(a) EFFECTIVE DATE
This AD is effective November 28, 2018.
(b) AFFECTED ADS
This AD replaces AD 2016-24-03, Amendment 39-18720 (81 FR 88623,
December 8, 2016) ("AD 2016-24-03").
(c) APPLICABILITY
This AD applies to Bombardier, Inc., Model DHC-8-400, -401 and -402
airplanes, certificated in any category, serial numbers 4001 and sub-
sequent.
(d) SUBJECT
Air Transport Association (ATA) of America Code 55, Stabilizers.
(e) REASON
This AD was prompted by reports of cracked and corroded barrel nuts
found at the mid-spar location of the horizontal-stabilizer-to
-vertical-stabilizer attachment joint, and the issuance of new service
information that includes a terminal modification. We are issuing this
AD to address cracked and corroded barrel nuts, which could compromise
the structural integrity of the vertical-stabilizer attachment joints
and lead to loss of control of the airplane.
(f) COMPLIANCE
Comply with this AD within the compliance times specified, unless
already done.
(g) RETAINED DETAILED INSPECTION OF BARREL NUTS FOR CRACKS AND CORROSION,
WITH NO CHANGES
This paragraph restates the requirements of paragraphs (g)(1) and (g)
(2) of AD 2016-24-03, with no changes.
(1) For airplanes that have accumulated 5,400 flight hours or more or have
been in service 32 months or more since the date of issuance of the
original certificate of airworthiness or the date of issuance of the
original export certificate of airworthiness, as of January 12, 2017
(the effective date of AD 2016-24-03): Within 600 flight hours or 4
months, whichever occurs first after January 12, 2017, do a detailed
visual inspection for signs of cracks and corrosion of the barrel nut
and cradle, in accordance with paragraph 3.B., "Procedure," of the
Accomplishment Instructions of Bombardier Alert Service Bulletin A84
-55-04, Revision C, dated May 3, 2016.
(2) For airplanes that have less than 5,400 flight hours and have been in-
service for less than 32 months since the date of issuance of the
original certificate of airworthiness or the date of issuance of the
original export certificate of airworthiness, as of January 12, 2017:
Before the accumulation of 6,000 total flight hours or 36 months since
the date of issuance of the original certificate of airworthiness or
the date of issuance of the original export certificate of
airworthiness, whichever occurs first, do a detailed visual inspection
of the barrel nut for signs of cracks and corrosion of the barrel nut
and cradle, in accordance with paragraph 3.B., "Procedure," of the
Accomplishment Instructions of Bombardier Alert Service Bulletin A84
-55-04, Revision C, dated May 3, 2016.
(h) RETAINED CORRECTIVE ACTIONS, DETAILED INSPECTION, AND REPETITIVE IN-
SPECTIONS, WITH NEW SERVICE INFORMATION, REFERENCE TO TERMINATING
ACTION, AND REFERENCE TO CORRECTIVE ACTIONS
This paragraph restates the requirements of paragraph (h) of AD 2016-
24-03, with new service information and terminating action. Depending
on the findings of any inspection required by paragraphs (g) and (j)
of this AD, do the applicable actions in paragraphs (h)(1), (h)(2),
(h)(3), and (h)(4) of this AD. Accomplishment of the actions required
by paragraphs (l) and (m) of this AD, as applicable, terminates the
requirements of this paragraph.
(1) If any barrel nut or cradle is found cracked or broken, before further
flight, replace the barrel nut and associated hardware, in accordance
with paragraph 3.B., "Procedure," of the Accomplishment Instructions
of Bombardier Service Bulletin 84-55-08, Revision A, dated August 2,
2017.
(i) Concurrently with the replacement of any barrel nut, do a detailed in-
spection for corrosion and damage of the bore of the fitting, in
accordance with paragraph 3.B., "Procedure," of the Accomplishment
Instructions of Bombardier Service Bulletin 84-55-08, Revision A,
dated August 2, 2017, and, before further flight, repair all corrosion
and damage, in accordance with Bombardier Repair Drawing (RD) 8/4-55
-1143, Issue 1, dated May 21, 2015; or Bombardier RD 8/4-55-1143,
Issue 2, dated May 25, 2015. If the bore of the fitting cannot be
repaired in accordance with Bombardier RD 8/4-55-1143, Issue 1, dated
May 21, 2015; or Bombardier RD 8/4-55-1143, Issue 2, dated May 25,
2015; accomplish corrective actions in accordance with the procedures
specified in paragraph (q)(2) of this AD. As of the effective date of
this AD, use Bombardier RD 8/4-55-1143, Issue 2, dated May 25, 2015,
for the repair required by this paragraph.
(ii) Within 600 flight hours or 4 months, whichever occurs first, after
the replacement of a cracked barrel nut, replace the remaining barrel
nuts and their associated hardware at the horizontal-stabilizer-to
-vertical-stabilizer attachment joints, in accordance with paragraph
3.B., "Procedure," of the Accomplishment Instructions of Bombardier
Service Bulletin 84-55-08, Revision A, dated August 2, 2017.
(2) If any corrosion is found on any barrel nut on the front or rear-spar
joints, before further flight, replace the barrel nut in accordance
with paragraph 3.B., "Procedure," of the Accomplishment Instructions
of Bombardier Service Bulletin 84-55-08, Revision A, dated August 2,
2017, or accomplish corrective actions in accordance with the
procedures specified in paragraph (q)(2) of this AD.
(3) If any corrosion above level 1, as defined in Bombardier Alert Service
Bulletin A84-55-04, Revision C, dated May 3, 2016, is found on a
barrel nut at the mid-spar joint, before further flight, replace the
barrel nut and accomplish corrective actions in accordance with the
procedures specified in paragraph (q)(2) of this AD.
(4) If all corrosion found is at level 1 or below as defined in Bombardier
Alert Service Bulletin A84-55-04, Revision C, dated May 3, 2016, on a
barrel nut at the mid-spar joint, repeat the inspection specified in
paragraph (g) of this AD at intervals not to exceed 600 flight hours
or 4 months, whichever occurs first, until completion of the actions
required by paragraph (k) of this AD.
(i) RETAINED PRELOAD INDICATING (PLI) WASHER CHECK, WITH NEW TERMINATING
ACTION
This paragraph restates the requirements of paragraph (i) of AD 2016-
24-03, with new terminating action. For airplanes with PLI washers
installed at the front and rear-spar joints, before further flight
after accomplishing any inspection required by paragraph (g) of this
AD and all applicable corrective actions required by paragraph (h) of
this AD, check the bolt preload, and do all applicable corrective
actions, in accordance with paragraph 3.B., "Procedure," of the
Accomplishment Instructions of Bombardier Alert Service Bulletin A84
-55-04, Revision C, dated May 3, 2016. Do all applicable corrective
actions before further flight. Accomplishment of the actions required
by paragraphs (l) and (m) of this AD, as applicable, terminates the
requirements of this paragraph.
(j) RETAINED REPETITIVE INSPECTION INTERVAL, WITH NEW TERMINATING ACTION
This paragraph restates the requirements of paragraph (j) of AD 2016
-24-03, with new terminating action. Repeat the inspection and preload
check required by paragraphs (g) and (i) of this AD at intervals not
to exceed 3,600 flight hours or 18 months, whichever occurs first,
except as provided by paragraph (k) of this AD. Accomplishment of the
actions required by paragraphs (l) and (m) of this AD, as applicable,
terminates the requirements of this paragraph.
(k) RETAINED OPTIONAL BARREL NUT REPLACEMENT, WITH NEW SERVICE INFORMATION
This paragraph restates the provisions of paragraph (k) of AD 2016-24-
03, with new service information. Inspection and replacement of all
barrel nuts at the horizontal-stabilizer-to-vertical-stabilizer
attachment joints, in accordance with paragraph 3.B., "Procedure," of
the Accomplishment Instructions of Bombardier Service Bulletin 84-55
-08, Revision A, dated August 2, 2017, extends the next inspection
required by paragraph (j) of this AD to within 6,000 flight hours or
36 months, whichever occurs first, after accomplishing the
replacement.
(l) NEW REQUIREMENT OF THIS AD: SEALING DISK INSTALLATION
Within 8,000 flight hours or 48 months, whichever occurs first, after
the effective date of this AD, install a sealing disk at the mid-spar
location of the vertical stabilizer in accordance with paragraph 3.B.,
"Procedure," of the Accomplishment Instructions of Bombardier Service
Bulletin 84-55-06, dated January 31, 2017. Accomplishment of the
actions required by paragraphs (l) and (m) of this AD, as applicable,
terminates the requirements of paragraphs (h), (i), and (j) of this
AD.
(m) NEW REQUIREMENT OF THIS AD: REPLACEMENT OF DSC228 SERIES BARREL NUTS
For Bombardier, Inc., Model DHC-8-400, -401 and -402 airplanes, serial
numbers 4001 through 4524 inclusive: Within 8,000 flight hours or 48
months, whichever occurs first, after the effective date of this AD,
replace all DSC228 series barrel nuts at the horizontal-stabilizer-to
-vertical-stabilizer attachment joints with B0203073 series barrel
nuts in accordance with paragraph 3.B., "Procedure," of the
Accomplishment Instructions of Bombardier Service Bulletin 84-55-08,
Revision A, dated August 2, 2017. Accomplishment of the actions
required by paragraphs (l) and (m) of this AD, as applicable,
terminates the requirements of paragraphs (h), (i), and (j) of this
AD.
(n) PARTS INSTALLATION PROHIBITION
After modification of an airplane as required by paragraphs (l) and
(m) of this AD, no person may install a DSC228 series barrel nut at
the horizontal-stabilizer-to-vertical-stabilizer attachment joint on
the modified airplane.
(o) TERMINATING ACTIONS FOR PARAGRAPHS (H), (I), AND (J) OF THIS AD
Accomplishment of the actions required by paragraphs (l) and (m) of
this AD, as applicable, terminates the requirements of paragraphs (h),
(i), and (j) of this AD.
(p) CREDIT FOR PREVIOUS ACTIONS
(1) This paragraph provides credit for actions required by paragraphs (g)
(1), (g)(2), (h)(1), (h)(1)(i), (h)(1)(ii), (h)(2), (h)(3), (h)(4),
(i), and (k) of this AD, if those actions were performed before the
effective date of this AD using the service information identified in
paragraphs (p)(1)(i) through (p)(1)(iii) of this AD.
(i) Bombardier Alert Service Bulletin A84-55-04, dated May 21, 2015, which
is not incorporated by reference in this AD.
(ii) Bombardier Alert Service Bulletin A84-55-04, Revision A dated June 2,
2015, which is not incorporated by reference in this AD.
(iii) Bombardier Alert Service Bulletin A84-55-04, Revision B, dated July
30, 2015, which is not incorporated by reference in this AD.
(2) This paragraph provides credit for actions required by paragraphs (h)
(1), (h)(1)(i), (h)(1)(ii), (h)(2), and (k) of this AD, if those
actions were performed before the effective date of this AD using the
service information identified in paragraphs (p)(2)(i) and (p)(2)(ii)
of this AD.
(i) Bombardier Service Bulletin 84-55-08, dated January 27, 2017, which is
not incorporated by reference in this AD.
(ii) Bombardier Alert Service Bulletin A84-55-04, Revision C, dated May 3,
2016, which was incorporated by reference in AD 2016-24-03.
(q) OTHER FAA AD PROVISIONS
(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.
(i) Before using any approved AMOC, notify your appropriate principal in-
spector, or lacking a principal inspector, the manager of the local
flight standards district office/certificate holding district office.
(ii) AMOCs approved previously for AD 2016-24-03 are approved as AMOCs for
the corresponding provisions of this AD.
(2) Contacting the Manufacturer: For any requirement in this AD to obtain
corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, New York ACO
Branch, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier,
Inc.'s TCCA Design Approval Organization (DAO). If approved by the
DAO, the approval must include the DAO-authorized signature.
(r) RELATED INFORMATION
(1) Refer to Mandatory Continuing Airworthiness Information (MCAI)
Canadian AD CF-2015-13R1, dated June 26, 2017, 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-2018-0160.
(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) Service information identified in this AD that is not incorporated by
reference is available at the addresses specified in paragraphs (s)(5)
and (s)(6) of this AD.
(s) 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.
(3) The following service information was approved for IBR on November 28,
2018.
(i) Bombardier Repair Drawing (RD) 8/4-55-1143, Issue 2, dated May 25,
2015.
(ii) Bombardier Service Bulletin 84-55-06, dated January 31, 2017.
(iii) Bombardier Service Bulletin 84-55-08, Revision A, dated August 2,
2017.
(4) The following service information was approved for IBR on January 12,
2017 (81 FR 88623, December 8, 2016).
(i) Bombardier Alert Service Bulletin A84-55-04, Revision C, dated May 3,
2016.
(ii) Reserved.
(5) For service information identified in this AD, contact Bombardier,
Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto,
Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-4539; e-
mail thd.qseries@aero.bombardier.com; internet http://www.bombardier.
com.
(6) 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.
(7) You may view this service information that is incorporated by
reference at the National Archives and Records Administration (NARA).
For information on the availability of this material at NARA, call 202
-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-
locations.html.
Issued in Des Moines, Washington, on October 12, 2018. Michael Kaszycki,
Acting 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-2018-0160; Product Identifier 2017-NM-139-AD; Amendment
39-19476; AD 2018-22-03]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are superseding Airworthiness Directive (AD) 2016-24-03,
which applied to certain Bombardier, Inc., Model DHC-8-400 series
airplanes. AD 2016-24-03 required repetitive detailed inspections of
barrel nuts and cradles, a check of the bolt torque of the preload
indicating (PLI) washers, and corrective actions if necessary. This AD
retains the requirements of AD 2016-24-03 and requires modifying the
airplane by installing a sealing disk to a certain location and
replacing certain barrel nuts. This AD was prompted by reports of
cracked and corroded barrel nuts found at the mid-spar location of the
horizontal-stabilizer-to-vertical-stabilizer attachment joint, and the
issuance of new service information that includes a terminal
modification. We are issuing this AD to address the unsafe condition on
these products.
DATES: This AD is effective November 28, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 28,
2018.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of January
12, 2017 (81 FR 88623, December 8, 2016).
ADDRESSES: For service information identified in this final rule,
contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000;
fax 416-375-4539; email thd.qseries@aero.bombardier.com; internet
http://www.bombardier.com. You may view this referenced 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 http://www.regulations.gov by searching for and locating
Docket No. FAA-2018-0160.
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-2018-
0160; 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 (phone: 800-647-
5527) 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
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2016-24-03, Amendment 39-18720 (81 FR 88623,
December 8, 2016) (``AD 2016-24-03''). AD 2016-24-03 applied to certain
Bombardier, Inc., Model DHC-8-400 series airplanes. The NPRM published
in the Federal Register on March 9, 2018 (83 FR 10408). The NPRM was
prompted by reports of cracked and corroded barrel nuts found at the
mid-spar location of the horizontal-stabilizer-to-vertical-stabilizer
attachment joint, and the issuance of new service information that
includes a terminal modification. The NPRM proposed to continue to
require repetitive detailed inspections of each barrel nut and cradle,
a check of the bolt torque of the PLI washers, and corrective action if
necessary. The NPRM also proposed to require modifying the airplane by
installing a sealing disk to a certain location and replacing certain
barrel nuts. We are issuing this AD to address cracked and corroded
barrel nuts, which could compromise the structural integrity of the
vertical-stabilizer attachment joints and lead to loss of control of
the airplane.
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD CF-2015-13R1, dated June
26, 2017 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for certain Bombardier, Inc., Model DHC-8-400 series
airplanes. The MCAI states:
There has been one in-service report of a cracked and corroded
barrel nut, part number (P/N) DSC228-12, found at the mid-spar
location of the horizontal stabilizer to vertical stabilizer
attachment joint. There have also been two other reports of corroded
barrel nuts found at mid-spar locations.
Preliminary investigation determined that the cracking is
initiated by corrosion. Further investigation confirmed that the
corrosion was caused by inadequate cadmium plating on the barrel
nuts. Failure of the barrel nuts could compromise the structural
integrity of the joint and could lead to loss of control of the
aeroplane.
The original version of this [Canadian] AD was issued to mandate
the initial and repetitive inspections of the barrel nuts [and
cradles for cracks and corrosion] at each of the horizontal
stabilizer to vertical stabilizer attachment joints.
Revision 1 of this [Canadian] AD is issued to terminate the
repetitive inspection requirement by requiring the incorporation of
a modification to install a sealing disc at the middle spar location
of the horizontal stabilizer to vertical stabilizer attachment
joint, and the replacement of the DSC228 series barrel nuts with
B0203073 series barrel nuts that are more resistant to corrosion.
The applicability has been changed to account for the introduction
of the modifications in production.
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-2018-
0160.
Comments
We gave the public the opportunity to participate in developing
this final rule. The following presents the comment received on the
NPRM and the FAA's response.
Request To Refer to New Repair Drawing (RD)
Horizon Air requested that we revise paragraph (h)(1)(i) of the
proposed AD to refer to Bombardier RD 8/4-55-1143, Issue 2, dated May
25, 2015 (we referred to Bombardier RD 8/4-55-1143, Issue 1, dated May
21, 2015, as the appropriate source of service information for the
repair specified in paragraph (h)(1)(i) of the proposed AD). Horizon
Air noted that Bombardier RD 8/4-55-1143, Issue 2, dated May 25, 2015,
adds nominal bore diameters to sheets 1-4.
We agree with the commenter's request. Bombardier RD 8/4-55-1143,
Issue 2, dated May 25, 2015, clarifies the bore hole diameters for
repair but does not otherwise change the substantive requirements of
this AD. No additional work is necessary for airplanes on which
Bombardier RD 8/4-55-1143, Issue 1, dated May 21, 2015, has already
been done. We have revised paragraph (h)(1)(i) of this AD to include
Bombardier RD 8/4-55-1143, Issue 2, dated May 25, 2015, as the
appropriate service information for repairing corrosion and damage of
the bore of the fitting.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this final rule with the change described previously and minor
editorial changes. We have 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.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.
Related Service Information Under 1 CFR Part 51
Bombardier has issued the following service information.
Bombardier Alert Service Bulletin A84-55-04, Revision C,
dated May 3, 2016. This service information describes procedures for a
detailed inspection and repair for cracks and corrosion of the barrel
nuts and cradles; a bolt preload check of the PLI washers and
applicable corrective actions; a detailed inspection and repair for
corrosion and damage of the bore of the fitting; and replacement of the
barrel nuts.
Bombardier Service Bulletin 84-55-06, dated January 31,
2017. This service information describes procedures for installing an
aluminum sealing disk at the mid-spar location of the vertical
stabilizer.
Bombardier Service Bulletin 84-55-08, Revision A, dated
August 2, 2017. This service information describes procedures for an
inspection for part number and damage of the barrel nuts at the
horizontal-stabilizer-to-vertical-stabilizer attachment joints, and
replacement of discrepant parts.
Bombardier Repair Drawing (RD) 8/4-55-1143, Issue 2, dated
May 25, 2015. This service information describes procedures for
repairing corrosion and damage of the fitting bore.
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
We estimate that this AD affects 54 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
Action
|
Labor cost
|
Parts cost
|
Cost per
product
|
Cost on
U.S. operators
|
Inspections (retained actions
from AD 2016-24-03) |
8 work-hours x $85 per
hour = $680 |
$0 |
$680 |
$36,720 |
Sealing disk installation (new
action) |
4 work-hours x $85 per
hour = $340 |
781 |
1,121 |
60,534 |
Replacement of DSC228 series
barrel nuts (new action) |
2 work-hours x $85 per hour
= $170 |
2,236 |
2,406 |
129,924 |
We estimate the following costs to
do any necessary replacements
that would be required based on the results of the inspection. We have
no way of determining the number of aircraft that might need these
replacements:
On-Condition Costs
Action
|
Labor cost
|
Parts cost
|
Cost per
product
|
Replacement (retained action
from AD 2016-24-03) |
2 work-hours x $85 per hour =
$170 |
$8,881
|
$9,051
|
We have received no definitive data
that would enable us to provide
cost estimates for the other on-condition actions specified in this AD.
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.
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
We determined that 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. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
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 removing Airworthiness Directive (AD)
2016-24-03, Amendment 39-18720 (81 FR 88623, December 8, 2016), and
adding the following new AD:
|