Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 340A (SAAB/SF340A) and SAAB 340B Airplanes Modified in Accordance With Supplemental Type Certificate (STC) ST00224WI-D, ST00146WI-D, or SA984GL-D, 3564-3566 [2011-1118]
Download as PDF
<![CDATA[
3564
Federal Register / Vol. 76, No. 13 / Thursday, January 20, 2011 / Proposed Rules
engines; as identified in Boeing Alert Service
Bulletin 777–78A0065, Revision 2, dated
May 6, 2010.
Subject
(d) Air Transport Association (ATA) of
America Code 78: Engine exhaust.
Unsafe Condition
(e) This AD results from reports of thrust
reverser events related to thermal damage of
the thrust reverser (T/R) inner wall. The
Federal Aviation Administration is issuing
this AD to detect and correct a degraded T/
R inner wall panel, which could lead to
failure of a T/R and adjacent components and
their consequent separation from the
airplane, which could result in a rejected
takeoff (RTO) and cause asymmetric thrust
and consequent loss of control of the airplane
during reverse thrust operation. If a T/R inner
wall overheats, separated components could
cause structural damage to the airplane,
damage to other airplanes, or possible injury
to people on the ground.
emcdonald on DSK2BSOYB1PROD with PROPOSALS
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Records Review, Inspections, and Related
Investigative and Corrective Actions
(g) Except as required by paragraphs (h),
(i), (j), and (k) of this AD, at the applicable
times in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 777–78A0065,
Revision 2, dated May 6, 2010 (‘‘this service
bulletin’’), review the airplane maintenance
records to determine whether sealant was
added, do the actions specified in paragraphs
(g)(1), (g)(2), (g)(3), (g)(4), and (g)(5) of this
AD, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of this service bulletin, except as
required by paragraph (l) of this AD. Do all
applicable related investigative and
corrective actions before further flight.
Repeat the inspections required by
paragraphs (g)(1), (g)(2), (g)(3), (g)(4), and
(g)(5) of this AD thereafter at the applicable
intervals specified in paragraph 1.E.,
‘‘Compliance,’’ of the service bulletin.
(1) Do a detailed inspection of all T/R inner
wall insulation blanket edges, grommet
holes, penetrations, and seams for sealant
that is cracked, has gaps, is loose, or is
missing; do a general visual inspection of
click bond studs, blanket studs, and
temporary fasteners; and replace sealant as
applicable; in accordance with Work Package
1 of the Accomplishment Instructions of this
service bulletin.
(2) Do the actions required by paragraph
(g)(2)(i) or (g)(2)(ii) of this AD.
(i) Do a full inner wall panel nondestructive test (NDT) for delamination and
disbonding of each T/R half, and do a general
visual inspection for areas of thermal
degradation, in accordance with Work
Package 2 of the Accomplishment
Instructions of this service bulletin.
(ii) Do a limited area NDT of the inner wall
panel of each T/R half for delamination and
disbonding, and do a general visual
VerDate Mar<15>2010
18:20 Jan 19, 2011
Jkt 223001
inspection for areas of thermal degradation,
in accordance with Work Package 6 of the
Accomplishment Instructions of this service
bulletin.
(3) Do a general visual inspection of the T/
R perforated wall aft of the intermediate
pressure compressor 8th stage (IP8) and the
high pressure compressor 3rd stage (HP3)
bleed port exits for a color that is different
from that of the general area, in accordance
with Work Package 5 of the Accomplishment
Instructions of this service bulletin.
(4) Do a detailed inspection of the powered
door opening system (PDOS) lug bushings on
the upper number 1 compression pad fittings
for hole elongation, deformation, and contact
with the PDOS actuator, in accordance with
Work Package 3 of the Accomplishment
Instructions of this service bulletin.
(5) Do an NDT of the number 1 upper and
numbers 1 and 2 lower compression pad
fittings, in accordance with Work Package 4
of the Accomplishment Instructions of this
service bulletin.
Service Bulletin 777–78A0065, dated June
23, 2008; or Revision 1, dated January 29,
2009; are acceptable for compliance with the
corresponding requirements of this AD.
Exceptions to the Service Bulletin
(h) Where Boeing Alert Service Bulletin
777–78A0065, Revision 2, dated May 6, 2010,
specifies a compliance time after the date on
the original issue of that service bulletin, this
AD requires compliance within the specified
compliance time after the effective date of
this AD.
(i) Where paragraph 1.E., ‘‘Compliance,’’ in
Boeing Alert Service Bulletin 777–78A0065,
Revision 2, dated May 6, 2010, specifies a
compliance time of ‘‘2,000 flight cycles after
the date of the operator’s own inspections,’’
for doing Work Packages 2 and 5, or Work
Packages 2 and 6, this AD requires
compliance within 2,000 flight cycles after
the date of the operator’s own inspections or
within 12 months after the effective date of
this AD, whichever occurs later.
(j) Where the Condition columns in Table
2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 777–78A0065,
Revision 2, dated May 6, 2010, refer to ‘‘All
airplanes, each T/R half’’ that has or has not
‘‘been inspected before the date on this
service bulletin,’’ this AD applies to all
airplanes, each T/R half that has or has not
been inspected before the effective date of
this AD.
(k) Where the Condition columns in the
Tables of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 777–78A0065,
Revision 2, dated May 6, 2010, refer to total
flight cycles, this AD applies to the airplanes
with the specified total flight cycles as of the
effective date of this AD.
(l) Where Boeing Alert Service Bulletin
777–78A0065, Revision 2, dated May 6, 2010,
specifies to contact Boeing for appropriate
action: Before further flight, repair in
accordance with a method approved by the
Manager, Seattle Aircraft Certification Office
(ACO), FAA. For a repair method to be
approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
Issued in Renton, Washington, on January
12, 2011.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(m) Actions done before the effective date
of this AD in accordance with Boeing Alert
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Fmt 4702
Sfmt 4702
Alternative Methods of Compliance
(AMOCs)
(n)(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. Send information to Attn:
Margaret Langsted, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 917–6500; fax (425)
917–6590. Or, e-mail information to 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(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.
[FR Doc. 2011–1121 Filed 1–19–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0042; Directorate
Identifier 2009–NM–010–AD]
RIN 2120–AA64
Airworthiness Directives; Saab AB,
Saab Aerosystems Model SAAB 340A
(SAAB/SF340A) and SAAB 340B
Airplanes Modified in Accordance With
Supplemental Type Certificate (STC)
ST00224WI–D, ST00146WI–D, or
SA984GL–D
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
AGENCY:
We are revising an earlier
proposed airworthiness directive (AD)
for certain Saab AB, Saab Aerosystems
Model SAAB 340A (SAAB/SF340A) and
SAAB 340B airplanes. The first
supplemental NPRM would have
required inspecting the fuselage surface
for corrosion and cracking behind the
external adapter plate of the antennae
installation, and repair if necessary. The
first supplemental NPRM resulted from
a report of a crack found behind the
external adapter plate of the antennae
during inspection. Similar cracking was
found on two additional airplanes, and
SUMMARY:
E:\FR\FM\20JAP1.SGM
20JAP1
Federal Register / Vol. 76, No. 13 / Thursday, January 20, 2011 / Proposed Rules
emcdonald on DSK2BSOYB1PROD with PROPOSALS
extensive corrosion was found on one
airplane. This action revises the first
supplemental NPRM by correcting an
STC number, which would expand the
applicability of the first supplemental
NPRM. We are proposing this second
supplemental NPRM to detect and
correct corrosion and cracking behind
the external adapter plate of the
antennae of certain damage-tolerant
structure, which could result in reduced
structural integrity and consequent
rapid depressurization of the airplane.
DATES: We must receive comments on
this supplemental NPRM by March 7,
2011.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
William Griffith, Aerospace Engineer,
Airframe Branch, ACE–118W, FAA,
Wichita Aircraft Certification Office,
1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas
67209; telephone (316) 946–4116; fax
(316) 946–4107.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2010–0042; Directorate Identifier
2009–NM–010–AD’’ at the beginning of
VerDate Mar<15>2010
18:20 Jan 19, 2011
Jkt 223001
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 https://
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
We issued a supplemental notice of
proposed rulemaking (NPRM) (the ‘‘first
supplemental NPRM’’) to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that would apply to
certain Saab AB, Saab Aerosystems
Model SAAB 340A (SAAB/SF340A) and
SAAB 340B airplanes. That first
supplemental NPRM was published in
the Federal Register on August 23, 2010
(75 FR 51696). That first supplemental
NPRM proposed to require inspecting
the fuselage surface for corrosion and
cracking behind the external adapter
plate of the antennae installation, and
repair if necessary.
Actions Since First Supplemental
NPRM Was Issued
Since we issued the first
supplemental NPRM, we have
determined that STC number
SA00224WI–D, identified in the
applicability of the first supplemental
NPRM, is an incorrect STC number; the
correct number is ST00224WI–D. We
have corrected this error, which
expands the airplanes affected by the
first supplemental NPRM.
Comments
We gave the public the opportunity to
comment on the first supplemental
NPRM. We received no comments on
that NPRM or on the determination of
the cost to the public.
FAA’s Determination and Proposed
Requirements of the Supplemental
NPRM
We are proposing this second
supplemental NPRM because we
evaluated all pertinent information and
determined an unsafe condition exists
and is likely to exist or develop on other
products of these same type designs.
The change described above expands
the scope of the first supplemental
NPRM. As a result, we have determined
that it is necessary to reopen the
comment period to provide additional
PO 00000
Frm 00026
Fmt 4702
Sfmt 4702
3565
opportunity for the public to comment
on this second supplemental NPRM.
Proposed Requirements of the
Supplemental NPRM
This second supplemental NPRM
would retain all the requirements in the
first supplemental NPRM.
Costs of Compliance
We estimate that this proposed AD
would affect 201 airplanes of U.S.
registry. The proposed inspection would
take about 4 work hours per airplane, at
an average labor rate of $85 per work
hour. Based on these figures, the
estimated cost of the proposed AD for
U.S. operators is $68,340, or $340 per
airplane.
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), and
(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
E:\FR\FM\20JAP1.SGM
20JAP1
3566
Federal Register / Vol. 76, No. 13 / Thursday, January 20, 2011 / Proposed Rules
under the criteria of the Regulatory
Flexibility Act.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Saab AB, Saab Aerosystems: Docket No.
FAA–2010–0042; Directorate Identifier
2009–NM–010–AD.
Comments Due Date
(a) We must receive comments by March 7,
2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the Saab AB, Saab
Aerosystems airplanes, certificated in any
category, identified in paragraphs (c)(1) and
(c)(2) of this AD, that have been modified in
accordance with Supplemental Type
Certificate (STC) ST00224WI–D,
ST00146WI–D, or SA984GL–D.
(1) Model SAAB 340A (SAAB/SF340A)
airplanes, serial numbers 004 through 159
inclusive.
(2) Model SAAB 340B airplanes, serial
numbers 160 through 459 inclusive.
emcdonald on DSK2BSOYB1PROD with PROPOSALS
Subject
(d) Joint Aircraft System Component
(JASC)/Air Transport Association (ATA) of
America Code 53: Fuselage.
Unsafe Condition
(e) This AD results from a report of a crack
found behind the external adapter plate of
the antennae during inspection. Similar
cracking was found on two additional
airplanes, and extensive corrosion was found
on one airplane. The Federal Aviation
Administration is issuing this AD to detect
and correct corrosion and cracking behind
the external adapter plate of the antennae of
certain damage-tolerant structure, which
could result in reduced structural integrity
and consequent rapid depressurization of the
airplane.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified.
VerDate Mar<15>2010
18:20 Jan 19, 2011
Jkt 223001
Inspection/Corrective Actions
(g) Within 600 flight cycles after the
effective date of this AD: Remove the external
adapter plate of the antennae installation and
do a general visual inspection of the fuselage
surface for corrosion and cracking behind the
external adapter plate of the antennae
installation. If any corrosion or cracking is
found, repair before further flight. If no
corrosion or cracking is found, before further
flight, ensure that proper corrosion
protection has been applied before
reinstalling the adapter plate. Do all the
actions required by this paragraph in
accordance with a method approved by the
Manager, Wichita Aircraft Certification Office
(ACO), FAA.
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to ensure visual access to
all surfaces in the inspection area. This level
of inspection is made under normally
available lighting conditions such as
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
Reporting Requirement
(h) At the applicable time specified in
paragraph (h)(1) or (h)(2) of this AD: Submit
a report of the positive findings of the
inspections required by paragraph (g) of this
AD. Send the report to the Manager, Wichita
ACO. The report must contain, at a
minimum, the inspection results, a
description of any discrepancies found, the
airplane serial number, and the number of
flight cycles and flight hours on the airplane
since installation of the STC. Under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements contained in this AD and has
assigned OMB Control Number 2120–0056.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
(3) A Federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 5 minutes per
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
PO 00000
Frm 00027
Fmt 4702
Sfmt 4702
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave., SW, Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
Special Flight Permit
(i) Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), may be issued to operate the
airplane to a location where the requirements
of this AD can be accomplished, but
concurrence by the Manager, Wichita ACO,
FAA, is required prior to issuance of the
special flight permit.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, Wichita ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. Send information to ATTN:
William Griffith, Aerospace Engineer,
Airframe Branch, ACE–118W, FAA, Wichita
ACO, 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas 67209;
telephone (316) 946–4116; fax (316) 946–
4107.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. 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.
Issued in Renton, Washington on January
12, 2011.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2011–1118 Filed 1–19–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0026; Directorate
Identifier 2010–NM–104–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 777–200 and –300
Series Airplanes Equipped With Pratt
and Whitney Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Model 777–200 and –300 series
airplanes. This proposed AD would
require repetitive inspections for
SUMMARY:
E:\FR\FM\20JAP1.SGM
20JAP1
]]>Agencies
[Federal Register Volume 76, Number 13 (Thursday, January 20, 2011)]
[Proposed Rules]
[Pages 3564-3566]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-1118]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0042; Directorate Identifier 2009-NM-010-AD]
RIN 2120-AA64
Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB
340A (SAAB/SF340A) and SAAB 340B Airplanes Modified in Accordance With
Supplemental Type Certificate (STC) ST00224WI-D, ST00146WI-D, or
SA984GL-D
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
-----------------------------------------------------------------------
SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) for certain Saab AB, Saab Aerosystems Model SAAB 340A (SAAB/
SF340A) and SAAB 340B airplanes. The first supplemental NPRM would have
required inspecting the fuselage surface for corrosion and cracking
behind the external adapter plate of the antennae installation, and
repair if necessary. The first supplemental NPRM resulted from a report
of a crack found behind the external adapter plate of the antennae
during inspection. Similar cracking was found on two additional
airplanes, and
[[Page 3565]]
extensive corrosion was found on one airplane. This action revises the
first supplemental NPRM by correcting an STC number, which would expand
the applicability of the first supplemental NPRM. We are proposing this
second supplemental NPRM to detect and correct corrosion and cracking
behind the external adapter plate of the antennae of certain damage-
tolerant structure, which could result in reduced structural integrity
and consequent rapid depressurization of the airplane.
DATES: We must receive comments on this supplemental NPRM by March 7,
2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: William Griffith, Aerospace Engineer,
Airframe Branch, ACE-118W, FAA, Wichita Aircraft Certification Office,
1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas
67209; telephone (316) 946-4116; fax (316) 946-4107.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-0042;
Directorate Identifier 2009-NM-010-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 https://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
We issued a supplemental notice of proposed rulemaking (NPRM) (the
``first supplemental NPRM'') to amend 14 CFR part 39 to include an
airworthiness directive (AD) that would apply to certain Saab AB, Saab
Aerosystems Model SAAB 340A (SAAB/SF340A) and SAAB 340B airplanes. That
first supplemental NPRM was published in the Federal Register on August
23, 2010 (75 FR 51696). That first supplemental NPRM proposed to
require inspecting the fuselage surface for corrosion and cracking
behind the external adapter plate of the antennae installation, and
repair if necessary.
Actions Since First Supplemental NPRM Was Issued
Since we issued the first supplemental NPRM, we have determined
that STC number SA00224WI-D, identified in the applicability of the
first supplemental NPRM, is an incorrect STC number; the correct number
is ST00224WI-D. We have corrected this error, which expands the
airplanes affected by the first supplemental NPRM.
Comments
We gave the public the opportunity to comment on the first
supplemental NPRM. We received no comments on that NPRM or on the
determination of the cost to the public.
FAA's Determination and Proposed Requirements of the Supplemental NPRM
We are proposing this second supplemental NPRM because we evaluated
all pertinent information and determined an unsafe condition exists and
is likely to exist or develop on other products of these same type
designs. The change described above expands the scope of the first
supplemental NPRM. As a result, we have determined that it is necessary
to reopen the comment period to provide additional opportunity for the
public to comment on this second supplemental NPRM.
Proposed Requirements of the Supplemental NPRM
This second supplemental NPRM would retain all the requirements in
the first supplemental NPRM.
Costs of Compliance
We estimate that this proposed AD would affect 201 airplanes of
U.S. registry. The proposed inspection would take about 4 work hours
per airplane, at an average labor rate of $85 per work hour. Based on
these figures, the estimated cost of the proposed AD for U.S. operators
is $68,340, or $340 per airplane.
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), and
(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
[[Page 3566]]
under the criteria of the Regulatory Flexibility Act.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, 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 AD:
Saab AB, Saab Aerosystems: Docket No. FAA-2010-0042; Directorate
Identifier 2009-NM-010-AD.
Comments Due Date
(a) We must receive comments by March 7, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the Saab AB, Saab Aerosystems airplanes,
certificated in any category, identified in paragraphs (c)(1) and
(c)(2) of this AD, that have been modified in accordance with
Supplemental Type Certificate (STC) ST00224WI-D, ST00146WI-D, or
SA984GL-D.
(1) Model SAAB 340A (SAAB/SF340A) airplanes, serial numbers 004
through 159 inclusive.
(2) Model SAAB 340B airplanes, serial numbers 160 through 459
inclusive.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 53: Fuselage.
Unsafe Condition
(e) This AD results from a report of a crack found behind the
external adapter plate of the antennae during inspection. Similar
cracking was found on two additional airplanes, and extensive
corrosion was found on one airplane. The Federal Aviation
Administration is issuing this AD to detect and correct corrosion
and cracking behind the external adapter plate of the antennae of
certain damage-tolerant structure, which could result in reduced
structural integrity and consequent rapid depressurization of the
airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified.
Inspection/Corrective Actions
(g) Within 600 flight cycles after the effective date of this
AD: Remove the external adapter plate of the antennae installation
and do a general visual inspection of the fuselage surface for
corrosion and cracking behind the external adapter plate of the
antennae installation. If any corrosion or cracking is found, repair
before further flight. If no corrosion or cracking is found, before
further flight, ensure that proper corrosion protection has been
applied before reinstalling the adapter plate. Do all the actions
required by this paragraph in accordance with a method approved by
the Manager, Wichita Aircraft Certification Office (ACO), FAA.
Note 1: For the purposes of this AD, a general visual
inspection is: ``A visual examination of an interior or exterior
area, installation, or assembly to detect obvious damage, failure,
or irregularity. This level of inspection is made from within
touching distance unless otherwise specified. A mirror may be
necessary to ensure visual access to all surfaces in the inspection
area. This level of inspection is made under normally available
lighting conditions such as daylight, hangar lighting, flashlight,
or droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''
Reporting Requirement
(h) At the applicable time specified in paragraph (h)(1) or
(h)(2) of this AD: Submit a report of the positive findings of the
inspections required by paragraph (g) of this AD. Send the report to
the Manager, Wichita ACO. The report must contain, at a minimum, the
inspection results, a description of any discrepancies found, the
airplane serial number, and the number of flight cycles and flight
hours on the airplane since installation of the STC. Under the
provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.),
the Office of Management and Budget (OMB) has approved the
information collection requirements contained in this AD and has
assigned OMB Control Number 2120-0056.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
(3) A Federal agency may not conduct or sponsor, and a person is
not required to respond to, nor shall a person be subject to a
penalty for failure to comply with a collection of information
subject to the requirements of the Paperwork Reduction Act unless
that collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave., SW, Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
Special Flight Permit
(i) Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), may be issued to operate the airplane to a location
where the requirements of this AD can be accomplished, but
concurrence by the Manager, Wichita ACO, FAA, is required prior to
issuance of the special flight permit.
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, Wichita ACO, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. Send information to ATTN: William Griffith,
Aerospace Engineer, Airframe Branch, ACE-118W, FAA, Wichita ACO,
1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas
67209; telephone (316) 946-4116; fax (316) 946-4107.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
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.
Issued in Renton, Washington on January 12, 2011.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-1118 Filed 1-19-11; 8:45 am]
BILLING CODE 4910-13-P
