[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: 
<a href="/cdn-cgi/l/email-protection#e58585809581c88481868a8888808b9196a588848c89cb8d94cb838484cb828a93">``<span class="__cf_email__" data-cfemail="aacfdace87cbcec9c5c7c7cfc4ded9eac7cbc3c684c2db84cccbcb84cdc5dc">[email protected]</span></a>''.
    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:

------------------------------------------------------------------------
           Document No.              Pages              Date            
------------------------------------------------------------------------
No. 484...........................     1-4  January 30, 1989.           
Total pages: 4.                                                         
No. 499...........................     1-4  June 14, 1991.              
Total pages: 4.                                                         
------------------------------------------------------------------------

    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.
BILLING CODE 4910-13-U

[[Page 29006]]

APPENDIX 1
[GRAPHIC] [TIFF OMITTED] TR07JN96.000


[FR Doc. 96-14220 Filed 6-6-96; 8:45 am]
BILLING CODE 4910-13-C

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