[Federal Register Volume 67, Number 126 (Monday, July 1, 2002)]
[Rules and Regulations]
[Pages 44024-44027]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-15937]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-CE-22-AD; Amendment 39-12789; AD 2002-13-02]
RIN 2120-AA64


Airworthiness Directives; Air Tractor, Inc. Models AT-300, AT-
301, AT-302, AT-400, and AT-400A Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to all Air Tractor, Inc. (Air Tractor) Models AT-300, AT-301, 
AT-302, and AT-400A airplanes that have aluminum spar caps; certain Air 
Tractor Models AT-400 airplanes that have aluminum spar caps; and all 
Models AT-300 and AT-301 airplanes that have aluminum spar caps and are 
or have been converted to turbine power. This AD requires you to 
inspect (one-time) the wing centerline splice joint for cracks and, if 
any crack is found, replace the affected wing spar lower cap. This AD 
also requires you to report the results of the inspection to the 
Federal Aviation Administration (FAA) and replace the wing spar lower 
caps after a certain amount of usage. This AD is the result of an 
incident on one of the affected airplanes where the wing separated from 
the airplane. Preliminary reports indicate that fatigue caused the 
lower aluminum spar cap to fail across the \3/8\-inch bolt hole (6.5 
inches outboard of the fuselage centerline in the centersplice 
connection). The actions specified by this AD are intended to detect 
and correct cracks in the wing centerline splice joint. If not detected 
and corrected, these cracks could eventually result in the wing 
separating from the airplane during flight.

DATES: This AD becomes effective on July 9, 2002.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulation as of July 
9, 2002.
    The FAA must receive any comments on this rule on or before August 
23, 2002.

ADDRESSES: Submit comments to FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2002-CE-22-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. You may view any 
comments at this location between 8 a.m. and 4 p.m., Monday through 
Friday, except Federal holidays. You may also send comments 
electronically to the following address: [email protected]. 
Comments sent electronically must contain ``Docket No. 2002-CE-22-AD'' 
in the subject line. If you send comments electronically as attached 
electronic files, the files must be formatted in Microsoft Word 97 for 
Windows or ASCII text.
    You may get the service information referenced in this AD from Air 
Tractor, Inc., P.O. Box 485, Olney, Texas 76374. You may view this 
information at FAA, Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 2002-CE-22-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: Andy McAnaul, Aerospace Engineer, FAA, 
Fort Worth Airplane Certification Office, 2601 Meacham Boulevard, Fort 
Worth, Texas 76193-0150; telephone: (817) 222-5156; facsimile: (817) 
222-5960.

SUPPLEMENTARY INFORMATION:

Discussion

What Events Have Caused This AD?

    Recently, the wing of an Air Tractor Model AT-400A separated from 
the airplane during flight. Investigation reveals that the right-hand 
lower spar cap failed due to fatigue at the \3/8\-inch outboard bolt, 
which is located 6.5 inches outboard of the fuselage centerline.
    The following airplanes have a similar type design to that of the 
accident airplane:

--All Models AT-300, AT-301, AT-302, and AT-400A airplanes that have 
aluminum spar caps;
--Air Tractor Models AT-400 airplanes, serial numbers 400-0244 through 
400-0415, that have aluminum spar caps; and
--All Models AT-300 and AT-301 airplanes that have aluminum spar caps 
and are or have been converted to turbine power.

    In addition, some airplanes have had Snow Engineering Co. Service 
Letter 55 incorporated. When incorporated, the affected area 
would be (1) the left and right side second outermost \7/16\-inch 
boltholes, which are located 5.38 inches from centerline; and (2) the 
left and right side outermost \3/8\-inch boltholes, which are located 
6.5 inches outboard from centerline.

What Are the Consequences if the Condition is Not Corrected?

    If not detected and corrected in a timely manner, cracks in the 
wing centerline splice joint could eventually result in the wing 
separating from the airplane during flight.

Is There Service Information That Applies to This Subject?

    Air Tractor has issued the following:

--Snow Engineering Co. Process Specification 197, dated February 23, 
2001; Revised May 1, 2002, and Revised May 3, 2002, which specify 
procedures for accomplishing an eddy current inspection of the wing 
centerline splice joint on the affected airplanes; and
--Snow Engineering Co. Service Letter 220, dated May 3, 2002, 
which

[[Page 44025]]

specifies the procedures for gaining access to perform the eddy current 
inspection.

The FAA's Determination and an Explanation of the Provisions of this AD

What Has FAA Decided?

    The FAA has reviewed all available information and determined that:

--The unsafe condition referenced in this document exists or could 
develop on other Air Tractor Models AT-300, AT-301, AT-302, AT-400, and 
AT-400A airplanes of the same type design;
--A one-time eddy current inspection should be accomplished on these 
airplanes to detect and correct cracks in the wing centerline splice 
joint;
--The wing lower spar caps should be replaced at a certain time; and
--Final rule; request for comments (immediately adopted rule) AD action 
should be taken to address this condition.

What Does This AD Require?

    This AD requires you to inspect (one-time) the wing centerline 
splice joint for cracks and, if any crack is found, replace the 
affected wing spar lower cap. This AD also requires you to report the 
results of the inspection to FAA and replace the wing spar lower caps 
after a certain amount of usage.
    You must accomplish these actions in accordance with the 
previously-referenced service information.
    We will evaluate the information received from the reporting 
requirement of this AD to determine whether additional rulemaking 
action should be taken. This could include repetitive inspections, 
parts replacement, modifications, or no further action.
    In preparation of this rule, we contacted type clubs and aircraft 
operators to obtain technical information and information on 
operational and economic impacts. We have included, in the rulemaking 
docket, a discussion of information that may have influenced this 
action.

Will I have the Opportunity To Comment Prior to the Issuance of the 
Rule?

    Because the unsafe condition described in this document could 
result in the wing separating from the airplane during flight, we find 
that notice and opportunity for public prior comment are impracticable. 
Therefore, good cause exists for making this amendment effective in 
less than 30 days.

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 your 
comments on the 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 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. Factual information that supports your ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether we need to take additional rulemaking 
action.

Are There Any Specific Portions of the AD I Should Pay Attention to?

    We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. You may view all comments we receive 
before and after the closing date of the rule in the Rules Docket. We 
will file a report in the Rules Docket that summarizes each FAA contact 
with the public that concerns the substantive parts of this AD.

How Can I be Sure 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. 2002-CE-22-AD.'' We will date stamp and mail 
the postcard back to you.

Regulatory Impact

Does This AD Impact Various Entities?

    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. Therefore, FAA has determined that this 
final rule does not have federalism implications under Executive Order 
13132.

Does This AD Involve a Significant Rule or Regulatory Action?

    We have determined that this regulation 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. It has been determined further that this action involves 
an emergency regulation under DOT Regulatory Policies and Procedures 
(44 FR 11034, February 26, 1979). If it is determined that this 
emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the Rules Docket (otherwise, an evaluation is 
not required). A copy of it, if filed, may be obtained 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

    Accordingly, under 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 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

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

2002-13-02 Air Tractor, Inc.: Amendment 39-12789; Docket No. 2002-
CE-22-AD.

    (a) What airplanes are affected by this AD? This AD applies to 
the following airplanes that are certificated in any category:
    (1) Models AT-300, AT-301, AT-302, and AT-400A airplanes, all 
serial numbers, that have aluminum spar caps;
    (2) Models AT-400 airplanes, serial numbers 400-0244 through 
400-0415, that have aluminum spar caps; and
    (3) Models AT-300 and AT-301 airplanes, all serial numbers that 
have aluminum spar caps and are or have been converted to turbine 
power.
    (b) Who must comply with this AD? Anyone who wishes to operate 
any airplane identified in paragraph (a)(1), (a)(2), or (a)(3) of 
this AD must comply with this AD.
    (c) What problem does this AD address? The actions specified by 
this AD are intended to detect and correct cracks in the wing 
centerline splice joint. If not detected and corrected, these cracks 
could eventually result in the wing separating from the airplane 
during flight.
    (d) What must I do to address this problem? To address this 
problem, you must accomplish the following actions:

[[Page 44026]]



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             Actions                  Compliance          Procedures
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(1) Inspect, using eddy current   For affected        Inspect in
 inspection methods, the wing      airplanes           accordance with
 centerline splice joint. The      (turbine-powered    Snow Engineering
 particular inspection area        or piston engine-   Co. Service
 depends on whether Snow           powered) with at    Letter 220, dated May
 55 is incorporated.      spar lower cap      3, 2002; and Snow
 Specifics are included in the     having 6,990 or     Enigneering Co.
 service information. The          more hours time-    Process
 inspection must be accompanied    in-service (TIS)    Specification
 by one of the following: (i) a    as of the           197, dated
 Level 2 or Level 3 inspector      effective date of   February 23,
 that is certified for eddy-       this AD: Inspect    2001; Revised May
 current inspection using the      within the next     1, 2002, or
 guidelines established by the     10 hours TIS        Revised May 3,
 American Society for              after July 9,       2002.
 Nondestructive Testing or MIL-    2002 (the
 STD-410; or (ii) A person         effective date of
 authorized to perform AD work     this AD), unless
 who has completed and passed      already
 the Air Tractor, Inc. training    accomplished
 course on Eddy Current            after
 Inspection on wing lower spar     accumulating
 caps.                             6,000 hours TIS;
                                   For affected
                                   piston engine-
                                   powered airplanes
                                   with at least one
                                   wing spar lower
                                   cap having less
                                   than 6,990 hours
                                   TIS as of the
                                   effective date of
                                   this AD: Inspect
                                   upon the
                                   accumulation of
                                   6,000 hours TIS
                                   or within the
                                   next 50 hours TIS
                                   after July 9,
                                   2002 (the
                                   effective date of
                                   this AD),
                                   whichever occurs
                                   later, unless
                                   already
                                   accomplished
                                   after
                                   accumulating
                                   6,000 hours TIS;
                                   or For affected
                                   turbine-powered
                                   aiplanes with at
                                   least one wing
                                   spar lower cap
                                   having less than
                                   6,999 hours TIS
                                   as of the
                                   effective day of
                                   this AD. Upon the
                                   accumulation of
                                   4,000 hours TIS
                                   or within the
                                   next 50 hours TIS
                                   after July 9,
                                   2002 (the
                                   effective date of
                                   this AD),
                                   whichever occurs
                                   later, unless
                                   already
                                   accomplished
                                   after accumlating
                                   4,000 hours TIS.
(2) If cracks are found during    Prior to further    In accordance with
 the inspection required by        flight after the    the instructions
 paragraph (d)(1) of this AD,      inspection          in the applicable
 replace the affected wing spar    required by         maintenance
 lower cap.                        paragraph (d)(1)    manual.
                                   of this AD.
(3) Report the results of the     If the inspection   Submit the form
 inspection in paragraph (d)(1)    is accomplished     (Figure 1 of
 of this AD to FAA. The Office     after the           paragraph (d)(3)
 of Management and Budget (OMB)    effective date of   of this AD) to
 approved the information          this AD: Within     FAA, Fort Worth
 collection requirements           10 days after the   Airplane
 contained in this regulation      inspection          Certification
 under the provisions of the       required in         Office, 2601
 Paperwork Reduction Act of 1980   paragraph (d)(1)    Meacham
 (44 U.S.C. 3501 et seq.) and      of this AD; or If   Boulevard, Fort
 assigned OMB Control Number       the inspection      Worth, Texas
 2120-0056.                        was already         76193-0150;
                                   accomplished        telephone: (817)
                                   prior to the        222-5156;
                                   effective date of   facsimile: (817)
                                   this AD: within     222-5960.
                                   the next 10 days
                                   after July 9,
                                   2002 (the
                                   effective date of
                                   this AD).
(4) Replace each wing spar lower  Replace each lower  In accordance with
 cap.                              cap upon the        instructions in
                                   accumulation of     the applicable
                                   7,000 hours TIS     maintenance
                                   on each wing spar   manual.
                                   lower cap or
                                   within the next
                                   200 hours TIS
                                   after July 9,
                                   2002 (the
                                   effective date of
                                   this AD),
                                   whichever occurs
                                   later.
------------------------------------------------------------------------

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[GRAPHIC] [TIFF OMITTED] TR01JY02.049

    (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 paragraphs 
(a)(1), (a)(2), and (a)(3) 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) 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 that the 
following is adhered to:
    (1) Operate in day visual flight rules (VFR) only.
    (2) Ensure that the hopper is empty.
    (3) Limit airspeed to 135 miles per hour (mph) indicated 
airspeed (IAS).
    (4) Avoid any unnecessary g-forces.
    (5) Avoid areas of turbulence.
    (6) Plan the flight to follow the most direct route.
    (g) Are any service bulletins incorporated into this AD by 
reference? Replacement and inspection actions required by this AD 
must be done in accordance with Snow Engineering Co. Service Letter 
220, dated May 3, 2002; and Snow Engineering Co. Process 
Specification 197, dated February 23, 2001, Revised May 1, 2002, or 
Revised May 3, 2002. The Director of the Federal Register approved 
this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 
51. You can get copies from Air Tractor, Inc., P.O. Box 485, Olney, 
Texas 76374. You may view 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.
    (h) When does this amendment become effective? This amendment 
becomes effective on July 9, 2002.

    Issued in Kansas City, Missouri, on June 18, 2002.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-15937 Filed 6-28-02; 8:45 am]
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