(a) EFFECTIVE DATE
This AD is effective February 10, 2020.
(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 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
______________________________________________________________________
DESCRIPTION TOTAL FLIGHT HOURS TOTAL WATER DROPS TOTAL OPERATION
AS OF THE EFFECTIVE AS OF THE EFFECTIVE CYCLES AS OF THE
DATE OF THIS AD DATE OF THIS AD EFFECTIVE DATE
OF THIS AD
______________________________________________________________________
Initial
Inspection
Threshold 7,500 10,000 12,000
______________________________________________________________________
FIGURE 2 TO PARAGRAPHS (I) AND (M) – REPETITIVE COMPLIANCE TIMES
______________________________________________________________________
DESCRIPTION FLIGHT HOURS WATER DROPS TOTAL OPERATION
CYCLES
______________________________________________________________________
Repetitive Inspection 3,750 5,000 6,000
______________________________________________________________________
(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 ACCOMP-
LISHED
______________________________________________________________________
TOTAL TOTAL WATER TOTAL OPERATION COMPLIANCE TIME
FLIGHT DROPS AS OF CYCLES AS OF THE
HOURS AS THE EFFECTIVE EFFECTIVE DATE
OF THE DATE OF THIS AD OF THIS AD
EFFECTIVE
DATE OF
THIS AD
______________________________________________________________________
7,500 or more Or 22,001 or Or 26,401 or Within 4 months
more more after the effective
date of this AD
7,500 or more Or 20,001 to Or 24,001 to Within 8 months
22,000 26,400 after the effective
date of this AD
7,500 or more Or 10,000 to Or 12,000 to Within 18 months
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 inspection
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 TOTAL WATER TOTAL OPERATION COMPLIANCE TIME
FLIGHT DROPS AS OF CYCLES AS OF THE
HOURS AS THE EFFECTIVE EFFECTIVE DATE OF
OF THE DATE OF THIS THIS AD
EFFECTIVE AD
DATE OF
THIS AD
______________________________________________________________________
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 24,000 Within 18 months
more 20,000 after the effective
date of this AD
Less than And less than And less than 12,000 At or before the
7,500 10,000 initial inspection
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 as required by this AD. Send comments regarding this burden
estimate or any other aspect of this collection of information,
including suggestions for reducing this burden to Information
Collection Clearance Officer, Federal Aviation Administration, 10101
Hillwood Parkway, Fort Worth, TX 76177-1524.
(p) RELATED INFORMATION
(1) Refer to Mandatory Continuing Airworthiness Information (MCAI)
Canadian AD CF-2019-07, dated March 4, 2019, for related information.
This MCAI may be found in the AD docket on the internet at
https://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.
(q) MATERIAL INCORPORATED BY REFERENCE
(1) The Director of the Federal Register approved the incorporation by
reference (IBR) of the service information listed in this paragraph
under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do the actions
required by this AD, unless this AD specifies otherwise.
(i) Viking Alert Service Bulletin 215-A568, Revision 4, dated January 22,
2019.
(ii) [Reserved]
(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 https://www.vikingair.
com.
(4) 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.
(5) You may view this service information that is incorporated by refer-
ence at the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, email
fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal
-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on December 12, 2019. Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
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.
|
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0710; Product Identifier 2019-NM-060-AD; Amendment
39-21009; AD 2019-25-11]
RIN 2120-AA64
Airworthiness Directives; Viking Air Limited (Type Certificate
Previously Held by Bombardier, Inc.; Canadair Limited) Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Viking Air Limited Model CL-215-1A10 and CL-215-6B11 (CL-215T
Variant) airplanes. This AD was prompted by reports of cracks on the
wing lower skin under the drag angle at a certain wing station (WS).
This AD requires 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 AD also requires replacing
certain rivets with certain fasteners, and corrective actions if
necessary. The FAA is issuing this AD to address the unsafe condition
on these products.
DATES: This AD is effective February 10, 2020.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of February 10, 2020.
ADDRESSES: For service information identified in this final rule,
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 https://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. It is also available on the internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2019-0710.
Examining the AD Docket
You may examine the AD docket on the internet at https://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 final rule, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations is U.S. Department
of Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: 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:
Discussion
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD 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 https://www.regulations.gov by searching for and locating
Docket No. FAA-2019-0710.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain Viking Air
Limited Model CL-215-1A10 and CL-215-6B11 (CL-215T Variant) airplanes.
The NPRM published in the Federal Register on October 4, 2019 (84 FR
53076). The NPRM was prompted by reports of cracks on the wing lower
skin under the drag angle at a certain WS. The NPRM proposed to 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. The NPRM also proposed to require replacing
certain rivets with certain fasteners, and corrective actions if
necessary. 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. See the MCAI for additional background
information.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The FAA received no comments on the NPRM or
on the determination of the cost to the public.
Conclusion
The FAA reviewed the relevant data and determined that air safety
and the public interest require adopting this final rule as proposed,
except for minor editorial changes. The FAA has determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
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.
Costs of Compliance
The FAA estimates that this AD affects 4 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this 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 reporting requirement in this 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 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 AD is 2120-
0056. The paperwork cost associated with this AD 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 AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to
Information Collection Clearance Officer, Federal Aviation
Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177-1524.
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 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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a "significant regulatory action" under Executive Order 12866,
(2) 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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
|