(a) COMMENTS DUE DATE
The FAA must receive comments by November 18, 2019.
(b) AFFECTED ADS
None.
(c) APPLICABILITY
This AD applies to the Viking Air Limited (Type Certificate previously
held by Bombardier, Inc.; Canadair Limited) airplanes, certificated in
any category, identified in paragraphs (c)(1) and (2) of this AD.
(1) Model CL-215-1A10 airplanes serial numbers 1001 through 1125 inclusive
(2) Model CL-215-6B11 (CL-215T Variant) airplanes, serial numbers 1001
through 1125 inclusive.
(d) SUBJECT
Air Transport Association (ATA) of America Code 57, Wings.
(e) REASON
This proposed AD was prompted by reports of cracks on the wing lower
skin under the drag angle at a certain wing station (WS). The FAA is
issuing this AD to address this condition, which if not detected and
corrected, may lead to widespread fatigue damage and wing structure
failure.
(f) COMPLIANCE
Comply with this AD within the compliance times specified, unless
already done.
(g) REPORTING OF EXISTING REPAIRS
(1) Within 10 months after the effective date of this AD: Perform a one-
time inspection to identify existing standard structural repair manual
(SRM) repairs and non-standard repairs on the wing box between WS 355L
and WS 355R in accordance with the Accomplishment Instructions of
Viking Alert Service Bulletin 215-A568, Revision 4, dated January 22,
2019. A review of airplane maintenance records is acceptable in lieu
of this inspection if accomplishment of the repair or modification can
be conclusively determined from that review. For the purposes of this
AD, replacement of damaged wing box primary structural member is
considered a "repair."
(2) If, during the inspection required by paragraph (g)(1) of this AD, a
repair or modification of the wing box between WS 355L and WS 355R is
found: Within 11 months after the effective date of this AD: Submit an
Inspection Reply Form with details of the repair or modification to
Viking Air Limited via email at technical.support@vikingair.com or via
fax at 1-403-295-8888, and request inspection instructions for the
repaired or modified structure in accordance with the procedures
specified in paragraph (o)(2) of this AD.
(h) RECORD KEEPING
Beginning no later than 30 days after the effective date of this AD:
Record all water landings, land landings, and water drops, and use
this data to determine compliance times for the inspections required
by paragraph (i) of this AD. For the purposes of this AD, total
operation cycles equals water drops plus water landings (non-water
scooping/dropping operations) plus land landings. If there are no
records of water landings, determine total operation cycles using only
land landings and water drops.
(i) REPETITIVE ACTIONS
Except as specified in paragraph (m) of this AD, at the earliest of
the times specified in figure 1 to paragraphs (i), (l), and (m) of
this AD: Do the actions specified in paragraphs (i)(1) through (6) of
this AD. Repeat the actions thereafter at intervals not to exceed the
earliest of the times specified in figure 2 to paragraphs (i) and (m)
of this AD.
(1) Perform a visual inspection of the fastener installation for abnormal
conditions (missed, sheared, distorted, deformed or loose fastener
heads/collar/nuts, and corrosion) in accordance with Section II.A.1.
of the Accomplishment Instructions of Viking Alert Service Bulletin
215-A568, Revision 4, dated January 22, 2019.
(2) Perform a visual inspection of the open fastener holes for cracks,
burrs, elongation, double or mis-drilled holes, and corrosion in
accordance with Section II.A.1. of the Accomplishment Instructions of
Viking Alert Service Bulletin 215-A568, Revision 4, dated January 22,
2019.
(3) Perform a visual inspection of the drag angles, wing lower skin, lower
stringers, spar lower caps/webs, and fuselage structures (internally
and externally) where fasteners are removed for surface cracks or
evidence of distortion and surface defects in accordance with Section
II.A.2. of the Accomplishment Instructions of Viking Alert Service
Bulletin 215-A568, Revision 4, dated January 22, 2019.
(4) Perform a bolt hole eddy current (BHEC) inspection of all identified
fastener holes (except reference holes) specified in Figure 1 of
Viking Alert Service Bulletin 215-A568, Revision 4, dated January 22,
2019, for any cracks in accordance with Section II.A.3. of the
Accomplishment Instructions of Viking Alert Service Bulletin 215-A568,
Revision 4, dated January 22, 2019.
(5) Perform an eddy current surface scan for surface defects and cracks of
the drag angle (along the bending radius) and all fastener holes in
which crack(s) indication have been observed in accordance with
Section II.A.4. of the Accomplishment Instructions of Viking Alert
Service Bulletin 215-A568, Revision 4, dated January 22, 2019.
(6) Perform a structural gap check between the drag angles and the wing
lower skin in accordance with Section II.A.5. of the Accomplishment
Instructions of Viking Alert Service Bulletin 215-A568, Revision 4,
dated January 22, 2019.
FIGURE 1 TO PARAGRAPHS (I), (L), AND (M) – INITIAL COMPLIANCE TIMES
______________________________________________________________________
TOTAL OPERATION
TOTAL FLIGHT HOURS TOTAL WATER DROPS CYCLES AS OF
AS OF THE EFFECTIVE AS OF THE EFFECTIVE THE EFFECTIVE
DESCRIPTION DATE OF THIS AD DATE OF THIS AD DATE OF THIS AD
______________________________________________________________________
Initial 7,500 10,000 12,000
Inspection
Threshold
______________________________________________________________________
FIGURE 2 TO PARAGRAPH (I) AND (M) – REPETITIVE COMPLIANCE TIMES
______________________________________________________________________
DESCRIPTION FLIGHT HOURS WATER DROPS TOTAL OPERATION CYCLES
______________________________________________________________________
Repetitive 3,750 5,000 6,000
Inspection
______________________________________________________________________
(j) CORRECTIVE ACTIONS
If any of the findings identified in paragraphs (j)(1) through (6) of
this AD are found, before further flight, repair using a method
approved by the Manager, New York ACO Branch, FAA; or Transport Canada
Civil Aviation (TCCA); or Viking Air Limited's TCCA Design Approval
Organization (DAO). If approved by the DAO, the approval must include
the DAO-authorized signature.
(1) If, during any inspection required by paragraph (i)(1) of this AD, any
abnormal condition is found.
(2) If, during any inspection required by paragraph (i)(2) of this AD, any
cracks, burrs, elongation, double or mis-drilled holes, or corrosion
are found.
(3) If, during any inspection required by paragraph (i)(3) of this AD, any
surface cracks or evidence of distortion or surface defects are found.
(4) If, during any inspection required by paragraph (i)(4) of this AD, any
cracks are found.
(5) If, during any inspection required by paragraph (i)(5) of this AD, any
surface defects or cracks are found.
(6) If, during any structural gap check required by paragraph (i)(6) of
this AD, any gaps are found.
(k) EXCEPTION TO SERVICE INFORMATION
Where Viking Alert Service Bulletin 215-A568, Revision 4, dated
January 22, 2019, specifies that preventative Repair Engineering Order
(REO) 215-57-V022 may be installed and certain inspections may be done
as specified in that REO, this AD does not allow the use of that REO
for compliance with this AD.
(l) REPLACE RIVETS
For airplanes on which the actions specified in Viking Alert Service
Bulletin 215-A568, Revision 3, dated June 15, 2016, or earlier, have
been accomplished: At the earliest of the times specified in figure 1
to paragraphs (i), (l), and (m) of this AD, perform a one-time
replacement of installed NAS1242AD rivets with Titanium Hi-Lite
fasteners and do a BHEC inspection of the open holes for cracks in
accordance with the Accomplishment Instructions of Viking Alert
Service Bulletin 215-A568, Revision 4, dated January 22, 2019. If any
crack is found, before further flight, repair using a method approved
by the Manager, New York ACO Branch, FAA; or TCCA; or Viking Air
Limited's TCCA DAO. If approved by the DAO, the approval must include
the DAO-authorized signature.
(m) INITIAL COMPLIANCE TIME FOR CERTAIN AIRPLANES
(1) For airplanes on which the actions specified in Viking Alert Service
Bulletin 215-A568, Revision 3, dated June 15, 2016, or earlier, have
not been accomplished: At the times specified in figure 3 to paragraph
(m)(1) of this AD, accomplish the actions required by paragraph (i) of
this AD. Repeat the actions thereafter at the times specified in
figure 2 to paragraphs (i) and (m) of this AD. For the purposes of
this AD, the earliest compliance time applies if the accumulated
airplane flight times (flight hours, water drops, or total operation
cycles) meet multiple criteria.
FIGURE 3 TO PARAGRAPH (M)(1)–INITIAL COMPLIANCE TIMES FOR AIRPLANES
ON WHICH THE ACTIONS SPECIFIED IN VIKING
ALERT SERVICE BULLETIN 215-A568, REVISION
3, DATED JUNE 15, 2016, OR EARLIER, HAVE
NOT BEEN ACCOMPLISHED
______________________________________________________________________
TOTAL
FLIGHT
HOURS AS TOTAL WATER
OF THE DROPS AS OF TOTAL OPERATION
EFFECTIVE THE EFFECTIVE CYCLES AS OF THE
DATE OF DATE OF THIS EFFECTIVE DATE OF COMPLIANCE
THIS AD AD THIS AD TIME
______________________________________________________________________
7,500 or Or 22,001 or Or 26,401 or more Within 4 months
more more after the
effective date
of this AD
7,500 or Or 20,001 to Or 24,001 to Within 8 months
more 22,000 26,400 after the
effective date
of this AD
7,500 or Or 10,000 to Or 12,000 to Within 18 months
more 20,000 24,000 after the
effective date
of this AD
Less than And less than And less than At or before the
7,500 10,000 12,000 initial inspec-
tion time in
figure 1 to
paragraphs (i),
(l), and (m) of
this AD, or
within 18
months after the
effective date
of this AD,
whichever occurs
later
______________________________________________________________________
(2) For airplanes on which the actions specified in Viking Alert Service
Bulletin 215-A568, Revision 3, dated June 15, 2016, or earlier, have
been accomplished: At the times specified in figure 4 to paragraph
(m)(2) of this AD, accomplish the actions required by paragraph (i) of
this AD. Repeat the actions thereafter at the times specified in
figure 2 to paragraphs (i) and (m) of this AD. For the purposes of
this AD, the earliest compliance time applies if the accumulated
airplane flight times (flight hours, water drops, or total operation
cycles) meet multiple criteria.
FIGURE 4 TO PARAGRAPH (M)(2)–INITIAL COMPLIANCE TIMES FOR AIRPLANES
ON WHICH THE ACTIONS SPECIFIED IN VIKING
ALERT SERVICE BULLETIN 215-A568, REVISION
3, DATED JUNE 15, 2016, OR EARLIER, HAVE
BEEN ACCOMPLISHED
______________________________________________________________________
TOTAL
FLIGHT
HOURS AS TOTAL WATER
OF THE DROPS AS OF TOTAL OPERATION
EFFECTIVE THE EFFECTIVE CYCLES AS OF THE
DATE OF DATE OF THIS EFFECTIVE DATE OF COMPLIANCE
THIS AD AD THIS AD TIME
______________________________________________________________________
7,500 or Or 20,001 or Or 24,001 or more Within 12 months
more more after the
effective date
of this AD
7,500 or Or 10,000 to Or 12,000 to Within 18 months
more 20,000 24,000 after the
effective date
of this AD
Less than And less than And less than At or before the
7,500 10,000 12,000 initial inspec-
tion time in
figure 1 to
paragraphs (i),
(l), and (m) of
this AD, or
within 18 months
after the
effective date
of this AD,
whichever occurs
later
______________________________________________________________________
(n) REPORTING
At the applicable time specified in paragraph (n)(1) or (2) of this AD
Report the results of the actions required by paragraph (i) of this AD
to Viking Air Limited via email at technicalsupport@vikingair.com or
fax at 1-403-295-8888 in accordance with the instructions of Viking
Alert Service Bulletin 215-A568, Revision 4, dated January 22, 2019.
(1) If the action was done on or after the effective date of this AD:
Submit the report within 30 days after the inspection.
(2) If the action was done before the effective date of this AD: Submit
the report within 30 days after the effective date of this AD.
(o) OTHER FAA AD PROVISIONS
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO
Branch, 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 certification office, send
it to ATTN: Program Manager, Continuing Operational Safety, FAA, New
York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
telephone 516-228-7300; fax 516-794-5531. 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.
(2) Contacting the Manufacturer: For any requirement in this AD to obtain
instructions from a manufacturer, the instructions must be
accomplished using a method approved by the Manager, New York ACO
Branch, FAA; or TCCA; or Viking Air Limited's TCCA DAO. If approved by
the DAO, the approval must include the DAO-authorized signature.
(3) Reporting Requirements: 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 1 hour 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.
(p) RELATED INFORMATION
(1) Refer to Mandatory Continuing Airworthiness Information (MCAI)
Canadian Airworthiness Directive CF-2019-07, dated March 4, 2019, for
related information. This MCAI may be found in the AD docket on the
internet at http://www.regulations.gov by searching for and locating
Docket No. FAA-2019-0710.
(2) For more information about this AD, contact Aziz Ahmed, Aerospace
Engineer, Airframe and Propulsion Section, FAA, New York ACO Branch,
1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-
7329; fax 516-794-5531; email 9-avs-nyaco-cos@faa.gov.
(3) For service information identified in this AD, contact Viking Air
Limited, 1959 de Havilland Way, Sidney, British Columbia V8L 5V5,
Canada; telephone +1-250-656-7227; fax +1-250-656-0673; email acs-
technical.publications@vikingair.com; internet http://www.vikingair.
com. You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St, Des Moines, WA. For information
on the availability of this material at the FAA, call 206-231-3195.
Issued in Des Moines, Washington, on September 24, 2019. Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification Service
DATES: The FAA must receive comments on this proposed AD by November 18,
2019.
|
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0710; Product Identifier 2019-NM-060-AD]
RIN 2120-AA64
Airworthiness Directives; Viking Air Limited (Type Certificate
Previously Held by Bombardier, Inc.; Canadair Limited) Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive
(AD)
for certain Viking Air Limited Model CL-215-1A10 and CL-215-6B11 (CL-
215T Variant) airplanes. This proposed AD was prompted by reports of
cracks on the wing lower skin under the drag angle at a certain wing
station (WS). This proposed AD would require a one-time inspection of
the wing lower skin under the drag angle at a certain WS to determine
if a certain repair or modification has been accomplished; repetitive
visual inspections of certain fuselage structures; repetitive eddy
current inspections of the front spar along a certain WS reference
line, the drag angle, and all fastener holes; repetitive structural gap
checks of a certain surface; and corrective actions if necessary. This
proposed AD would also require replacing certain rivets with certain
fasteners, and corrective actions if necessary. The FAA is proposing
this AD to address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by November
18, 2019.
ADDRESSES: You may send comments, using the procedures found in
14 CFR
11.43 and 11.45, 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 NPRM, contact Viking Air
Limited, 1959 de Havilland Way, Sidney, British Columbia V8L 5V5,
Canada; telephone +1-250-656-7227; fax +1-250-656-0673; email acs-
technical.publications@vikingair.com; internet http://www.vikingair.com.
You may view this service information at the FAA, Transport Standards
Branch, 2200 South 216th St., Des Moines, WA. For information on the
availability of this material at the FAA, call 206-231-3195.
Examining the AD Docket
You may examine the AD docket on the internet at http://www.regulations.
gov by searching for and locating Docket No. FAA-2019-0710;
or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer,
Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7329; fax 516-
794-5531; email 9-avs-nyaco-cos@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites 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-2019-0710;
Product Identifier 2019-NM-060-AD" at the beginning of your comments.
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this NPRM. The FAA will
consider all comments received by the closing date and may amend this
NPRM because of those comments.
The FAA will post all comments, without change, to http://www.regulations.
gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact the agency receives about this NPRM.
Discussion
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2019-07, dated March 4, 2019 (referred to after this as the Mandatory
Continuing Airworthiness Information, or "the MCAI"), to correct an
unsafe condition for certain Viking Air Limited Model CL-215-1A10 and
CL-215-6B11 (CL-215T Variant) airplanes. You may examine the MCAI in
the AD docket on the internet at http://www.regulations.gov by
searching for and locating Docket No. FAA-2019-0710.
This proposed AD was prompted by reports of cracks on the wing
lower skin under the drag angle at a certain wing station (WS). The FAA
is proposing this AD to address this condition, which if not detected
and corrected, may lead to widespread fatigue damage and wing structure
failure. See the MCAI for additional background information.
Related Service Information Under 1 CFR Part 51
Viking has issued Alert Service Bulletin 215-A568, Revision 4,
dated January 22, 2019. This service information describes procedures
for a one-time inspection of the wing lower skin under the drag angle
at a certain WS to determine if a certain repair or modification has been
accomplished; repetitive visual inspections of fastener installation
for abnormal conditions (missed, sheared, distorted, deformed or loose
fastener heads/collar/nuts, and corrosion) and corrective actions as
necessary; repetitive visual inspections of the open fastener holes for
cracks, burrs, elongation, double or mis-drilled holes, or corrosion,
and corrective actions as necessary; repetitive visual inspections of
drag angles, wing lower skin, lower stringers, spar lower caps/webs,
and fuselage structures (internally and externally) where fasteners are
removed for surface cracks or evidence of distortion and surface
defects (scratches, gouges, nicks, scores, dents, surface pitting/
corrosion, or other surface damage), and corrective actions as
necessary; repetitive bolt hole eddy current (BHEC) inspections of all
identified fastener holes (except reference holes) for cracks, and
corrective actions as necessary; repetitive eddy current surface scans
for surface defects and cracks of the drag angle (along the bending
radius) and all fastener holes in which crack(s) indication is
observed, and corrective actions as necessary; repetitive structural
gap checks of the mating surface between the wing lower skin and the
drag angles and corrective actions as necessary; and procedures for
replacing certain rivets with certain fasteners, and corrective actions
as necessary. Corrective actions include, among other things, repair,
replacement, and oversizing any affected holes.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
FAA's Determination
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to the FAA's bilateral agreement with the State of Design Authority,
the FAA has been notified of the unsafe condition described in the MCAI
and service information referenced above. The FAA is proposing this AD
because the FAA evaluated all the relevant information and determined
the unsafe condition described previously is likely to exist or develop
on other products of the same type design.
Proposed Requirements of This NPRM
This proposed AD would require accomplishing the actions specified
in the service information described previously. This proposed AD also
would require sending the inspection results to Viking.
Differences Between This Proposed AD and the MCAI or Service
Information
Although Viking Alert Service Bulletin 215-A568, Revision 4, dated
January 22, 2019, allows, for certain airplanes, the installation of
preventative Repair Engineering Order (REO) 215-57-V022, and the
accomplishment of certain inspections as specified in that REO, this
proposed AD would not allow those actions to be done using REO 215-57-
V022. The FAA has determined that REO 215-57-V022 provides only generic
instructions, not instructions tailored to the type of damage that
might be found during the inspections required by this proposed AD.
Costs of Compliance
The FAA estimates that this proposed AD affects 4 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this
proposed AD:
Estimated Costs for Required Actions *
|
Labor cost
|
Parts cost
|
Cost per
product
|
Cost on
U.S. operators
|
| Up to 48 work-hours x $85 per
hour = Up to $4,080 |
$0
|
Up to $4,080
|
Up to $16,320
|
* Table does not include estimated
costs for reporting.
The FAA estimates that it would take about 1 work-hour per product
to comply with the proposed reporting requirement in this proposed AD.
The average labor rate is $85 per hour. Based on these figures, the FAA
estimates the cost of reporting the inspection results on U.S.
operators to be $340, or $85 per product.
The FAA has received no definitive data that would enable the
agency to provide cost estimates for the on-condition actions specified
in this proposed AD.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to 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 control
number for the collection of information required by this NPRM is 2120-
0056. The paperwork cost associated with this NPRM has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this NPRM is 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.
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.
The FAA is 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.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes and associated appliances to the
Director of the System Oversight Division.
Regulatory Findings
The FAA 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) Will not affect intrastate aviation in Alaska, and
(3) 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):
|