[Federal Register Volume 76, Number 64 (Monday, April 4, 2011)]
[Proposed Rules]
[Pages 18454-18457]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-7878]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0318; Directorate Identifier 2010-CE-033-AD]
RIN 2120-AA64
Airworthiness Directives; Burl A. Rogers (Type Certificate
Previously Held by William Brad Mitchell and Aeronca, Inc.) Models 15AC
and S15AC Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD would require repetitive
inspections of the upper and lower main wing spar cap angles for cracks
and/or corrosion and installing inspection access panels. This AD would
also require replacing the wing spar cap angles if moderate or severe
corrosion is found and applying corrosion inhibitor. This proposed 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 proposing this AD to detect and correct cracks,
intergranular exfoliation 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.
DATES: We must receive comments on this proposed AD by May 19, 2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Burl's Aircraft, LLC, P.O. Box 671487, Chugiak, Alaska 99567-1487;
phone: (907) 688-3715; fax (907) 688-5031; e-mail [email protected];
Internet: http://www.burlac.com. You may review copies of the
referenced 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.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Eric Wright, Aerospace Engineer, FAA,
Anchorage Aircraft Certification Office, 222 W. 7th Ave., 14,
Anchorage, Alaska 99513; telephone: (907) 271-2648; fax: (907) 271-
6365; e-mail: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section.
Include ``Docket No. FAA-2011-0318; Directorate Identifier 2010-CE-
033-AD'' at the beginning of your comments. We specifically invite
comments on the overall regulatory, economic, environmental, and energy
aspects of this proposed AD. We will consider all comments received by
the closing date and may amend this proposed AD because of those
comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
[[Page 18455]]
Discussion
Since first discovered in 1998, we have received 34 reports of
intergranular corrosion and exfoliation found on the upper and lower
wing main spar cap angles on Burl A. Rogers Models 15AC and S15AC
airplanes. The cause of the corrosion is unknown and does not have a
direct correlation to the type, location, or operation performed by the
airplane. In the original type design wing skins, there is a lack of
access panels, making the main wing spar caps difficult to inspect. If
left undetected, the corrosion in the wing main spar caps could become
severe enough to reduce the strength of the spar and the load carrying
capacity of the wing. This condition, if not corrected, could result in
wing failure. This failure could lead to loss of control.
Relevant Service Information
We have reviewed Burl's Aircraft, LLC Mandatory Service Bulletin
No. 15AC06-08-10, dated June 8, 2010.
The service information describes procedures for:
Inspecting the leading and trailing edges of the upper and
lower main wing spar cap angles for cracks, intergranular exfoliation,
and corrosion;
Installing wing inspection access panels;
Applying corrosion inhibitor on the upper and lower spar
cap angles; and
Replacing the main wing spar cap angles if cracks,
intergranular exfoliation, or moderate or severe corrosion is found.
Corrosion definitions and limits are contained in FAA Advisory
Circular (AC) 43-4A, paragraph 640 (a)(b)(c).
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in the service information described.
Costs of Compliance
We estimate that this proposed AD would affect 255 airplanes in the
U.S. registry.
We estimate the following costs to comply with this proposed AD:
Estimated costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Initial inspection................ 10 work-hours x $85 Not applicable....... $850 $216,750
per hour = $850.
Installation of inspection access 30 work-hours x $85 $630................. 3,180 810,900
panels and inspection. per hour = $2,550.
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We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed
inspections. We have no way of determining the number of aircraft that
might need these replacements:
On-Condition Costs
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Cost per
Action Labor cost Parts cost product per
wing
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Replacement of main spar cap............ 80 work-hours x $85 per $1,200 per wing........... $8,000
hour = $6,800 per wing.
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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
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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 adding the following new
airworthiness directive (AD):
Burl A. Rogers (Type Certificate Previously Held by William Brad
Mitchell and Aeronca, Inc.) Models 15AC and S15AC
[[Page 18456]]
Airplanes: Docket No. FAA-2011-0318; Directorate Identifier 2010-CE-
033-AD.
Comments Due Date
(a) We must receive comments by May 19, 2011.
Affected ADs
(b) None.
Applicability
(c) 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.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 57, Wings.
Unsafe Condition
(e) 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.
Compliance
(f) 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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Actions Compliance Procedures
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(1) Inspect the exposed Within the next 10 Follow Burl's
trailing edges of both the hours time-in- Aircraft, LLC
upper and lower main spar service (TIS) after Mandatory Service
cap angles on both the left the effective date Bulletin No. 15AC06-
and right wing for signs of of this AD or 3 08-10, dated June
cracks, intergranular months after the 8, 2010; and FAA
exfoliation, and corrosion. effective date of Advisory Circular
this AD, whichever (AC) 43.13-1B,
occurs first; or if Change 1, Chapter
the left and/or 6. AC 43.13-1B can
right wing have be found at http://
been repaired and rgl.faa.gov/.
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 the
effective date of
this AD, whichever
occurs later. This
compliance time
applies separately
to each wing.
(2) After completing the
inspection required in
paragraph (f)(1) of this
AD:
(i) Install new (i) Install Follow Burl's
inspection hole skin inspection hole Aircraft, LLC
reinforcement doublers skin reinforcement Mandatory Service
and the associated doublers: Within Bulletin No. 15AC06-
screw cover plate in the next 25 hours 08-10, dated June
both the left and right TIS after the 8, 2010; Burl's
wing. effective date of Aircraft, LLC
this AD or within 6 Drawing No. SB
months after the 15AC06-08-10 (not
effective date of dated), and FAA
this AD, whichever Advisory Circular
occurs first; or if (AC) 43.13-1B,
the left and/or Change 1, Chapter
right wing have 6. AC 43.13-1B can
been repaired and be found at http://
both the upper and rgl.faa.gov/.
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 the
effective date of
this AD, whichever
occurs later. This
compliance time
applies separately
to each wing.
(ii) Through the (ii) Inspect: Before
inspection access further flight
panels, inspect the after installing
leading and trailing the inspection hole
edges of both the upper skin reinforcement
and lower main spar cap doublers.
angles on both the left
and right wing for
signs of cracks,
intergranular
exfoliation and
corrosion; and
(iii) Remove any light (iii) Remove
corrosion and treat the corrosion and treat
entirety of both the with corrosion
upper and lower main inhibitor: Before
spar cap angles on both further flight
the left and right wing after the
with corrosion inspection required
inhibitor. in paragraph
(f)(2)(ii) of this
AD.
(3) 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 08-10, dated June
(f)(1) or (f)(2)(ii) of (f)(2)(ii) of this 8, 2010; and
this AD, replace the AD. contact Burl's
affected main spar cap Aircraft, LLC in
angles in their entirety as paragraph (i) of
a single piece. Splicing of this AD for a
the main spar cap angles is replacement scheme
not permitted. and incorporate the
replacement scheme
(4) Removing the wing (i) 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; and FAA
signs of cracks, in paragraph Advisory Circular
intergranular exfoliation, (f)(2)(ii) of this (AC) 43.13-1B,
and corrosion. AD. Change 1, Chapter
6. AC 43.13-1B can
be found at http://rgl.faa.gov/.
(5) After each inspection
required in paragraph
(f)(4) of this AD:
[[Page 18457]]
(i) If only light Before further Follow Burl's
corrosion is found, flight after each Aircraft, LLC
remove the corrosion inspection required Mandatory Service
and treat the main spar in paragraph (f)(4) Bulletin No. 15AC06-
cap angles with of this AD. 08-10, dated June
corrosion inhibitor;. Continue with the 8, 2010; and FAA
repetitive Advisory Circular
inspections (AC) 43.13-1B,
required in Change 1, Chapter
paragraph (f)(4) of 6. AC 43.13-1B can
this AD. be found at http://rgl.faa.gov/.
Contact Burl's
Aircraft, LLC in
paragraph (i) of
this AD for a
replacement scheme
and incorporate the
replacement scheme.
(ii) 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.
(6) Only install main spar As of the effective Not applicable.
cap angles that have been date of this AD.
inspected and are free of
cracks, intergranular
exfoliation, or moderate or
severe corrosion.
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Alternative Methods of Compliance (AMOCs)
(g)(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.
Related Information
(h) For more information about this AD, contact Eric Wright,
Aerospace Engineer, FAA, Anchorage ACO, 222 W. 7th Ave.,
14, Anchorage, Alaska 99513; telephone: (907) 271-2648;
fax: (907) 271-6365; e-mail: [email protected].
(i) 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; e-mail
[email protected]; Internet: http://www.burlac.com. You may
review copies of the referenced 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.
Issued in Kansas City, Missouri, on March 28, 2011.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011-7878 Filed 4-1-11; 8:45 am]
BILLING CODE 4910-13-P