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 » » »
(1) Eddy current inspect for cracks the center splice joint outboard
two fastener holes in both the left and right wing main spar lower
caps.
COMPLIANCE » » »
Initially inspect upon accumulating 1,700 hours time-in
-service (TIS) or within the next 50 hours TIS after April
21, 2006 (the effective date of AD 2006-08-09), whichever
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.
PROCEDURES » » »
Follow 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.
______________________________________________________________________
ACTIONS » » »
(2) If you find any cracks as a result of any inspection required in
paragraph (f)(1) of this AD, do the following actions:
(i) For cracks that can be repaired, repair the airplane by doing
the following actions:
(A) Install center splice plate, P/N 20997-2, and extended
8-bolt splice blocks, P/N 20985-1 & -2, 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 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.
COMPLIANCE » » »
Before further flight after the inspection where a crack
was found. If, before the airplane reaches a total of
3,200 hours TIS, you repair your airplane following
paragraph (f)(2)(i) of this AD, you must do the eddy
current inspections following the compliance times found
in paragraph (f)(5) of this AD. If, at 3,200 hours TIS or
after, you repair your airplane following paragraph
(f)(2)(i) of this AD, this repair terminates the
inspection requirements of paragraph (f)(1) of this AD.
PROCEDURES » » »
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; 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 2, Rev. D., dated November 25,
2005; and Snow Engineering Co. Service Letter
#240, dated September 30, 2004.
______________________________________________________________________
ACTIONS » » »
(3) Replace the wing main spar lower caps, the web plates, the center
joint splice blocks and hardware, and the wing attach angles and
hardware, and install the steel web splice plate. This replacement
terminates the repetitive inspections required in paragraph (f)(1)
of this AD.
COMPLIANCE » » »
(i) Do the replacement at whichever of the following
compliance times occurs first:
(A) Before further flight when cracks are found that
cannot be repaired by incorporating the
modification in paragraph (f)(2)(i) of this AD; or
(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.
PROCEDURES » » »
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; Snow Engineering
Co. Service Letter #80GG, revised December 21,
2005; Snow Engineering Co. Drawing Number
20975, Sheet 4, Rev. A, dated January 7, 2009.
______________________________________________________________________
ACTIONS » » »
(4) To extend the safe life of the wing main spar lower cap to a total
of 8,000 hours TIS, you may incorporate the following optional
modification. This modification terminates the repetitive
inspections required in paragraph (f)(1) of this AD, unless you
performed the modification before the airplane reaches a total of
3,200 hours TIS to repair cracks:
(i) Install center splice plate, P/N 20997-2, and extended 8-bolt
splice blocks, P/N 20985-1 & -2, and cold-work the lower spar
cap fastener holes; and
(ii) 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 modification and is separate from the
inspections required in paragraph (f)(1) of this AD.
COMPLIANCE » » »
Modify at whichever of the following compliance times
occurs first:
(A) Before further flight after any inspection required in
paragraph (f)(1) of this AD where a crack is found. If
you modify your airplane before the airplane reaches a
total of 3,200 hours TIS to repair cracks as required
in paragraph (f)(2)(i) of this AD, you must do the
eddy current inspections following the compliance
times found in paragraph (f)(5) of this AD.
(B) Between 3,200 hours TIS and 4,100 hours TIS.
PROCEDURES » » »
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; 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 2, Rev. D., dated November 25,
2005; and Snow Engineering Co. Service Letter
#240, dated September 30, 2004.
______________________________________________________________________
(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
______________________________________________________________________
CONDITION OF THE AIRPLANE » » »
(i) If the airplane has already had the center splice plate and
extended 8-bolt splice blocks installed at or after 3,200 hours
TIS but the fastener holes have not been cold worked, at any time
you may cold work the fastener holes to terminate the repetitive
inspection requirements of this paragraph.
INITIALLY INSPECT » » »
When the airplane reaches a total of 2,400 hours TIS after
the modification or within the next 100 days after
September 9, 2010 (the effective date of this AD),
whichever occurs later.
REPETITIVELY INSPECT THEREAFTER
AT INTERVALS NOT TO EXCEED » » »
1,200 hours TIS until the 8,000 hours TIS spar
replacement time.
______________________________________________________________________
CONDITION OF THE AIRPLANE » » »
(ii) Before reaching 3,200 hours TIS, the airplane had the center
splice plate and extended 8-bolt splice blocks already installed
but the fastener holes have not been cold worked.
INITIALLY INSPECT » » »
When the airplane reaches a total of 2,400 hours TIS after
the modification or within the next 100 days after
September 9, 2010 (the effective date of this AD),
whichever occurs later.
REPETITIVELY INSPECT THEREAFTER
AT INTERVALS NOT TO EXCEED » » »
1,200 hours TIS. Upon reaching 4,800 hours TIS
after the modification, inspect repetitively
thereafter at intervals not to exceed 600
hours TIS until the 8,000 hours TIS spar
replacement time.
______________________________________________________________________
CONDITION OF THE AIRPLANE » » »
(iii) Before reaching 3,200 hours TIS, the airplane had the center
splice plate and extended 8-bolt splice blocks installed and the
fastener holes have been cold worked.
INITIALLY INSPECT » » »
When the airplane reaches a total of 4,800 hours TIS after
the modification or within the next 100 days after
September 9, 2010 (the effective date of this AD),
whichever occurs later.
REPETITIVELY INSPECT THEREAFTER
AT INTERVALS NOT TO EXCEED » » »
600 hours TIS until the 8,000 hours TIS spar
replacement time.
______________________________________________________________________
(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 » » »
(1) Eddy current inspect for cracks the center splice joint outboard
two fastener holes in both the left and right wing main spar lower
caps.
COMPLIANCE » » »
Initially inspect upon accumulating 1,700 hours TIS or
within the next 50 hours TIS after September 9, 2010 (the
effective date of this AD), whichever occurs later, and
repetitively thereafter at intervals not to exceed 800
hours TIS. If the center splice plate, P/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.
PROCEDURES » » »
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; 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.
______________________________________________________________________
ACTIONS » » »
(2) If you find any cracks as a result of any inspection required by
paragraph (g)(1) of this AD, do the following actions. This repair
modification terminates the repetitive inspections required in
paragraph (g)(1) 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;
(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.
COMPLIANCE » » »
Before further flight after the inspection where a crack
was found.
PROCEDURES » » »
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; 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, Snow Engineering Co. Service
Letter #281, dated August 1, 2009; and Snow
Engineering Co. Drawing Number 20995, Sheet 3,
dated November 25, 2005.
______________________________________________________________________
ACTIONS » » »
(3) Replace the wing main spar lower caps, the web plates, the center
joint splice blocks and hardware, and the wing attach angles and
hardware, and install the steel web splice plate. This replacement
terminates the repetitive inspections required in paragraph (g)(1)
of this AD.
COMPLIANCE » » »
(i) Do the replacement at whichever of the following
compliance times occurs first:
(A) Before further flight when cracks are found that
cannot be repaired by incorporating the
modification in paragraph (g)(2)(i) of this AD; or
(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.
PROCEDURES » » »
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; Snow Engineering
Co. Service Letter #80GG, revised December 21,
2005; Snow Engineering Co. Drawing Number
20975, Sheet 4, Rev. A, dated January 7, 2009.
______________________________________________________________________
ACTIONS » » »
(4) To extend the safe life of the wing main spar lower cap to a total
of 8,000 hours TIS, you may incorporate the following optional
modification:
(i) Install center splice plate, P/N 20994-2, if not already
installed as part of a repair, and cold-work the lower spar
cap fastener holes; and
(ii) 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 modification and is separate from the
inspections required in paragraph (g)(1) of this AD.
COMPLIANCE » » »
Before the airplane reaches a total of 4,100 hours TIS.
After installation of the center splice plate, P/N 20994
-2, do the repetitive inspections required in paragraph
(g)(1) at intervals not to exceed 2,000 hours TIS. If as
of September 9, 2010 (the effective date of this AD) you
have already exceeded the 4,100 hours TIS threshold for
extending the safe life to 8,000 hours TIS, you may be
eligible for an alternative method of compliance following
paragraph (m) in this AD.
PROCEDURES » » »
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; 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
20975, Sheet 4, Rev. A., dated January 7,
2009; and Snow Engineering Co. Service Letter
#245, dated April 25, 2005.
______________________________________________________________________
ACTIONS » » »
(5) If you find any cracks as a result of any repetitive inspection
required by paragraph (g)(4) of this AD, do the following actions.
This repair modification terminates the repetitive inspections
required in paragraph (g)(4) 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 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.
COMPLIANCE » » »
Before further flight after the inspection where a crack
was found.
PROCEDURES » » »
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; 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, Snow Engineering Co. Service
Letter #281, dated August 1, 2009; and Snow
Engineering Co. Drawing Number 20995, Sheet 3,
dated November 25, 2005.
______________________________________________________________________
(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 » » »
(1) Do an initial eddy current inspection for cracks of the center
splice joint outboard two fastener holes in both the left and
right wing main spar lower caps. After this initial inspection,
you may do the optional cold-working of the lower spar cap
fastener holes to increase the hours TIS between repetitive
inspections required in paragraph (h)(2) of this AD.
COMPLIANCE » » »
Before the airplane reaches a total of 5,500 hours TIS or
within the next 50 hours TIS after September 9, 2010 (the
effective date of this AD), whichever occurs later.
PROCEDURES » » »
Follow 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. Service Letter #245, dated
April 25, 2005; and Snow Engineering Co.
Service Letter #284, dated October 4, 2009.
______________________________________________________________________
ACTIONS » » »
(2) Repetitively eddy current inspect for cracks the center splice
joint outboard two fastener holes in both the left and right wing
main spar lower caps.
COMPLIANCE » » »
(i) For fastener holes that are cold-worked: After the
initial inspection, repetitively thereafter inspect at
intervals not to exceed 2,200 hours TIS.
(ii) For fastener holes not cold-worked: After the initial
inspection, repetitively thereafter inspect at
intervals not to exceed 1,100 hours TIS.
PROCEDURES » » »
Follow 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. Service Letter #284, dated
October 4, 2009; and (optional) Snow
Engineering Co. Service Letter #245, dated
April 25, 2005.
______________________________________________________________________
ACTIONS » » »
(3) If you find any cracks as a result of any inspection required by
paragraphs (h)(1) and (h)(2) of this AD, do the following actions.
This modification terminates the 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.
COMPLIANCE » » »
Before further flight after the inspection where a crack
was found.
PROCEDURES » » »
Follow Snow Engineering Co. Service Letter
#281, dated August 1, 2009; and Snow
Engineering Co. Drawing Number 20995, Sheet 3,
dated November 25, 2005.
______________________________________________________________________
ACTIONS » » »
(4) Replace the wing main spar lower caps, the web plates, the center
joint splice blocks and hardware, and the wing attach angles and
hardware, and install the steel web splice plate. This replacement
terminates the repetitive inspections required in paragraphs
(h)(1) and (h)(2) of this AD.
COMPLIANCE » » »
(i) Do the replacement at whichever of the following
compliance times occurs first:
(A) Before further flight when cracks are found that
cannot be repaired by incorporating the repair in
paragraph (h)(3)(i) of this AD; or
(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.
PROCEDURES » » »
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; Snow Engineering
Co. Service Letter #80GG, revised December 21,
2005; Snow Engineering Co. Drawing Number
20975, Sheet 4, Rev. A, dated January 7, 2009.
______________________________________________________________________
(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 » » »
Replace the wing main spar lower caps, the web plates, the center
joint splice blocks and hardware, and the wing attach angles and
hardware, and install the steel web splice plate.
COMPLIANCE » » »
By the 8,000 hours TIS safe-life or within the next 50
hours TIS after September 9, 2010 (the effective date of
this AD), whichever occurs later. After this replacement
the subsequent new spar safe life is 11,700 hours TIS.
PROCEDURES » » »
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; Snow Engineering
Co. Service Letter #80GG, revised December 21,
2005; Snow Engineering Co. Drawing Number
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 » » »
Replace the wing main spar lower caps, the web plates, the center
joint splice blocks and hardware, and the wing attach angles and
hardware, and install the steel web splice plate.
COMPLIANCE » » »
By the 11,700 hours TIS safe-life or within the next 50
hours TIS after September 9, 2010 (the effective date of
this AD), whichever occurs later. After this replacement
the subsequent new spar safe life is 11,700 hours TIS.
PROCEDURES » » »
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; Snow Engineering
Co. Service Letter #80GG, revised December 21,
2005; Snow Engineering Co. Drawing Number
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.
ILLUSTRATION (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.
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.
|
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.
DATES: This AD becomes effective on September 9, 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-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.
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
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. 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:
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