Airworthiness Directives; Burl A. Rogers (Type Certificate Previously Held by William Brad Mitchell and Aeronca, Inc.) Airplanes, 14681-14686 [2012-5864]
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Federal Register / Vol. 77, No. 49 / Tuesday, March 13, 2012 / Rules and Regulations
paragraph (g)(1) of this AD, if the
replacement was done before June 24, 2002
(the effective date of AD 2002–10–06,
Amendment 39–12752 (67 FR 35425, May 20,
2002)), using Airbus Service Bulletin A320–
31–1106, dated January 3, 1997; Revision 01,
dated April 16, 1997; Revision 02, dated
January 20, 1998; or Revision 03, dated July
9, 1999.
(h) Restatement of Requirements of AD
2002–10–06, Amendment 39–12752 (67 FR
35425, May 20, 2002): Optional Method of
Compliance
Installation of a FWC standard in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
31–1141, Revision 04, dated February 14,
2002, is an acceptable method of compliance
with the replacement required by paragraph
(g) of this AD.
(i) New Requirements of This AD: Flight
Warning Computer Replacement
Within 48 months after the effective date
of this AD: Replace both FWC units with
FWC part number 350E053020909, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–31–1334, Revision 04,
including Appendix 01, dated September 12,
2011.
(j) Credit for Previous Actions
(1) For all airplanes, except for Model
A319 series airplanes on which
modifications 28238, 28162, and 28342 have
been incorporated: This paragraph provides
credit for replacing both FWCs, as required
by paragraph (i) of this AD, if the
replacements were performed before the
effective date of this AD using Airbus Service
Bulletin A320–31–1334, dated July 30, 2009;
Revision 01, dated December 14, 2009;
Revision 02, dated September 13, 2010; or
Revision 03, dated March 15, 2011.
(2) This paragraph provides credit for
replacing both FWCs in lieu of the
installation specified in paragraph (h) of this
AD, if the replacements were performed
before the effective date of this AD using
Airbus Service Bulletin A320–31–1141,
dated March 6, 2000; Revision 01, dated May
25, 2000; Revision 02, dated January 22,
2001; or Revision 03, dated June 12, 2001.
srobinson on DSK4SPTVN1PROD with RULES
(k) Parts Installation
As of the effective date of this AD, and
after accomplishing the actions in paragraph
(i) of this AD, no person may install a FWC
with a part number listed in table 1 of this
AD on any airplane.
(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 International Branch, send it to ATTN:
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Tim Dulin, Aerospace Engineer, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, 1601 Lind Avenue SW.,
Renton, Washington 98057–3356; telephone
425–227–2141; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(m) Related Information
Refer to MCAI EASA Airworthiness
Directive 2011–0001, dated January 10, 2011;
Airbus Service Bulletin A320–31–1106,
Revision 04, dated December 21, 1999;
Airbus Mandatory Service Bulletin A320–31–
1106, Revision 05, dated September 21, 2000;
Airbus Service Bulletin A320–31–1141,
Revision 04, dated February 14, 2002; and
Airbus Mandatory Service Bulletin A320–31–
1334, Revision 04, including Appendix 01,
dated September 12, 2011; for related
information.
(n) Material Incorporated by Reference
(1) You must use the following service
information to do the actions required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference (IBR) of the
following service information under 5 U.S.C.
552(a) and 1 CFR part 51 on the date
specified.
(2) The following service information was
approved for IBR on April 17, 2012.
(i) Airbus Mandatory Service Bulletin
A320–31–1106, Revision 05, dated
September 21, 2000.
(ii) Airbus Service Bulletin A320–31–1141,
Revision 04, dated February 14, 2002.
(iii) Airbus Mandatory Service Bulletin
A320–31–1334, Revision 04, including
Appendix 01, dated September 12, 2011.
(3) The following service information was
approved for IBR on IBR June 24, 2002 (67
FR 35425, May 20, 2002).
(i) Airbus Service Bulletin A320–31–1106,
Revision 04, dated December 21, 1999.
(4) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 44 51; email:
account.airworth-eas@airbus.com; Internet
https://www.airbus.com.
(5) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
(6) You may also review copies of the
service information that is incorporated by
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14681
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 https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on January
24, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–5859 Filed 3–12–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0318; Directorate
Identifier 2010–CE–033–AD; Amendment
39–16966; AD 2012–04–10]
RIN 2120–AA64
Airworthiness Directives; Burl A.
Rogers (Type Certificate Previously
Held by William Brad Mitchell and
Aeronca, Inc.) Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all Burl
A. Rogers (type certificate previously
held by William Brad Mitchell and
Aeronca, Inc.) Models 15AC and S15AC
airplanes. This AD was prompted by
reports of intergranular exfoliation and
corrosion of the upper and/or lower
wing main spar cap angles found on the
affected airplanes. This AD requires
repetitive inspections of the upper and
lower main wing spar cap angles for
cracks and/or corrosion and installing
inspection access panels. This AD also
requires replacing the wing spar cap
angles if moderate or severe corrosion is
found and applying corrosion inhibitor.
We are issuing this AD to correct the
unsafe condition on these products.
DATES: This AD is effective April 17,
2012.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of April 17, 2012.
ADDRESSES: For service information
identified in this AD, contact Burl’s
Aircraft, LLC, P.O. Box 671487,
Chugiak, Alaska 99567–1487; phone:
(907) 688–3715; fax (907) 688–5031;
email burl@biginalaska.com; Internet:
https://www.burlac.com. You may
review copies of the referenced service
information at the FAA, Small Airplane
SUMMARY:
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Directorate, 901 Locust, Room 301,
Kansas City, MO 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 https://
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 address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
August Asay, Supervisory Aerospace
Engineer, FAA, Anchorage Aircraft
Certification Office, 222 W. 7th Ave.,
#14, Anchorage, Alaska 99513;
telephone: (907) 271–2668; fax: (907)
271–6365; email: august.asay@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM published in the Federal
Register on April 4, 2011 (76 FR 18454).
That NPRM proposed to require
repetitive inspections of the upper and
lower main wing spar cap angles for
cracks and/or corrosion and installing
inspection access panels. That NPRM
also proposed to require replacing the
wing spar cap angles if moderate or
severe corrosion is found and applying
corrosion inhibitor.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal (76 FR 18454,
April 4, 2011) and the FAA’s response
to each comment.
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Request To Extend Comment Period
The Experimental Aircraft
Association (EAA), John Poulter,
Andrew Cooper Crow, Eric Sandberg,
Rodney David Pollard, Kyle W.
Boatright, and 10 other commenters
requested an extension of the comment
period.
The commenters stated that
additional time was needed to receive
all of the data requested through the
Freedom of Information Act and to
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prepare a request for an alternative
method of compliance (AMOC).
We do not agree to extend the
comment period again. We issued the
proposed AD (76 FR 18454, April 4,
2011) with a 45-day open comment
period. Due to several public comments
received at that time requesting an
extension of the comment period to
facilitate fact finding/information
gathering, we issued an extension of the
comment period (76 FR 23920, April 29,
2011) that extended the comment period
for an additional 45 days. Even though
we did not extend the comment period
any further, we have accepted all
comments to the docket that were
received after the comment close date.
We have determined it is in the best
interest of the public to go forward with
this AD to address the unsafe condition
on these airplanes. The public may
always propose AMOCs to show
compliance to the requirements cited in
the AD. We will review and consider all
AMOC requests we receive provided
they follow the procedures in 14 CFR
39.19 and this AD.
We made no change to the AD based
on this comment.
Request To Use Different Inspection
Method
John Poulter, Kyle W. Boatright,
Douglas T. Rounds, Frank Charles,
Gerald Wayne Cox, John Landers, Ron
Craig Cooper, and four other
commenters requested approval to use
the borescope inspection method.
The commenters stated that using a
borescope when inspecting the main
spar cap angles on the wings for
corrosion would save time and the
expense of installing access covers in
the wings.
We agree that a borescope inspection
could provide an acceptable level of
safety for doing the required inspection;
however, we disagree with approving it
for this AD because we do not have
written detailed guidance for doing a
borescope inspection that we can refer
to in this AD at this time.
The public may always propose
AMOCs to show compliance to the
requirements cited in the AD. We will
review and consider all AMOC requests
we receive provided they follow the
procedures in 14 CFR 39.19 and this
AD.
We made no change to the AD based
on this comment.
Request To Change the Costs of
Compliance Section
An anonymous commenter stated that
the Costs of Compliance section should
be re-evaluated.
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The commenter stated that the
estimated cost information in the
proposed AD (76 FR 18454, April 4,
2011) is misleading since some of the
information is presented per wing
instead of per airplane. The commenter
also stated that the estimated cost of
replacing the main spar cap on both
wings could exceed the value of the
airplane, and the estimated cost to
inspect and install inspection panels
could easily amount to 10 to 25 percent
of the value of the airplane.
The commenter stated that there are
less costly, yet as effective, options to
comply with the AD, and we should
include those costs in the AD.
We do not agree with the commenter.
We determined that the estimated costs
stated in the proposed AD (76 FR 18454,
April 4, 2011) represent the most
accurate estimate we can make at this
time. Total fleet repair costs were not
calculated because we have no way of
determining the number of wings that
will be found to be corroded and/or
cracked that will need to be replaced.
The public may always propose
AMOCs to show compliance to the
requirements cited in the AD. The FAA
will review and consider all AMOC
requests we receive provided they
follow the procedures in 14 CFR 39.19
and this AD.
We made no change to the AD based
on this comment.
Request To Incorporate Revised Service
Information
Burl’s Aircraft, LLC issued additional
installation instructions for installing
the 2–1272 reinforcement doubler and
the 2–1285 inspection cover assemblies.
We infer that Burl’s Aircraft, LLC wants
the FAA to include the installation
instructions into the final rule AD
action.
We agree. We have revised the final
rule AD action to incorporate using the
installation instructions.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
with the change described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (76 FR
18454, April 4, 2011) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (76 FR 18454,
April 4, 2011).
We also determined that these
changes will not increase the economic
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burden on any operator or increase the
scope of the AD.
Costs of Compliance
14683
We estimate the following costs to
comply with this AD:
We estimate that this AD will affect
255 airplanes in the U.S. registry.
ESTIMATED COSTS
Cost per product
Action
Labor cost
Parts cost
Initial inspection ..........................................
Installation of inspection access panels
and inspection.
10 work-hours × $85 per hour = $850 .....
30 work-hours × $85 per hour = $2,550 ..
Not applicable .........
$630 ........................
We estimate the following costs to do
any necessary replacements that will be
required based on the results of the
inspections. We have no way of
$850
3,180
Cost on U.S.
operators
$216,750
810,900
determining the number of aircraft that
might need these replacements:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per
product
per wing
Replacement of main spar cap .............................
80 work-hours × $85 per hour = $6,800 per wing
$1,200 per wing ............
$8,000
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
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(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
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2012–04–10 Burl A. Rogers (Type
Certificate Previously Held by William
Brad Mitchell and Aeronca, Inc.)
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Models 15AC and S15AC Airplanes:
Amendment 39–16966; Docket No.
FAA–2011–0318; Directorate Identifier
2010–CE–033–AD.
(a) Effective Date
This AD is effective April 17, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Burl A. Rogers (type
certificate previously held by William Brad
Mitchell and Aeronca, Inc.) Model 15AC and
S15AC airplanes, all serial numbers, that are
certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of
intergranular exfoliation and corrosion of the
upper and/or lower wing main spar cap
angles found on the affected airplanes. We
are issuing this AD to detect and correct
cracks and corrosion in the wing main spar
cap angles, which could result in reduced
strength of the wing spar and the load
carrying capacity of the wing. This could
lead to wing failure and consequent loss of
control.
(f) Actions, Compliance, and Procedures
Comply with this AD within the
compliance times specified, unless already
done (does not eliminate the repetitive
actions of this AD).
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When must it be done?
How must it be done?
(1) Inspect the exposed trailing edges of both
the upper and lower main spar cap angles on
both the left and right wing for signs of
cracks, intergranular exfoliation, and corrosion.
(i) Within the next 25 hours time-in-service
(TIS) after April 17, 2012 (the effective date
of this AD) or within the next 6 months after
April 17, 2012 (the effective date of this
AD), whichever occurs first; or
(ii) If the left and/or right wing have been repaired and both the upper and lower main
spar caps have been replaced using new
parts: Inspect at or before the next annual
inspection that occurs 10 years after the replacement or within the next 100 hours TIS
after April 17, 2012 (the effective date of
this AD), whichever occurs later. This compliance time applies separately to each
wing.
Follow Burl’s Aircraft, LLC Mandatory Service
Bulletin No. 15AC06–08–10, dated June 8,
2010; Burl’s Aircraft, LLC Mandatory Service Bulletin No. 15AC06–08–10, Amendment A, dated June 23, 2010; or Burl’s Aircraft, LLC Mandatory Service Bulletin No.
15AC06–08–10, Amendment B, dated June
23, 2010, Rev. Original, September 15,
2011; and FAA Advisory Circular (AC)
43.13–1B, Change 1, Chapter 6. AC 43.13–
1B can be found at https://rgl.faa.gov/.
(2) After completing the inspection required in
paragraph (f)(1) of this AD, install new inspection hole skin reinforcement doublers
and the associated screw cover plate in both
the left and right wing.
(i) Within 12 months after April 17, 2012 (the
effective date of this AD); or
(ii) If the left and/or right wing have been repaired and both the upper and lower main
spar caps have been replaced using new
parts: At or before the next annual inspection that occurs 10 years after the replacement or within the next 100 hours TIS after
April 17, 2012 (the effective date of this
AD), whichever occurs later. This compliance time applies separately to each wing.
Follow Burl’s Aircraft, LLC Mandatory Service
Bulletin No. 15AC06–08–10, dated June 8,
2010, which includes Burl’s Aircraft, LLC
Drawing No. SB 15AC06–08–10 (not
dated); Burl’s Aircraft, LLC Mandatory Service Bulletin No. 15AC06–08–10, Amendment A, dated June 23, 2010; or Burl’s Aircraft, LLC Mandatory Service Bulletin No.
15AC06–08–10, Amendment B, dated June
23, 2010, Rev. Original, September 15,
2011, which references Burl’s Aircraft, LLC
Installation Instruction No. SB 15AC06–08–
10, dated September 9, 2011, Burl’s Aircraft, LLC Sketch No. SB 15AC06–08–10,
dated September 9, 2011, and Burl’s Aircraft, LLC Drawing No. 2–1272 Splice,
dated September 6, 2011; and FAA Advisory Circular (AC) 43.13–1B, Change 1,
Chapter 6. AC 43.13–1B can be found at
https://rgl.faa.gov/.
(3) After completing the inspection required in
paragraph (f)(1) of this AD and installing the
new inspection hole skin reinforcement doublers in the left and right wing as required in
paragraph (f)(2) of this AD, through the inspection access panels, inspect the leading
and trailing edges of both the upper and
lower main spar cap angles on both the left
and right wing for signs of cracks, intergranular exfoliation and corrosion.
Before further flight after installing the inspection hole skin reinforcement doublers as required in paragraph (f)(2) of this AD.
Follow Burl’s Aircraft, LLC Mandatory Service
Bulletin No. 15AC06–08–10, dated June 8,
2010; Burl’s Aircraft, LLC Mandatory Service Bulletin No. 15AC06–08–10, Amendment A, dated June 23, 2010; or Burl’s Aircraft, LLC Mandatory Service Bulletin No.
15AC06–08–10, Amendment B, dated June
23, 2010, Rev. Original, September 15,
2011.
(4) Remove any light corrosion found during the
inspection required in paragraph (f)(3) of this
AD and treat the entirety of both the upper
and lower main spar cap angles on both the
left and right wing with corrosion inhibitor.
Before further flight after the inspection required in paragraph (f)(3) of this AD.
Follow Burl’s Aircraft, LLC Mandatory Service
Bulletin No. 15AC06–08–10, dated June 8,
2010; Burl’s Aircraft, LLC Mandatory Service Bulletin No. 15AC06–08–10, Amendment A, dated June 23, 2010; or Burl’s Aircraft, LLC Mandatory Service Bulletin No.
15AC06–08–10, Amendment B, dated June
23, 2010, Rev. Original, September 15,
2011.
(5) If cracks, intergranular exfoliation, or moderate or severe corrosion is found during the
inspection required in paragraphs (f)(1) or
(f)(3) of this AD, replace the affected main
spar cap angles in their entirety as a single
piece. Splicing of the main spar cap angles is
not permitted.
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What must be done?
Before further flight after the inspection required in paragraphs (f)(1) and (f)(3) of this
AD.
Follow Burl’s Aircraft, LLC Mandatory Service
Bulletin No. 15AC06–08–10, dated June 8,
2010; Burl’s Aircraft, LLC Mandatory Service Bulletin No. 15AC06–08–10, Amendment A, dated June 23, 2010; or Burl’s Aircraft, LLC Mandatory Service Bulletin No.
15AC06–08–10, Amendment B, dated June
23, 2010, Rev. Original, September 15,
2011; and contact Burl’s Aircraft, LLC in
paragraph (i) of this AD for a replacement
scheme and incorporate the replacement
scheme.
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14685
What must be done?
When must it be done?
How must it be done?
(6) Removing the wing inspection access panels, repetitively inspect both the upper and
lower forward main spar caps on both the left
and right wing for signs of cracks, intergranular exfoliation, and corrosion.
Repetitively thereafter at intervals not to exceed every 12 months after the inspection
required in paragraph (f)(3) of this AD.
Follow Burl’s Aircraft, LLC Mandatory Service
Bulletin No. 15AC06–08–10, dated June 8,
2010; Burl’s Aircraft, LLC Mandatory Service Bulletin No. 15AC06–08–10, Amendment A, dated June 23, 2010; or Burl’s Aircraft, LLC Mandatory Service Bulletin No.
15AC06–08–10, Amendment B, dated June
23, 2010, Rev. Original, September 15,
2011; and FAA Advisory Circular (AC)
43.13–1B, Change 1, Chapter 6. AC 43.13–
1B can be found at https://rgl.faa.gov/.
(7) After each inspection required in paragraph
(f)(6) of this AD, if only light corrosion is
found, remove the corrosion and treat the
main spar cap angles with corrosion inhibitor.
Before further flight after each inspection required in paragraph (f)(6) of this AD. Continue with the repetitive inspections required
in paragraph (f)(6) of this AD.
Follow Burl’s Aircraft, LLC Mandatory Service
Bulletin No. 15AC06–08–10, dated June 8,
2010; Burl’s Aircraft, LLC Mandatory Service Bulletin No. 15AC06–08–10, Amendment A, dated June 23, 2010; or Burl’s Aircraft, LLC Mandatory Service Bulletin No.
15AC06–08–10, Amendment B, dated June
23, 2010, Rev. Original, September 15,
2011; and FAA Advisory Circular (AC)
43.13–1B, Change 1, Chapter 6. AC 43.13–
1B can be found at https://rgl.faa.gov/. Contact Burl’s Aircraft, LLC in paragraph (i) of
this AD for a replacement scheme and incorporate the replacement scheme.
(8) After each inspection required in paragraph
(f)(6) of this AD, if cracks, intergranular exfoliation, or moderate or severe corrosion is
found, replace the affected main spar cap angles in their entirety as a single piece. Splicing of the main spar cap angles is not permitted.
Before further flight after each inspection required in paragraph (f)(6) of this AD. Continue with the repetitive inspections required
in paragraph (f)(6) of this AD.
Follow Burl’s Aircraft, LLC Mandatory Service
Bulletin No. 15AC06–08–10, dated June 8,
2010; Burl’s Aircraft, LLC Mandatory Service Bulletin No. 15AC06–08–10, Amendment A, dated June 23, 2010; or Burl’s Aircraft, LLC Mandatory Service Bulletin No.
15AC06–08–10, Amendment B, dated June
23, 2010, Rev. Original, September 15,
2011; and FAA Advisory Circular (AC)
43.13–1B, Change 1, Chapter 6. AC 43.13–
1B can be found at https://rgl.faa.gov/. Contact Burl’s Aircraft, LLC in paragraph (i) of
this AD for a replacement scheme and incorporate the replacement scheme.
(9) Only install main spar cap angles that have
been inspected and are free of cracks, intergranular exfoliation, or moderate or severe
corrosion.
As of April 17, 2012 (the effective date of this
AD).
Not applicable.
srobinson on DSK4SPTVN1PROD with RULES
(g) Alternative Methods of Compliance
(AMOCs)
telephone: (907) 271–2668; fax: (907) 271–
6365; email: august.asay@faa.gov.
(1) The Manager, Anchorage Aircraft
Certification Office (ACO), 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 appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(i) Material Incorporated by Reference
(h) Related Information
For more information about this AD,
contact August Asay, Supervisory Aerospace
Engineer, FAA, Anchorage ACO, 222 W. 7th
Ave., #14, Anchorage, Alaska 99513;
VerDate Mar<15>2010
17:06 Mar 12, 2012
Jkt 226001
(1) You must use the following service
information to do the actions required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference (IBR) under 5
U.S.C. 552(a) and 1 CFR part 51.
(i) Burl’s Aircraft, LLC Mandatory Service
Bulletin No. 15AC06–08–10, dated June 8,
2010;
(ii) Burl’s Aircraft, LLC Mandatory Service
Bulletin No. 15AC06–08–10, Amendment A,
dated June 23, 2010;
(iii) Burl’s Aircraft, LLC Mandatory Service
Bulletin No. 15AC06–08–10, Amendment B,
dated June 23, 2010, Rev. Original,
September 15, 2011;
(iv) Burl’s Aircraft, LLC Installation
Instruction No. SB 15AC06–08–10, dated
September 9, 2011;
(v) Burl’s Aircraft, LLC Drawing No. SB
15AC06–08–10 (not dated);
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
(vi) Burl’s Aircraft, LLC Sketch No. SB
15AC06–08–10, dated September 9, 2011;
and
(vii) Burl’s Aircraft, LLC Drawing No. 2–
1272 Splice, dated September 6, 2011; and
(2) For service information identified in
this AD, contact Burl’s Aircraft, LLC, P.O.
Box 671487, Chugiak, Alaska 99567–1487;
telephone: (907) 688–3715; fax (907) 688–
5031; email burl@biginalaska.com; Internet:
https://www.burlac.com.
(3) You may review copies of the service
information at the FAA, Small Airplane
Directorate, 901 Locust, Room 301, Kansas
City, MO 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 NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
E:\FR\FM\13MRR1.SGM
13MRR1
14686
Federal Register / Vol. 77, No. 49 / Tuesday, March 13, 2012 / Rules and Regulations
Issued in Kansas City, Missouri, on
February 21, 2012.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2012–5864 Filed 3–12–12; 8:45 am]
BILLING CODE 4910–13–P
NATIONAL AERONAUTICS AND
SPACE ADMINISTRATION
14 CFR Part 1245
[Notice: (12–022)]
RIN 2700–AD63
Claims for Patent and Copyright
Infringement
National Aeronautics and
Space Administration.
ACTION: Final rule.
AGENCY:
The following are National
Aeronautics and Space Administration
(NASA) regulations relating to
requirements for the filing of claims
against NASA where a potential
claimant believes NASA is infringing
privately owned rights in patented
inventions or copyrighted works. The
requirements for filing an administrative
claim are important since the filing of a
claim carries with it certain rights
relating to the applicable statute of
limitations for filing suit against the
Government. The regulations set forth
guidelines as to what NASA considers
necessary to file a claim for patent or
copyright infringement, and they also
provide for written notification to the
claimant upon completion of an
investigation by NASA.
DATES: This rule is effective on March
13, 2012.
FOR FURTHER INFORMATION CONTACT: Ms.
Helen M. Galus, National Aeronautics
and Space Administration, Office of the
General Counsel, Washington, DC
20546–0001. Telephone 202–358–3437.
SUPPLEMENTARY INFORMATION: On July
26, 2011, the Administrator published a
notice of proposed rulemaking (NPRM)
for patent and copyright infringement
claims in the Federal Register (76 FR
44504). No public comments were
received. Accordingly, NASA is issuing
this rule with minor edits and only one
change to reduce burden on
respondents, namely, § 1245.202(b)(6),
was amended to delete the request for
a brief summary of any defenses or
counterclaims made and positions
maintained by opposing parties
regarding noninfringement of patent(s),
in prior initiated litigation.
The National Aeronautics and Space
Act (51 U.S.C. 20113) authorizes the
srobinson on DSK4SPTVN1PROD with RULES
SUMMARY:
VerDate Mar<15>2010
17:06 Mar 12, 2012
Jkt 226001
Administrator of NASA to settle
administrative claims of patent and
copyright infringement by NASA. In
addition to that authority to acquire
license rights and interests in patents
and copyrights through settlement of
claims, the Administrator has authority
to settle claims of patent and copyright
infringement pursuant to 22 U.S.C.
2356, 35 U.S.C. 183 and 286, and 28
U.S.C. 1498(b).
In accordance with these authorities,
NASA is issuing regulations setting
forth requirements for the filing of
claims against NASA where a potential
claimant believes NASA is infringing
privately owned rights in patented
inventions or copyrighted works. The
regulations are designed to inform
potential claimants as to what
information must be supplied in their
communication to NASA regarding
alleged infringement before NASA will
consider a claim to have been filed. The
regulations identify certain commonly
received communications which are
concerned with rights in patents and
copyrights, but which will not be
considered sufficient to constitute the
formal filing of a claim.
The requirements for filing an
administrative claim are important since
the filing of a claim carries with it
certain rights relating to the applicable
statute of limitations for filing suit
against the Government. In the case of
patent infringement claims, Title 35
U.S.C. 286 provides that the six-year
statute of limitations for filing suits for
patent infringement may, in the case of
claims against the Government, be
tolled up to six years between the date
of receipt of a written claim for
compensation by the Government and
the date of mailing by the Government
of a notice that the claim has been
denied. Copyright infringement claims
can be tolled indefinitely under 28
U.S.C. 1498(b) between the date of
receipt of a written claim for
compensation by the Government and
the date of mailing by the Government
of a notice that the claim has been
denied. The regulations set forth
guidelines as to what NASA considers
necessary to file a claim for patent or
copyright infringement.
Section 1245.202(a) provides that in
order for a potential claimant’s
communication to NASA to formally
instigate a claim, it must specifically
allege infringement by NASA, request
compensation, identify a patent or
copyright alleged to be infringed, and
indicate an act or item which the
potential claimant believes infringes the
claimant’s patent or copyright. Section
1245.203(a) advises the potential
claimant where to forward
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
communications regarding the alleged
infringement. Section 1245.202(b) of the
regulation identifies information which,
although not necessary in order for a
communication to be considered
sufficient to constitute the filing of a
claim, is usually necessary to process a
claim and, therefore, if presented
initially with the claim, may serve to
expedite the handling of the claim. The
regulations provide for written
notification to the claimant upon
completion of an investigation by
NASA.
The revisions to this rule are part of
NASA’s retrospective plan under E.O.
13563 completed in August 2011.
NASA’s full plan can be accessed at:
https://www.nasa.gov/pdf/581545main
_Final%20Plan%20for%20
Retrospective%20Analysis%20of%20
Existing%20Regulations.pdf.
Regulatory Analysis Section
Paperwork Reduction Act Statement
This rule does not contain an
information collection requirement
subject to the Paperwork Reduction Act
of 1995 (44 U.S.C. 3501 et seq.).
Executive Order 12866 and Executive
Order 13563
Executive Orders 13563 and 12866
direct agencies to assess all costs and
benefits of available regulatory
alternatives and, if regulation is
necessary, to select regulatory
approaches that maximize net benefits
(including potential economic,
environmental, public health and safety
effects, distributive impacts, and
equity). Executive Order 13563
emphasizes the importance of
quantifying both costs and benefits, of
reducing costs, of harmonizing rules,
and of promoting flexibility. This rule
has been designated a ‘‘significant
regulatory action’’ although not
economically significant, under section
3(f) of Executive Order 12866.
Accordingly, the rule has been reviewed
by the Office of Management and
Budget.
Regulatory Flexibility Act
It has been certified that this rule is
not subject to the Regulatory Flexibility
Act (5 U.S.C. 601) because it would not,
if promulgated, have a significant
economic impact on a substantial
number of small entities. The rule sets
forth policies and procedures for the
filing and disposition of claims of
infringement of privately owned rights
in patented inventions or copyrighted
works asserted against NASA. These
policies and procedures would not have
a significant economic impact on a
E:\FR\FM\13MRR1.SGM
13MRR1
]]>Agencies
[Federal Register Volume 77, Number 49 (Tuesday, March 13, 2012)]
[Rules and Regulations]
[Pages 14681-14686]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-5864]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0318; Directorate Identifier 2010-CE-033-AD;
Amendment 39-16966; AD 2012-04-10]
RIN 2120-AA64
Airworthiness Directives; Burl A. Rogers (Type Certificate
Previously Held by William Brad Mitchell and Aeronca, Inc.) Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Burl A. Rogers (type certificate previously held by William Brad
Mitchell and Aeronca, Inc.) Models 15AC and S15AC airplanes. This AD
was prompted by reports of intergranular exfoliation and corrosion of
the upper and/or lower wing main spar cap angles found on the affected
airplanes. This AD requires repetitive inspections of the upper and
lower main wing spar cap angles for cracks and/or corrosion and
installing inspection access panels. This AD also requires replacing
the wing spar cap angles if moderate or severe corrosion is found and
applying corrosion inhibitor. We are issuing this AD to correct the
unsafe condition on these products.
DATES: This AD is effective April 17, 2012.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of April 17,
2012.
ADDRESSES: For service information identified in this AD, contact
Burl's Aircraft, LLC, P.O. Box 671487, Chugiak, Alaska 99567-1487;
phone: (907) 688-3715; fax (907) 688-5031; email burl@biginalaska.com;
Internet: https://www.burlac.com. You may review copies of the
referenced service information at the FAA, Small Airplane
[[Page 14682]]
Directorate, 901 Locust, Room 301, Kansas City, MO 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 https://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 address for the
Docket Office (phone: 800-647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: August Asay, Supervisory Aerospace
Engineer, FAA, Anchorage Aircraft Certification Office, 222 W. 7th
Ave., 14, Anchorage, Alaska 99513; telephone: (907) 271-2668;
fax: (907) 271-6365; email: august.asay@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM published in the Federal Register on April 4, 2011 (76 FR
18454). That NPRM proposed to require repetitive inspections of the
upper and lower main wing spar cap angles for cracks and/or corrosion
and installing inspection access panels. That NPRM also proposed to
require replacing the wing spar cap angles if moderate or severe
corrosion is found and applying corrosion inhibitor.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(76 FR 18454, April 4, 2011) and the FAA's response to each comment.
Request To Extend Comment Period
The Experimental Aircraft Association (EAA), John Poulter, Andrew
Cooper Crow, Eric Sandberg, Rodney David Pollard, Kyle W. Boatright,
and 10 other commenters requested an extension of the comment period.
The commenters stated that additional time was needed to receive
all of the data requested through the Freedom of Information Act and to
prepare a request for an alternative method of compliance (AMOC).
We do not agree to extend the comment period again. We issued the
proposed AD (76 FR 18454, April 4, 2011) with a 45-day open comment
period. Due to several public comments received at that time requesting
an extension of the comment period to facilitate fact finding/
information gathering, we issued an extension of the comment period (76
FR 23920, April 29, 2011) that extended the comment period for an
additional 45 days. Even though we did not extend the comment period
any further, we have accepted all comments to the docket that were
received after the comment close date.
We have determined it is in the best interest of the public to go
forward with this AD to address the unsafe condition on these
airplanes. The public may always propose AMOCs to show compliance to
the requirements cited in the AD. We will review and consider all AMOC
requests we receive provided they follow the procedures in 14 CFR 39.19
and this AD.
We made no change to the AD based on this comment.
Request To Use Different Inspection Method
John Poulter, Kyle W. Boatright, Douglas T. Rounds, Frank Charles,
Gerald Wayne Cox, John Landers, Ron Craig Cooper, and four other
commenters requested approval to use the borescope inspection method.
The commenters stated that using a borescope when inspecting the
main spar cap angles on the wings for corrosion would save time and the
expense of installing access covers in the wings.
We agree that a borescope inspection could provide an acceptable
level of safety for doing the required inspection; however, we disagree
with approving it for this AD because we do not have written detailed
guidance for doing a borescope inspection that we can refer to in this
AD at this time.
The public may always propose AMOCs to show compliance to the
requirements cited in the AD. We will review and consider all AMOC
requests we receive provided they follow the procedures in 14 CFR 39.19
and this AD.
We made no change to the AD based on this comment.
Request To Change the Costs of Compliance Section
An anonymous commenter stated that the Costs of Compliance section
should be re-evaluated.
The commenter stated that the estimated cost information in the
proposed AD (76 FR 18454, April 4, 2011) is misleading since some of
the information is presented per wing instead of per airplane. The
commenter also stated that the estimated cost of replacing the main
spar cap on both wings could exceed the value of the airplane, and the
estimated cost to inspect and install inspection panels could easily
amount to 10 to 25 percent of the value of the airplane.
The commenter stated that there are less costly, yet as effective,
options to comply with the AD, and we should include those costs in the
AD.
We do not agree with the commenter. We determined that the
estimated costs stated in the proposed AD (76 FR 18454, April 4, 2011)
represent the most accurate estimate we can make at this time. Total
fleet repair costs were not calculated because we have no way of
determining the number of wings that will be found to be corroded and/
or cracked that will need to be replaced.
The public may always propose AMOCs to show compliance to the
requirements cited in the AD. The FAA will review and consider all AMOC
requests we receive provided they follow the procedures in 14 CFR 39.19
and this AD.
We made no change to the AD based on this comment.
Request To Incorporate Revised Service Information
Burl's Aircraft, LLC issued additional installation instructions
for installing the 2-1272 reinforcement doubler and the 2-1285
inspection cover assemblies. We infer that Burl's Aircraft, LLC wants
the FAA to include the installation instructions into the final rule AD
action.
We agree. We have revised the final rule AD action to incorporate
using the installation instructions.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the change described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (76 FR 18454, April 4, 2011) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (76 FR 18454, April 4, 2011).
We also determined that these changes will not increase the
economic
[[Page 14683]]
burden on any operator or increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect 255 airplanes in the U.S.
registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Initial inspection............... 10 work-hours x $85 per Not applicable..... $850 $216,750
hour = $850.
Installation of inspection access 30 work-hours x $85 per $630............... 3,180 810,900
panels and inspection. hour = $2,550.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that will be required based on the results of the inspections. We have
no way of determining the number of aircraft that might need these
replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product per
wing
----------------------------------------------------------------------------------------------------------------
Replacement of main spar cap.......... 80 work-hours x $85 per hour $1,200 per wing......... $8,000
= $6,800 per wing.
----------------------------------------------------------------------------------------------------------------
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
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 adding the following new airworthiness
directive (AD):
2012-04-10 Burl A. Rogers (Type Certificate Previously Held by
William Brad Mitchell and Aeronca, Inc.) Models 15AC and S15AC
Airplanes: Amendment 39-16966; Docket No. FAA-2011-0318; Directorate
Identifier 2010-CE-033-AD.
(a) Effective Date
This AD is effective April 17, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Burl A. Rogers (type certificate previously
held by William Brad Mitchell and Aeronca, Inc.) Model 15AC and
S15AC airplanes, all serial numbers, that are certificated in any
category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of intergranular exfoliation and
corrosion of the upper and/or lower wing main spar cap angles found
on the affected airplanes. We are issuing this AD to detect and
correct cracks and corrosion in the wing main spar cap angles, which
could result in reduced strength of the wing spar and the load
carrying capacity of the wing. This could lead to wing failure and
consequent loss of control.
(f) Actions, Compliance, and Procedures
Comply with this AD within the compliance times specified,
unless already done (does not eliminate the repetitive actions of
this AD).
[[Page 14684]]
------------------------------------------------------------------------
When must it be
What must be done? done? How must it be done?
------------------------------------------------------------------------
(1) Inspect the exposed (i) Within the next Follow Burl's
trailing edges of both the 25 hours time-in- Aircraft, LLC
upper and lower main spar service (TIS) after Mandatory Service
cap angles on both the left April 17, 2012 (the Bulletin No. 15AC06-
and right wing for signs of effective date of 08-10, dated June
cracks, intergranular this AD) or within 8, 2010; Burl's
exfoliation, and corrosion. the next 6 months Aircraft, LLC
after April 17, Mandatory Service
2012 (the effective Bulletin No. 15AC06-
date of this AD), 08-10, Amendment A,
whichever occurs dated June 23,
first; or 2010; or Burl's
(ii) If the left and/ Aircraft, LLC
or right wing have Mandatory Service
been repaired and Bulletin No. 15AC06-
both the upper and 08-10, Amendment B,
lower main spar dated June 23,
caps have been 2010, Rev.
replaced using new Original, September
parts: Inspect at 15, 2011; and FAA
or before the next Advisory Circular
annual inspection (AC) 43.13-1B,
that occurs 10 Change 1, Chapter
years after the 6. AC 43.13-1B can
replacement or be found at https://
within the next 100 rgl.faa.gov/.
hours TIS after
April 17, 2012 (the
effective date of
this AD), whichever
occurs later. This
compliance time
applies separately
to each wing.
------------------------------------------------------------------------
(2) After completing the (i) Within 12 months Follow Burl's
inspection required in after April 17, Aircraft, LLC
paragraph (f)(1) of this 2012 (the effective Mandatory Service
AD, install new inspection date of this AD); Bulletin No. 15AC06-
hole skin reinforcement or 08-10, dated June
doublers and the associated (ii) If the left and/ 8, 2010, which
screw cover plate in both or right wing have includes Burl's
the left and right wing. been repaired and Aircraft, LLC
both the upper and Drawing No. SB
lower main spar 15AC06-08-10 (not
caps have been dated); Burl's
replaced using new Aircraft, LLC
parts: At or before Mandatory Service
the next annual Bulletin No. 15AC06-
inspection that 08-10, Amendment A,
occurs 10 years dated June 23,
after the 2010; or Burl's
replacement or Aircraft, LLC
within the next 100 Mandatory Service
hours TIS after Bulletin No. 15AC06-
April 17, 2012 (the 08-10, Amendment B,
effective date of dated June 23,
this AD), whichever 2010, Rev.
occurs later. This Original, September
compliance time 15, 2011, which
applies separately references Burl's
to each wing. Aircraft, LLC
Installation
Instruction No. SB
15AC06-08-10, dated
September 9, 2011,
Burl's Aircraft,
LLC Sketch No. SB
15AC06-08-10, dated
September 9, 2011,
and Burl's
Aircraft, LLC
Drawing No. 2-1272
Splice, dated
September 6, 2011;
and FAA Advisory
Circular (AC) 43.13-
1B, Change 1,
Chapter 6. AC 43.13-
1B can be found at
https://rgl.faa.gov/
.
------------------------------------------------------------------------
(3) After completing the Before further Follow Burl's
inspection required in flight after Aircraft, LLC
paragraph (f)(1) of this AD installing the Mandatory Service
and installing the new inspection hole Bulletin No. 15AC06-
inspection hole skin skin reinforcement 08-10, dated June
reinforcement doublers in doublers as 8, 2010; Burl's
the left and right wing as required in Aircraft, LLC
required in paragraph paragraph (f)(2) of Mandatory Service
(f)(2) of this AD, through this AD. Bulletin No. 15AC06-
the inspection access 08-10, Amendment A,
panels, inspect the leading dated June 23,
and trailing edges of both 2010; or Burl's
the upper and lower main Aircraft, LLC
spar cap angles on both the Mandatory Service
left and right wing for Bulletin No. 15AC06-
signs of cracks, 08-10, Amendment B,
intergranular exfoliation dated June 23,
and corrosion. 2010, Rev.
Original, September
15, 2011.
------------------------------------------------------------------------
(4) Remove any light Before further Follow Burl's
corrosion found during the flight after the Aircraft, LLC
inspection required in inspection required Mandatory Service
paragraph (f)(3) of this AD in paragraph (f)(3) Bulletin No. 15AC06-
and treat the entirety of of this AD. 08-10, dated June
both the upper and lower 8, 2010; Burl's
main spar cap angles on Aircraft, LLC
both the left and right Mandatory Service
wing with corrosion Bulletin No. 15AC06-
inhibitor. 08-10, Amendment A,
dated June 23,
2010; or Burl's
Aircraft, LLC
Mandatory Service
Bulletin No. 15AC06-
08-10, Amendment B,
dated June 23,
2010, Rev.
Original, September
15, 2011.
------------------------------------------------------------------------
(5) If cracks, intergranular Before further Follow Burl's
exfoliation, or moderate or flight after the Aircraft, LLC
severe corrosion is found inspection required Mandatory Service
during the inspection in paragraphs Bulletin No. 15AC06-
required in paragraphs (f)(1) and (f)(3) 08-10, dated June
(f)(1) or (f)(3) of this of this AD. 8, 2010; Burl's
AD, replace the affected Aircraft, LLC
main spar cap angles in Mandatory Service
their entirety as a single Bulletin No. 15AC06-
piece. Splicing of the main 08-10, Amendment A,
spar cap angles is not dated June 23,
permitted. 2010; or Burl's
Aircraft, LLC
Mandatory Service
Bulletin No. 15AC06-
08-10, Amendment B,
dated June 23,
2010, Rev.
Original, September
15, 2011; and
contact Burl's
Aircraft, LLC in
paragraph (i) of
this AD for a
replacement scheme
and incorporate the
replacement scheme.
------------------------------------------------------------------------
[[Page 14685]]
(6) Removing the wing Repetitively Follow Burl's
inspection access panels, thereafter at Aircraft, LLC
repetitively inspect both intervals not to Mandatory Service
the upper and lower forward exceed every 12 Bulletin No. 15AC06-
main spar caps on both the months after the 08-10, dated June
left and right wing for inspection required 8, 2010; Burl's
signs of cracks, in paragraph (f)(3) Aircraft, LLC
intergranular exfoliation, of this AD. Mandatory Service
and corrosion. Bulletin No. 15AC06-
08-10, Amendment A,
dated June 23,
2010; or Burl's
Aircraft, LLC
Mandatory Service
Bulletin No. 15AC06-
08-10, Amendment B,
dated June 23,
2010, Rev.
Original, September
15, 2011; and FAA
Advisory Circular
(AC) 43.13-1B,
Change 1, Chapter
6. AC 43.13-1B can
be found at https://rgl.faa.gov/.
------------------------------------------------------------------------
(7) After each inspection Before further Follow Burl's
required in paragraph flight after each Aircraft, LLC
(f)(6) of this AD, if only inspection required Mandatory Service
light corrosion is found, in paragraph (f)(6) Bulletin No. 15AC06-
remove the corrosion and of this AD. 08-10, dated June
treat the main spar cap Continue with the 8, 2010; Burl's
angles with corrosion repetitive Aircraft, LLC
inhibitor. inspections Mandatory Service
required in Bulletin No. 15AC06-
paragraph (f)(6) of 08-10, Amendment A,
this AD. dated June 23,
2010; or Burl's
Aircraft, LLC
Mandatory Service
Bulletin No. 15AC06-
08-10, Amendment B,
dated June 23,
2010, Rev.
Original, September
15, 2011; and FAA
Advisory Circular
(AC) 43.13-1B,
Change 1, Chapter
6. AC 43.13-1B can
be found at https://rgl.faa.gov/.
Contact Burl's
Aircraft, LLC in
paragraph (i) of
this AD for a
replacement scheme
and incorporate the
replacement scheme.
------------------------------------------------------------------------
(8) After each inspection Before further Follow Burl's
required in paragraph flight after each Aircraft, LLC
(f)(6) of this AD, if inspection required Mandatory Service
cracks, intergranular in paragraph (f)(6) Bulletin No. 15AC06-
exfoliation, or moderate or of this AD. 08-10, dated June
severe corrosion is found, Continue with the 8, 2010; Burl's
replace the affected main repetitive Aircraft, LLC
spar cap angles in their inspections Mandatory Service
entirety as a single piece. required in Bulletin No. 15AC06-
Splicing of the main spar paragraph (f)(6) of 08-10, Amendment A,
cap angles is not permitted. this AD. dated June 23,
2010; or Burl's
Aircraft, LLC
Mandatory Service
Bulletin No. 15AC06-
08-10, Amendment B,
dated June 23,
2010, Rev.
Original, September
15, 2011; and FAA
Advisory Circular
(AC) 43.13-1B,
Change 1, Chapter
6. AC 43.13-1B can
be found at https://rgl.faa.gov/.
Contact Burl's
Aircraft, LLC in
paragraph (i) of
this AD for a
replacement scheme
and incorporate the
replacement scheme.
------------------------------------------------------------------------
(9) Only install main spar As of April 17, 2012 Not applicable.
cap angles that have been (the effective date
inspected and are free of of this AD).
cracks, intergranular
exfoliation, or moderate or
severe corrosion.
------------------------------------------------------------------------
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Anchorage Aircraft Certification Office (ACO),
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 appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(h) Related Information
For more information about this AD, contact August Asay,
Supervisory Aerospace Engineer, FAA, Anchorage ACO, 222 W. 7th Ave.,
14, Anchorage, Alaska 99513; telephone: (907) 271-2668;
fax: (907) 271-6365; email: august.asay@faa.gov.
(i) Material Incorporated by Reference
(1) You must use the following service information to do the
actions required by this AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the incorporation by
reference (IBR) under 5 U.S.C. 552(a) and 1 CFR part 51.
(i) Burl's Aircraft, LLC Mandatory Service Bulletin No. 15AC06-
08-10, dated June 8, 2010;
(ii) Burl's Aircraft, LLC Mandatory Service Bulletin No. 15AC06-
08-10, Amendment A, dated June 23, 2010;
(iii) Burl's Aircraft, LLC Mandatory Service Bulletin No.
15AC06-08-10, Amendment B, dated June 23, 2010, Rev. Original,
September 15, 2011;
(iv) Burl's Aircraft, LLC Installation Instruction No. SB
15AC06-08-10, dated September 9, 2011;
(v) Burl's Aircraft, LLC Drawing No. SB 15AC06-08-10 (not
dated);
(vi) Burl's Aircraft, LLC Sketch No. SB 15AC06-08-10, dated
September 9, 2011; and
(vii) Burl's Aircraft, LLC Drawing No. 2-1272 Splice, dated
September 6, 2011; and
(2) For service information identified in this AD, contact
Burl's Aircraft, LLC, P.O. Box 671487, Chugiak, Alaska 99567-1487;
telephone: (907) 688-3715; fax (907) 688-5031; email
burl@biginalaska.com; Internet: https://www.burlac.com.
(3) You may review copies of the service information at the FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, MO
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 NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
[[Page 14686]]
Issued in Kansas City, Missouri, on February 21, 2012.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2012-5864 Filed 3-12-12; 8:45 am]
BILLING CODE 4910-13-P
