:
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Document No. Pages Date
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No. 484........................... 1-4 January 30, 1989.
Total pages: 4.
No. 499........................... 1-4 June 14, 1991.
Total pages: 4.
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This incorporation by reference was approved by the Director of
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51 as of November 4, 1991. Copies may be obtained from Textron
Lycoming/Subsidiary of Textron Inc., Williamsport, PA 17701;
telephone (717) 327-7278, fax (717) 327-7022. Copies may be
inspected at the FAA, New England Region, Office of the Assistant
Chief Counsel, 12 New England Executive Park, Burlington, MA; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
(f) This amendment becomes effective on June 27, 1996.
Issued in Burlington, Massachusetts, on May 29, 1996.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
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[FR Doc. 96-14220 Filed 6-6-96; 8:45 am]
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