Airworthiness Directives; Bombardier, Inc., Airplanes, 26367-26370 [2021-10259]
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Federal Register / Vol. 86, No. 92 / Friday, May 14, 2021 / Rules and Regulations
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
■ a. Removing Airworthiness Directive
(AD) 2015–25–04, Amendment 39–
18342 (80 FR 76381, December 9, 2015);
and
■ b. Adding the following new AD:
■
2021–10–24 Leonardo S.p.a (Type
Certificate Previously Held by Agusta
S.p.A.): Amendment 39–21557; Docket
No. FAA–2021–0127; Project Identifier
MCAI–2020–00829–R.
(a) Effective Date
This airworthiness directive (AD) is
effective June 18, 2021.
(b) Affected ADs
This AD replaces AD 2015–25–04,
Amendment 39–18342 (80 FR 76381,
December 9, 2015).
This AD applies to Leonardo S.p.a. (Type
Certificate previously held by Agusta S.p.A.)
Model A109A and A109A II helicopters,
certificated in any category, with a slider
assembly pitch control (slider) part number
(P/N) 109–0130–11–7 installed, except those
sliders marked with an ‘‘R’’ after the serial
number.
(d) Subject
Joint Aircraft Service Component (JASC)
Code: 6720, Tail Rotor Control System.
(e) Unsafe Condition
This AD defines the unsafe condition as
play on a slider. This condition could result
in loss of tail rotor pitch control and
consequently loss of helicopter control.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Required Actions
(1) Within 25 hours time-in-service (TIS)
after the effective date of this AD, and
thereafter at intervals not to exceed 25 hours
TIS, inspect the slider for play. If there is
play greater than 2.3 millimeters (0.09 inch),
before further flight, replace the slider with
a slider P/N 109–0130–11–7 with suffix ‘‘R’’
marked after the serial number.
(2) Within 800 hours TIS after the effective
date of this AD, if not previously required per
paragraph (g)(1) of this AD, replace slider
P/N 109–0130–11–7 with slider P/N 109–
0130–11–7 with suffix ‘‘R’’ marked after the
serial number.
(3) Installing slider P/N 109–0130–11–7
with suffix ‘‘R’’ marked after the serial
number is a terminating action for the
repetitive inspections required by paragraph
(g)(1) of this AD.
(4) As of the effective date of this AD, do
not install slider P/N 109–0130–11–7 on any
helicopter unless the slider is marked with
suffix ‘‘R’’ after the serial number.
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(h) Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(1) 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. 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 International Validation
Branch, send it to the attention of the person
identified in paragraph (i)(1) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
Federal Aviation Administration
(i) Related Information
(c) Applicability
26367
(1) For more information about this AD,
contact Matthew Fuller, AD Program
Manager, Operational Safety Branch,
Airworthiness Products Section, General
Aviation & Rotorcraft Unit, telephone (817)
222–5110; email matthew.fuller@faa.gov.
(2) Leonardo Helicopters Alert Service
Bulletin No. 109–149, Revision A, dated May
18, 2020, which is not incorporated by
reference, contains additional information
about the subject of this AD. For service
information identified in this AD, contact
Leonardo S.p.a. Helicopters, Emanuele
Bufano, Head of Airworthiness, Viale
G.Agusta 520, 21017 C.Costa di Samarate
(Va) Italy; telephone +39–0331–225074; fax
+39–0331–229046; or at https://
www.leonardocompany.com/en/home. You
may view this referenced service information
at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(3) The subject of this AD is addressed in
European Union Aviation Safety Agency
(EASA) AD 2020–0142, dated June 25, 2020.
You may view the EASA AD at https://
www.regulations.gov in Docket No. FAA–
2021–0127.
Issued on May 6, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–10191 Filed 5–13–21; 8:45 am]
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14 CFR Part 39
[Docket No. FAA–2021–0342; Project
Identifier MCAI–2020–01547–T; Amendment
39–21530; AD 2021–09–16]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc., Model BD–100–1A10
airplanes. This AD was prompted by a
report of a number of low altitude
engine surge incidents during takeoff.
This AD requires revising the existing
airplane flight manual and applicable
corresponding operational procedures to
provide the flightcrew with procedures
to require the engine bleeds to be ‘‘ON’’
during takeoff. The FAA is issuing this
AD to address the unsafe condition on
these products.
DATES: This AD becomes effective June
1, 2021.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 1, 2021.
The FAA must receive comments on
this AD by June 28, 2021.
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 final rule, contact Bombardier, Inc.,
200 Coˆte Vertu Road West, Dorval,
Que´bec H4S 2A3, Canada; North
America toll-free telephone 1–866–538–
1247 or direct-dial telephone 1–514–
855–2999; email ac.yul@
aero.bombardier.com; internet https://
www.bombardier.com. You may view
this referenced service information at
the FAA, Airworthiness Products
SUMMARY:
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Federal Register / Vol. 86, No. 92 / Friday, May 14, 2021 / Rules and Regulations
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–2021–0342.
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–2021–
0342; or in person at the Docket
Operations office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this AD, any comments
received, and other information. The
street address for the Docket Operations
office is listed above.
FOR FURTHER INFORMATION CONTACT:
Jiwan Karunatilake, Aerospace
Engineer, Airframe and Propulsion
Section, FAA, New York ACO Branch,
1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 516–
228–7300; fax 516–794–5531; email 9avs-nyaco-cos@faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
Transport Canada Civil Aviation
(TCCA) which is the aviation authority
for Canada, has issued TCCA AD CF–
2020–47, dated November 18, 2020
(TCCA AD CF–2020–47) (referred to
after this as the Mandatory Continuing
Airworthiness Information, or the
MCAI), to correct an unsafe condition
for certain Bombardier, Inc., Model BD–
100–1A10 airplanes. You may examine
the MCAI on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0342.
This AD was prompted by a report of
a number of low altitude engine surge
incidents during takeoff. Under certain
environmental conditions (e.g.,
temperature/thermal inversion), the
existing engine control features can lead
to engine surge. The FAA is issuing this
AD to address engine surges during
takeoff, which can result in significant
loss of engine thrust or even engine
shutdown and can occur on both
engines at the same time. See the MCAI
for additional background information.
Related Service Information Under 1
CFR Part 51
Bombardier has issued Section 02–04,
‘‘Systems Limitations,’’ of Chapter 02,
‘‘LIMITATIONS’’; and Section 04–03 of
Chapter 04, ‘‘NORMAL PROCEDURES’’;
of Challenger 300 Airplane Flight
Manual (Imperial Version), Publication
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No. CSP 100–1, Revision 63, dated April
1, 2021. Section 02–04, ‘‘Systems
Limitations,’’ of Chapter 02,
‘‘LIMITATIONS’’ provides a procedure
for ‘‘Air Conditioning and
Pressurization’’; and Section 04–03 of
Chapter 04, ‘‘NORMAL PROCEDURES’’
provides a procedure for ‘‘Taxi and
Before Takeoff.’’ The procedures require
the left and right engine bleeds to be
‘‘ON’’ during takeoff. (For obtaining the
procedures for Bombardier Challenger
300 Airplane Flight Manual (Imperial
Version), Publication No. CSP 100–1,
use Document Identification No. CH 300
AFM–I.) This service information is
reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section.
FAA’s Determination
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to the
FAA’s bilateral agreement with the State
of Design Authority, the FAA has been
notified of the unsafe condition
described in the MCAI and service
information referenced above. The FAA
is issuing this AD because the FAA
evaluated all pertinent information and
determined the unsafe condition exists
and is likely to exist or develop on other
products of the same type design.
Requirements of This AD
This AD requires revising the existing
airplane flight manual and applicable
corresponding operational procedures to
provide the flightcrew with procedures
that require the engine bleeds to be
‘‘ON’’ during takeoff.
Explanation of Incorporating
Information Specified in an AFM
Revision
This AD requires including the
information that is provided in the
referenced AFM revision in paragraph
(g) of this AD. The language in
paragraph (g) of this AD is designed to
allow incorporating the specific
information, regardless of the revision
level of the AFM in use, provided the
language is identical to the referenced
AFM revisions specified in paragraph
(g) of this AD. The language in a later
revision of the Challenger 300 Airplane
Flight Manual, Publication No. CSP
100–1 that is the same as the language
in Challenger 300 Airplane Flight
Manual, Publication No. CSP 100–1,
Revision 63, dated April 1, 2021, may be
incorporated.
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FAA’s Justification and Determination
of the Effective Date
An unsafe condition exists that
requires the immediate adoption of this
AD without providing an opportunity
for public comments prior to adoption.
The FAA has found that the risk to the
flying public justifies waiving notice
and comment prior to adoption of this
rule because engine surges during
takeoff can result in significant loss of
engine thrust or even engine shutdown
and can occur on both engines at the
same time. In addition, the compliance
time for the required action is shorter
than the time necessary for the public to
comment and for publication of the final
rule. Therefore, the FAA finds good
cause that notice and opportunity for
prior public comment are impracticable.
In addition, for the reasons stated above,
the FAA finds that good cause exists for
making this amendment effective in less
than 30 days.
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2021–0342; Project Identifier MCAI–
2020–01547–T’’ at the beginning of your
comments. The most helpful comments
reference a specific portion of the final
rule, explain the reason for any
recommended change, and include
supporting data. The FAA will consider
all comments received by the closing
date and may amend this final rule
because of those comments.
Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
agency will also post a report
summarizing each substantive verbal
contact received about this final rule.
Confidential Business Information
CBI is commercial or financial
information that is both customarily and
actually treated as private by its owner.
Under the Freedom of Information Act
(FOIA) (5 U.S.C. 552), CBI is exempt
from public disclosure. If your
comments responsive to this AD contain
commercial or financial information
that is customarily treated as private,
that you actually treat as private, and
that is relevant or responsive to this AD,
it is important that you clearly designate
the submitted comments as CBI. Please
mark each page of your submission
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Federal Register / Vol. 86, No. 92 / Friday, May 14, 2021 / Rules and Regulations
containing CBI as ‘‘PROPIN.’’ The FAA
will treat such marked submissions as
confidential under the FOIA, and they
will not be placed in the public docket
of this AD. Submissions containing CBI
should be sent to Jiwan Karunatilake,
Aerospace Engineer, Airframe and
Propulsion Section, FAA, New York
ACO Branch, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590;
telephone 516–228–7300; fax 516–794–
5531; email 9-avs-nyaco-cos@faa.gov.
Any commentary that the FAA receives
which is not specifically designated as
CBI will be placed in the public docket
for this rulemaking.
Interim Action
The FAA considers this AD interim
action. The engine manufacturer is in
the process of developing new engine
control software to address the problem
of low altitude engine surges occurring
under certain environmental conditions.
Once this software is developed,
approved, and available, the FAA might
consider additional rulemaking.
Regulatory Flexibility Act (RFA)
The requirements of the RFA do not
apply when an agency finds good cause
pursuant to 5 U.S.C. 553 to adopt a rule
without prior notice and comment.
Because the FAA has determined that it
has good cause to adopt this rule
without notice and comment, RFA
analysis is not required.
Costs of Compliance
The FAA estimates that this AD
affects 356 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
1 work-hour × $85 per hour = $85 ..............................................................................................
$0
$85
$30,260
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.
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Regulatory Findings
The FAA 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,
and
(2) Will not affect intrastate aviation
in Alaska.
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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:
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2021–09–16 Bombardier, Inc.: Amendment
39–21530; Docket No. FAA–2021–0342;
Project Identifier MCAI–2020–01547–T.
(a) Effective Date
This airworthiness directive (AD) becomes
effective June 1, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc.,
Model BD–100–1A10 airplanes, certificated
in any category, serial numbers 20003
through 20457 inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 36, Pneumatic; 73, Engine
Fuel and Control.
(e) Reason
This AD was prompted by a report of a
number of low altitude engine surge
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Revision of the Airplane Flight Manual
(AFM)
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
incidents during takeoff. The FAA is issuing
this AD to address engine surges during
takeoff, which can result in significant loss
of engine thrust or even engine shutdown
and can occur on both engines at the same
time.
Within 60 days after the effective date of
this AD: Revise the existing AFM and
applicable corresponding operational
procedures to include the information in the
‘‘Air Conditioning and Pressurization’’
procedure in Section 02–04, ‘‘Systems
Limitations,’’ of Chapter 02,
‘‘LIMITATIONS’’; and the ‘‘Taxi and Before
Takeoff’’ procedure in Section 04–03 of
Chapter 04, ‘‘NORMAL PROCEDURES’’; of
the Bombardier Challenger 300 Airplane
Flight Manual (Imperial Version), Publication
No. CSP 100–1, Revision 63, dated April 1,
2021.
Note 1 to paragraph (g): For obtaining the
procedures for Bombardier Challenger 300
Airplane Flight Manual (Imperial Version),
Publication No. CSP 100–1, use Document
Identification No. CH 300
AFM–I.
(h) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using the
information in Section 02–04, ‘‘Systems
Limitations,’’ of Chapter 02,
‘‘LIMITATIONS’’; and Section 04–03 of
Chapter 04, ‘‘NORMAL PROCEDURES’’; of
any airplane flight manual specified in
paragraphs (h)(1) through (3) of this AD.
(1) Challenger 300 Airplane Flight Manual
(Imperial Version), Publication No. CSP 100–
1, Revision 60, dated July 1, 2020.
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Federal Register / Vol. 86, No. 92 / Friday, May 14, 2021 / Rules and Regulations
Note 2 to paragraph (h)(1): For obtaining
the procedures for Bombardier Challenger
300 Airplane Flight Manual (Imperial
Version), Publication No. CSP 100–1, use
Document Identification No. CH 300
AFM–I.
(2) Challenger 300 Airplane Flight Manual
(Imperial Version), Publication No. CSP 100–
1, Revision 61, dated September 25, 2020.
(3) Challenger 300 Airplane Flight Manual
(Imperial Version), Publication No. CSP 100–
1, Revision 62, dated December 22, 2020.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York ACO
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your responsible Flight Standards
Office, as appropriate. If sending information
directly to the manager of the certification
office, send it to ATTN: Program Manager,
Continuing Operational Safety, FAA, New
York ACO Branch, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone
516–228–7300; fax 516–794–5531. Before
using any approved AMOC, notify your
appropriate principal inspector, or lacking a
principal inspector, the manager of the
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, 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.
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(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) TCCA AD
CF–2020–47, dated November 18, 2020, 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–2021–0342.
(2) For more information about this AD,
contact Jiwan Karunatilake, Aerospace
Engineer, Airframe and Propulsion Section,
FAA, New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590;
telephone 516–228–7300; 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 (k)(3) and (4) of this AD.
(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.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Section 02–04, ‘‘Systems Limitations,’’
of Chapter 02, ‘‘LIMITATIONS,’’ of the
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Bombardier Challenger 300 Airplane Flight
Manual (Imperial Version), Publication No.
CSP 100–1, Revision 63, dated April 1, 2021.
(ii) Section 04–03 of Chapter 04,
‘‘NORMAL PROCEDURES,’’ of the
Bombardier Challenger 300 Airplane Flight
Manual (Imperial Version), Publication No.
CSP 100–1, Revision 63, dated April 1, 2021.
(3) For service information identified in
this AD, contact Bombardier, Inc., 200 Coˆte
Vertu Road West, Dorval, Que´bec H4S 2A3,
Canada; North America toll-free telephone 1–
866–538–1247 or direct-dial telephone 1–
514–855–2999; email ac.yul@
aero.bombardier.com; internet https://
www.bombardier.com.
Note 2 to paragraph (j)(3): For obtaining
the procedures for Bombardier Challenger
300 Airplane Flight Manual (Imperial
Version), Publication No. CSP 100–1, use
Document Identification No. CH 300 AFM–
I.
(4) 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.
(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/ibrlocations.html.
Issued on April 23, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–10259 Filed 5–11–21; 4:15 pm]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0341; Project
Identifier AD–2021–00325–T; Amendment
39–21529; AD 2021–09–15]
RIN 2120–AA64
Airworthiness Directives; Lockheed
Martin Corporation/Lockheed Martin
Aeronautics Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
Lockheed Martin Corporation/Lockheed
Martin Aeronautics Company Model
382, 382B, 382E, 382F, and 382G
airplanes, type certificated in any
category; and Model C–130A, C–130B,
C–130BL, C–130E, C–130H, C–130H–30,
SUMMARY:
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C–130J, C–130J–30, EC–130Q, HC–
130H, KC–130H, NC–130B, NC–130,
and WC–130H airplanes, type
certificated in the restricted or amateur
category. This AD was prompted by a
crack found on the web attachment
flange of the center wing upper forward
corner fitting. This AD requires an eddy
current surface scan for cracks of the
center wing upper and lower forward
corner fittings and fasteners, a torque
check of the left and right outer-wingto-center-wing front-beam-web-jointsplice-angle fasteners, and repair,
retorqueing, or replacement if necessary.
The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective June 1, 2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of June 1, 2021.
The FAA must receive comments on
this AD by June 28, 2021.
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 final rule, contact Lockheed Martin
Corporation/Lockheed Martin
Aeronautics Company, Customer
Support Center, Dept. 3E1M, Zone 0591,
86 S Cobb Drive, Marietta, GA 30063;
telephone 770–494–9131; email
hercules.support@lmco.com; internet
https://www.lockheedmartin.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 at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0341.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0341; or in person at Docket
Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
E:\FR\FM\14MYR1.SGM
14MYR1
]]>Agencies
[Federal Register Volume 86, Number 92 (Friday, May 14, 2021)]
[Rules and Regulations]
[Pages 26367-26370]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-10259]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0342; Project Identifier MCAI-2020-01547-T;
Amendment 39-21530; AD 2021-09-16]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was
prompted by a report of a number of low altitude engine surge incidents
during takeoff. This AD requires revising the existing airplane flight
manual and applicable corresponding operational procedures to provide
the flightcrew with procedures to require the engine bleeds to be
``ON'' during takeoff. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD becomes effective June 1, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 1, 2021.
The FAA must receive comments on this AD by June 28, 2021.
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 final rule, contact
Bombardier, Inc., 200 C[ocirc]te Vertu Road West, Dorval, Qu[eacute]bec
H4S 2A3, Canada; North America toll-free telephone 1-866-538-1247 or
direct-dial telephone 1-514-855-2999; email [email protected];
internet https://www.bombardier.com. You may view this referenced
service information at the FAA, Airworthiness Products
[[Page 26368]]
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-2021-
0342.
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-2021-
0342; or in person at the Docket Operations office between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, any comments received, and other information. The
street address for the Docket Operations office is listed above.
FOR FURTHER INFORMATION CONTACT: Jiwan Karunatilake, Aerospace
Engineer, Airframe and Propulsion Section, FAA, New York ACO Branch,
1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-
7300; fax 516-794-5531; email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada Civil Aviation (TCCA) which is the aviation
authority for Canada, has issued TCCA AD CF-2020-47, dated November 18,
2020 (TCCA AD CF-2020-47) (referred to after this as the Mandatory
Continuing Airworthiness Information, or the MCAI), to correct an
unsafe condition for certain Bombardier, Inc., Model BD-100-1A10
airplanes. You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0342.
This AD was prompted by a report of a number of low altitude engine
surge incidents during takeoff. Under certain environmental conditions
(e.g., temperature/thermal inversion), the existing engine control
features can lead to engine surge. The FAA is issuing this AD to
address engine surges during takeoff, which can result in significant
loss of engine thrust or even engine shutdown and can occur on both
engines at the same time. See the MCAI for additional background
information.
Related Service Information Under 1 CFR Part 51
Bombardier has issued Section 02-04, ``Systems Limitations,'' of
Chapter 02, ``LIMITATIONS''; and Section 04-03 of Chapter 04, ``NORMAL
PROCEDURES''; of Challenger 300 Airplane Flight Manual (Imperial
Version), Publication No. CSP 100-1, Revision 63, dated April 1, 2021.
Section 02-04, ``Systems Limitations,'' of Chapter 02, ``LIMITATIONS''
provides a procedure for ``Air Conditioning and Pressurization''; and
Section 04-03 of Chapter 04, ``NORMAL PROCEDURES'' provides a procedure
for ``Taxi and Before Takeoff.'' The procedures require the left and
right engine bleeds to be ``ON'' during takeoff. (For obtaining the
procedures for Bombardier Challenger 300 Airplane Flight Manual
(Imperial Version), Publication No. CSP 100-1, use Document
Identification No. CH 300 AFM-I.) This service information is
reasonably available because the interested parties have access to it
through their normal course of business or by the means identified in
the ADDRESSES section.
FAA's Determination
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to the FAA's bilateral agreement with the State of Design Authority,
the FAA has been notified of the unsafe condition described in the MCAI
and service information referenced above. The FAA is issuing this AD
because the FAA evaluated all pertinent information and determined the
unsafe condition exists and is likely to exist or develop on other
products of the same type design.
Requirements of This AD
This AD requires revising the existing airplane flight manual and
applicable corresponding operational procedures to provide the
flightcrew with procedures that require the engine bleeds to be ``ON''
during takeoff.
Explanation of Incorporating Information Specified in an AFM Revision
This AD requires including the information that is provided in the
referenced AFM revision in paragraph (g) of this AD. The language in
paragraph (g) of this AD is designed to allow incorporating the
specific information, regardless of the revision level of the AFM in
use, provided the language is identical to the referenced AFM revisions
specified in paragraph (g) of this AD. The language in a later revision
of the Challenger 300 Airplane Flight Manual, Publication No. CSP 100-1
that is the same as the language in Challenger 300 Airplane Flight
Manual, Publication No. CSP 100-1, Revision 63, dated April 1, 2021,
may be incorporated.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies waiving notice and comment prior to adoption of this rule
because engine surges during takeoff can result in significant loss of
engine thrust or even engine shutdown and can occur on both engines at
the same time. In addition, the compliance time for the required action
is shorter than the time necessary for the public to comment and for
publication of the final rule. Therefore, the FAA finds good cause that
notice and opportunity for prior public comment are impracticable. In
addition, for the reasons stated above, the FAA finds that good cause
exists for making this amendment effective in less than 30 days.
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
ADDRESSES. Include ``Docket No. FAA-2021-0342; Project Identifier MCAI-
2020-01547-T'' at the beginning of your comments. The most helpful
comments reference a specific portion of the final rule, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this final rule because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this final rule.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this AD contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this AD, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission
[[Page 26369]]
containing CBI as ``PROPIN.'' The FAA will treat such marked
submissions as confidential under the FOIA, and they will not be placed
in the public docket of this AD. Submissions containing CBI should be
sent to Jiwan Karunatilake, Aerospace Engineer, Airframe and Propulsion
Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 516-228-7300; fax 516-794-5531; email [email protected]. Any commentary that the FAA receives which is
not specifically designated as CBI will be placed in the public docket
for this rulemaking.
Interim Action
The FAA considers this AD interim action. The engine manufacturer
is in the process of developing new engine control software to address
the problem of low altitude engine surges occurring under certain
environmental conditions. Once this software is developed, approved,
and available, the FAA might consider additional rulemaking.
Regulatory Flexibility Act (RFA)
The requirements of the RFA do not apply when an agency finds good
cause pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and
comment. Because the FAA has determined that it has good cause to adopt
this rule without notice and comment, RFA analysis is not required.
Costs of Compliance
The FAA estimates that this AD affects 356 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $85 per hour = $85............................. $0 $85 $30,260
----------------------------------------------------------------------------------------------------------------
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 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, and
(2) Will not affect intrastate aviation in Alaska.
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
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:
2021-09-16 Bombardier, Inc.: Amendment 39-21530; Docket No. FAA-
2021-0342; Project Identifier MCAI-2020-01547-T.
(a) Effective Date
This airworthiness directive (AD) becomes effective June 1,
2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc., Model BD-100-1A10
airplanes, certificated in any category, serial numbers 20003
through 20457 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 36, Pneumatic;
73, Engine Fuel and Control.
(e) Reason
This AD was prompted by a report of a number of low altitude
engine surge incidents during takeoff. The FAA is issuing this AD to
address engine surges during takeoff, which can result in
significant loss of engine thrust or even engine shutdown and can
occur on both engines at the same time.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Revision of the Airplane Flight Manual (AFM)
Within 60 days after the effective date of this AD: Revise the
existing AFM and applicable corresponding operational procedures to
include the information in the ``Air Conditioning and
Pressurization'' procedure in Section 02-04, ``Systems
Limitations,'' of Chapter 02, ``LIMITATIONS''; and the ``Taxi and
Before Takeoff'' procedure in Section 04-03 of Chapter 04, ``NORMAL
PROCEDURES''; of the Bombardier Challenger 300 Airplane Flight
Manual (Imperial Version), Publication No. CSP 100-1, Revision 63,
dated April 1, 2021.
Note 1 to paragraph (g): For obtaining the procedures for
Bombardier Challenger 300 Airplane Flight Manual (Imperial Version),
Publication No. CSP 100-1, use Document Identification No. CH 300
AFM-I.
(h) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using the information in Section 02-04,
``Systems Limitations,'' of Chapter 02, ``LIMITATIONS''; and Section
04-03 of Chapter 04, ``NORMAL PROCEDURES''; of any airplane flight
manual specified in paragraphs (h)(1) through (3) of this AD.
(1) Challenger 300 Airplane Flight Manual (Imperial Version),
Publication No. CSP 100-1, Revision 60, dated July 1, 2020.
[[Page 26370]]
Note 2 to paragraph (h)(1): For obtaining the procedures for
Bombardier Challenger 300 Airplane Flight Manual (Imperial Version),
Publication No. CSP 100-1, use Document Identification No. CH 300
AFM-I.
(2) Challenger 300 Airplane Flight Manual (Imperial Version),
Publication No. CSP 100-1, Revision 61, dated September 25, 2020.
(3) Challenger 300 Airplane Flight Manual (Imperial Version),
Publication No. CSP 100-1, Revision 62, dated December 22, 2020.
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York ACO Branch, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your request to your responsible
Flight Standards Office, as appropriate. If sending information
directly to the manager of the certification office, send it to
ATTN: Program Manager, Continuing Operational Safety, FAA, New York
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
telephone 516-228-7300; fax 516-794-5531. Before using any approved
AMOC, notify your appropriate principal inspector, or lacking a
principal inspector, the manager of the 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, 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.
(j) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) TCCA AD CF-2020-47, dated November 18, 2020, 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-2021-0342.
(2) For more information about this AD, contact Jiwan
Karunatilake, Aerospace Engineer, Airframe and Propulsion Section,
FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone 516-228-7300; fax 516-794-5531; email [email protected].
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (k)(3) and (4) of this AD.
(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.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Section 02-04, ``Systems Limitations,'' of Chapter 02,
``LIMITATIONS,'' of the Bombardier Challenger 300 Airplane Flight
Manual (Imperial Version), Publication No. CSP 100-1, Revision 63,
dated April 1, 2021.
(ii) Section 04-03 of Chapter 04, ``NORMAL PROCEDURES,'' of the
Bombardier Challenger 300 Airplane Flight Manual (Imperial Version),
Publication No. CSP 100-1, Revision 63, dated April 1, 2021.
(3) For service information identified in this AD, contact
Bombardier, Inc., 200 C[ocirc]te Vertu Road West, Dorval,
Qu[eacute]bec H4S 2A3, Canada; North America toll-free telephone 1-
866-538-1247 or direct-dial telephone 1-514-855-2999; email
[email protected]; internet https://www.bombardier.com.
Note 2 to paragraph (j)(3): For obtaining the procedures for
Bombardier Challenger 300 Airplane Flight Manual (Imperial Version),
Publication No. CSP 100-1, use Document Identification No. CH 300
AFM-I.
(4) 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.
(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 April 23, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-10259 Filed 5-11-21; 4:15 pm]
BILLING CODE 4910-13-P
