Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes, 10744-10747 [2021-03476]
Download as PDF
<![CDATA[
10744
Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2021–04–09 Yabora˜ Indu´stria Aerona´utica
S.A. (Type Certificate Previously Held
by Embraer S.A.): Amendment 39–
21430; Docket No. FAA–2020–1035;
Project Identifier MCAI–2020–01017–T.
(a) Effective Date
This airworthiness directive (AD) is
effective March 30, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Yabora˜ Indu´stria
Aerona´utica S.A. Model EMB–135BJ,
–135ER, –135KE, –135KL, and –135LR
airplanes; and Model EMB–145, –145EP,
–145ER, –145LR, –145MP, –145MR, and
–145XR airplanes; certificated in any
category; as identified in Ageˆncia Nacional
de Aviac
¸a˜o Civil (ANAC) AD 2020–07–02,
effective July 21, 2020 (ANAC AD 2020–07–
02).
(d) Subject
Air Transport Association (ATA) of
America Code 73, Engine fuel and control.
(e) Reason
This AD was prompted by reports that
calculations provided by the automatic
VerDate Sep<11>2014
21:28 Feb 22, 2021
Jkt 253001
takeoff thrust control system (ATTCS) are
incorrect under certain conditions. The FAA
is issuing this AD to address the risk of overprediction of the operational margins,
without the necessary alert being provided to
the flightcrew in some situations. This
condition, if not corrected, could lead to a
performance reduction during takeoff, in
which case the airplane may not be able to
take off safely.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, ANAC AD 2020–07–02.
(h) Exceptions to ANAC AD 2020–07–02
(1) Where ANAC AD 2020–07–02 refers to
its effective date, this AD requires using the
effective date of this AD.
(2) The ‘‘Alternative method of compliance
(AMOC)’’ section of ANAC AD 2020–07–02
does not apply to this AD.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Large Aircraft
Section, International Validation 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 responsible Flight
Standards Office, as appropriate. If sending
information directly to the Large Aircraft
Section, International Validation Branch,
send it to the attention of the person
identified in paragraph (j) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the responsible
Flight Standards 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, Large Aircraft Section,
International Validation Branch, FAA; or
ANAC; or ANAC’s authorized Designee. If
approved by the ANAC Designee, the
approval must include the Designee’s
authorized signature.
(j) Related Information
For more information about this AD,
contact Kathleen Arrigotti, Aerospace
Engineer, Large Aircraft Section,
International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA 98198;
telephone and fax 206–231–3218; email
kathleen.arrigotti@faa.gov.
(k) 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.
PO 00000
Frm 00042
Fmt 4700
Sfmt 4700
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Ageˆncia Nacional de Aviac
¸a˜o Civil
(ANAC) AD 2020–07–02, effective July 21,
2020.
(ii) [Reserved]
(3) For ANAC AD 2020–07–02, contact
National Civil Aviation Agency (ANAC),
Aeronautical Products Certification Branch
(GGCP), Rua Dr. Orlando Feirabend Filho,
230—Centro Empresarial Aquarius—Torre
B—Andares 14 a 18, Parque Residencial
Aquarius, CEP 12.246–190—Sa˜o Jose´ dos
Campos—SP, BRAZIL, Tel: 55 (12) 3203–
6600; Email: pac@anac.gov.br; internet
www.anac.gov.br/en/. You may find this IBR
material on the ANAC website at https://
sistemas.anac.gov.br/certificacao/DA/
DAE.asp.
(4) You may view this material at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195. This material may be found
in the AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2020–1035.
(5) You may view this material that is
incorporated by reference 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 on February 5, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–03586 Filed 2–22–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0813; Product
Identifier 2019–CE–040–AD; Amendment
39–21387; AD 2021–02–04]
RIN 2120–AA64
Airworthiness Directives; Pilatus
Aircraft Ltd. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for Pilatus
Aircraft Ltd. (Pilatus) Model PC–12/47E
airplanes. This AD was prompted by
mandatory continuing airworthiness
information (MCAI) originated by an
aviation authority of another country to
identify and correct an unsafe condition
on an aviation product. The MCAI
describes the unsafe condition as
SUMMARY:
E:\FR\FM\23FER1.SGM
23FER1
Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations
inboard flap fairings aft (IFFAs) having
an incorrect shape, which may result in
chafing between the IFFA and the
associated front inboard tension rod.
This AD requires an inspection of the
IFFAs for the correct shape and chafing
between the IFFA and the associated
front inboard tension rod, with
corrective action as necessary. This
condition could lead to failure of the
inboard flap drive arm with consequent
asymmetric flap extension, resulting in
reduced control of the airplane. The
FAA is issuing this AD to address the
unsafe condition on these products.
This AD is effective March 30,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 30, 2021.
DATES:
For service information
identified in this final rule, contact
Pilatus Aircraft, Ltd., Customer Support
PC–12, CH–6371 Stans, Switzerland;
phone: +41 41 619 33 33; fax: +41 41
619 73 11; email: supportPC12@pilatusaircraft.com; website: https://
www.pilatus-aircraft.com. You may
review this referenced service
information at the FAA, Airworthiness
Products Section, Operational Safety
Branch, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA,
call (816) 329–4148. It is also available
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0813.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0813; 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 MCAI, 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:
Doug Rudolph, Aviation Safety
Engineer, General Aviation & Rotorcraft
Section, International Validation
Branch, FAA, 901 Locust, Room 301,
Kansas City, Missouri 64106; phone:
(816) 329–4059; fax: (816) 329–4090;
email: doug.rudolph@faa.gov.
SUPPLEMENTARY INFORMATION:
VerDate Sep<11>2014
21:28 Feb 22, 2021
Jkt 253001
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Pilatus Model PC–12/47E
airplanes. The NPRM published in the
Federal Register on September 16, 2020
(85 FR 57804). In the NPRM, the FAA
proposed to require an inspection of the
IFFAs for the correct shape and chafing
between the IFFA and the associated
front inboard tension rod, with
corrective action as necessary.
The NPRM was based on MCAI from
the European Union Aviation Safety
Agency (EASA), which is the Technical
Agent for the Member States of the
European Union. EASA issued AD No.:
2019–0231, dated September 13, 2019
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for Pilatus
Model PC–12/47E airplanes. The MCAI
states:
On the final assembly line of PC–12/47E
aeroplanes, IFFAs were detected having an
incorrect shape. As a consequence, chafing
between the IFFA and the associated front
inboard tension rod could occur, may cause
corrosion of the bare rod aluminium tube and
reduce aluminium thickness.
This condition, if not detected and
corrected, could lead to failure of the inboard
flap drive arm with consequent asymmetric
flap extension, possibly resulting in reduced
control of the aeroplane.
To address this potential unsafe condition,
Pilatus issued the [service bulletin] SB to
provide inspection and modification
instructions.
For the reason described above, this
[EASA] AD requires a one-time inspection of
both IFFA and, depending on findings, a
follow-on inspection of the associated front
inboard tension rod for chafing, and
modification or replacement of affected parts.
You may examine the MCAI at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0813.
Discussion of Final Airworthiness
Directive
Comments
The FAA received two comments
from Pilatus. The following presents the
comments received on the NPRM and
the FAA’s response to each comment.
Pilatus requested the FAA reduce the
applicability of the proposed AD from
all Model PC–12/47E airplanes to Model
PC–12/47E airplanes with serial number
(S/N) 1576 and higher. Pilatus stated
that due to an engineering change in
2014, the left-hand (LH) IFFA, part
number (P/N) 557.52.12.223, and the
right-hand (RH) IFFA, P/N
557.52.12.224, introduced on airplanes
with S/N 1576 and higher, have
different attachment hole positions and
PO 00000
Frm 00043
Fmt 4700
Sfmt 4700
10745
a maximum hole position difference of
more than 12mm. As a result, it is not
physically possible to install P/Ns
557.52.12.223 and 557.52.12.224 on
airplanes with an S/N lower than 1576.
The FAA partially agrees. The
commenter is correct that the affected
IFFAs cannot be installed on Model PC–
12/47E airplanes with an S/N lower
than 1576. The FAA has revised
paragraph (f) of this AD to limit the
inspection of the IFFAs to airplanes
with an S/N 1576 and higher.
Pilatus acknowledged that tension rod
P/N 527.52.12.135 can be installed on
all Model PC–12/47E airplanes but
requested the FAA limit the tension rod
inspection for airplanes with an S/N
lower than 1576 to only those with
maintenance records showing that the
tension rod had been installed.
The FAA partially agrees. The FAA
has revised the tension rod inspection to
limit its scope for airplanes with an S/
N lower than 1576. Because the tension
rods are not life-limited parts, there is
no regulatory requirement for them to be
serialized or for operators to record or
retain information about the part’s
traceability. Therefore, operators would
be unable to comply with, and the FAA
would be unable to enforce, the change
requested by the commenter, as
maintenance records may not identify if
a tension rod was removed from an
airplane with an S/N 1576 or higher.
Instead, the FAA has changed the AD so
that the inspection of the tension rod is
required for all airplanes with a S/N
1576 or higher and for airplanes with a
S/N 1001 through 1575 if tension rod P/
N 527.52.12.135 is installed.
Conclusion
The FAA reviewed the relevant data,
considered any comments received, and
determined that air safety requires
adopting this AD as proposed.
Accordingly, the FAA is issuing this AD
to address the unsafe condition on these
products. Except for the changes
described previously, this AD is
adopted as proposed in the NPRM.
None of the changes will increase the
economic burden on any operator.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Pilatus PC–12
Service Bulletin No: 27–026, dated July
10, 2019 (Pilatus SB No. 27–026). The
service information specifies procedures
for inspecting and correcting chafing
between the left and right IFFAs and the
associated front inboard tension rods.
This service information is reasonably
available because the interested parties
have access to it through their normal
E:\FR\FM\23FER1.SGM
23FER1
10746
Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations
course of business or by the means
identified in ADDRESSES.
Differences Between This AD and the
MCAI
The MCAI only requires inspection of
the tension rods if the IFFAs are
modified because they have been found
to have the incorrect shape. Due to the
length of time between manufacture and
the issuance of this AD, operators could
have installed an affected tension rod
onto an airplane that was not
manufactured with the defective part.
Therefore, this AD requires inspection
for chafing damage on the tension rods
on all Model PC–12/47E airplanes that
have an affected tension rod installed.
Costs of Compliance
The FAA estimates that this AD will
affect 18 products of U.S. registry. The
FAA also estimates that it will take
about 2.5 work-hours per product to
comply with the requirements of this
AD. The average labor rate is $85 per
work-hour. Required parts will cost
about $1,600 per product.
Based on these figures, the FAA
estimates the cost of this AD on U.S.
operators will be $32,634 or $1,813 per
product.
The FAA has included all costs in this
cost estimate. According to the
manufacturer, however, all or some of
the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected operators.
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
This AD will not have federalism
implications under Executive Order
VerDate Sep<11>2014
21:28 Feb 22, 2021
Jkt 253001
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.
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2021–02–04 Pilatus Aircraft Ltd.:
Amendment 39–21387; Docket No.
FAA–2020–0813; Product Identifier
2019–CE–040–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective March 30, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Pilatus Aircraft Ltd.
Model PC–12/47E airplanes, all serial
numbers (S/Ns), certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)
Code 2700: Flight Controls.
(e) Reason
This AD was prompted by mandatory
continuing airworthiness information (MCAI)
originated by an aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as inboard
PO 00000
Frm 00044
Fmt 4700
Sfmt 4700
flap fairings aft (IFFAs) having an incorrect
shape. The FAA is issuing this AD to prevent
chafing between the IFFA and the front
inboard tension rod, and consequent
corrosion of the bare rod aluminum tube and
reduced aluminum thickness. This condition,
if not corrected, could lead to failure of the
inboard flap drive arm, asymmetric flap
extension, and reduced control of the
airplane.
(f) Actions and Compliance
(1) For airplanes with a S/N 1576 and
higher, unless already done, within 100
hours time-in-service (TIS) after the effective
date of this AD or within 6 months after the
effective date of this AD, whichever occurs
first, inspect the left-hand (LH) and righthand (RH) IFFAs for correct shape and
clearance with the LH and RH tension rods
by following step 3.B.(1) and Figures 2 and
3 of the Accomplishment Instructions—
Aircraft in Pilatus PC–12 Service Bulletin No:
27–026, dated July 10, 2019 (Pilatus SB 27–
026).
(i) If the shape of the LH or RH IFFA is
incorrect or if the clearance between the
IFFA and the tension rod is less than 5 mm
(0.2 inch), before further flight, modify the
IFFA and inspect the tension rods for chafing
by following section 3.C. of the
Accomplishment Instructions—Aircraft in
Pilatus SB 27–026.
(ii) If the shape of the LH and RH IFFAs
is correct and the clearance between the IFFA
and the tension rod is at least 5 mm (0.2
inch), before further flight, inspect the front
inboard LH and RH tension rods for chafing
by following step 3.C.(12)(a) of the
Accomplishment Instructions—Aircraft in
Pilatus SB 27–026. If the LH or RH tension
rod has any chafing, before further flight,
replace the tension rod by following step
3.C.(12)(b) of the Accomplishment
Instructions—Aircraft in Pilatus SB 27–026.
(2) For airplanes with a S/N 1001 through
S/N 1575, inclusive, that have a tension rod
part number (P/N) 527.52.12.135 installed,
unless already done, within 100 hours TIS
after the effective date of this AD or within
6 months after the effective date of this AD,
whichever occurs first, inspect the front
inboard LH and RH tension rods for chafing
by following step 3.C.(12)(a) of the
Accomplishment Instructions—Aircraft in
Pilatus SB 27–026. If the LH or RH tension
rod has any chafing, before further flight,
replace the tension rod by following step
3.C.(12)(b) of the Accomplishment
Instructions—Aircraft in Pilatus SB 27–026.
(3) For all Model PC–12/47E airplanes, as
of the effective date of this AD, do not install
on any airplane an LH IFFA P/N
557.52.12.223, RH IFFA P/N 557.52.12.224,
or tension rod P/N 527.52.12.135 unless the
part has been inspected and all corrective
actions have been taken as required by this
AD.
(g) Alternative Methods of Compliance
(AMOCs)
E:\FR\FM\23FER1.SGM
23FER1
Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations
The Manager, International Validation
Branch, FAA, has the authority to approve
AMOCs for this AD if requested using the
procedures found in 14 CFR 39.19. Send
information to Doug Rudolph, Aviation
Safety Engineer, General Aviation &
Rotorcraft Section, International Validation
Branch, FAA, 901 Locust, Room 301, Kansas
City, Missouri 64106; phone: (816) 329–4059;
fax: (816) 329–4090; email:
doug.rudolph@faa.gov. Before using any
approved AMOC on any airplane to which
the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking
a PI, your local FSDO.
(h) Related Information
(1) Refer to MCAI European Union
Aviation Safety Agency AD No. 2019–0231,
dated September 13, 2019, for related
information. You may examine the MCAI at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2020–0813.
(2) For service information related to this
AD, contact Pilatus Aircraft, Ltd., Customer
Support PC–12, CH–6371 Stans, Switzerland;
phone: +41 41 619 33 33; fax: +41 41 619 73
11; email: supportPC12@pilatus-aircraft.com;
website: https://www.pilatus-aircraft.com.
You may review this referenced service
information at the FAA, Airworthiness
Products Section, Operational Safety Branch,
901 Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference 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 the AD specifies otherwise.
(i) Pilatus Service Bulletin No: 27–026,
dated July 10, 2019.
(ii) [Reserved]
(3) For Pilatus Aircraft Ltd. service
information identified in this AD, contact
Pilatus Aircraft, Ltd., Customer Support PC–
12, CH–6371 Stans, Switzerland; phone: +41
41 619 33 33; fax: +41 41 619 73 11; email:
supportPC12@pilatus-aircraft.com; website:
https://www.pilatus-aircraft.com.
(4) You may view this service information
at FAA, Airworthiness Products Section,
Operational Safety Branch, 901 Locust,
Kansas City, Missouri 64106. For information
on the availability of this material at the
FAA, call (816) 329–4148.
(5) 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,
email: fedreg.legal@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on January 6, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–03476 Filed 2–22–21; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
21:28 Feb 22, 2021
Jkt 253001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0843; Product
Identifier 2020–NM–073–AD; Amendment
39–21420; AD 2021–03–17]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc., Model BD–700–1A10
airplanes. This AD was prompted by a
report of smoke and signs of an
overheating condition from the
emergency light battery (ELB) due to
excessive corrosion surrounding the
internal lead acid batteries, which
caused an electrical short circuit that
led to the smoke and overheating
condition. This AD requires an
inspection to determine the last
replacement date of the ELB, and
replacement if necessary. This AD also
requires the incorporation of a new
maintenance task into the existing
maintenance or inspection program. The
FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective March 30,
2021.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 30, 2021.
ADDRESSES: For service information
identified in this final rule, contact
Bombardier, Inc., 400 Coˆte-Vertu Road
West, Dorval, Que´bec H4S 1Y9, Canada;
telephone 514–855–5000; fax 514–855–
7401; email ac.yul@
aero.bombardier.com; internet https://
www.bombardier.com. You may view
this service information at the FAA,
Airworthiness Products Section,
Operational Safety 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–2020–0843.
SUMMARY:
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–
PO 00000
Frm 00045
Fmt 4700
Sfmt 4700
10747
0843; 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,
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:
Thomas Niczky, Aerospace Engineer,
Avionics and Electrical Systems
Section, FAA, New York ACO Branch,
1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 516–
228–7347; fax 516–794–5531; email 9avs-nyaco-cos@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian AD
CF–2020–07, dated March 17, 2020 (also
referred to as the Mandatory Continuing
Airworthiness Information, or the
MCAI), to correct an unsafe condition
for certain Bombardier, Inc., Model BD–
700–1A10 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–2020–0843.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Bombardier, Inc., Model
BD–700–1A10 airplanes. The NPRM
published in the Federal Register on
September 17, 2020 (85 FR 58010). The
NPRM was prompted by a report of
smoke and signs of an overheating
condition from the ELB due to excessive
corrosion surrounding the internal lead
acid batteries, which caused an
electrical short circuit that led to the
smoke and overheating condition. The
NPRM proposed to require an
inspection to determine the last
replacement date of the ELB, and
replacement if necessary. The NPRM
also proposed to require the
incorporation of a new maintenance
task into the existing maintenance or
inspection program. The FAA is issuing
this AD to address smoke and an
overheating condition of the ELB due to
corrosion, which could cause fire
onboard the airplane. See the MCAI for
additional background information.
Comments
The FAA 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 to that comment.
E:\FR\FM\23FER1.SGM
23FER1
]]>Agencies
[Federal Register Volume 86, Number 34 (Tuesday, February 23, 2021)]
[Rules and Regulations]
[Pages 10744-10747]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-03476]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0813; Product Identifier 2019-CE-040-AD; Amendment
39-21387; AD 2021-02-04]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Pilatus Aircraft Ltd. (Pilatus) Model PC-12/47E airplanes. This AD was
prompted by mandatory continuing airworthiness information (MCAI)
originated by an aviation authority of another country to identify and
correct an unsafe condition on an aviation product. The MCAI describes
the unsafe condition as
[[Page 10745]]
inboard flap fairings aft (IFFAs) having an incorrect shape, which may
result in chafing between the IFFA and the associated front inboard
tension rod. This AD requires an inspection of the IFFAs for the
correct shape and chafing between the IFFA and the associated front
inboard tension rod, with corrective action as necessary. This
condition could lead to failure of the inboard flap drive arm with
consequent asymmetric flap extension, resulting in reduced control of
the airplane. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective March 30, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 30,
2021.
ADDRESSES: For service information identified in this final rule,
contact Pilatus Aircraft, Ltd., Customer Support PC-12, CH-6371 Stans,
Switzerland; phone: +41 41 619 33 33; fax: +41 41 619 73 11; email:
aircraft.com">[email protected]aircraft.com; website: https://www.pilatus-
aircraft.com. You may review this referenced service information at the
FAA, Airworthiness Products Section, Operational Safety Branch, 901
Locust, Kansas City, Missouri 64106. For information on the
availability of this material at the FAA, call (816) 329-4148. It is
also available at https://www.regulations.gov by searching for and
locating Docket No. FAA-2020-0813.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2020-0813; 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
MCAI, 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: Doug Rudolph, Aviation Safety
Engineer, General Aviation & Rotorcraft Section, International
Validation Branch, FAA, 901 Locust, Room 301, Kansas City, Missouri
64106; phone: (816) 329-4059; fax: (816) 329-4090; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to all Pilatus Model PC-
12/47E airplanes. The NPRM published in the Federal Register on
September 16, 2020 (85 FR 57804). In the NPRM, the FAA proposed to
require an inspection of the IFFAs for the correct shape and chafing
between the IFFA and the associated front inboard tension rod, with
corrective action as necessary.
The NPRM was based on MCAI from the European Union Aviation Safety
Agency (EASA), which is the Technical Agent for the Member States of
the European Union. EASA issued AD No.: 2019-0231, dated September 13,
2019 (referred to after this as ``the MCAI''), to correct an unsafe
condition for Pilatus Model PC-12/47E airplanes. The MCAI states:
On the final assembly line of PC-12/47E aeroplanes, IFFAs were
detected having an incorrect shape. As a consequence, chafing
between the IFFA and the associated front inboard tension rod could
occur, may cause corrosion of the bare rod aluminium tube and reduce
aluminium thickness.
This condition, if not detected and corrected, could lead to
failure of the inboard flap drive arm with consequent asymmetric
flap extension, possibly resulting in reduced control of the
aeroplane.
To address this potential unsafe condition, Pilatus issued the
[service bulletin] SB to provide inspection and modification
instructions.
For the reason described above, this [EASA] AD requires a one-
time inspection of both IFFA and, depending on findings, a follow-on
inspection of the associated front inboard tension rod for chafing,
and modification or replacement of affected parts.
You may examine the MCAI at https://www.regulations.gov by
searching for and locating Docket No. FAA-2020-0813.
Discussion of Final Airworthiness Directive
Comments
The FAA received two comments from Pilatus. The following presents
the comments received on the NPRM and the FAA's response to each
comment.
Pilatus requested the FAA reduce the applicability of the proposed
AD from all Model PC-12/47E airplanes to Model PC-12/47E airplanes with
serial number (S/N) 1576 and higher. Pilatus stated that due to an
engineering change in 2014, the left-hand (LH) IFFA, part number (P/N)
557.52.12.223, and the right-hand (RH) IFFA, P/N 557.52.12.224,
introduced on airplanes with S/N 1576 and higher, have different
attachment hole positions and a maximum hole position difference of
more than 12mm. As a result, it is not physically possible to install
P/Ns 557.52.12.223 and 557.52.12.224 on airplanes with an S/N lower
than 1576.
The FAA partially agrees. The commenter is correct that the
affected IFFAs cannot be installed on Model PC-12/47E airplanes with an
S/N lower than 1576. The FAA has revised paragraph (f) of this AD to
limit the inspection of the IFFAs to airplanes with an S/N 1576 and
higher.
Pilatus acknowledged that tension rod P/N 527.52.12.135 can be
installed on all Model PC-12/47E airplanes but requested the FAA limit
the tension rod inspection for airplanes with an S/N lower than 1576 to
only those with maintenance records showing that the tension rod had
been installed.
The FAA partially agrees. The FAA has revised the tension rod
inspection to limit its scope for airplanes with an S/N lower than
1576. Because the tension rods are not life-limited parts, there is no
regulatory requirement for them to be serialized or for operators to
record or retain information about the part's traceability. Therefore,
operators would be unable to comply with, and the FAA would be unable
to enforce, the change requested by the commenter, as maintenance
records may not identify if a tension rod was removed from an airplane
with an S/N 1576 or higher. Instead, the FAA has changed the AD so that
the inspection of the tension rod is required for all airplanes with a
S/N 1576 or higher and for airplanes with a S/N 1001 through 1575 if
tension rod P/N 527.52.12.135 is installed.
Conclusion
The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for the changes described
previously, this AD is adopted as proposed in the NPRM. None of the
changes will increase the economic burden on any operator.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Pilatus PC-12 Service Bulletin No: 27-026, dated
July 10, 2019 (Pilatus SB No. 27-026). The service information
specifies procedures for inspecting and correcting chafing between the
left and right IFFAs and the associated front inboard tension rods.
This service information is reasonably available because the interested
parties have access to it through their normal
[[Page 10746]]
course of business or by the means identified in ADDRESSES.
Differences Between This AD and the MCAI
The MCAI only requires inspection of the tension rods if the IFFAs
are modified because they have been found to have the incorrect shape.
Due to the length of time between manufacture and the issuance of this
AD, operators could have installed an affected tension rod onto an
airplane that was not manufactured with the defective part. Therefore,
this AD requires inspection for chafing damage on the tension rods on
all Model PC-12/47E airplanes that have an affected tension rod
installed.
Costs of Compliance
The FAA estimates that this AD will affect 18 products of U.S.
registry. The FAA also estimates that it will take about 2.5 work-hours
per product to comply with the requirements of this AD. The average
labor rate is $85 per work-hour. Required parts will cost about $1,600
per product.
Based on these figures, the FAA estimates the cost of this AD on
U.S. operators will be $32,634 or $1,813 per product.
The FAA has included all costs in this cost estimate. According to
the manufacturer, however, all or some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
operators.
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
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.
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
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2021-02-04 Pilatus Aircraft Ltd.: Amendment 39-21387; Docket No.
FAA-2020-0813; Product Identifier 2019-CE-040-AD.
(a) Effective Date
This airworthiness directive (AD) is effective March 30, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Pilatus Aircraft Ltd. Model PC-12/47E
airplanes, all serial numbers (S/Ns), certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC) Code 2700: Flight
Controls.
(e) Reason
This AD was prompted by mandatory continuing airworthiness
information (MCAI) originated by an aviation authority of another
country to identify and correct an unsafe condition on an aviation
product. The MCAI describes the unsafe condition as inboard flap
fairings aft (IFFAs) having an incorrect shape. The FAA is issuing
this AD to prevent chafing between the IFFA and the front inboard
tension rod, and consequent corrosion of the bare rod aluminum tube
and reduced aluminum thickness. This condition, if not corrected,
could lead to failure of the inboard flap drive arm, asymmetric flap
extension, and reduced control of the airplane.
(f) Actions and Compliance
(1) For airplanes with a S/N 1576 and higher, unless already
done, within 100 hours time-in-service (TIS) after the effective
date of this AD or within 6 months after the effective date of this
AD, whichever occurs first, inspect the left-hand (LH) and right-
hand (RH) IFFAs for correct shape and clearance with the LH and RH
tension rods by following step 3.B.(1) and Figures 2 and 3 of the
Accomplishment Instructions--Aircraft in Pilatus PC-12 Service
Bulletin No: 27-026, dated July 10, 2019 (Pilatus SB 27-026).
(i) If the shape of the LH or RH IFFA is incorrect or if the
clearance between the IFFA and the tension rod is less than 5 mm
(0.2 inch), before further flight, modify the IFFA and inspect the
tension rods for chafing by following section 3.C. of the
Accomplishment Instructions--Aircraft in Pilatus SB 27-026.
(ii) If the shape of the LH and RH IFFAs is correct and the
clearance between the IFFA and the tension rod is at least 5 mm (0.2
inch), before further flight, inspect the front inboard LH and RH
tension rods for chafing by following step 3.C.(12)(a) of the
Accomplishment Instructions--Aircraft in Pilatus SB 27-026. If the
LH or RH tension rod has any chafing, before further flight, replace
the tension rod by following step 3.C.(12)(b) of the Accomplishment
Instructions--Aircraft in Pilatus SB 27-026.
(2) For airplanes with a S/N 1001 through S/N 1575, inclusive,
that have a tension rod part number (P/N) 527.52.12.135 installed,
unless already done, within 100 hours TIS after the effective date
of this AD or within 6 months after the effective date of this AD,
whichever occurs first, inspect the front inboard LH and RH tension
rods for chafing by following step 3.C.(12)(a) of the Accomplishment
Instructions--Aircraft in Pilatus SB 27-026. If the LH or RH tension
rod has any chafing, before further flight, replace the tension rod
by following step 3.C.(12)(b) of the Accomplishment Instructions--
Aircraft in Pilatus SB 27-026.
(3) For all Model PC-12/47E airplanes, as of the effective date
of this AD, do not install on any airplane an LH IFFA P/N
557.52.12.223, RH IFFA P/N 557.52.12.224, or tension rod P/N
527.52.12.135 unless the part has been inspected and all corrective
actions have been taken as required by this AD.
(g) Alternative Methods of Compliance (AMOCs)
[[Page 10747]]
The Manager, International Validation Branch, FAA, has the
authority to approve AMOCs for this AD if requested using the
procedures found in 14 CFR 39.19. Send information to Doug Rudolph,
Aviation Safety Engineer, General Aviation & Rotorcraft Section,
International Validation Branch, FAA, 901 Locust, Room 301, Kansas
City, Missouri 64106; phone: (816) 329-4059; fax: (816) 329-4090;
email: [email protected]. Before using any approved AMOC on any
airplane to which the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(h) Related Information
(1) Refer to MCAI European Union Aviation Safety Agency AD No.
2019-0231, dated September 13, 2019, for related information. You
may examine the MCAI at https://www.regulations.gov by searching for
and locating Docket No. FAA-2020-0813.
(2) For service information related to this AD, contact Pilatus
Aircraft, Ltd., Customer Support PC-12, CH-6371 Stans, Switzerland;
phone: +41 41 619 33 33; fax: +41 41 619 73 11; email:
aircraft.com">[email protected]aircraft.com; website: https://www.pilatus-
aircraft.com. You may review this referenced service information at
the FAA, Airworthiness Products Section, Operational Safety Branch,
901 Locust, Kansas City, Missouri 64106. For information on the
availability of this material at the FAA, call (816) 329-4148.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference 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 the AD specifies otherwise.
(i) Pilatus Service Bulletin No: 27-026, dated July 10, 2019.
(ii) [Reserved]
(3) For Pilatus Aircraft Ltd. service information identified in
this AD, contact Pilatus Aircraft, Ltd., Customer Support PC-12, CH-
6371 Stans, Switzerland; phone: +41 41 619 33 33; fax: +41 41 619 73
11; email: aircraft.com">[email protected]aircraft.com; website: https://
www.pilatus-aircraft.com.
(4) You may view this service information at FAA, Airworthiness
Products Section, Operational Safety Branch, 901 Locust, Kansas
City, Missouri 64106. For information on the availability of this
material at the FAA, call (816) 329-4148.
(5) 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, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on January 6, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-03476 Filed 2-22-21; 8:45 am]
BILLING CODE 4910-13-P
