[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

[[Page 54372]]

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