[Federal Register Volume 63, Number 140 (Wednesday, July 22, 1998)]
[Proposed Rules]
[Pages 39254-39256]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-19486]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-CE-20-AD]
RIN 2120-AA64
Airworthiness Directives; Mooney Aircraft Corporation Models
M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K, M20L, M20M, and M20R
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to certain Mooney Aircraft Corporation (Mooney)
Models M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K, M20L, M20M, and
M20R airplanes. The proposed AD would require repetitively inspecting
the aileron control link welded area, and if cracks are found,
replacing the control link with a part of improved design. Service
difficulty reports (SDR's) on the aileron control link and reported
failures of the aileron control link prompted the proposed action. The
actions specified by the proposed AD are intended to detect and correct
cracked aileron control links, which could result in loss of aileron
control and loss of the airplane.
DATES: Comments must be received on or before September 30, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 98-CE-20-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106. Comments may be inspected at this location
between 8 a.m. and 4 p.m., Monday through Friday, holidays excepted.
Service information that applies to the proposed AD may be obtained
from Mooney Aircraft Corporation, Louis Schreiner Field, Kerrville,
Texas, 78028. This information also may be examined at the Rules Docket
at the address above.
FOR FURTHER INFORMATION CONTACT: Bob D. May, Aerospace Engineer, FAA,
Airplane Certification Office, 2601 Meacham Boulevard, Fort Worth,
Texas 76193-0150; telephone: (817) 222-5156; facsimile: (817) 222-5960.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 proposal 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 No. 98-CE-20-AD.'' The
[[Page 39255]]
postcard will be date stamped and returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Central Region, Office of the Regional Counsel, Attention:
Rules Docket No. 98-CE-20-AD, Room 1558, 601 E. 12th Street, Kansas
City, Missouri 64106.
Discussion
The FAA has received several SDR's from the field on the failure of
the aileron center control link during flight and on the ground for the
Mooney M20 series airplanes. These failures are occurring in the heat-
affected zones of the weld joints at the 90-degree corners of the
assemblies. In 1994, the airplane design was changed to incorporate a
reinforcing gusset in the corner joints. This design change was
accomplished as field repair or rework and was found not to be a
practical alteration of the part. Since then, the manufacturer has
designed an improved part.
Relevant Service Information
Mooney Aircraft Corporation has issued Engineering Design Service
Bulletin No. M20-264, dated February 1, 1998, which specifies
procedures for inspecting for a reinforcing gusset or cracks in the
aileron control link at the second 90-degree angled joint from the Heim
bearing. If the gusset is found, then no further action is required. If
no gusset is found, the service information specifies procedures for
repetitively inspecting (using a magnetic particle method) for cracks
at the second 90-degree angled joint, and if cracks are found,
replacing the aileron control link with one of improved design. The
installation of the improved part is considered a terminating action to
the repetitive inspections. If no cracks are found, the service
information specifies repetitively inspecting the area until cracks are
found, and then replacing the aileron control link with a part of
improved design.
The FAA's Determination
After examining the circumstances and reviewing all available
information related to the incidents described above, the FAA has
determined that AD action should be taken to detect and correct cracked
aileron control links, which could result in loss of aileron control
and loss of the airplane.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Mooney Model M20B, M20C, M20D, M20E, M20F,
M20G, M20J, M20K, M20L, M20M, and M20R airplanes of the same type
design, the proposed AD would require inspecting the aileron control
link for a reinforcing gusset, and if there is no gusset, repetitively
inspecting the aileron control links (left-hand and right-hand) for
cracks using a magnetic particle method. If a crack is found, the
proposed AD would require replacing the aileron control links with
parts of improved design. Replacing the aileron control link would be
considered a terminating action for the repetitive inspections.
Accomplishment of the proposed actions would be required in accordance
with the previously referenced service information.
Cost Impact
The FAA estimates that 7,500 airplanes in the U.S. registry would
be affected by the proposed initial inspections, that it would take
approximately 2 workhours per airplane to accomplish the proposed
initial inspection, and that the average labor rate is approximately
$60 an hour. Based on these figures, the total cost impact of the
proposed initial inspection specified in the proposed AD on U.S.
operators is estimated to be $900,000, or $120 per airplane.
The FAA has no way of determining the number of repetitive
inspections that would be incurred over the life of the airplane or
whether a cracked part would be found as the result of the proposed
initial inspection. Therefore, these actions are not figured into the
initial total cost impact estimated for the proposed AD.
Regulatory Impact
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (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); and (3) if promulgated,
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. A copy of the draft regulatory evaluation
prepared for this action has been placed in the Rules Docket. A copy of
it may be obtained by contacting the Rules Docket at the location
provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
Mooney Aircraft Corporation: Docket No. 98-CE-20-AD.
Applicability: The following airplane models and serial numbers,
certificated in any category.
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Models Serial numbers
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M20B................................ all serial numbers
M20C................................ all serial numbers
M20D................................ all serial numbers
M20E................................ all serial numbers
M20F.............. all serial numbers
M20G................................ all serial numbers
M20L................................ all serial numbers
Model M20J.......................... 24-0001 through 24-3359
Model M20K.......................... 25-0001 through 25-1999
Model 20M........................... 27-0001 through 27-0197
Model M20R.......................... 29-0001 through 29-0042
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Note 1: This AD applies to each airplane 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 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 (d) 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 as indicated in the body of this AD, unless
already accomplished.
To detect and correct cracked aileron control links, which could
result in loss of
[[Page 39256]]
aileron control and loss of the airplane, accomplish the following:
(a) Within the next 100 hours time-in-service (TIS) after the
effective date of this AD, visually inspect the aileron control
links (left-hand and right-hand) at the second 90-degree angle joint
from the second Heim bearing for a reinforcement gusset in
accordance with the Instructions section of Engineering Design
Service Bulletin (SB) No. M20-264, Issue Date:
February 1, 1998.
(1) If a reinforcement gusset is found, no further action is
required.
(2) If a reinforcement gusset is not found, prior to further
flight, inspect the aileron control links, using a magnetic particle
method, for any cracks in accordance with the Instructions section
of Engineering Design SB No. M20-264, Issue Date: February 1, 1998.
(i) If cracks are found, prior to further flight, replace the
aileron control link with a part of improved design in accordance
with the Instructions section of Engineering Design SB No. M20-264,
Issue Date: February 1, 1998.
(ii) If no cracks are found, re-inspect for cracks at intervals
not to exceed 100 hours TIS in accordance with the Instructions
section of Engineering Design SB No. M20-264, Issue Date: February
1, 1998. If cracks are found during any inspection required by
paragraphs (a)(2) and (a)(2)(ii) of this AD, prior to further
flight, replace the aileron control link with a part of improved
design in accordance with the Instructions section of Engineering
Design SB No. M20-264, Issue Date: February 1, 1998.
(b) Replacing the aileron control link in accordance with
Engineering Design SB No. M20-264, Issue Date: February 1, 1998, is
considered a terminating action for the repetitive inspections
required in paragraph (a)(2)(ii) of this AD and may be accomplished
at any time.
(c) 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.
(d) 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, Fort Worth Airplane
Certification Office (ACO), 2601 Meacham Boulevard, Fort Worth,
Texas 76193-0150. The request shall be forwarded through an
appropriate FAA Maintenance Inspector, who may add comments and then
send it to the Manager, Fort Worth ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Fort Worth Aircraft Certification Office.
(e) All persons affected by this directive may obtain copies of
the document referred to herein upon request to Mooney Aircraft
Corporation, Louis Schreiner Field, Kerrville, Texas, 78028; or may
examine this document at the FAA, Central Region, Office of the
Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City,
Missouri 64106.
Issued in Kansas City, Missouri, on July 16, 1998.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-19486 Filed 7-21-98; 8:45 am]
BILLING CODE 4910-13-U
