AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Mooney Aviation Company, Inc. (Mooney) Models M20R and M20TN airplanes.
This emergency AD was sent previously to all known U.S. owners and
operators of these airplanes. This AD requires inspecting the tail
pitch trim assembly for correct positioning and proper attachment and
inspecting the Huck Bolt fasteners for proper security with repair as
necessary. The AD also requires sending the inspection results to the
FAA and Mooney. This AD was prompted by a report of an incident on a
Mooney Model M20TN airplane regarding failure of the tail pitch trim
assembly, which could result in loss of control. We are issuing this AD
to correct the unsafe condition on these products.

DATES: This AD is effective February 29, 2012 to all persons except
those persons to whom it was made immediately effective by Emergency AD
2012-03-52, issued on February 10, 2012, which contained the
requirements of this amendment.
The Director of the Federal Register approved the incorporation by
reference of a certain publication identified in the AD as of February
29, 2012.
We must receive comments on this AD by April 16, 2012.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
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.
Fax: 202-493-2251.
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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Mooney
Aviation Company, Inc., 165 Al Mooney Road North, Kerrville, Texas
78028; telephone: (830) 896-6000; email: technicalsupport@mooney.com;
Internet: www.mooney.com. You may review copies of the referenced
service information at the FAA, Small Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For information on the availability of
this material at the FAA, call (816) 329-4148.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov;
or in person at the Docket Operations Office
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 Operations 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: Andrew McAnaul, Aerospace Engineer,
ASW-150 (c/o MIDO-43), 10100 Reunion Place, Suite 650, San Antonio,
Texas 78216; telephone: (210) 308-3365; facsimile: (210) 308-3370;
email: andrew.mcanaul@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

On February 10, 2012, we issued Emergency AD 2012-03-52, which
requires inspecting the trim fitting, hinge, and filler plate of the
tail pitch trim assembly for correct positioning and proper attachment
and inspecting the Huck Bolt fasteners for proper security on certain
Mooney Aviation Company, Inc. (Mooney) Models M20R and M20TN airplanes.
If incorrect positioning or improper/loose attachment is found, the
owner/operator must contact Mooney for FAA-approved repair
instructions. The AD also requires sending the inspection results to
the FAA and Mooney. This emergency AD was sent previously to all known
U.S. owners and operators of these airplanes.
This AD action was prompted by a report of an incident on a Mooney
Model M20TN airplane regarding the tail pitch trim assembly. In this
report, the affected airplane experienced an un-commanded significant
pitch up attitude within seconds after takeoff and during the climb.
The pilot then pushed the yoke forward and the aircraft still
maintained a nose-up attitude.
The pilot stated that the ``forces acting on the control column
were so large that single pilot wasn't able to handle that for more
than just a few minutes.'' The pilot and copilot had to use their knees
to hold forward pressure on the flight controls to aid in preventing a
departure from controlled flight. They had to maintain between 80 to
100 percent power to keep the aircraft at about 90 knots indicated
airspeed to prevent the airplane from stalling. The only way they were
able to descend was to introduce a series of turns.
On Mooney Models M20TN and M20R airplanes, the pitch trim is
adjusted by rotating the entire tail assembly. The actuating arm pushes
on a hinge fixed to the empennage forward bulkhead. The hinge attaches
to the bulkhead using 10 Huck Bolt fasteners with swaged collars.
This aircraft was immediately inspected, and all 10 swaged collars
that hold the tail trim assembly together had become unattached.
Mooney inspected several other aircraft and found that on one
airplane the filler plate was incorrectly installed. The filler plate
was not correctly installed between the aft side of the hinge and the
bulkhead. Instead, the filler plate was located on the forward side of
the hinge between the hinge and trim fitting. It was then noted the
incident aircraft had the same issue, as shown in the upper circle of
figure 1.
Because the hinge has a lip on the bottom, on the side toward the
bulkhead (as shown in the bottom circle of figure 1), if the filler
plate is not installed correctly, the hinge will not fit flush against
the bulkhead, the Huck Bolt fasteners will not fit perpendicular to the
bulkhead, and the collars will not swage properly. The condition also
causes excessive tension pre-load on the Huck Bolts.

ILLUSTRATION (Figure 1)

The incident aircraft was manufactured in 2008. Mooney has
determined the incorrect installation was a manufacturing quality
escape during production.
We are issuing this AD to detect incorrect positioning and improper
attachment of the trim fitting, hinge, and filler plate of the tail
pitch trim assembly and to verify security of the attaching Huck Bolt
fasteners, which could lead to failure of the tail pitch trim assembly
with consequent loss of pitch control.

Relevant Service Information

We reviewed Mooney Aviation Company, Inc. Service Bulletin No. M20-
313, dated February 7, 2012. The service information describes
procedures for inspecting the trim fitting, hinge, filler plate, and
attaching fasteners of the tail pitch trim assembly.

FAA's Determination

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.

AD Requirements

This AD requires inspecting the trim fitting, hinge, and filler
plate of the tail pitch trim assembly for correct positioning and
proper attachment, and inspecting the Huck Bolt fasteners for proper
security. If incorrect positioning or improper/loose attachment is
found, the owner/operator must contact Mooney for FAA-approved repair
instructions. The AD also requires sending the inspection results to
the FAA and Mooney.

Interim Action

We consider this AD interim action. Mooney and the FAA will analyze
the results of the inspection required by this AD. We may take further
rulemaking action in the future.

FAA's 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
failure of the tail pitch trim assembly could result in loss of
control. 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.

Comments Invited

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-2012-0182 and
Directorate Identifier 2012-CE-005-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 those comments.
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 170 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:

Estimated Costs

We have no way of determining the cost of repair/replacement at
this time. We have no way of determining the number of aircraft that
might need repair or replacement.
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.

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
rulemaking action.

Regulatory Findings

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
Order 12866,
(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
reference, Safety.

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
directive (AD):