Airworthiness Directives:
Federal Register: December 30, 2010 (Volume 75, Number 250)
Rules and Regulations
Page 82219-82228
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
DOCID:fr30de10-2
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.
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: airmail@airtractor.com; 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: andrew.mcanaul@faa.gov.
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
Action
Labor cost
Parts cost
Cost per product
Cost on U.S. operators
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.
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
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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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: andrew.mcanaul@faa.gov.
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: airmail@airtractor.com;
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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