DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9512; Directorate Identifier 2016-NE-27-AD;
Amendment 39-18909; AD 2017-11-10]
Airworthiness Directives; Lycoming Engines Reciprocating Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
SUMMARY: We are adopting a new airworthiness directive (AD) for
Lycoming TIO-540-AJ1A reciprocating engines. This AD requires initial
and repetitive inspections of engine exhaust system weld joints and
torque checking the exhaust pipe flange mounting nuts. This AD was
prompted by several reports of engine exhaust leaks. We are
issuing this AD to correct the unsafe condition on these products.
DATES: This AD is effective June 28, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 28,
We must receive comments on this AD by July 28, 2017.
ADDRESSES: You may send comments, using the procedures found in
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.
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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this final rule, contact
Lycoming Engines, 652 Oliver Street, Williamsport, PA 17701; phone:
800-258-3279; fax: 570-327-7101; Internet: www.lycoming.com/Lycoming/SUPPORT/TechnicalPublications/ServiceBulletins.
aspx. You may view this service information at the FAA, Engine & Propeller
Directorate, 1200 District Avenue, Burlington, MA. For information on
of this material at the FAA, call 781-238-7125. It is also available on
the internet at http://www.regulations.gov by searching for and
locating Docket No. FAA-2016-9512.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov
by searching for and locating Docket No. FAA-2016-
9512; 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 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: Norman Perenson, Aerospace Engineer,
New York Aircraft Certification Office, FAA, Engine & Propeller
Directorate, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone:
516-228-7337; fax: 516-794-5531; email: Norman.Perenson@faa.gov.
We received several reports of cracked engine exhaust pipes and
exhaust studs pulling out from cylinders on Lycoming TIO-540-AJ1A
reciprocating engines. This AD requires initial and repetitive
inspections of all engine exhaust system weld joints and torque
checking the exhaust pipe flange mounting nuts. We are issuing this AD
to prevent engine exhaust leaks, which could lead to uncontrolled
engine fire, harmful exhaust gases entering the cabin resulting in crew
incapacitation, and damage to the airplane.
Related Service Information Under 1 CFR Part 51
We reviewed Lycoming Engines Mandatory Service Bulletin (MSB) No.
627C, dated November 17, 2016. The MSB describes procedures for exhaust
system inspection and flange nut torque check. This service information
is reasonably available because the interested parties have access to
it through their normal course of business or by the means identified
in the ADDRESSES section.
Other Related Service Information
We reviewed Lycoming Engines MSB No. 614A, dated October 10, 2014,
which provides maintenance instructions on the exhaust system for
certain Lycoming engines. The FAA issued AD 2015-10-06, Amendment 39-
18162 (80 FR 30345, May 28, 2015), (``AD 2015-10-06'') that mandates
replacement of the turbocharger mounting bracket and inspection of the
exhaust pipes in accordance with Lycoming Engines MSB No. 614A, dated
October 10, 2014. The requirements in this AD are in addition to the
requirements of AD 2015-10-06. Complying with AD 2015-10-06 and
Lycoming Engines MSB No. 614A, dated October 10, 2014, does not
constitute compliance with this AD.
We are issuing 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 the same type design.
This AD requires initial and repetitive inspections of all engine
exhaust system weld joints and torque checking the exhaust pipe flange
Differences Between This AD and the Service Information
Table 1 of Lycoming Engines MSB No. 627C, dated November 17, 2016,
provides a longer time between inspections of the engine exhaust system
when an operational carbon monoxide detector is installed in the
airplane. This AD does not consider whether an operational carbon
monoxide detector is installed in the airplane.
We consider this AD interim action. Lycoming is determining the
root cause for the unsafe condition identified in this AD. Once a root
cause is determined, we will consider additional rulemaking.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
engine exhaust leaks could lead to uncontrolled engine fire, harmful
exhaust gases entering the cabin resulting in crew incapacitation, and
damage to the airplane. Therefore, we find that notice and opportunity
for prior public comment are impracticable and that good cause exists
for making this amendment effective in less than 30 days.
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send any written data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include the docket number FAA-2016-9512 and
Directorate Identifier 2016-NE-27-AD at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because of
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 AD.
Costs of Compliance
We estimate that this AD affects 758 engines, installed on
airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
||Cost per product
||Cost on U.S. operators
|Inspection and torque check
||1 work-hour x $85 per hour =
$85 per inspection cycle
||$64,430.00 per inspection
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW., Washington, DC 20591. ATTN: Information
Collection Clearance Officer, AES-200.
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
This AD will not have federalism implications under Executive Order
13132. This AD will 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
(2) Is not a ``significant rule'' under 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
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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 adding the following new airworthiness