(a) COMMENTS DUE DATE
The FAA must receive comments by April 27, 2020.
(b) AFFECTED ADS
This AD replaces AD 2010-23-04, Amendment 39-16493 (75 FR 68174,
November 5, 2010) ("AD 2010-23-04").
(c) APPLICABILITY
This AD applies to De Havilland Aircraft of Canada Limited (Type
Certificate Previously Held by Bombardier, Inc.) Model DHC-8-400, -401
and -402 airplanes, certificated in any category, serial numbers 4001
and subsequent.
(d) SUBJECT
Air Transport Association (ATA) of America Code 54, Nacelles/pylons.
(e) REASON
This AD was prompted by reports of cracked nacelle attachment fittings
which a preliminary investigation determined to be caused by stress
corrosion. The FAA is issuing this AD to address this condition,
which, if not detected and corrected, could compromise the structural
integrity of the nacelle attachment fitting and possibly result in
collapse of the landing gear.
(f) COMPLIANCE
Comply with this AD within the compliance times specified, unless al-
ready done.
(g) RETAINED DETAILED AND CONDUCTIVITY INSPECTIONS AND REPLACEMENT, WITH
REVISED SERVICE INFORMATION AND REVISED REPLACEMENT INSTRUCTIONS
This paragraph restates the requirements of paragraph (g) of AD 2010-
23-04, with revised service information and revised replacement in-
structions. For airplanes having serial numbers 4001 through 4304 in-
clusive, 4314, and 4315: Within 100 flight hours after November 22,
2010 (the effective date of AD 2010-23-04), do a detailed inspection
for cracking, and a conductivity inspection on each of the 4 nacelle
attachment fittings in accordance with the Accomplishment Instructions
of Bombardier Service Bulletin 84-54-14, Revision K, dated August 7,
2018. Repeat the detailed inspection at intervals not to exceed 300
flight hours, except as provided by paragraph (i) of this AD.
Accomplishing the replacement specified in paragraph (g)(1)(ii) or (g)
(2)(ii)(B) of this AD terminates the inspections required by this
paragraph.
(1) If any nacelle attachment fitting is found cracked, before further
flight, do the action specified in paragraph (g)(1)(i) or (ii) of this
AD. As of the effective date of this AD, only the action specified in
paragraph (g)(1)(ii) of this AD may be done.
(i) Replace the fitting with a new fitting in accordance with paragraph
(2) of Part A of the Accomplishment Instructions of Bombardier Service
Bulletin 84-54-14, Revision K, dated August 7, 2018.
(ii) Replace the rear spar nacelle attachment fitting and associated
structure with a new nacelle attachment fitting, part number (P/N)
8Z9305, and do all applicable related investigative and corrective
actions, in accordance with Part B of the Accomplishment Instructions
of Bombardier Service Bulletin 84-54-16 Revision D, dated August 7,
2018. Do all applicable related investigative and corrective actions
before further flight.
(2) If the conductivity of any test points on any fitting is found to be
greater than 45.0 percent International Annealed Copper Standard
(IACS) or if the conductivity of any test points on any fitting is
found to be less than 38.0 percent IACS, do the actions required by
paragraphs (g)(2)(i) and (ii) of this AD.
(i) Within 24 hours after accomplishing the conductivity inspection speci-
fied in paragraph (g) of this AD, do a detailed inspection of the
nacelle attachment fitting for cracking, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 84-54-14,
Revision K, dated August 7, 2018, and repeat thereafter at intervals
not to exceed 24 hours. If cracking is found, before further flight,
replace the fitting with a new fitting in accordance with the
requirements of paragraph (g)(2)(ii) of this AD. Replacement of the
fitting terminates the daily detailed inspection requirements of this
paragraph.
(ii) Except as required by paragraph (g)(2)(i) of this AD: Within 300
flight hours after accomplishing the conductivity inspection speci-
fied in paragraph (g) of this AD, do the action specified in para-
graph (g)(2)(ii)(A) or (B) of this AD. As of the effective date of
this AD, only the action specified in paragraph (g)(2)(ii)(B) of this
AD may be done.
(A) Replace the fitting with a new fitting in accordance with paragraph
(2) of Part A of the Accomplishment Instructions of Bombardier Service
Bulletin 84-54-14, Revision K, dated August 7, 2018.
(B) Replace the rear spar nacelle attachment fitting and associated
structure with a new nacelle attachment fitting, P/N 8Z9305, and do
all applicable related investigative and corrective actions, in
accordance with Part B of the Accomplishment Instructions of
Bombardier Service Bulletin 84-54-16 Revision D, dated August 7, 2018.
Do all applicable related investigative and corrective actions before
further flight.
(h) RETAINED INSPECTIONS AND REPLACEMENT WITH REVISED SERVICE INFORMATION,
REVISED AFFECTED AIRPLANES, AND REVISED REPLACEMENT INSTRUCTIONS
This paragraph restates the requirements of paragraph (i) of AD 2010-
23-04, with revised service information, revised affected airplanes,
and revised replacement instructions. For airplanes having serial
numbers 4305 through 4313 inclusive, and 4316 through 4380 inclusive,
and airplanes that have replaced nacelle attachment fitting(s) with
P/N 854146663: Within 1,200 flight hours after November 22, 2010 (the
effective date of AD 2010-23-04), do a detailed inspection for
cracking on each of the 4 nacelle attachment fittings, in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
84-54-14, Revision K, dated August 7, 2018. If any nacelle attachment
fitting is found cracked, before further flight, do the action
specified in paragraph (h)(1) or (2) of this AD. As of the effective
date of this AD, only the action specified in paragraph (h)(2) of this
AD may be done. Thereafter, repeat the detailed inspection at
intervals not to exceed 300 flight hours, except as provided by
paragraph (i) of this AD. Accomplishing the replacement specified in
paragraph (h)(2) of this AD terminates the inspections required by
this paragraph.
(1) Replace the fitting with a new fitting in accordance with paragraph
(2) of Part A of the Accomplishment Instructions of Bombardier Service
Bulletin 84-54-14, Revision K, dated August 7, 2018.
(2) Replace the rear spar nacelle attachment fitting and associated
structure with a new nacelle attachment fitting, P/N 8Z9305, and do
all applicable related investigative and corrective actions, in
accordance with Part B of the Accomplishment Instructions of
Bombardier Service Bulletin 84-54-16 Revision D, dated August 7, 2018.
Do all applicable related investigative and corrective actions before
further flight.
(i) RETAINED INSPECTION COMPLIANCE TIME, WITH REVISED SERVICE INFORMATION
This paragraph restates the requirements of paragraph (j) of AD 2010-
23-04, with revised service information. For any fitting that is re-
placed in accordance with paragraph (3) of Part A of the Accomplish-
ment Instructions of Bombardier Service Bulletin 84-54-14, Revision J,
dated September 17, 2010 or paragraph (2) of Part A of the Accomplish-
ment Instructions of Bombardier Service Bulletin 84-54-14, Revision K,
dated August 7, 2018, as specified in paragraph (g) or (h) of this AD:
Within 1,200 flight hours after replacing the fitting, do a detailed
inspection of that replaced fitting as specified in paragraph (g) or
(h) of this AD, and repeat the detailed inspection thereafter at in-
tervals not to exceed 300 flight hours. Accomplishing the replacement
specified in paragraph (g)(1)(ii), (g)(2)(ii)(B), or (h)(2) of this AD
terminates the inspections required by this paragraph.
(j) RETAINED CREDIT FOR PREVIOUS ACTIONS (REPLACING THE FITTING), WITH RE-
VISED PARAGRAPH REFERENCES
This paragraph restates the credit provided in paragraph (k) of AD
2010-23-04, with revised paragraph references. Accomplishing the re-
placement of the nacelle fittings in accordance with any Bombardier
service bulletin identified in figure 1 to paragraphs (j) and (k) of
this AD before November 22, 2010 (the effective date of AD 2010-23-04)
is also acceptable for compliance with the fitting replacements speci-
fied in paragraphs (g)(1)(i), (g)(2)(ii)(A), and (h)(1) of this AD.
FIGURE 1 TO PARAGRAPHS (J) AND (K) – ACCEPTABLE SERVICE INFORMATION
______________________________________________________________________
BOMBARDIER SERVICE BULLETIN REVISION DATED
______________________________________________________________________
84-54-14 Original April 16, 2010
84-54-14 A April 22, 2010
84-54-14 B June 11, 2010
84-54-14 C June 30, 2010
84-54-14 D July 5, 2010
84-54-14 E August 19, 2010
84-54-14 F August 20, 2010
84-54-14 G September 9, 2010
84-54-14 H September 10, 2010
______________________________________________________________________
(k) RETAINED CREDIT FOR PREVIOUS ACTIONS (INSPECTIONS), WITH NO CHANGES
This paragraph restates the credit provided in paragraph (l) of AD
2010-23-04 with no changes. Accomplishment of the inspections required
by paragraphs (g) and (h) of this AD before November 22, 2010 (the
effective date of AD 2010-23-04) in accordance with any Bombardier
service bulletin identified in figure 1 to paragraphs (j) and (k) of
this AD is acceptable for compliance with the corresponding actions
required by paragraphs (g) and (h) of this AD.
(l) NEW REQUIREMENTS OF THIS AD: MODIFICATION OF THE REAR SPAR FITTING AND
NACELLE ATTACHING STRUCTURE
For airplanes with nacelle attachment fitting P/N 85414663: Unless al-
ready done as specified in paragraph (g)(1)(ii), (g)(2)(ii)(B), or
(h)(2) of this AD: Within 8,000 flight hours or 48 months, whichever
occurs first, from the effective date of this AD, replace the rear
spar nacelle attachment fitting and associated structure with a new
nacelle attachment fitting, P/N 8Z9305, and do all applicable related
investigative and corrective actions, in accordance with Part B of the
Accomplishment Instructions of Bombardier Service Bulletin 84-54-16,
Revision D, dated August 7, 2018. Do all applicable related
investigative and corrective actions before further flight.
(m) NEW CREDIT FOR PREVIOUS ACTIONS
(1) This paragraph provides credit for actions required by paragraphs (g)
and (h) of this AD that are identified in Bombardier Service Bulletin
84-54-14, Revision K, dated August 7, 2018, if those actions were
performed before the effective date of this AD using Bombardier
Service Bulletin 84-54-14, Revision J, dated September 17, 2010, which
was incorporated by reference in AD 2010-23-04; except as provided by
paragraph (p) of this AD.
(2) This paragraph provides credit for accomplishing the replacement of
the rear spar fitting and nacelle attaching structure required by
paragraph (l) of this AD, if those actions were performed before the
effective date of this AD using the service information specified in
paragraphs (m)(2)(i) through (iii) of this AD.
(i) Bombardier Service Bulletin 84-54-16, dated April 29, 2011.
(ii) Bombardier Service Bulletin 84-54-16, Revision A, dated August 1,
2011.
(iii) Bombardier Service Bulletin 84-54-16, Revision C, dated January 31,
2017.
(3) This paragraph provides credit for accomplishing the replacement of
the rear spar fitting and nacelle attaching structure required by
paragraph (l) of this AD, if those actions were performed before the
effective date of this AD using Bombardier Service Bulletin 84-54-16,
Revision B dated October 6, 2016. Although Bombardier Service Bulletin
84-54-16, Revision B, dated October 6, 2016, incorrectly stated that
airworthiness limitations (AWLs) or damage tolerance inspections
(DTIs) are not affected, they are affected. Refer to the applicable
AWLs for Post/Pre-Modification Summary (ModSum) 4-113697 and
Bombardier Service Bulletin 84-54-16 in the existing maintenance
requirements manual.
(4) This paragraph provides credit for accomplishing the action identified
in Bombardier Service Bulletin 84-54-14, Revision K, dated August 7,
2018, that are required by paragraphs (g) and (h) of this AD, if those
actions were performed before the effective date of this AD using the
service information specified in paragraphs (m)(4)(i) through (iv) of
this AD.
(i) Bombardier Service Bulletin 84-54-15, dated August 20, 2010.
(ii) Bombardier Service Bulletin 84-54-15, Revision A, dated October 25,
2010.
(iii) Bombardier Service Bulletin 84-54-15, Revision B, dated February 2,
2017.
(iv) Bombardier Service Bulletin 84-54-15, Revision C, dated August 7,
2018.
(n) TERMINATING ACTION FOR CERTAIN ACTIONS IN PARAGRAPHS (G), (H), AND (I)
OF THIS AD
Accomplishing the modification of the rear spar fitting and nacelle
attaching structure required by paragraph (l) of this AD terminates
the repetitive inspection required by paragraphs (g), (h), and (i) of
this AD for that airplane.
(o) PARTS INSTALLATION LIMITATIONS
As of the effective date of this AD, no person may install a rear spar
nacelle attachment fitting P/N 85414663 on any airplane.
(p) CREDIT FOR ALTERNATIVE TO CERTAIN CREDIT ACTIONS
For airplanes on which Bombardier Service Bulletin 84 54 14, Revision
J, dated September 17, 2010, was done before the effective date of
this AD: As an alternative to applying sealant to each fitting and
access panel as specified in paragraph C.(1) of the Accomplishment
Instructions of Bombardier Service Bulletin 84-54-14, Revision J,
dated September 17, 2010, the use of the instructions of Bombardier
Modification Summary Package IS4Q5400012, Revision B, dated July 11,
2012, to apply sealant is also acceptable if accomplished before the
effective date of this AD.
(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 2010-23-04, are approved as AMOCs
for the corresponding provisions of this AD.
(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 Transport Canada Civil Aviation (TCCA); or de
Havilland'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 Airworthiness Directive CF-2010-30R2, dated July 30, 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-2020-0099.
(2) For more information about this AD, contact Andrea Jimenez, Aerospace
Engineer, Airframe and Propulsion Section, FAA, New York ACO Branch,
1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-
7330; fax 516-794-5531; email 9-avs-nyaco-cos@faa.gov.
(3) For service information identified in this AD, contact De Havilland
Aircraft of Canada Limited, Q-Series Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000;
fax 416-375-4539; email thd@dehavilland.com; internet https://
dehavilland.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 on February 12, 2020. Gaetano A. Sciortino, Deputy Director for
Strategic Initiatives, Compliance & Airworthiness Division, Aircraft
Certification Service.
DATES: The FAA must receive comments on this proposed AD by April 27, 2020
|
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0099; Product Identifier 2019-NM-169-AD]
RIN 2120-AA64
Airworthiness Directives; De Havilland Aircraft of Canada Limited
(Type Certificate Previously Held by Bombardier, Inc.) Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive
(AD)
2010-23-04, which applies to all De Havilland Aircraft of Canada
Limited Model DHC-8-400 series airplanes. AD 2010-23-04 requires
repetitive detailed inspections of the nacelle attachment fittings for
cracks, a conductivity inspection of the nacelle attachment fittings,
and replacement if necessary. Since AD 2010-23-04 was issued, the FAA
has determined that it is necessary to do a replacement with new
nacelle attachment fittings. This proposed AD would retain the
requirements of AD 2010-23-04, remove a certain inspection requirement
for certain airplanes, and add a new requirement to replace the rear
spar fitting and nacelle attaching structure with a new nacelle
attachment fitting. 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 April
27,
2020.
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 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: 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 De
Havilland Aircraft of Canada Limited, Q-Series Technical Help Desk, 123
Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-
4000; fax 416-375-4539; email thd@dehavilland.com; internet https://
dehavilland.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 https://www.regulations.
gov by searching for and locating Docket No. FAA-2020-0099;
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 listed above.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer,
Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7330; 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-2020-0099;
Product Identifier 2019-NM-169-AD" at the beginning of your comments.
The FAA specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. The
FAA will consider all comments received by the closing date and may
amend this proposed AD based on those comments.
The FAA will post all comments received, without change, to https://www.
regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact received about this proposed AD.
Discussion
The FAA issued AD 2010-23-04, Amendment 39-16493 (75 FR 68174,
November 5, 2010) ("AD 2010-23-04"), for all De Havilland Aircraft of
Canada Limited Model DHC-8-400 series airplanes. AD 2010-23-04 requires
repetitive detailed inspections of the nacelle attachment fittings for
cracks, a conductivity inspection of the nacelle attachment fittings,
and replacement if necessary. AD 2010-23-04 resulted from reports of
cracked nacelle attachment fittings, which a preliminary investigation
determined to be caused by stress corrosion. The FAA issued AD 2010-23-
04 to address this condition, which, if not detected and corrected,
could compromise the structural integrity of the nacelle attachment
fitting and possibly result in collapse of the landing gear.
Actions Since AD 2010-23-04 Was Issued
Since AD 2010-23-04 was issued, the FAA has determined that it is
necessary to require a replacement with new nacelle attachment
fittings, which would be terminating action for the inspections
specified in AD 2010-23-04. Additionally, paragraph (i) of AD 2010-23-
04 requires repetitive detailed inspections for cracking on each of the
four nacelle attachment fittings for airplanes having serial numbers
4305 through 4313 inclusive, and 4316 and subsequent. The FAA has
retained this inspection in paragraph (h) of this proposed AD, but
serial numbers 4381 and subsequent were modified in production and
cannot have the affected part installed, so those airplanes were
removed from the retained actions in paragraph (h) of this proposed AD.
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD CF-2010-30R2, dated July
30, 2019 (referred to after this as the Mandatory Continuing
Airworthiness Information, or "the MCAI"), to correct an unsafe
condition for all De Havilland Aircraft of Canada Limited Model DHC-8-
400 series 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-2020-0099.
This proposed AD was prompted by a determination that it is
necessary to install new nacelle attachment fitting in order to address
the unsafe condition. The FAA is proposing this AD to address cracked
nacelle attachment fittings, which a preliminary investigation
determined to be caused by stress corrosion. This condition, if not
detected and corrected, could compromise the structural integrity of
the nacelle attachment fitting and possibly result in collapse of the
landing gear. See the MCAI for additional background information.
Related Service Information Under 1 CFR Part 51
Bombardier has issued Service Bulletin 84-54-14, Revision K, dated
August 7, 2018. This service bulletin describes procedures for a
conductivity inspection of the nacelle attachment fittings, repetitive
detailed inspections of the nacelle attachment fittings for cracks, and
replacement of the fitting.
Bombardier has also issued Service Bulletin 84-54-16, Revision D,
dated August 7, 2018. This service information describes procedures for
replacing the rear spar nacelle attachment fitting and associated
structure with a new nacelle attachment fitting, part number (P/N)
8Z9305. The replacement includes applicable related investigative and
corrective actions. The related investigative actions include an
inspection of the internal bore and external surface of the main
landing gear yoke pins, the drag strut pins, and the stabilizer brace
pins for signs of corrosion and damage; an inspection of the inner bore
and outer surface of the coat hangar pins for signs of corrosion and
damage. The corrective actions include repair, rework, or replacement.
Bombardier has also issued Modification Summary Package
IS4Q5400012, Revision B, dated July 11, 2012. This service information
describes procedures for applying a fay sealant gasket to the rear spar
access fitting access panel.
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 a 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 agency 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 retain all of the requirements of AD 2010-
23-04. This proposed AD would also require accomplishing the actions
specified in the service information described previously.
Costs of Compliance
The FAA estimates that this proposed AD affects 54 airplanes of
U.S. registry.
The FAA estimates the following costs to comply with this proposed
AD:
Estimated Costs for Required Actions *
|
Action
|
Labor cost
|
Parts cost
|
Cost per
product
|
Cost on
U.S. operators
|
| Retained actions from AD 2010-23-04 |
3 work-hours x $85 per hour =
$255 |
$0 |
$255 |
$13,770 |
| New proposed actions |
320 work-hours x $85 per hour
= $27,200 |
Up to $104,739 |
Up to $131,939 |
Up to $7,124,706 |
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.
Regulatory Findings
The FAA has 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 removing Airworthiness Directive (AD)
2010-23-04, Amendment 39-16493 (75 FR 68174, November 5, 2010), and
adding the following new AD:
|