[Federal Register Volume 60, Number 179 (Friday, September 15, 1995)]
[Rules and Regulations]
[Pages 47864-47866]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-22048]



-----------------------------------------------------------------------


DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-CE-57-AD; Amendment 39-9337; AD 95-17-06]


Airworthiness Directives; Mooney Aircraft Corporation Model M20K 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to Mooney Aircraft Corporation (Mooney) Model M20K airplanes 
with a Continental TSIO-520-NB engine installed in accordance with 
Supplemental Type Certificate (STC) SA5691NM. This action requires 
repetitively inspecting the exhaust transition tube and turbo mount 
assembly for cracks, and replacing any part found cracked. A report of 
a cracked exhaust transition tube that connects the exhaust manifolds 
to the turbocharger inlet on one of the affected airplanes prompted 
this action. The actions specified by this AD are intended to prevent 
exhaust gases from entering the cabin heating system because of a 
cracked exhaust transition tube, which, if not detected and corrected, 
could result in hazardous levels of carbon monoxide in the airplane 
cabin.

DATES: Effective September 25, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 25, 1995.
    Comments for inclusion in the Rules Docket must be received on or 
before November 27, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket 95-CE-57-AD, Room 1558, 601 E. 12th 
Street, Kansas City, Missouri 64106.
    Service information that applies to this AD may be obtained from 
the Rocket Engineering Corporation, East 6247 Rutter Road, Felts Field, 
Spokane, Washington 99212. This information may also be examined at the 
Federal Aviation Administration (FAA), Central Region, Office of the 
Assistant Chief Counsel, Attention: Rules Docket 95-CE-57-AD, Room 
1558, 601 E. 12th Street, Kansas City, Missouri 64106; or at the Office 
of the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr. Kevin Masterson, Aerospace 
Engineer, FAA, Northwest Mountain Region, 1601 Lind Avenue S.W., 
Renton, Washington 98055-4056; telephone (206) 227-2596; facsimile 
(206) 227-1181.

SUPPLEMENTARY INFORMATION: The FAA has received a report of a cracked 
exhaust transition tube that connects the exhaust manifolds to the 
turbocharger inlet on a Mooney Model M20K airplane. This airplane has a 
Continental TSIO-520-NB engine installed in accordance with 
Supplemental Type Certificate (STC) SA5691NM, which is owned by the 
Rocket Engineering Corporation. Included with this STC SA5691NM 
installation is an AiResearch THO8A67 turbocharger and intercooler.
    In the above-referenced incident, a 4 to 5-inch crack had developed 
in the exhaust transition tube. In addition, the turbo mount brace was 
found cracked. These cracks were discovered following an incident where 
the pilot reported loss of engine power while in flight. A cracked 
exhaust transition tube that connects the engine manifolds and the 
turbocharger inlet could allow exhaust gases to enter the cabin heating 
system. In this instance, a hazardous level of carbon monoxide could 
enter the airplane cabin, resulting in pilot injury and subsequent loss 
of control of the airplane.
    The Rocket Engineering Corporation has issued Mandatory Service 
Bulletin MSB95-305-1, dated August 9, 1995, which specifies procedures 
for inspecting the exhaust transition tube and turbo mount assembly on 
Mooney Model M20K airplanes with a Continental TSIO-520-NB engine 
installed in accordance with STC SA5691NM.
    The FAA examined all available information related to the incident 
described above including the referenced service information and has 
determined that AD action should be taken to prevent exhaust gases from 
entering the cabin heating system because of a cracked exhaust 
transition tube, which, if not detected and corrected, could result in 
hazardous levels of carbon monoxide in the airplane cabin.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Mooney Model M20K airplanes of the same type 
design that have a Continental TSIO-520-NB engine installed in 
accordance with STC SA5691NM, this AD requires repetitively inspecting 
the exhaust transition tube and turbo mount assembly for cracks, and 
replacing any part found cracked. Accomplishment of these actions will 
be in accordance with Rocket Engineering Corporation Mandatory Service 
Bulletin MSB95-305-1, dated August 9, 1995.
    Since a situation exists (possible hazardous carbon monoxide levels 
in the airplane cabin) that requires the immediate adoption of this 
regulation, it is found that notice and opportunity for public prior 
comment hereon are impracticable, and that good cause exists for making 
this amendment effective in less than 30 days.

[[Page 47865]]


Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting immediate flight safety and, thus, was not 
preceded by notice and opportunity to 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 above. All communications 
received on or before 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 request must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 95-CE-57-AD.'' 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 and 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 (otherwise, an evaluation is 
not required). A copy of it, if filed, may be obtained from the Rules 
Docket.

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 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
(AD) to read as follows:

95-17-06  Mooney Aircraft Corporation: Amendment 39-9337; Docket No. 
95-CE-57-AD.

    Applicability: Model M20K airplanes (all serial numbers), 
certificated in any category, that have a Continental TSIO-520-NB 
engine installed in accordance with Supplemental Type Certificate 
(STC) SA5691NM, which is owned by the Rocket Engineering 
Corporation.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability revision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes 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 (f) 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 initially within the next 10 hours time-in-
service (TIS) after the effective date of this AD, and thereafter as 
indicated in the body of this AD.
    To prevent exhaust gases from entering the cabin heating system 
because of a cracked exhaust transition tube, which, if not detected 
and corrected, could result in hazardous levels of carbon monoxide 
in the airplane cabin, accomplish the following:
    (a) Inspect the following parts of the exhaust system for cracks 
in accordance with Rocket Engineering Corporation Mandatory Service 
Bulletin MSB95-305-1, dated August 9, 1995:
    (1) Exhaust Transition Tube, part number 305-01-507HS, 305-01-
507HS-Rev A, or 305-01-507HS-Rev B.
    (2) Left Hand Forward Mount Tube, part number 305-03-501, 305-
03-501-Rev A, or 305-03-501-Rev B.
    (3) Right Hand Forward Mount Tube, part number 305-03-502 or 
305-03-502-Rev A.
    (b) If cracks are found in either the exhaust transition tube or 
the turbo mount tubes during any of the required inspections, prior 
to further flight, accomplish the following in accordance with 
Rocket Engineering Corporation Mandatory Service Bulletin MSB95-305-
1, dated August 9, 1995.
    (1) Replace any cracked exhaust transition tube with Exhaust 
Transition Tube, part number 305-01-507HS-Rev C, and reinspect this 
new exhaust transition tube at intervals not to exceed 50 hours TIS.
    (2) Replace any cracked left hand forward mount tube with Left 
Hand Forward Mount Tube, part number 305-03-501-Rev C. The 
repetitive inspections of this part required by this AD may be 
terminated after this replacement.
    (3) Replace any cracked right hand forward mount tube with Right 
Hand Forward Mount Tube, part number 305-03-502-Rev B. The 
repetitive inspections of this part required by this AD may be 
terminated after this replacement.
    (c) If no cracks are found in either the exhaust transition tube 
or the turbo mount tubes during any of the inspections required by 
this AD, reinspect at intervals not to exceed 25 hours TIS provided 
the parts are crack-free.
    (d) The replacements required by paragraphs (b)(1), (b)(2), and 
(b)(3) of this AD may be accomplished regardless of whether a part 
is found cracked in order to extend the repetitive inspection time 
of the exhaust transition tube or eliminate the repetitive 
inspection requirement of the left and right hand forward mount tube 
as is specified in the applicable paragraph of this AD.
    (e) 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 airplane to a location where 
the requirements of this AD can be accomplished.
    (f) An alternative method of compliance or adjustment of the 
initial or repetitive compliance times that provides an equivalent 
level of safety may be approved by the Manager, Seattle Aircraft 
Certification Office (ACO), FAA, Northwest Mountain Region, 1601 
Lind Avenue SW., Renton, Washington 98055-4056. The request shall be 
forwarded through an appropriate FAA Maintenance Inspector, who may 
add comments and then send it to the Manager, Seattle ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

    (g) The inspections and replacements required by this AD shall 
be done in accordance with Rocket Engineering Corporation Mandatory 
Service Bulletin MSB95-305-1, dated August 9, 1995. This 

[[Page 47866]]
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. 
Copies may be obtained from the Rocket Engineering Corporation, East 
6247 Rutter Road, Felts Field, Spokane, Washington 99212. Copies may 
be inspected at the FAA, Central Region, Office of the Assistant 
Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, 
or at the Office of the Federal Register, 800 North Capitol Street, 
NW., 7th Floor, suite 700, Washington, DC.
    (h) This amendment (39-9337) becomes effective on September 25, 
1995.

    Issued in Kansas City, Missouri, on August 30, 1995.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-22048 Filed 9-14-95; 8:45 am]
BILLING CODE 4910-13-U