AD 97-04-11

[Federal Register Volume 62, Number 32 (Tuesday, February 18, 1997)]
[Rules and Regulations]
[Pages 7152-7153]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-3839]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-CE-48-AD; Amendment 39-9935; AD 97-04-11]
RIN 2120-AA64


Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-
802A Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain Air Tractor, Inc. (Air Tractor) Models AT-802 and 
AT-802A airplanes. This action requires revising the Airworthiness 
Limitations section of the applicable maintenance manual to change the 
life limit of the tail landing gear spring. This action results from 
analysis of the life limits of both the tail landing gear and main 
landing gear after a fatigue failure of the main landing gear on one of 
the affected airplanes. This analysis revealed that the life limit of 
the tail landing gear spring should be 3,000 hours time-in-service 
(TIS) instead of 3,500 hours TIS to be consistent with the main landing 
gear spring. The actions specified by this 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.

EFFECTIVE DATE: April 4, 1997.

ADDRESSES: Service information that applies to this 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 may also be 
examined at the Federal Aviation Administration (FAA), Central Region, 
Office of the Assistant Chief Counsel, Attention: Rules Docket 96-CE-
48-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: Bob May, Aerospace Engineer, FAA, 
Airplane Certification Office, 2601 Meacham Boulevard, Fort Worth, 
Texas 76193-0150; telephone (817) 222-5155; facsimile (817) 222-5960.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This AD

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to Air Tractor Models 
AT-802 and AT-802A airplanes was published in the Federal Register as a 
notice of proposed rulemaking (NPRM) on October 18, 1996 (61 FR 54370). 
The action proposed to require revising the Airworthiness Limitations 
section of the applicable maintenance manual to change the life limit 
of the tail landing gear spring. The proposed action as specified in 
the NPRM would be accomplished by incorporating the revision (dated May 
24, 1996) to Section 6, Airworthiness Limitations, of the Air Tractor 
AT 802/802A Maintenance Manual.
    The NPRM resulted from analysis of the life limits of both the tail 
landing gear and main landing gear after a fatigue failure of the main 
landing gear on one of the affected airplanes. This analysis revealed 
that the life limit of the tail landing gear spring should be 3,000 
hours time-in-service (TIS) instead of 3,500 hours TIS to be consistent 
with the main landing gear spring.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposed rule or the FAA's determination of the cost to the public.

The FAA's Determination

    After careful review of all available information related to the 
subject presented above, the FAA has determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. The FAA has determined that these minor 
corrections will not change the meaning of the AD and will not add any 
additional burden upon the public than was already proposed.

Cost Impact

    The FAA estimates that 37 airplanes in the U.S. registry will be 
affected by this AD. An owner/operator of one of the affected airplanes 
holding at least a private pilot certificate is allowed to incorporate 
the manual revision as authorized by Sec. 43.7 of the Federal Aviation 
Regulations (14 CFR 43.7). However, the change in the life limit would 
require owners/operators of the affected airplanes to have the tail 
landing gear spring replaced every 3,000 hours TIS instead of every 
3,500 hours TIS. The owners/operators of the affected airplanes will be 
required to have this part replaced 500 hours TIS sooner than already 
required. The FAA has no way of determining the total hours TIS each 
owner/operator would accumulate over the life of the affected airplanes 
and, therefore, cannot calculate the number of additional tail landing 
gear springs each owner/operator would need to have replaced.

Regulatory Impact

    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.
    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) 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 final evaluation prepared for this 
action is contained 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.

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), 40113, 44701.

[[Page 7153]]

Sec. 39.13  [Amended]

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

97-04-11  Air Tractor, Inc.: Amendment 39-9935; 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 (dated May 24, 1996) to Section 6, 
Airworthiness Limitations, of the Air Tractor AT 802/802A 
Maintenance Manual.
    (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 time that provides an equivalent level of safety may be 
approved by the Manager, FAA, 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 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.
    (f) This amendment (39-9935) becomes effective on April 4, 1997.

    Issued in Kansas City, Missouri, on February 10, 1997.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-3839 Filed 2-14-97; 8:45 am]
BILLING CODE 4910-13-U