[Federal Register Volume 65, Number 147 (Monday, July 31, 2000)]
[Rules and Regulations]
[Pages 46567-46569]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-18995]



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  Federal Register / Vol. 65, No. 147 / Monday, July 31, 2000 / Rules 
and Regulations  

[[Page 46567]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-CE-40-AD; Amendment 39-11837; AD 2000-14-51]
RIN 2120-AA64


Airworthiness Directives; Air Tractor, Inc. Models AT-501, AT-
502, and AT-502A Airplanes

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This document publishes in the Federal Register an amendment 
adopting emergency Airworthiness Directive (AD) 2000-14-51. The Federal 
Aviation Administration (FAA) previously sent emergency AD 2000-14-51 
to all known U.S. owners and operators of Air Tractor Models AT-501, 
AT-502, and AT-502A airplanes. This AD requires you to inspect the wing 
lower spar cap for cracks and modify or replace any cracked lower spar 
cap. This AD is the result of an accident report of an Air Tractor 
Model AT-502A airplane where the wing separated in flight. The actions 
specified by this AD are intended to detect and correct fatigue cracks 
in the wing lower spar cap, which could result in an in-flight 
separation of the wing from the airplane.

DATES: The AD becomes effective August 4, 2000, to all affected persons 
who did not receive emergency AD 2000-14-51, issued July 3, 2000. 
Emergency AD 2000-14-51 contained the requirements of this amendment 
and became effective immediately upon receipt.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulation as of August 
4, 2000.
    The FAA must receive any comments on this rule on or before 
September 15, 2000.

ADDRESSES: Submit comments in triplicate to FAA, Central Region, Office 
of the Regional Counsel, Attention: Rules Docket No. 2000-CE-40-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. You may read comments 
and information related to this AD at this location between 8 a.m. and 
4 p.m., Monday through Friday, except holidays.
    You may get the service information referenced in this AD from Air 
Tractor, Incorporated, P.O. Box 485, Olney, Texas 76374. You may 
examine this information at FAA, Central Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2000-CE-40-AD, 901 Locust, Room 
506, 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: Rob Romero, Aerospace Engineer, FAA, 
Fort Worth ACO, 2601 Meacham Boulevard, Fort Worth, Texas 76193-0150; 
telephone: (817) 222-5102; facsimile: (817) 222-5960.

SUPPLEMENTARY INFORMATION:

Discussion

What Has Happened So Far?

    The FAA has received a report of an accident of an Air Tractor 
Model AT-502A airplane where the wing separated in flight. 
Investigation revealed that the wing lower spar cap was cracked at the 
wing center splice connection. We surveyed the Air Tractor Models AT-
501, AT-502, and AT-502A airplane fleet and discovered 2 other 
airplanes that have had similar cracks in the lower spar caps.
    On July 3, 2000, we issued emergency AD 2000-14-51. This AD 
directed the following:

--Repetitively inspect each wing lower spar cap for cracks; and
--Modify or replace any cracked lower spar cap, as specified in the 
service information.

    Accomplishment of this action is required in accordance with the 
procedures in Snow Engineering Co. Service Letter #197, dated June 13, 
2000.

Why Is It Important To Publish This AD?

    The FAA found that immediate corrective action was required, notice 
and opportunity for prior public comment were impracticable and 
contrary to the public interest, and good cause existed to make the AD 
effective immediately by individual letters issued on July 3, 2000, to 
all known U.S. operators of Air Tractor, Inc. Models AT-501, AT-502, 
and AT-502A airplanes. These conditions still exist, and the AD is 
published in the Federal Register as an amendment to section 39.13 of 
the Federal Aviation Regulations (14 CFR 39.13) to make it effective as 
to all persons.

Comments Invited

How Do I Comment on This AD?

    Although this action is in the form of a final rule and was not 
preceded by notice and opportunity for public comment, FAA invites 
comments on this rule. You may submit whatever written data, views, or 
arguments you choose. You need to include the rule's docket number and 
submit your comments in triplicate to the address specified under the 
caption ADDRESSES. We will consider all comments received on or before 
the closing date specified above. We may amend this rule in light of 
comments received.

How Can We Communicate More Clearly With You?

    The FAA is reviewing the writing style we currently use in 
regulatory documents, in response to the Presidential memorandum of 
June 1, 1998. That memorandum requires federal agencies to communicate 
more clearly with the public. We are interested in your comments on the 
ease of understanding this document, and any other suggestions you 
might have to improve the clarity of FAA communications that affect 
you. You can get more information about the Presidential memorandum and 
the plain language initiative at http://www.faa.gov/language/.
    The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. You may examine all comments we 
receive in the Rules Docket. We will file a report in the Rules Docket 
that summarizes each

[[Page 46568]]

FAA contact with the public that concerns the substantive parts of this 
AD.

How Can I Be Sure the FAA Receives My Comment?

    If you want us to acknowledge the receipt of your comments, you 
must include a self-addressed, stamped postcard. On the postcard, write 
``Comments to Docket No. 2000-CE-40-AD.'' We will date stamp and mail 
the postcard back to you.

Regulatory Impact

How Does This AD Impact Relations Between Federal and State 
governments?

    These regulations 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. The FAA has determined that this final 
rule does not have federalism implications under Executive Order 13132.

How Does This Action Involve an Emergency Situation?

    The FAA determined that this is an emergency regulation that must 
be issued immediately to correct an unsafe condition in aircraft, and 
is not a significant regulatory action under Executive Order 12866. 
This action involves an emergency regulation under Department of 
Transportation (DOT) Regulatory Policies and Procedures (44 FR 11034, 
February 26, 1979). The FAA will prepare a final regulatory evaluation 
if we determine that this emergency regulation is significant under DOT 
Regulatory Policies and Procedures. You may obtain a copy of the 
evaluation (if required) from the Rules Docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration (FAA) 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 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

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

2000-14-51  Air Tractor Incorporated: Amendment 39-11837; Docket No. 
2000-CE-40-AD.

    (a) What airplanes are affected by this AD? This AD applies to 
the following Air Tractor airplane models and serial numbers:

------------------------------------------------------------------------
        Model                           Serial numbers
------------------------------------------------------------------------
AT-501..............  501-002 through 501-0060 that have been converted
                       to turboprop power.
AT-502..............  502-003 through 502-0061, except those that have
                       been upgraded to the 8,000-pound gross weight
                       configuration through the incorporation of Snow
                       Engineering Co. Service Letter #80J.
AT-502A.............  All serial numbers.
------------------------------------------------------------------------

    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the above airplanes on the U.S. Register must comply with 
this AD.
    (c) What problem does this AD address? This AD is intended to 
detect and correct fatigue cracks in the wing lower spar cap, which 
could result in an in-flight separation of the wing from the 
airplane.
    (d) What actions must I accomplish to address this problem? To 
address this problem, you must accomplish the following:

------------------------------------------------------------------------
           Action                     When               Procedures
------------------------------------------------------------------------
(1) Initial Inspection:       At whichever of the   Accomplish this
 Visually inspect the wing     following that is     inspection in
 lower spar cap at the wing    applicable:           accordance with the
 center splice connection     (i) For the Models     Inspection
 for cracks.                   AT-501 and AT-502     Requirements
                               airplanes: Upon       section of Snow
                               accumulating 4,000    Engineering Co.
                               hours time-in-        Service Letter
                               service (TIS) on      #197, dated June
                               each wing or within   13, 2000.
                               the next 10 hours
                               TIS after the
                               effective date of
                               this AD, whichever
                               occurs later; or.
                              (ii) For the Model
                               AT-502A airplanes:
                               Upon accumulating
                               3,000 hours TIS on
                               each wing or within
                               the next 10 hours
                               TIS after the
                               effective date of
                               this AD, whichever
                               occurs later.
(2) Repetitive Inspections:   For all affected      Accomplish these
 Inspect using visual or       airplanes,            inspections in
 ultrasonic methods the wing   accomplish the        accordance with the
 lower spar cap at center      repetitive            Inspection
 splice connection for         inspections as        Requirements
 cracks.                       follows:              section of Snow
                              (i) Visually: Within   Engineering Co. the
                               50 hours TIS after    Service Letter
                               the initial           #197, dated June
                               inspection and        13, 2000.
                               thereafter at
                               intervals not to
                               exceed 50 hours
                               TIS; or.
                              (ii) Using
                               ultrasonic methods:
                               Within 400 hours
                               TIS after the
                               initial inspection
                               and thereafter at
                               intervals not to
                               exceed 400 hours
                               TIS.
(3) Replace or modify any     Prior to further      Accomplish the
 cracked wing lower spar       flight after the      replacement and
 cap, as specified in the      inspection where      modification as
 service information.          the crack is found.   follows:
                                                    (i) Replacement:
                                                     Remove the wing
                                                     with the cracked
                                                     lower spar cap and
                                                     return to Air
                                                     Tractor for spar
                                                     cap replacement.
                                                     Immediately notify
                                                     Air Tractor that
                                                     you are sending the
                                                     wing if the cracked
                                                     spar cap can not be
                                                     modified.

[[Page 46569]]

 
                                                    (ii) Modification:
                                                     In accordance with
                                                     the TERMINATING
                                                     ACTION section of
                                                     Snow Engineering
                                                     Co. Service Letter
                                                     #197, dated June
                                                     13, 2000.
(4) Modifying each lower      This terminating      Accomplish in
 spar cap is considered        action may be         accordance with the
 terminating action for the    accomplished at any   TERMINATING ACTION
 repetitive inspection         time provided the     section of Snow
 requirement. This             lower spar caps are   Engineering Co.
 modification can only be      not cracked.          Service Letter
 accomplished if the lower                           #197, dated June
 spar caps are inspected                             13, 2000.
 before the modification is
 incorporated and:
(i) no cracks are found; or
(ii) any crack found can be
 removed by drilling the
 hole to the next larger
 size.
------------------------------------------------------------------------

    (e) Can I comply with this AD in any other way? You may use an 
alternative method of compliance or adjust the compliance time if:
    (1) Your alternative method of compliance provides an equivalent 
level of safety; and
    (2) The Manager, Fort Worth Airplane Certification Office (ACO), 
approves your alternative. Submit your request through an FAA 
Principal Maintenance Inspector. The inspector may add comments 
before sending it to the Manager, Fort Worth ACO.

    Note: This AD applies to each airplane identified in paragraph 
(a) of this AD, 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 (e) 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 you have not eliminated the unsafe condition, specific 
actions you propose to address it.

    (f) Where can I get information about any already-approved 
alternative methods of compliance? Contact Rob Romero, Aerospace 
Engineer, FAA, Fort Worth ACO, 2601 Meacham Boulevard, Fort Worth, 
Texas 76193-0150; telephone: (817) 222-5102; facsimile: (817) 222-
5960.
    (g) What if I need to fly the airplane to another location to 
comply with this AD? The FAA can issue a special flight permit under 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate your airplane to a location where 
you can accomplish the requirements of this AD provided you comply 
with the following:
    (1) The hopper is empty;
    (2) Vne is reduced to 138 miles per hour (mph) (120 knots) 
indicated airspeed (IAS); and
    (3) Flight into known turbulence is prohibited.
    (h) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with Snow Engineering Co. Service Letter #197, dated June 13, 2000. 
The Director of the Federal Register approved this incorporation by 
reference under 5 U.S.C. 552(a) and 1 CFR part 51. You may get 
copies of this document from Air Tractor, Incorporated, P.O. Box 
485, Olney, Texas 76374. You may look at copies at FAA, Central 
Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas 
City, Missouri, or at the Office of the Federal Register, 800 North 
Capitol Street, NW, suite 700, Washington, DC.
    (i) When does this AD become effective? This AD becomes 
effective August 4, 2000, to all affected persons who did not 
receive emergency AD 2000-14-51, issued July 3, 2000. Emergency AD 
2000-14-51 contained the requirements of this amendment and became 
effective immediately upon receipt.

    Issued in Kansas City, Missouri, on July 20, 2000.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-18995 Filed 7-28-00; 8:45 am]
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