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ADs updated daily at www.Tdata.com
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| PROPOSED AD |
BURL A. ROGERS (TYPE CERTIFICATE PREVIOUSLY HELD BY WILLIAM BRAD MITCHELL AND AERONCA, INC.) MODELS 15AC AND S15AC AIRPLANES:
Docket No. FAA-2011-0318; Directorate Identifier 2010-CE-033-AD.
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TDATA NOTE: The FAA extended the comment period for Docket No. FAA-2011-
0318; Directorate Identifier 2010-CE-033-AD to July 3, 2011.
The entire NPRM is not being republished since no portion of
the NPRM or other regulatory information has been changed.
COMMENTS DUE DATE
(a) We must receive comments by July 3, 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 corr-
osion 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:
(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 ins-
pector, 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:
eric.wright@faa.gov.
(i) For service information identified in this AD, contact Burl's Air-
craft, LLC, P.O. Box 671487, Chugiak, Alaska 99567-1487; telephone:
(907) 688-3715; fax (907) 688-5031; e-mail burl@biginalaska.com;
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.
DATES: We must receive comments on this proposed AD by July 3, 2011.
| PREAMBLE |
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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 July 3, 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 burl@biginalaska.com; 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:
eric.wright@faa.gov.
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.
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 exfoliat-
ion, 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 Not applicable. $850 $216,750
x $85 per hour
= $850.
Installation of
inspection access 30 work-hours $630.......... 3,180 810,900
panels and ins- x $85 per hour
pection. = $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 80 work-hours x
main spar cap.. $85 per hour = $1,200 per wing.. $8,000
$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 devel-
op 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 responsib-
ilities 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 Pro-
cedures (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 Reg-
ulatory 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):