Airworthiness Directives:
Federal Register: August 25, 2010 (Volume 75, Number 164)
Rules and Regulations
Page 52255-52263
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
DOCID:fr25au10-11
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA-2010-0827; Directorate Identifier 2010-CE-029-AD;
Amendment 39-16412; AD 2010-17-18
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 adopting a new airworthiness directive (AD) to supersede AD 2010-13-08, which applies to all Air Tractor, Inc. (Air
Tractor) Models AT-802 and AT-802A airplanes. AD 2010-13-08 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 cap. Since we issued 2010-13-08, we evaluated service information issued by Air Tractor and determined we need to add inspections, add modifications, and change the safe life for certain serial number (SN) ranges. Consequently, this AD would retain the actions of AD 2010-13-08 and would add inspections, add modifications, and change the safe life for certain SN ranges. 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 becomes effective on September 9, 2010.
On September 9, 2010, the Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Service Letter 80GG, revised December 21, 2005; Snow Engineering Co. Service
Letter 284, dated October 4, 2009; Snow Engineering Co.
Service Letter 281, dated August 1, 2009; Snow Engineering Co.
Service Letter 245, dated April 25, 2005; Snow Engineering Co.
Drawing Number 20995, Sheet 3, dated November 25, 2005; Snow
Engineering Co. Drawing Number 20995, Sheet 2, Rev. D., dated November 25, 2005; and Snow Engineering Co. Drawing Number 20975, Sheet 4, Rev.
A., dated January 7, 2009, listed in this AD.
As of April 21, 2006 (71 FR 19994, April 19, 2006), the Director of the Federal Register approved the incorporation by reference of Snow
Engineering Co. Service Letter 240, dated September 30, 2004; and Snow Engineering Co. Process Specification 197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002, listed in this AD.
We must receive any comments on this AD by October 12, 2010.
ADDRESSES: Use one of the following addresses to comment on this AD.
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-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.
To get the 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.
To view the comments to this AD, go to http://www.regulations.gov.
The docket number is FAA-2010-0827; Directorate Identifier 2010-CE-029-
AD.
FOR FURTHER INFORMATION CONTACT: Andrew McAnaul, Aerospace Engineer,
ASW-150 (c/o MIDO-43), 10100 Reunion Place, Suite 650, San Antonio,
Texas 78216; telephone: (210) 308-3365; facsimile: (210) 308-3370.
SUPPLEMENTARY INFORMATION:
Discussion
Since 2000, we have issued several ADs related to the wing spar inspection and safe life on Air Tractor AT-400, AT-500, AT-600, and AT- 800 series airplanes.
In 2001, we issued AD 2001-10-04, Amendment 39-12230 (66 FR 27014,
May 16, 2001) to lower the safe life for the wing lower spar cap on Air
Tractor AT-400, AT-500, and AT-800 series airplanes. This AD allowed for inspection (using eddy current methods) of the wing lower spar cap for airplanes that were at or over the lower safe life and for which parts were not available. Later that same year, we revised that AD to remove AT-800 series airplanes from the applicability that were equipped with the factory-supplied computerized fire gate (part number 80540) and engaged in full-time firefighting.
In 2002, we issued AD 2002-11-05, Amendment 39-12766 (67 FR 37967,
May 31, 2002) that retained the actions for the AT-802 series airplanes and further reduced the safe life for certain AT-400 series airplanes and certain AT-500 series airplanes that either incorporate or have incorporated Marburger winglets.
After receiving reports of fatigue cracking found on three Model
AT-802A airplanes that were below the reduced safe life established in
AD 2001-10-04, we issued AD 2006-08-09, Amendment 39-14565 (71 FR 27794, May 12, 2006). AD 2006-08-09 required repetitively inspecting the two outboard fastener holes in both of the wing main spar lower caps at the center splice joint for cracks and repairing or replacing any cracked spar cap.
After issuing AD 2006-08-09, we determined the need to clarify the affected SN applicability. Models AT-
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802 and AT-802A share a common SN range. Sometimes service information listed only one of the models with a starting or ending SN within a SN range, depending on which model was produced with that specific SN, even though the service information applied to both models. We superseded AD 2006-08-09 and issued AD 2010-13-08, Amendment 39-16339
(75 FR 35616, June 23, 2010) to retain the actions from AD 2006-08-09, clarify serial number applicability, and add an option of modifying the wing main spar lower caps to extend the safe life limit.
After completing fatigue analysis on Models AT-802 and AT-802A airplanes, Air Tractor issued service information that adds inspections, adds modifications, and changes the safe life for certain
SN ranges. Since we issued 2010-13-08, we evaluated this new service information and determined the need to add inspections, add modifications, and change the safe life for certain SN ranges.
This condition, if not corrected, could result in failure of the spar cap and lead to wing separation and loss of control of the airplane.
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 and Requirements of This AD
We are issuing this AD because we evaluated all the information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. This 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 cap.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists for making this amendment effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and an opportunity for public comment. We invite you to send any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number ``FAA-2010-0827;
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 the AD. We will consider all comments received by the closing date and may amend the AD in light 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 concerning this AD.
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.
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Regulatory Flexibility Determination
The Regulatory Flexibility Act of 1980 (Pub. L. 96-354) (RFA) establishes as a principle of regulatory issuance that agencies shall endeavor, consistent with the objective of the rule and of applicable statutes, to fit regulatory and informational requirements to the scale of the businesses, organizations, and governmental jurisdictions subject to regulation.
To achieve that principle, the RFA requires agencies to solicit and consider flexible regulatory proposals and to explain the rationale for their actions. The RFA covers a wide-range of small entities, including small businesses, not-for-profit organizations, and small governmental jurisdictions.
Agencies must perform a review to determine whether a proposed or final rule will have a significant economic impact on a substantial number of small entities. In accordance with Section 608 of the
Regulatory Flexibility Act, an agency head may waive or delay completion of some or all of the requirements of Section 603 by providing a written finding that this final rule is being promulgated in response to an emergency that makes compliance or timely compliance with the provisions of Section 603 impracticable.
We are performing a review to determine whether this final rule AD action will have a significant economic impact on a substantial number of small entities. However, the immediate safety of flight conditions of this AD action make compliance with the provisions of Section 603 impracticable. Our justification for immediate adoption of this rule, and therefore of impracticability, is stated in FAA's Justification and
Determination of the Effective Date. After we determine whether this final rule AD action has a significant economic impact on a substantial number of small entities or not, we will publish in the Federal
Register our determination and, if required, our final regulatory flexibility analysis.
Examining the AD Docket
You may examine the AD docket that contains the AD, the regulatory evaluation, any comments received, and other information 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 Docket Office (telephone (800) 647-5527) is located at the street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
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 14 CFR part 39 as follows:
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) 2010-13-08, Amendment 39-16339 (75 FR 35616, June 23, 2010), and by adding a new AD to read as follows: 2010-17-18 Air Tractor, Inc.: Amendment 39-16412; Docket No. FAA- 2010-0827; Directorate Identifier 2010-CE-029-AD.
Effective Date
(a) This AD becomes effective on September 9, 2010.
Affected ADs
(b) This AD supersedes AD 2010-13-08; Amendment 39-16339.
Applicability
(c) This AD affects Models AT-802 and AT-802A airplanes, all serial numbers (SNs) beginning with -0001, 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) Air Transport Association of America (ATA) Code 57: Wings.
Unsafe Condition
(e) This AD results from our determination that we need to require the actions in the new service information to add inspections, add modifications, and change the safe life for certain
SN ranges. 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) 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 cracks Initially inspect upon accumulating Follow Snow Engineering Co. Process the center splice joint outboard
1,700 hours time-in-service (TIS)
Specification 197, page 1, two fastener holes in both the left or within the next 50 hours TIS
revised June 4, 2002; pages 2 and right wing main spar lower
after April 21, 2006 (the effective through 4, dated February 23, 2001; caps.
date of AD 2006-08-09), whichever
and page 5, dated May 3, 2002. occurs later, and repetitively thereafter at intervals not to exceed 800 hours TIS. If, before
September 9, 2010 (the effective date of this AD), you installed the center splice plate and extended 8- bolt splice blocks, use the inspection compliance times found in paragraph (f)(5) of this AD.
Page 52258
(2) If you find any cracks as a
Before further flight after the
Follow Snow Engineering Co. Service result of any inspection required
inspection where a crack was found. Letter 284, dated October in paragraph (f)(1) of this AD, do
If, before the airplane reaches a
4, 2009; Snow Engineering Co. the following actions:
total of 3,200 hours TIS, you
Process Specification 197,
(i) For cracks that can be repaired, repair your airplane following
page 1, revised June 4, 2002; pages repair the airplane by doing the
paragraph (f)(2)(i) of this AD, you 2 through 4, dated February 23, following actions:
must do the eddy current
2001; and page 5, dated May 3,
(A) Install center splice plate, P/N inspections following the
2002; Snow Engineering Co. Drawing 20997-2, and extended 8[dash]bolt
compliance times found in paragraph Number 20995, Sheet 2, Rev. D., splice blocks, P/N 20985-1 & -2,
(f)(5) of this AD. If, at 3,200
dated November 25, 2005; and Snow and cold-work the lower spar cap
hours TIS or after, you repair your Engineering Co. Service Letter fastener holes; and
airplane following paragraph
240, dated September 30,
(B) Eddy current inspect for cracks
(f)(2)(i) of this AD, this repair
2004. the center splice joint outboard
terminates the inspection two fastener holes in both the left requirements of paragraph (f)(1) of and right wing main spar lower
this AD. caps. This eddy current inspection is required as part of the modification and is separate from the inspections required in paragraph (f)(1) of this AD.
(ii) For cracks that cannot 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 (f)(3) of this AD.
(3) Replace the wing main spar lower (i) Do the replacement at whichever Follow Snow Engineering Co. Service caps, the web plates, the center
of the following compliance times
Letter 284, dated October joint splice blocks and hardware,
occurs first:
4, 2009; Snow Engineering Co. and the wing attach angles and
(A) Before further flight when
Service Letter 80GG, hardware, and install the steel web cracks are found that cannot be
revised December 21, 2005; Snow splice plate. This replacement
repaired by incorporating the
Engineering Co. Drawing Number terminates the repetitive
modification in paragraph (f)(2)(i) 20975, Sheet 4, Rev. A, dated inspections required in paragraph
of this AD; or
January 7, 2009.
(f)(1) of this AD.
(B) Before or when 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 this AD), 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 this AD), 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
(f)(4) of this AD.
(4) To extend the safe life of the
Modify at whichever of the following Follow Snow Engineering Co. Service wing main spar lower cap to a total compliance times occurs first:
Letter 284, dated October of 8,000 hours TIS, you may
(A) Before further flight after any 4, 2009; Snow Engineering Co. incorporate the following optional inspection required in paragraph
Process Specification 197, modification. This modification
(f)(1) of this AD where a crack is page 1, revised June 4, 2002; pages terminates the repetitive
found. If you modify your airplane 2 through 4, dated February 23, inspections required in paragraph
before the airplane reaches a total 2001; and page 5, dated May 3,
(f)(1) of this AD, unless you
of 3,200 hours TIS to repair cracks 2002; Snow Engineering Co. Drawing performed the modification before
as required in paragraph (f)(2)(i)
Number 20995, Sheet 2, Rev. D., the airplane reaches a total of
of this AD, you must do the eddy
dated November 25, 2005; and Snow 3,200 hours TIS to repair cracks:
current inspections following the
Engineering Co. Service Letter
(i) Install center splice plate, P/N compliance times found in paragraph 240, dated September 30, 20997-2, and extended 8[dash]bolt
(f)(5) of this AD.
2004. splice blocks, P/N 20985-1 & -2, and cold-work the lower spar cap fastener holes; and
Page 52259
(ii) Eddy current inspect for cracks (B) Between 3,200 hours TIS and the center splice joint outboard
4,100 hours TIS. two fastener holes in both the left and right wing main spar lower caps. This eddy current inspection is required as part of the modification and is separate from the inspections required in paragraph (f)(1) of this AD.
(5) If, before September 9, 2010 (the effective date of this
AD) or as a result of performing the repair for cracks following paragraph (f)(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 (f)(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 (f)(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 this AD), repetitive inspection
whichever occurs requirements of this
later. paragraph.
(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 this AD),
TIS until the 8,000 whichever occurs
hours TIS spar later.
replacement time.
(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 this AD), whichever occurs later.
(g) 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 cracks Initially inspect upon accumulating Follow Snow Engineering Co. Service the center splice joint outboard
1,700 hours TIS or within the next
Letter 284, dated October two fastener holes in both the left 50 hours TIS after September 9,
4, 2009; and Snow Engineering Co. and right wing main spar lower
2010 (the effective date of this
Process Specification 197, caps.
AD), whichever occurs later, and
page 1, revised June 4, 2002; pages repetitively thereafter at
2 through 4, dated February 23, intervals not to exceed 800 hours
2001; and page 5, dated May 3,
TIS. If the center splice plate, P/ 2002.
N 20994-2, is installed as
.................................... specified in paragraph (g)(4) of this AD, do the repetitive inspections at intervals not to exceed 2,000 hours TIS.
(2) If you find any cracks as a
Before further flight after the
Follow Snow Engineering Co. Service result of any inspection required
inspection where a crack was found. Letter 284, dated October by paragraph (g)(1) of this AD, do
4, 2009; and Snow Engineering Co. the following actions. This repair
Process Specification 197, modification terminates the
page 1, revised June 4, 2002; pages repetitive inspections required in
2 through 4, dated February 23, paragraph (g)(1) of this AD:
2001; and page 5, dated May 3,
(i) For cracks that can be repaired,
2002, Snow Engineering Co. Service repair the airplane by doing the
Letter 281, dated August following actions:
1, 2009; and Snow Engineering Co.
(A) Install the 9-bolt splice blocks
Drawing Number 20995, Sheet 3, and cold-work the lower spar cap
dated November 25, 2005. fastener holes;
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(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 paragraph
(g)(1) of this AD; and
(C) Install the center splice plate,
P/N 20994-2, per paragraph (g)(4) if not already installed.
(ii) For cracks that cannot be repaired by doing the actions in paragraph (g)(2)(i) of this AD, replace the lower spar caps and associated parts listed following the procedures identified in paragraph (g)(3) of this AD.
(3) Replace the wing main spar lower (i) Do the replacement at whichever Follow Snow Engineering Co. Service caps, the web plates, the center
of the following compliance times
Letter 284, dated October joint splice blocks and hardware,
occurs first:
4, 2009; Snow Engineering Co. and the wing attach angles and
(A) Before further flight when
Service Letter 80GG, hardware, and install the steel web cracks are found that cannot be
revised December 21, 2005; Snow splice plate. This replacement
repaired by incorporating the
Engineering Co. Drawing Number terminates the repetitive
modification in paragraph (g)(2)(i) 20975, Sheet 4, Rev. A, dated inspections required in paragraph
of this AD; or
January 7, 2009.
(g)(1) of this AD.
(B) Before or when 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 this AD), 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
(g)(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.
(4) To extend the safe life of the
Before the airplane reaches a total Follow Snow Engineering Co. Service wing main spar lower cap to a total of 4,100 hours TIS. After
Letter 284, dated October of 8,000 hours TIS, you may
installation of the center splice
4, 2009; Snow Engineering Co. incorporate the following optional plate, P/N 20994-2, do the
Process Specification 197, modification:
repetitive inspections required in page 1, revised June 4, 2002; pages
(i) Install center splice plate, P/N paragraph (g)(1) at intervals not
2 through 4, dated February 23, 20994-2, if not already installed
to exceed 2,000 hours TIS. If as of 2001; and page 5, dated May 3, as part of a repair, and cold-work
September 9, 2010 (the effective
2002; Snow Engineering Co. Drawing the lower spar cap fastener holes; date of this AD) you have already
Number 20975, Sheet 4, Rev. A., and
exceeded the 4,100 hours TIS
dated January 7, 2009; and Snow
(ii) Eddy current inspect for cracks threshold for extending the safe
Engineering Co. Service Letter the center splice joint outboard
life to 8,000 hours TIS, you may be 245, dated April 25, 2005. two fastener holes in both the left eligible for an alternative method and right wing main spar lower
of compliance following paragraph caps. This eddy current inspection
(m) in this AD. is required as part of the modification and is separate from the inspections required in paragraph (g)(1) of this AD.
(5) If you find any cracks as a
Before further flight after the
Follow Snow Engineering Co. Service result of any repetitive inspection inspection where a crack was found. Letter 284, dated October required by paragraph (g)(4) of
4, 2009; and Snow Engineering Co. this AD, do the following actions.
Process Specification 197,
This repair modification terminates
page 1, revised June 4, 2002; pages the repetitive inspections required
2 through 4, dated February 23, in paragraph (g)(4) of this AD:
2001; and page 5, dated May 3,
(i) For cracks that can be repaired,
2002, Snow Engineering Co. Service repair the airplane by doing the
Letter 281, dated August following actions:
1, 2009; and Snow Engineering Co.
(A) Install the 9-bolt splice blocks
Drawing Number 20995, Sheet 3, and cold-work the lower spar cap
dated November 25, 2005. fastener holes; and
Page 52261
(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 paragraph
(g)(1) of this AD.
(ii) For cracks that cannot be repaired by doing the actions in paragraph (g)(5)(i) of this AD, replace the lower spar caps and associated parts listed following the procedures identified in paragraph (g)(3) of this AD.
(h) 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 current
Before the airplane reaches a total Follow Snow Engineering Co. Process inspection for cracks of the center of 5,500 hours TIS or within the
Specification 197, page 1, splice joint outboard two fastener next 50 hours TIS after September
revised June 4, 2002; pages 2 holes in both the left and right
9, 2010 (the effective date of this through 4, dated February 23, 2001; wing main spar lower caps. After
AD), whichever occurs later.
and page 5, dated May 3, 2002; Snow this initial inspection, you may do
Engineering Co. Service Letter the optional cold-working of the
245, dated April 25, 2005; lower spar cap fastener holes to
and Snow Engineering Co. Service increase the hours TIS between
Letter 284, dated October repetitive inspections required in
4, 2009. paragraph (h)(2) of this AD.
(2) Repetitively eddy current
(i) For fastener holes that are
Follow Snow Engineering Co. Process inspect for cracks the center
cold-worked: After the initial
Specification 197, page 1, splice joint outboard two fastener inspection, repetitively thereafter revised June 4, 2002; pages 2 holes in both the left and right
inspect at intervals not to exceed through 4, dated February 23, 2001; wing main spar lower caps.
2,200 hours TIS.
and page 5, dated May 3, 2002; Snow
(ii) For fastener holes not cold-
Engineering Co. Service Letter worked: After the initial
284, dated October 4, inspection, repetitively thereafter 2009; and (optional) Snow inspect at intervals not to exceed
Engineering Co. Service Letter 1,100 hours TIS.
245, dated April 25, 2005.
(3) If you find any cracks as a
Before further flight after the
Follow Snow Engineering Co. Service result of any inspection required
inspection where a crack was found. Letter 281, dated August by paragraphs (h)(1) and (h)(2) of
1, 2009; and Snow Engineering Co. this AD, do the following actions.
Drawing Number 20995, Sheet 3,
This modification terminates the
dated November 25, 2005. repetitive inspections required in paragraph (h)(1) and (h)(2) of this
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
(h)(1) and (h)(2) of this AD.
(ii) For cracks that cannot be repaired by doing the actions in paragraph (h)(3)(i) of this AD, replace the lower spar caps and associated parts listed following the procedures in paragraph (h)(4) of this AD.
Page 52262
(4) Replace the wing main spar lower (i) Do the replacement at whichever Follow Snow Engineering Co. Service caps, the web plates, the center
of the following compliance times
Letter 284, dated October joint splice blocks and hardware,
occurs first:
4, 2009; Snow Engineering Co. and the wing attach angles and
(A) Before further flight when
Service Letter 80GG, hardware, and install the steel web cracks are found that cannot be
revised December 21, 2005; Snow splice plate. This replacement
repaired by incorporating the
Engineering Co. Drawing Number terminates the repetitive
repair in paragraph (h)(3)(i) of
20975, Sheet 4, Rev. A, dated inspections required in paragraphs this AD; or
January 7, 2009.
(h)(1) and (h)(2) of this AD.
(B) Before or when 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 this AD), whichever occurs later.
(ii) After this replacement the new spar safe life is 11,700 hours TIS.
(i) 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 lower
By the 8,000 hours TIS safe-life or Follow Snow Engineering Co. Service caps, the web plates, the center
within the next 50 hours TIS after
Letter 284, dated October joint splice blocks and hardware,
September 9, 2010 (the effective
4, 2009; Snow Engineering Co. and the wing attach angles and
date of this AD), whichever occurs
Service Letter 80GG, hardware, and install the steel web later. After this replacement the
revised December 21, 2005; Snow splice plate.
subsequent new spar safe life is
Engineering Co. Drawing Number 11,700 hours TIS.
20975, Sheet 4, Rev. A, dated
January 7, 2009.
(j) To address this problem for AT-802 and AT-802A airplanes,
SNs -0270 and subsequent, you must do the following, unless already done:
Table 6--Actions, Compliance, and Procedures
Actions
Compliance
Procedures
Replace the wing main spar lower
By the 11,700 hours TIS safe-life or Follow Snow Engineering Co. Service caps, the web plates, the center
within the next 50 hours TIS after
Letter 284, dated October joint splice blocks and hardware,
September 9, 2010 (the effective
4, 2009; Snow Engineering Co. and the wing attach angles and
date of this AD), whichever occurs
Service Letter 80GG, hardware, and install the steel web later. After this replacement the
revised December 21, 2005; Snow splice plate.
subsequent new spar safe life is
Engineering Co. Drawing Number 11,700 hours TIS.
20975, Sheet 4, Rev. A, dated
January 7, 2009.
(k) Report any crack from any inspection required in paragraphs
(f), (g), or (h) 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; telephone: (210) 308-3365; facsimile: (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 part 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.
AD 2010-17-18 INSPECTION REPORT
REPORT ONLY IF CRACKS ARE FOUND
General Information
1. Inspection Performed By:
2. Phone:
3. Aircraft Model:
4. Aircraft Serial Number:
5. Engine Model Number:
6. Aircraft Total Hours TIS:
Page 52263
7. Wing Total Hours TIS:
8. Lower Spar Cap Hours TIS:
Previous Inspection/Repair History
9. Has the lower spar cap been
If yes, an inspection has occurred: inspected (eddy[dash]current, dye Date:------------------------ penetrant, magnetic particle, or
Inspection Method:------------ ultrasound) before?
Lower Spar Cap TIS:------------
squ
Yes [squ] No
Cracks found? [squ] Yes [squ] No
10. Has there been any major repair If yes, specify (Description and or alteration performed to the
hours TIS): spar cap?
squ
Yes [squ] No
Inspection for AD 2010-17-18
11. Date of AD inspection:
11a. Cracks found:
Inspection Results:
squ Left Hand [squ] Right Hand
11b. Crack Length:------------
11c. Does drilling hole to next larger size remove all traces of the crack(s)?
Location:------------
squ Yes [squ] No
12d. Corrective Action Taken:
Mail report (only if you find any cracks as a result of the inspection for AD 2010-17-18) to: Andrew McAnaul, Aerospace Engineer, ASW-150 (c/ o MIDO-43), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) 308-3365; facsimile: (210) 308-3370.
Figure 1
Alternative Methods of Compliance (AMOCs)
(m) 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. Send information to ATTN: Andy
McAnaul, Aerospace Engineer, ASW-150, FAA San Antonio MIDO-43, 10100
Reunion Pl., Ste. 650, San Antonio, Texas 78216, phone: (210) 308- 3365, fax: (210) 308-3370. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(n) AMOCs approved for AD 2010-13-08 are not approved for this
AD.
Material Incorporated by Reference
(o) You must use Snow Engineering Co. Service Letter 80GG, revised December 21, 2005; Snow Engineering Co.
Service Letter 284, dated October 4, 2009; Snow Engineering
Co. Service Letter 281, dated August 1, 2009; Snow
Engineering Co. Service Letter 245, dated April 25, 2005;
Snow Engineering Co. Service Letter 240, dated September 30, 2004; Snow Engineering Co. Process Specification 197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002; Snow Engineering Co. Drawing
Number 20995, Sheet 3, dated November 25, 2005; Snow Engineering Co.
Drawing Number 20995, Sheet 2, Rev. D., dated November 25, 2005; and
Snow Engineering Co. Drawing Number 20975, Sheet 4, Rev. A., dated
January 7, 2009, to do the actions required by this AD, unless the
AD specifies otherwise.
(1) The Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Service Letter 80GG, revised December 21, 2005; Snow Engineering Co.
Service Letter 284, dated October 4, 2009; Snow Engineering
Co. Service Letter 281, dated August 1, 2009; Snow
Engineering Co. Service Letter 245, dated April 25, 2005;
Snow Engineering Co. Drawing Number 20995, Sheet 3, dated November 25, 2005; Snow Engineering Co. Drawing Number 20995, Sheet 2, Rev.
D., dated November 25, 2005; and Snow Engineering Co. Drawing Number 20975, Sheet 4, Rev. A., dated January 7, 2009, under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On April 21, 2006 (71 FR 19994, April 19, 2006), the
Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Service Letter 240, dated
September 30, 2004; and Snow Engineering Co. Process Specification 197, page 1, revised June 4, 2002; pages 2 through 4, dated
February 23, 2001; and page 5, dated May 3, 2002.
(3) 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.
(4) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region,
Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the
Central Region, call (816) 329-3768.
(5) You may also review copies of the service information incorporated by reference for this AD at the National Archives and
Records Administration (NARA). For information on the availability of this material at NARA, 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 August 11, 2010.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
FR Doc. 2010-20555 Filed 8-24-10; 8:45 am
BILLING CODE 4910-13-P
