[Federal Register Volume 75, Number 250 (Thursday, December 30, 2010)]
[Rules and Regulations]
[Pages 82219-82228]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-32905]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0827; Directorate Identifier 2010-CE-029-AD;
Amendment 39-16552; AD 2010-17-18 R1]
RIN 2120-AA64
Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-
802A Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: We are revising an existing airworthiness directive (AD) for
Air Tractor, Inc. (Air Tractor) Models AT-802 and AT-802A airplanes.
That AD currently requires you to repetitively inspect (using the eddy
current method) the two outboard fastener holes in both of the wing
main spar lower caps at the center splice joint for cracks and repair
or replace any cracked spar, and changes the safe life for certain
serial (SN) ranges. This AD retains the actions of AD 2010-17-18 and
reduces the applicability from all serial numbers beginning with SN-
0001 as required by the previous AD to SN-0001 through SN-0269. This AD
was prompted by our evaluation of a comment from David Ligon, Air
Tractor, and our determination that we should reduce the applicability
from that already required by the previous AD. We are issuing this AD
to detect and correct cracks in the wing main spar lower cap at the
center splice joint, which could result in failure of the spar cap and
lead to wing separation and loss of control of the airplane.
DATES: This AD is effective January 14, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 9,
2010 (75 FR 52255, August 25, 2010).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of April
21, 2006 (71 FR 19994, April 19, 2006).
We must receive any comments on this AD by February 14, 2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-
[[Page 82220]]
30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue,
SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Air Tractor,
Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564-5616; fax:
(940) 564-5612; E-mail: [email protected]; Internet: http://www.airtractor.com. You may review copies of the referenced service
information at the FAA, Small Airplane Directorate, 901 Locust, Kansas
City, Missouri 64106. For information on the availability of this
material at the FAA, call 816-329-4148.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (phone: 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Andrew McAnaul, Aerospace Engineer,
ASW-150 (c/o MIDO-43), 10100 Reunion Place, Suite 650, San Antonio,
Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370; e-mail:
[email protected].
SUPPLEMENTARY INFORMATION:
Discussion
On August 11, 2010, we issued AD 2010-17-18, amendment 39-16412 (75
FR 52255, August 25, 2010), for all Air Tractor Models AT-802 and AT-
802A airplanes. That AD requires you to repetitively inspect (using the
eddy current method) the two outboard fastener holes in both of the
wing main spar lower caps at the center splice joint for cracks and
repair or replace any cracked spar, and changes the safe life for
certain SN ranges. That AD resulted from the FAA's evaluation of
service information issued by Air Tractor and our determination that we
needed to add inspections, add modifications, and change the safe life
for certain SN ranges. We issued that AD to detect and correct cracks
in the wing main spar lower cap at the center splice joint, which could
result in failure of the spar cap and lead to wing separation and loss
of control of the airplane.
Actions Since AD was Issued
Since we issued AD 2010-17-18, we have evaluated a comment from
David Ligon, Air Tractor, and determined that we should reduce the
applicability from all serial numbers beginning with SN-0001 as
required by the previous AD to SN-0001 through SN-0269. Airplane SN-
0270 and subsequent wing main spar components are life limited at
11,700 hours time-in-service as described in Air Tractor, Inc. AT 802/
802A Airworthiness Limitations, Pages 6-i, 6-1, and 6-2, dated:
September 16, 2009.
Relevant Service Information
We reviewed the following service information from Snow Engineering
Co.:
Service Letter 80GG, revised December 21, 2005;
Service Letter 284, dated October 4, 2009;
Service Letter 281, dated August 1, 2009;
Service Letter 245, dated April 25, 2005;
Service Letter 240, dated September 30, 2004;
Process Specification 197, page 1, revised June
4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated
May 3, 2002;
Drawing Number 20995, Sheet 3, dated November 25, 2005;
Drawing Number 20995, Sheet 2, Rev. D., dated November 25,
2005; and
Drawing Number 20975, Sheet 4, Rev. A., dated January 7,
2009.
The service information describes procedures for the following
actions:
Inspection (repetitively) of the two outboard fastener
holes in both of the wing main spar lower caps at the center splice
joint for cracks;
Repair or replacement of any cracked spar cap; and
Modification option to extend the safe life limit.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
AD Requirements
This AD requires accomplishing the actions specified in the service
information described previously. The AD also requires sending the
inspection results (if cracks are found) to Andrew McAnaul, Aerospace
Engineer, ASW-150 (c/o MIDO-43), 10100 Reunion Place, Suite 650, San
Antonio, Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because the
public has already had the opportunity to comment on the actions of
this unsafe condition. This action only reduces the applicability from
that already required by the previous AD. Therefore, we find that
notice and opportunity for prior public comment are unnecessary and
that good cause exists for making this amendment effective in less than
30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
the docket number FAA-2010-0827 and directorate identifier 2010-CE-029-
AD at the beginning of your comments. We specifically invite comments
on the overall regulatory, economic, environmental, and energy aspects
of this AD. We will consider all comments received by the closing date
and may amend this AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Costs of Compliance
We estimate that this AD affects 121 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
[[Page 82221]]
Estimated Costs
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Action Labor cost Parts cost Cost per product Cost on U.S. operators
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Eddy current inspection........... $500 to $800........ Not Applicable...... $500 to $800....................... $60,500 to $96,800
Spar cap replacement (two spars).. 495 work-hours x $85 $39,100 (two spars). $81,175............................ $9,822,175
per hour = $42,075.
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We estimate the following costs to do any necessary center splice
plate installation that would be required based on the results of the
inspection. We have no way of determining the number of aircraft that
might need this center splice plate installation:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Center splice plate installation.............. 185 work-hours x $85 per hour = $4,300 $20,025
$15,725.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary extended
splice block installation that would be required based on the results
of the inspection. We have no way of determining the number of aircraft
that might need this extended splice block installation:
On-Condition Costs
------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
------------------------------------------------------------------------
Extended splice block 70 work- $3,200......... $9,150
installation. hours x $85
per hour =
$5,950
------------------------------------------------------------------------
We estimate the following costs to do any necessary cold-work
lower spar cap fastener holes that would be required based on the
results of the inspection. We have no way of determining the number of
aircraft that might need this cold-work lower spar cap fastener holes:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Cold-work lower spar cap fastener holes....... $1,350................................ Not $1,350
Applicable
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD 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.
For the reasons discussed above, I certify that this AD:
(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),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends part 39 of the Federal Aviation Regulations (14 CFR part
39) as follows:
[[Page 82222]]
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2010-17-18, amendment 39-16412 (75 FR 52255, August 25, 2010) and
adding the following new AD:
2010-17-18 R1 Air Tractor, Inc.: Amendment 39-16552; Docket No. FAA-
2010-0827; Directorate Identifier 2010-CE-029-AD.
Effective Date
(a) This AD is effective January 14, 2011.
Affected ADs
(b) This AD revises AD 2010-17-18, Amendment 39-16412.
Applicability
(c) This AD affects Air Tractor, Inc. Models AT-802 and AT-802A
airplanes, serial numbers (SNs) -0001 through -0269, that are:
(1) certificated in any category;
(2) engaged in agricultural dispersal operations, including
those airplanes that have been converted from fire fighting to
agricultural dispersal or airplanes that convert between fire
fighting and agricultural dispersal;
(3) not equipped with the factory-supplied computerized fire
gate (part number (P/N) 80540); and
(4) not engaged in only full-time fire fighting.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 57: Wings.
Unsafe Condition
(e) This AD was prompted by our evaluation of a comment from
David Ligon, Air Tractor, and our determination that we should
reduce the applicability from the all serial numbers beginning with
SN -0001 as required by the previous AD to SN -0001 through SN-0269.
We are issuing this AD to detect and correct cracks in the wing main
spar lower cap at the center splice joint, which could result in
failure of the spar cap and lead to wing separation and loss of
control of the airplane.
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
(g) To address this problem for Models AT-802 and AT-802A
airplanes, SNs -0001 through -0091, you must do the following,
unless already done:
Table 1--Actions, Compliance, and Procedures
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Eddy current inspect for Initially inspect Follow Snow
cracks the center splice upon accumulating Engineering Co.
joint outboard two fastener 1,700 hours time-in- Process
holes in both the left and service (TIS) or Specification
right wing main spar lower within the next 50 197, page
caps. hours TIS after 1, revised June 4,
April 21, 2006 (the 2002; pages 2
effective date of through 4, dated
AD 2006-08-09), February 23, 2001;
whichever occurs and page 5, dated
later, and May 3, 2002.
repetitively
thereafter at
intervals not to
exceed 800 hours
TIS. If, before
September 9, 2010
(the effective date
of AD
2010[dash]17[dash]1
8), you installed
the center splice
plate and extended
8-bolt splice
blocks, use the
inspection
compliance times
found in paragraph
(g)(5) of this AD.
(2) If you find any cracks Before further Follow Snow
as a result of any flight after the Engineering Co.
inspection required in inspection where a Service Letter
paragraph (g)(1) of this crack was found. 284, dated
AD, do the following If, before the October 4, 2009;
actions: airplane reaches a Snow Engineering
(i) For cracks that can be total of 3,200 Co. Process
repaired, repair the hours TIS, you Specification
airplane by doing the repair your 197, page
following actions:. airplane following 1, revised June 4,
(A) Install center splice paragraph (g)(2)(i) 2002; pages 2
plate, P/N 20997-2, and of this AD, you through 4, dated
extended 8[dash]bolt splice must do the eddy February 23, 2001;
blocks, P/N 20985-1 & -2, current inspections and page 5, dated
and cold-work the lower following the May 3, 2002; Snow
spar cap fastener holes; compliance times Engineering Co.
and. found in paragraph Drawing Number
(B) Eddy current inspect for (g)(5) of this AD. 20995, Sheet 2,
cracks the center splice If, at 3,200 hours Rev. D., dated
joint outboard two fastener TIS or after, you November 25, 2005;
holes in both the left and repair your and Snow
right wing main spar lower airplane following Engineering Co.
caps. This eddy current paragraph (g)(2)(i) Service Letter
inspection is required as of this AD, this 240, dated
part of the modification repair terminates September 30, 2004.
and is separate from the the inspection
inspections required in requirements of
paragraph (g)(1) of this AD. paragraph (g)(1) of
(ii) For cracks that cannot this AD.
be repaired by
incorporating the
modification specified
above, do the actions to
replace the lower spar caps
and associated parts listed
following the procedures
identified in paragraph
(g)(3) of this AD.
[[Page 82223]]
(3) Replace the wing main (i) Do the Follow Snow
spar lower caps, the web replacement at Engineering Co.
plates, the center joint whichever of the Service Letter
splice blocks and hardware, following 284, dated
and the wing attach angles compliance times October 4, 2009;
and hardware, and install occurs first: Snow Engineering
the steel web splice plate. (A) Before further Co. Service Letter
This replacement terminates flight when cracks 80GG,
the repetitive inspections are found that revised December
required in paragraph cannot be repaired 21, 2005; Snow
(g)(1) of this AD. by incorporating Engineering Co.
the modification in Drawing Number
paragraph (g)(2)(i) 20975, Sheet 4,
of this AD; or. Rev. A, dated
(B) Before or when January 7, 2009.
the airplane
reaches the wing
main spar lower cap
safe life of a
total of 4,100
hours TIS or within
the next 50 hours
TIS after September
9, 2010 (the
effective date of
AD
2010[dash]17[dash]1
8), whichever
occurs later..
(ii) After this
replacement the new
spar safe life is
11,700 hours TIS.
If, before
September 9, 2010
(the effective date
of AD
2010[dash]17[dash]1
8), an airplane
main spar lower cap
was replaced with P/
N 21083-1/-2, the
spar safe life for
that P/N spar cap
is 8,000 hours TIS
until the main spar
lower cap is
replaced with P/N
21118-1/-2. The new
spar safe life for
P/N 21118-1/-2 is
11,700 hours..
(iii) To extend the
initial 4,100 hours
TIS safe life of
the wing main spar
lower cap to a
total of 8,000
hours TIS, you may
incorporate the
optional
modification
specified in
paragraph (g)(4) of
this AD..
(4) To extend the safe life Modify at whichever Follow Snow
of the wing main spar lower of the following Engineering Co.
cap to a total of 8,000 compliance times Service Letter
hours TIS, you may occurs first: 284, dated
incorporate the following (A) Before further October 4, 2009;
optional modification. This flight after any Snow Engineering
modification terminates the inspection required Co. Process
repetitive inspections in paragraph (g)(1) Specification
required in paragraph of this AD where a 197, page
(g)(1) of this AD, unless crack is found. If 1, revised June 4,
you performed the you modify your 2002; pages 2
modification before the airplane before the through 4, dated
airplane reaches a total of airplane reaches a February 23, 2001;
3,200 hours TIS to repair total of 3,200 and page 5, dated
cracks: hours TIS to repair May 3, 2002; Snow
(i) Install center splice cracks as required Engineering Co.
plate, P/N 20997-2, and in paragraph Drawing Number
extended 8[dash]bolt splice (g)(2)(i) of this 20995, Sheet 2,
blocks, P/N 20985-1 & -2, AD, you must do the Rev. D., dated
and cold-work the lower eddy current November 25, 2005;
spar cap fastener holes; inspections and Snow
and. following the Engineering Co.
(ii) Eddy current inspect compliance times Service Letter
for cracks the center found in paragraph 240, dated
splice joint outboard two (g)(5) of this AD.. September 30, 2004.
fastener holes in both the (B) Between 3,200
left and right wing main hours TIS and 4,100
spar lower caps. This eddy hours TIS..
current inspection is
required as part of the
modification and is
separate from the
inspections required in
paragraph (g)(1) of this
AD..
------------------------------------------------------------------------
(5) If, before September 9, 2010 (the effective date of AD
2010-17-18) or as a result of performing the repair for cracks
following paragraph (g)(2) of this AD, you installed the center
splice plate and extended 8-bolt splice blocks, use the following
table for compliance times to do the eddy current inspections
required in paragraph (g)(1) of this AD. If you find any cracks as a
result of any inspection following the compliance times in the
following table, you must do the replacement action in paragraph
(g)(2)(ii) of this AD:
Table 2--Eddy Current Inspection Compliance Times
------------------------------------------------------------------------
Repetitively inspect
thereafter at
Condition of the airplane Initially inspect intervals not to
exceed
------------------------------------------------------------------------
(i) If the airplane has When the airplane 1,200 hours TIS
already had the center reaches a total of until the 8,000
splice plate and extended 2,400 hours TIS hours TIS spar
8[dash]bolt splice blocks after the replacement time.
installed at or after 3,200 modification or
hours TIS but the fastener within the next 100
holes have not been cold days after
worked, at any time you may September 9, 2010
cold work the fastener (the effective date
holes to terminate the of AD
repetitive inspection 2010[dash]17[dash]1
requirements of this 8), whichever
paragraph. occurs later.
(ii) Before reaching 3,200 When the airplane 1,200 hours TIS.
hours TIS, the airplane had reaches a total of Upon reaching 4,800
the center splice plate and 2,400 hours TIS hours TIS after the
extended 8-bolt splice after the modification,
blocks already installed modification or inspect
but the fastener holes have within the next 100 repetitively
not been cold worked. days after thereafter at
September 9, 2010 intervals not to
(the effective date exceed 600 hours
of AD TIS until the 8,000
2010[dash]17[dash]1 hours TIS spar
8), whichever replacement time.
occurs later.
[[Page 82224]]
(iii) Before reaching 3,200 When the airplane 600 hours TIS until
hours TIS, the airplane had reaches a total of the 8,000 hours TIS
the center splice plate and 4,800 hours TIS spar replacement
extended 8-bolt splice after the time.
blocks installed and the modification or
fastener holes have been within the next 100
cold worked. days after
September 9, 2010
(the effective date
of AD
2010[dash]17[dash]1
8), whichever
occurs later.
------------------------------------------------------------------------
(h) To address this problem for AT-802 and AT-802A airplanes,
SNs-0092 through -0101, you must do the following, unless already
done:
Table 3--Actions, Compliance, and Procedures
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Eddy current inspect for Initially inspect Follow Snow
cracks the center splice upon accumulating Engineering Co.
joint outboard two fastener 1,700 hours TIS or Service Letter
holes in both the left and within the next 50 284, dated
right wing main spar lower hours TIS after October 4, 2009;
caps. September 9, 2010 and Snow
(the effective date Engineering Co.
of AD 2010-17-18), Process
whichever occurs Specification
later, and 197, page
repetitively 1, revised June 4,
thereafter at 2002; pages 2
intervals not to through 4, dated
exceed 800 hours February 23, 2001;
TIS. If the center and page 5, dated
splice plate, P/N May 3, 2002.
20994-2, is
installed as
specified in
paragraph (h)(4) of
this AD, do the
repetitive
inspections at
intervals not to
exceed 2,000 hours
TIS.
(2) If you find any cracks Before further Follow Snow
as a result of any flight after the Engineering Co.
inspection required by inspection where a Service Letter
paragraph (h)(1) of this crack was found. 284, dated
AD, do the following This repair October 4, 2009;
actions. This repair modification in and Snow
modification terminates the paragraph (h)(2)(i) Engineering Co.
repetitive inspections of this AD extends Process
required in paragraph the safe life of Specification
(h)(1) of this AD: the wing main spar 197, page
(i) For cracks that can be lower cap to a 1, revised June 4,
repaired, repair the total of 8,000 2002; pages 2
airplane by doing the hours TIS. through 4, dated
following actions:. February 23, 2001;
(A) Install the 9-bolt and page 5, dated
splice blocks and cold-work May 3, 2002, Snow
the lower spar cap fastener Engineering Co.
holes;. Service Letter
(B) Eddy current inspect for 281, dated
cracks the center splice August 1, 2009; and
joint outboard two fastener Snow Engineering
holes in both the left and Co. Drawing Number
right wing main spar lower 20995, Sheet 3,
caps. This eddy current dated November 25,
inspection is required as 2005.
part of the repair and is
separate from the
inspections required in
paragraph (h)(1) of this
AD; and.
(C) Install the center
splice plate, P/N 20994-2,
per paragraph (h)(4) if not
already installed..
(ii) For cracks that cannot
be repaired by doing the
actions in paragraph
(h)(2)(i) of this AD,
replace the lower spar caps
and associated parts listed
following the procedures
identified in paragraph
(h)(3) of this AD..
(3) Replace the wing main (i) Do the Follow Snow
spar lower caps, the web replacement at Engineering Co.
plates, the center joint whichever of the Service Letter
splice blocks and hardware, following 284, dated
and the wing attach angles compliance times October 4, 2009;
and hardware, and install occurs first: Snow Engineering
the steel web splice plate. (A) Before further Co. Service Letter
This replacement terminates flight when cracks 80GG,
the repetitive inspections are found that revised December
required in paragraph cannot be repaired 21, 2005; Snow
(h)(1) of this AD. by incorporating Engineering Co.
the modification in Drawing Number
paragraph (h)(2)(i) 20975, Sheet 4,
of this AD; or. Rev. A, dated
(B) Before or when January 7, 2009.
the airplane
reaches the wing
main spar lower cap
safe life of a
total of 4,100
hours TIS or within
the next 50 hours
TIS after September
9, 2010 (the
effective date of
AD 2010-17-18),
whichever occurs
later..
(ii) To extend the
initial 4,100 hours
TIS safe life of
the wing main spar
lower cap to a
total of 8,000
hours TIS, you may
incorporate the
optional
modification
specified in
paragraph (h)(4) of
this AD..
(iii)After
replacement of the
old spar with the
new lower spar cap,
P/N 21118-1/-2, the
new spar safe life
is 11,700 hours
TIS..
[[Page 82225]]
(4) To extend the safe life Before the airplane Follow Snow
of the wing main spar lower reaches a total of Engineering Co.
cap to a total of 8,000 4,100 hours TIS. Service Letter
hours TIS, you may After installation 284, dated
incorporate the following of the center October 4, 2009;
optional modification: splice plate, P/N Snow Engineering
(i) Install center splice 20994-2, do the Co. Process
plate, P/N 20994-2, if not repetitive Specification
already installed as part inspections 197, page
of a repair, and cold-work required in 1, revised June 4,
the lower spar cap fastener paragraph (h)(1) at 2002; pages 2
holes; and. intervals not to through 4, dated
(ii) Eddy current inspect exceed 2,000 hours February 23, 2001;
for cracks the center TIS. If as of and page 5, dated
splice joint outboard two September 9, 2010 May 3, 2002; Snow
fastener holes in both the (the effective date Engineering Co.
left and right wing main of AD 2010-17-18) Drawing Number
spar lower caps. This eddy you have already 20975, Sheet 4,
current inspection is exceeded the 4,100 Rev. A., dated
required as part of the hours TIS threshold January 7, 2009;
modification and is for extending the and Snow
separate from the safe life to 8,000 Engineering Co.
inspections required in hours TIS, you may Service Letter
paragraph (h)(1) of this be eligible for an 245, dated
AD.. alternative method April 25, 2005.
of compliance
following paragraph
(n) in this AD.
(5) If you find any cracks Before further Follow Snow
as a result of any flight after the Engineering Co.
repetitive inspection inspection where a Service Letter
required by paragraph crack was found. 284, dated
(h)(4) of this AD, do the October 4, 2009;
following actions. This and Snow
repair modification Engineering Co.
terminates the repetitive Process
inspections required in Specification
paragraph (h)(4) of this 197, page
AD: 1, revised June 4,
(i) For cracks that can be 2002; pages 2
repaired, repair the through 4, dated
airplane by doing the February 23, 2001;
following actions:. and page 5, dated
(A) Install the 9-bolt May 3, 2002, Snow
splice blocks and cold-work Engineering Co.
the lower spar cap fastener Service Letter
holes; and. 281, dated
(B) Eddy current inspect for August 1, 2009; and
cracks the center splice Snow Engineering
joint outboard two fastener Co. Drawing Number
holes in both the left and 20995, Sheet 3,
right wing main spar lower dated November 25,
caps. This eddy current 2005.
inspection is required as
part of the repair and is
separate from the
inspections required in
paragraph (h)(1) of this
AD..
(ii) For cracks that cannot
be repaired by doing the
actions in paragraph
(h)(5)(i) of this AD,
replace the lower spar caps
and associated parts listed
following the procedures
identified in paragraph
(h)(3) of this AD..
------------------------------------------------------------------------
(i) To address this problem for AT-802 and AT-802A airplanes,
SNs -0102 through -0178, you must do the following, unless already
done:
Table 4--Actions, Compliance, and Procedures
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Do an initial eddy Before the airplane Follow Snow
current inspection for reaches a total of Engineering Co.
cracks of the center splice 5,500 hours TIS or Process
joint outboard two fastener within the next 50 Specification
holes in both the left and hours TIS after 197, page
right wing main spar lower September 9, 2010 1, revised June 4,
caps. After this initial (the effective date 2002; pages 2
inspection, you may do the of AD through 4, dated
optional cold-working of 2010[dash]17[dash]1 February 23, 2001;
the lower spar cap fastener 8), whichever and page 5, dated
holes to increase the hours occurs later. May 3, 2002; Snow
TIS between repetitive Engineering Co.
inspections required in Service Letter
paragraph (i)(2) of this AD. 245, dated
April 25, 2005; and
Snow Engineering
Co. Service Letter
284, dated
October 4, 2009.
(2) Repetitively eddy (i) For fastener Follow Snow
current inspect for cracks holes that are cold- Engineering Co.
the center splice joint worked: After the Process
outboard two fastener holes initial inspection, Specification
in both the left and right repetitively 197, page
wing main spar lower caps. thereafter inspect 1, revised June 4,
at intervals not to 2002; pages 2
exceed 2,200 hours through 4, dated
TIS. February 23, 2001;
(ii) For fastener and page 5, dated
holes not cold- May 3, 2002; Snow
worked: After the Engineering Co.
initial inspection, Service Letter
repetitively 284, dated
thereafter inspect October 4, 2009;
at intervals not to and (optional) Snow
exceed 1,100 hours Engineering Co.
TIS. Service Letter
245, dated
April 25, 2005.
[[Page 82226]]
(3) If you find any cracks Before further Follow Snow
as a result of any flight after the Engineering Co.
inspection required by inspection where a Service Letter
paragraphs (i)(1) and crack was found. 281, dated
(i)(2) of this AD, do the August 1, 2009; and
following actions. This Snow Engineering
modification terminates the Co. Drawing Number
repetitive inspections 20995, Sheet 3,
required in paragraph dated November 25,
(i)(1) and (i)(2) of this 2005.
AD:
(i) For cracks that can be
repaired, repair the
airplane by doing the
following actions:.
(A) Install the 9-bolt
splice blocks and cold-work
the lower spar cap fastener
holes; and.
(B) Eddy current inspect for
cracks the center splice
joint outboard two fastener
holes in both the left and
right wing main spar lower
caps. This eddy current
inspection is required as
part of the repair and is
separate from the
inspections required in
paragraphs (i)(1) and
(i)(2) of this AD..
(ii) For cracks that cannot
be repaired by doing the
actions in paragraph
(i)(3)(i) of this AD,
replace the lower spar caps
and associated parts listed
following the procedures in
paragraph (i)(4) of this
AD..
(4) Replace the wing main (i) Do the Follow Snow
spar lower caps, the web replacement at Engineering Co.
plates, the center joint whichever of the Service Letter
splice blocks and hardware, following 284, dated
and the wing attach angles compliance times October 4, 2009;
and hardware, and install occurs first: Snow Engineering
the steel web splice plate. (A) Before further Co. Service Letter
This replacement terminates flight when cracks 80GG,
the repetitive inspections are found that revised December
required in paragraphs cannot be repaired 21, 2005; Snow
(i)(1) and (i)(2) of this by incorporating Engineering Co.
AD. the repair in Drawing Number
paragraph (i)(3)(i) 20975, Sheet 4,
of this AD; or. Rev. A, dated
(B) Before or when January 7, 2009.
the airplane
reaches the wing
main spar lower cap
safe life of a
total of 8,000
hours TIS or within
the next 50 hours
TIS after September
9, 2010 (the
effective date of
AD
2010[dash]17[dash]1
8), whichever
occurs later..
(ii) After this
replacement the new
spar safe life is
11,700 hours TIS..
------------------------------------------------------------------------
(j) To address this problem for AT-802 and AT-802A airplanes,
SNs -0179 through -0269, you must do the following, unless already
done:
Table 5--Actions, Compliance, and Procedures
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
Replace the wing main spar By the 8,000 hours Follow Snow
lower caps, the web plates, TIS safe-life or Engineering Co.
the center joint splice within the next 50 Service Letter
blocks and hardware, and hours TIS after 284, dated
the wing attach angles and September 9, 2010 October 4, 2009;
hardware, and install the (the effective date Snow Engineering
steel web splice plate. of AD Co. Service Letter
2010[dash]17[dash]1 80GG,
8), whichever revised December
occurs later. After 21, 2005; Snow
this replacement Engineering Co.
the subsequent new Drawing Number
spar safe life is 20975, Sheet 4,
11,700 hours TIS. Rev. A, dated
January 7, 2009.
------------------------------------------------------------------------
(k) Report any crack from any inspection required in paragraphs
(g), (h), or (i) of this AD within 10 days after the cracks are
found on the form in Figure 1 of this AD.
(1) Send your report to Andrew McAnaul, Aerospace Engineer, ASW-
150 (c/o MIDO-43), 10100 Reunion Place, Suite 650, San Antonio,
Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370.
(2) The Office of Management and Budget (OMB) approved the
information collection requirements contained in this regulation
under the provisions of the Paperwork Reduction Act and assigned OMB
Control Number 2120-0056.
Special Permit Flight
(l) Under 14 CFR 39.23, we are allowing special flight permits
for the purpose of compliance with this AD under the following
conditions:
(1) Only operate in day visual flight rules (VFR).
(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.
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[[Page 82227]]
[GRAPHIC] [TIFF OMITTED] TR30DE10.023
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[[Page 82228]]
Paperwork Reduction Act Burden Statement
(m) A federal agency may not conduct or sponsor, and a person is
not required to respond to, nor shall a person be subject to a
penalty for failure to comply with a collection of information
subject to the requirements of the Paperwork Reduction Act unless
that collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, Fort Worth Airplane Certification Office,
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD.
(2) Before using any approved AMOC, notify your Principal
Maintenance Inspector or Principal Avionics Inspector, as
appropriate, or lacking a principal inspector, your local Flight
Standards District Office.
(3) AMOCs approved for AD 2010-17-18 are approved as AMOCs for
this AD.
Related Information
(o) For more information about this AD, contact Andrew McAnaul,
Aerospace Engineer, ASW-150 (c/o MIDO-43), 10100 Reunion Place,
Suite 650, San Antonio, Texas 78216; phone: (210) 308-3365; fax:
(210) 308-3370; e-mail: [email protected].
Material Incorporated by Reference
(p)(1) You must use the service information contained in table 6
of this AD to do the actions required by this AD, unless the AD
specifies otherwise. The Director of the Federal Register previously
approved the incorporation by reference of the service information
contained in table 6 of this AD on the date specified in the column
``Incorporation by Reference Approval Date'' of Table 6.
Table 6--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Incorporation by reference
Document Revision Date approval date
----------------------------------------------------------------------------------------------------------------
(i) Snow Engineering Co. Service Not Applicable........ December 21, 2005..... September 9, 2010 (75 FR
Letter 80GG. 52255, August 25, 2010).
(ii) Snow Engineering Co. Service Not Applicable........ October 4, 2009....... September 9, 2010 (75 FR
Letter 284. 52255, August 25, 2010).
(iii) Snow Engineering Co. Service Not Applicable........ August 1, 2009........ September 9, 2010 (75 FR
Letter 281. 52255, August 25, 2010).
(iv) Snow Engineering Co. Service Not Applicable........ April 25, 2005........ September 9, 2010 (75 FR
Letter 245. 52255, August 25, 2010).
(v) Snow Engineering Co. Service Not Applicable........ September 30, 2004.... April 21, 2006 (71 FR
Letter 240. 19994, April 19, 2006).
(vi) Snow Engineering Co. Process ...................... ...................... April 21, 2006 (71 FR
Specification 197: 19994, April 19, 2006).
page 1......................... Not Applicable........ June 4, 2002.......... April 21, 2006 (71 FR
19994, April 19, 2006).
pages 2 through 4.............. Not Applicable........ February 23, 2001..... April 21, 2006 (71 FR
19994, April 19, 2006).
page 5......................... Not Applicable........ May 3, 2002........... April 21, 2006 (71 FR
19994, April 19, 2006).
(vii) Snow Engineering Co. Drawing ...................... ...................... September 9, 2010 (75 FR
Number 20995: 52255, August 25, 2010).
Sheet 2........................ Rev. D................ November 25, 2005..... September 9, 2010 (75 FR
52255, August 25, 2010).
Sheet 3........................ Not Applicable........ November 25, 2005..... September 9, 2010 (75 FR
52255, August 25, 2010).
(viii) Snow Engineering Co. Drawing Rev. A................ January 7, 2009....... September 9, 2010 (75 FR
Number 20975, Sheet 4. 52255, August 25, 2010).
----------------------------------------------------------------------------------------------------------------
(2) For service information identified in this AD, contact Air
Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940)
564-5616; fax: (940) 564-5612; E-mail: [email protected];
Internet: www.airtractor.com.
(3) You may review copies of the service information at the FAA,
Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106.
For information on the availability of this material at the FAA,
call 816-329-4148.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Kansas City, Missouri, on December 16, 2010.
William J. Timberlake,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-32905 Filed 12-29-10; 8:45 am]
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