[Federal Register Volume 61, Number 203 (Friday, October 18, 1996)]
[Proposed Rules]
[Pages 54370-54372]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-26700]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-CE-48-AD]
RIN 2120-AA64
Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-
802A 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 Air Tractor, Inc. (Air Tractor) Models
AT-802 and AT-802A airplanes. The proposed action would require
revising the Airworthiness Limitations section of the applicable
maintenance manual to change the life limit of the tail landing gear
spring. Results from a routine analysis of the life-limited parts of
the affected airplanes prompted the proposed AD. In particular, the
tail landing gear spring life limit is not consistent with that called
out for the main landing gear spring. The actions specified by the
proposed AD are intended to prevent fatigue failure of a tail landing
gear spring before the life limit of the part is achieved, which could
result in loss of control of the airplane.
DATES: Comments must be received on or before December 20, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 96-CE-48-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 Air Tractor, Inc., P. O. Box 485, Olney, Texas 76374; telephone
(817) 564-5616; facsimile (817) 564-2348. This information also may be
examined at the Rules Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Bob May, Aerospace Engineer, FAA,
Aircraft Certification Office, 2601 Meacham Boulevard, Fort Worth,
Texas 76193-0150; telephone (817) 222-5155; 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
[[Page 54371]]
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. 96-CE-48-AD.'' The 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 Assistant Chief Counsel,
Attention: Rules Docket No. 96-CE-48-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
Routine analysis of the life-limited parts on Air Tractor Models
AT-802 and AT-802A airplanes reveals that the life limit of the tail
landing gear spring is not consistent with that called out for the main
landing gear spring. Specifically, the tail landing gear spring life
limit was only related to hours time- in-service (TIS) and was not tied
to landings. When adjusting the life limit of the tail landing gear
spring to landings as well as hours TIS, the FAA noticed that the hours
TIS life limit for this part is not consistent with that of the main
landing gear spring; the life limit of the tail landing gear spring is
currently 3,500 hours TIS and should be 3,000 hours TIS to be
consistent with the main landing gear spring.
Applicable Maintenance Manual Revision
Air Tractor has revised Section 6, Airworthiness Limitations, of
the Air Tractor AT 802/802A Maintenance Manual. This revision changes
the life limit of the tail landing gear spring from 3,500 hours TIS to
3,000 hours TIS and includes 8,000 landings (the life limit being that
which comes first). This revision is dated May 24, 1996.
The FAA's Determination
After examining the circumstances and reviewing all available
information related to the situation described above, the FAA has
determined that (1) the life limit of the tail landing gear spring
should be changed; and (2) AD action should be taken to prevent fatigue
failure of a tail landing gear spring before the life limit of the part
is achieved, which could result in loss of control 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 Air Tractor Models AT-802 and AT-802A
airplanes of the same type design, the proposed AD would require
revising the Airworthiness Limitations section of the applicable
maintenance manual to change the life limit of the tail landing gear
spring. The proposed revision would be accomplished by incorporating
the revision to Section 6, Airworthiness Limitations, of the Air
Tractor AT 802/802A Maintenance Manual, dated May 24, 1996.
Cost Impact
The FAA estimates that 37 airplanes in the U.S. registry would be
affected by the proposed AD. An owner/operator of one of the affected
airplanes holding at least a private pilot certificate would be allowed
to incorporate the manual revision as authorized by section 43.7 of the
Federal Aviation Regulations (14 CFR 43.7). With this in mind, the only
impact the proposed AD would have upon U.S. owners/operators of the
affected airplanes would be the time it would take the individual
owners/operators of the affected airplanes to incorporate the proposed
manual revision.
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:
Air Tractor, Inc.: Docket No. 96-CE-48-AD.
Applicability: Models AT-802 and AT-802A airplanes (serial
numbers 0001 through 0038), certificated in any category.
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 within the next 100 hours time-in-service
after the effective date of this AD, unless already accomplished.
To prevent fatigue failure of a tail landing gear spring before
the life limit of the part is achieved, which could result in loss
of control of the airplane, accomplish the following:
(a) Incorporate the revision to Section 6, Airworthiness
Limitations, of the Air Tractor AT 802/802A Maintenance Manual,
dated May 24, 1996.
(b) Incorporating the maintenance manual revision as required by
paragraph (a) of this AD may be performed by the airplane owner/
operator holding at least a private pilot certificate as authorized
by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7),
and must be entered into the aircraft records showing compliance
with this AD in accordance with section 43.11 of the Federal
Aviation Regulations (14 CFR 43.11).
(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
compliance times that
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provides an equivalent level of safety may be approved by the
Manager, FAA, Aircraft Certification Office, 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 ACO.
(e) All persons affected by this directive may obtain copies of
the maintenance manual revision referred to herein upon request to
Air Tractor Inc., P. O. Box 485, Olney, Texas 76374; or may examine
this information at the FAA, Central Region, Office of the Assistant
Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri
64106.
Issued in Kansas City, Missouri, on October 10, 1996.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-26700 Filed 10-17-96; 8:45 am]
BILLING CODE 4910-13-U