[Federal Register Volume 84, Number 241 (Monday, December 16, 2019)]
[Proposed Rules]
[Pages 68370-68374]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-25719]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0876; Product Identifier 2019-NM-070-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11
airplanes. This proposed AD was prompted by a report that cracking was
discovered in a channel within a structural support member for the
rudder quadrant, rudder feel unit assembly, and environmental control
system due to fatigue. This proposed AD would require repetitive
inspections of the rudder quadrant box assembly for any cracking, and
modification of the rudder quadrant box assembly. The FAA is proposing
this AD to address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by January 30,
2020.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact
Bombardier, Inc.,
[[Page 68371]]
400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, Canada;
telephone 514-855-5000; fax 514-855-7401; email
[email protected]; internet https://www.bombardier.com. You
may view this service information at the FAA, Transport Standards
Branch, 2200 South 216th St., Des Moines, WA. For information on the
availability of this material at the FAA, call 206-231-3195.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0876; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations is listed above.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer,
Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7330;
fax 516-794-5531; email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2019-0876;
Product Identifier 2019-NM-070-AD'' at the beginning of your comments.
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this NPRM. The FAA will
consider all comments received by the closing date and may amend this
NPRM because of 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 NPRM.
Discussion
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2019-11, dated March 22, 2019 (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 in the AD docket on the
internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2019-0876.
This proposed AD was prompted by a report that cracking was
discovered in a channel within a structural support member for the
rudder quadrant, rudder feel unit assembly, and environmental control
system due to fatigue. The FAA is proposing this AD to address cracking
in the rudder quadrant support structure, which can lead to progressive
deterioration in the performance of the systems it supports, and could
eventually lead to uncommanded rudder movement and bleed air leakage.
See the MCAI for additional background information.
Related Service Information Under 1 CFR Part 51
Bombardier has issued the following service information.
Bombardier Service Bulletin 700-53-054, dated October 1,
2018.
Bombardier Service Bulletin 700-53-5013, dated October 1,
2018.
Bombardier Service Bulletin 700-53-6012, dated October 1,
2018.
Bombardier Service Bulletin 700-1A11-53-029, dated October
1, 2018.
This service information describes procedures for repetitive
detailed visual inspections of the rudder quadrant box assembly for any
cracking. These documents are distinct since they apply to different
airplane models.
Bombardier also issued the following service information:
Bombardier Service Bulletin 700-53-052, dated October 1,
2018.
Bombardier Service Bulletin 700-53-6010, dated October 1,
2018.
Bombardier Service Bulletin 700-1A11-53-027, dated October
1, 2018.
Bombardier Service Bulletin 700-53-5011, dated October 1,
2018.
This service information describes procedures for modification of
the rudder quadrant box assembly. The modification includes surface and
bolt-hole eddy current inspections for cracking of the left-hand (LH)
channel; a detailed visual inspection for cracking of the forward and
aft half ribs and bottom and top skins; replacement of the rudder
quadrant box half ribs, air systems support fitting, and LH channel;
and installation of new rudder quadrant box back-up fittings. 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 a bilateral agreement with the State of Design Authority, the FAA
has been notified of the unsafe condition described in the MCAI and
service information referenced above. The FAA is proposing this AD
because the agency evaluated all the relevant information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design.
Proposed Requirements of This NPRM
This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between this Proposed AD and the MCAI or Service
Information.''
Differences Between This Proposed AD and the MCAI or Service
Information
Canadian Airworthiness Directive CF-2019-11, dated March 22, 2019,
states that if any cracking is found during the repetitive detailed
visual inspections of the rudder quadrant box assembly, the repair can
be done within 100 flight cycles after the inspection. However, this AD
requires that, for the LH channel, if the length of the crack exceeds
the upper limit, the repair must be done before further flight. In
addition, if the length of the crack for the LH channel is within the
upper limit, the repair must be done within 50 flight cycles. These
differences have been coordinated with TCCA.
Costs of Compliance
The FAA estimates that this proposed AD affects 123 airplanes of
U.S. registry. The FAA estimates the following costs to comply with
this proposed AD:
[[Page 68372]]
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 per $0................................. $170 per $20,910 per
inspection cycle. inspection inspection
cycle cycle
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The FAA estimates the following costs to do any necessary on-
condition action 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 this on-condition action:
Estimated Costs of On-Condition Action
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Cost per
Labor cost Parts cost product
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46 work-hours x $85 per hour = $3,910. $355 $4,265
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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.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes and associated appliances to the
Director of the System Oversight Division.
Regulatory Findings
The FAA has determined that this proposed AD would not have
federalism implications under Executive Order 13132. This proposed AD
would not have a substantial direct effect on the States, on the
relationship between the national Government and the States, or on the
distribution of power and responsibilities among the various levels of
government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Will not affect intrastate aviation in Alaska; and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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):
Bombardier, Inc.: Docket No. FAA-2019-0876; Product Identifier 2019-
NM-070-AD.
(a) Comments Due Date
The FAA must receive comments by January 30, 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
9001 through 9844 inclusive, and 9998.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report that cracking was discovered in
a channel within a structural support member for the rudder
quadrant, rudder feel unit assembly, and environmental control
system due to fatigue. The FAA is issuing this AD to address
cracking in the rudder quadrant support structure, which can lead to
progressive deterioration in the performance of the systems it
supports, and could eventually lead to uncommanded rudder movement
and bleed air leakage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Initial and Repetitive Inspections
For airplanes that have accumulated fewer than 2,900 total
flight cycles as of the effective date of this AD, and that have not
been modified as specified in paragraph (i) of this AD: At the
applicable time specified in paragraph (g)(1) or (2) of this AD, do
a detailed visual inspection for cracking of the rudder quadrant box
assembly, in accordance with paragraph 2.B. of the Accomplishment
Instructions of the applicable service bulletin specified in figure
1 to paragraph (g) of this AD. Repeat the inspection thereafter at
intervals not to exceed 1,000 flight cycles.
(1) For airplanes that have accumulated fewer than 2,000 total
flight cycles as of the effective date of this AD: Inspect within
1,000 flight cycles after the effective date of this AD.
(2) For airplanes that have accumulated 2,000 total flight
cycles or more, but fewer than 2,900 total flight cycles, as of the
effective date of this AD: Inspect within 100
[[Page 68373]]
flight cycles after the effective date of this AD.
[GRAPHIC] [TIFF OMITTED] TP16DE19.076
(h) Corrective Actions for Inspection Findings
If any cracking is found during the inspection specified in
paragraph (g) of this AD, do the actions specified in paragraph (i)
of this AD at the applicable time specified in paragraphs (h)(1)
through (4) of this AD.
(1) If any crack of 1.20 inch (30.48 mm) or longer is found on
the forward (FWD) upper half rib: Do the actions within 100 flight
cycles after discovery of the crack.
(2) If any crack of 0.40 inch (10.16 mm) or longer is found on
the AFT lower half rib, do the actions within 100 flight cycles
after discovery of the crack.
(3) If any crack is found on the left-hand (LH) channel that has
grown from the air system's support fitting aft fastener hole to the
adjacent air systems support fitting fastener hole (which is 0.625
inch (15.88 mm) from hole edge to hole edge) or longer, do the
actions before further flight.
(4) If any crack is found on the LH channel that is less than
0.625 inch (15.88 mm) from hole edge to hole edge (which is the
distance from the air system's support fitting aft fastener hole to
the adjacent air system's support fitting fastener hole), do the
actions within 50 flight cycles after discovery of the crack.
(i) Modification of the Rudder Quadrant Box Assembly
At the applicable time specified in paragraph (i)(1) or (2) of
this AD, except as required by paragraph (h) of this AD: Modify the
rudder quadrant box assembly. The modification includes surface and
bolt-hole eddy current inspections for cracking of the left-hand
channel; a detailed visual inspection for cracking of the forward
and aft half ribs and bottom and top skins; applicable corrective
actions; replacement of the rudder quadrant box half ribs, air
systems support fitting, and LH channel; and installation of new
rudder quadrant box back-up fittings. Do the modification and
associated actions in accordance with paragraph 2.B., 2.C., and
2.D., of the Accomplishment Instructions of the applicable service
bulletin specified in figure 2 to paragraph (i) of this AD; except,
where the applicable service bulletin specifies to contact
Bombardier for appropriate action, corrective actions must be done
before further flight in accordance with the procedures specified in
paragraph (l)(2) of this AD.
(1) For airplanes that have accumulated 2,900 total flight
cycles or fewer as of the effective date of this AD, do the required
actions before the accumulation of 3,000 total flight cycles, or
within 60 months after the effective date of this AD, whichever
occurs first.
(2) For airplanes that have accumulated more than 2,900 total
flight cycles as of the effective date of this AD, do the required
actions within 100 flight cycles or 12 months, whichever occurs
first, after the effective date of this AD.
[[Page 68374]]
[GRAPHIC] [TIFF OMITTED] TP16DE19.077
(j) Alternative Modification
Airplanes that have been modified as specified by any
modification identified in paragraph (j)(1) through (4) of this AD
(which are not required by this AD), meet the requirements specified
in paragraph (i) of this AD.
(1) Bombardier Repair Modification R700T400669, Revision C,
dated January 19, 2018, or Bombardier Repair Modification
R700T400669, Revision G, dated May 30, 2018.
(2) Bombardier In-Service Modification IS700-53-0024, Revision
A, dated July 24, 2018.
(3) Bombardier Service Request for Product Support Action
(SRPSA) 000220372.
(4) Bombardier Service Request for Product Support Action
(SRPSA) 000271526.
(k) Terminating Action for Repetitive Inspections
Accomplishing the actions in paragraph (i) or (j) of this AD
terminates all of the requirements in paragraph (g) of this AD.
(l) 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 corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, New York ACO
Branch, FAA; or Transport Canada Civil Aviation (TCCA); or Canada's
TCCA Design Approval Organization (DAO). If approved by the DAO, the
approval must include the DAO-authorized signature.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directive CF-2019-11, dated March 22,
2019, for related information. This MCAI may be found in the AD
docket on the internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2019-0876.
(2) For more information about this AD, contact Andrea Jimenez,
Aerospace Engineer, Airframe and Mechanical Systems Section, FAA,
New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516-228-7330; fax 516-794-5531; email [email protected].
(3) For service information identified in this AD, contact
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email [email protected]; internet https://www.bombardier.com. You may view this service information at the
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines,
WA. For information on the availability of this material at the FAA,
call 206-231-3195.
Issued in Des Moines, Washington, on November 21, 2019.
Dorr Anderson,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-25719 Filed 12-13-19; 8:45 am]
BILLING CODE 4910-13-P