[Federal Register Volume 85, Number 132 (Thursday, July 9, 2020)]
[Rules and Regulations]
[Pages 41180-41184]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-14779]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0575; Product Identifier 2020-NM-096-AD; Amendment
39-19924; AD 2020-12-15]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes.
This AD was prompted by a report that certain safety valves at the
left- and right-hand sides of the cabin pressure control system were
not installed correctly and that the trunnion nuts used to fasten the
V-band clamp were over torqued. This AD requires a measurement of the
trunnion nut torque of the V-band clamp, an inspection of the safety
valve and airplane bulkhead flange area for any cracking and
deformations, and corrective actions, if necessary. The FAA is issuing
this AD to address the unsafe condition on these products.
DATES: This AD becomes effective July 24, 2020.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of July 24,
2020.
The FAA must receive comments on this AD by August 24, 2020.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC, 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 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-
0575.
[[Page 41181]]
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-
0575; 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.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Darren Gassetto, Aerospace Engineer,
Mechanical Systems and Administrative Services Section, FAA, New York
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
telephone 516-228-7323; fax 516-794-5531; email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD CF-2020-16, dated May 15,
2020 (referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''), to correct an unsafe condition for
certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes.
You may examine the MCAI on the internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2020-0575.
This AD was prompted by a report that certain safety valves at the
left- and right-hand sides of the cabin pressure control system were
not installed correctly and that the trunnion nuts used to fasten the
V-band clamp were over torqued. The FAA is issuing this AD to address
incorrect installation of the safety valves and over-torqued trunnion
nuts, which could cause damage to the safety valve flange and could
result in pressure leakage or cabin depressurization at altitude. See
the MCAI for additional background information.
Related Service Information Under 1 CFR Part 51
Bombardier has issued Service Bulletin 700-21-5009, Revision 02,
dated March 31, 2020; and Service Bulletin 700-21-6009, Revision 02,
dated March 31, 2020. This service information describes procedures for
a measurement of the trunnion nut torque of the V-band clamp at the
left- and right-hand sides of the cabin pressure control system safety
valves, a general visual or magnification inspection of the safety
valve and airplane bulkhead flange area for any cracking and
deformation, and corrective actions. The corrective actions include
replacement of the safety valve and repair of cracks on the airplane
bulkhead flange. These documents are distinct since they apply to
different airplane models.
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 our 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 accomplishing the actions specified in the service
information described previously.
Explanation of Compliance Time
In most ADs, we adopt a compliance time relative to the AD's
effective date. In this case, however, TCCA has already issued
regulations that require operators to measure the trunnion nut torque
of the V-band clamp to address the identified unsafe condition by a
certain date. Per the safety assessment of the design approval holder
and TCCA, the initial measurement of the trunnion nut torque of the V-
band clamp must be completed before August 31, 2020. In addition, TCCA
also requires operators to replace certain safety valves by that date.
To provide for coordinated implementation of TCCA's regulations and
this AD, we are using the same compliance date in this AD.
Differences Between This AD and the MCAI
Canadian AD CF-2020-16, dated May 15, 2020, requires an inspection
of the bulkhead flange but does not provide a corrective action. This
AD includes a corrective action as specified in paragraphs (h)(1)(iii)
and (h)(2)(B)(iii) of this AD.
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 incorrectly installed safety valves and over-torqued trunnion
nuts could cause damage to the safety valve flange and could result in
pressure leakage or cabin depressurization at altitude. 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
This AD is a final rule that involves requirements affecting flight
safety, and the FAA did not precede it by notice and opportunity for
public comment. The FAA invites you to send any written relevant data,
views, or arguments about this AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2020-0575;
Product Identifier 2020-NM-096-AD'' at the beginning of your comments.
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this AD. The FAA will
consider all comments received by the closing date and may amend this
AD based on those comments.
The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact received about this AD.
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 17 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
[[Page 41182]]
Estimated Costs for Required Actions
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Cost per Cost on U.S.
Labor cost Parts cost product operators
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2 work-hours x $85 per hour = $170........................... $0 $170 $2,890
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The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any
required actions. The FAA has no way of determining the number of
aircraft that might need these on-condition actions:
Estimated Costs of On-Condition Actions *
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Cost per
Labor cost Parts cost product
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3 work-hours x $85 per hour = $255.... $5,070 $5,325
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* The table does not include costs for the corrective action for the
bulkhead flange. The FAA has received no definitive data for the cost
of this corrective action.
According to the manufacturer, some or all of the parts costs of
this AD may be covered under warranty, thereby reducing the cost impact
on affected individuals. The FAA does not control warranty coverage for
affected individuals. As a result, the FAA has included all known costs
in our cost estimate.
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 (AD):
2020-12-15 Bombardier, Inc.: Amendment 39-19924; Docket No. FAA-
2020-0575; Product Identifier 2020-NM-096-AD.
(a) Effective Date
This AD becomes effective July 24, 2020.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc., Model BD-700-1A10 and BD-
700-1A11 airplanes, certificated in any category, serial numbers
9810 through 9838 inclusive, 9840 through 9842 inclusive, 9844
through 9846 inclusive, 9854 and 9855.
(d) Subject
Air Transport Association (ATA) of America Code 36, Pneumatic.
(e) Reason
This AD was prompted by a report that certain safety valves at
the left- and right-hand sides of the cabin pressure control system
were not installed correctly and that the trunnion nuts used to
fasten the V-band clamp were over torqued. The FAA is issuing this
AD to address incorrect installation of the safety valves and over-
torqued trunnion nuts, which could cause damage to the safety valve
flange and could result in pressure leakage or cabin
depressurization at altitude.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Measurement
Before August 31, 2020, measure the trunnion nut torque of the
V-band clamps at the left-and right-hand sides of the cabin pressure
control system safety valves, in accordance with paragraphs 2.B.(1)
and 2.B.(2) of the Accomplishment Instructions of the applicable
service information specified in figure 1 to paragraphs (g) and (h)
of this AD.
[[Page 41183]]
[GRAPHIC] [TIFF OMITTED] TR09JY20.019
(h) Inspection and Corrective Actions
Based on the torque measurement required by paragraph (g) of
this AD, do the applicable actions specified in paragraph (h)(1) or
(2) of this AD.
(1) For safety valves with a V-band clamp trunnion nut torque of
less than 80 lbf-in: Before further flight, do a general visual
inspection for any cracking and deformation, in accordance with
paragraph 2.B.(3)(a) of the Accomplishment Instructions of the
applicable service information specified in figure 1 to paragraphs
(g) and (h) of this AD.
(i) If no cracking and deformation is found on the safety valve
and airplane bulkhead flange: Before further flight, re-torque the
V-band clamp trunnion nut, in accordance with paragraph 2.B.(3)(b)
of the Accomplishment Instructions of the applicable service
information specified in figure 1 to paragraphs (g) and (h) of this
AD.
(ii) If any cracking or deformation is found on the safety
valve: Before further flight, replace the safety valve, in
accordance with paragraph 2.C. of the Accomplishment Instructions of
the applicable service information specified in figure 1 to
paragraphs (g) and (h) of this AD.
(iii) If any cracking or deformation is found on the airplane
bulkhead flange: Before further flight, repair 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.
(2) For safety valves with a V-band clamp trunnion nut torque of
80 lbf-in or higher: Before further flight, do a magnification
inspection for any cracking and deformation of the safety valve and
airplane bulkhead flange area, in accordance with paragraphs
2.B.(4)(a) and 2.B.(4)(b) of the Accomplishment Instructions of the
applicable service information specified in figure 1 to paragraphs
(g) and (h) of this AD.
(i) If no cracking and deformation is found on the safety valve
and airplane bulkhead flange, do the actions specified in paragraphs
(h)(2)(i)(A) and (B) of this AD.
(A) Before further flight, re-install the safety valve and
torque the V-band clamp trunnion nut, in accordance with paragraph
2.B.(4)(c) of the Accomplishment Instructions of the applicable
service information specified in figure 1 to paragraphs (g) and (h)
of this AD.
(B) Before August 31, 2021, replace the safety valve, in
accordance with paragraph 2.C. of the Accomplishment Instructions of
the applicable service information specified in figure 1 to
paragraphs (g) and (h) of this AD.
(ii) If any cracking or deformation is found on the safety
valve: Before further flight, replace the safety valve, in
accordance with paragraph 2.C. of the Accomplishment Instructions of
the applicable service information specified in figure 1 to
paragraphs (g) and (h) of this AD.
(iii) If any cracking or deformation is found on the airplane
bulkhead flange: Before further flight, repair using a method
approved by the Manager, New York ACO Branch, FAA; or TCCA; or
Bombardier, Inc.'s TCCA DAO. If approved by the DAO, the approval
must include the DAO-authorized signature.
(i) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using the following service
information.
(1) Bombardier Service Bulletin 700-21-5009, dated January 23,
2020; and Bombardier Service Bulletin 700-21-5009, Revision 01,
dated March 19, 2020.
(2) Bombardier Service Bulletin 700-21-6009, dated January 23,
2020; and Bombardier Service Bulletin 700-21-6009, Revision 01,
dated March 19, 2020.
(j) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York ACO Branch, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your request to your principal
inspector or local Flight Standards District Office, as appropriate.
If sending information directly to the manager of the certification
office, send it to ATTN: Program Manager, Continuing Operational
Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 516-228-7300; fax 516-794-5531. Before
using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
local flight standards district office/certificate holding district
office.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain instructions from a manufacturer, the instructions must be
accomplished using a method approved by the Manager, New York ACO
Branch, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO. If approved by
the DAO, the approval must include the DAO-authorized signature.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian AD CF-2020-16, dated May 15, 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-2020-0575.
(2) For more information about this AD, contact Darren Gassetto,
Aerospace Engineer, Mechanical Systems and Administrative Services
Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 516-228-7323; fax 516-794-5531; email
[email protected].
(l) 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) Bombardier Service Bulletin 700-21-5009, Revision 02, dated
March 31, 2020.
(ii) Bombardier Service Bulletin 700-21-6009, Revision 02, dated
March 31, 2020.
(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.
(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.
[[Page 41184]]
Issued on June 18, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020-14779 Filed 7-8-20; 8:45 am]
BILLING CODE 4910-13-P