(a) EFFECTIVE DATE
This AD is effective May 7, 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 al-
ready 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 flight cycles after the effective date of
this AD.
FIGURE 1 TO PARAGRAPH (G) – INSPECTION SERVICE INFORMATION
______________________________________________________________________
AIRPLANE MODEL SERVICE INFORMATION
______________________________________________________________________
BD-700-1A10 airplanes having Bombardier Service Bulletin
serial numbers 9002 through 700-53-054, Basic Issue, dated
9312 inclusive, 9314 through October 1, 2018
9380 inclusive, and 9384
through 9429 inclusive
BD-700-1A10 airplanes having Bombardier Service Bulletin
serial numbers 9313, 9381, and 700-53-6012, Basic Issue, dated
9432 through 9844 inclusive October 1, 2018
BD-700-1A11 airplanes having Bombardier Service Bulletin
serial numbers 9127 through 700-1A11-53-029, Basic Issue,
9383 inclusive, 9389 through dated October 1, 2018
9400 inclusive, 9404 through
9431 inclusive, and 9998
BD-700-1A11 airplanes having Bombardier Service Bulletin
serial numbers 9386, 9401, and 700-53-5013, Basic Issue, dated
9445 through 9840 inclusive October 1, 2018
______________________________________________________________________
(h) CORRECTIVE ACTIONS FOR INSPECTION FINDINGS
If any cracking is found during any 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 dis-
covery 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.
FIGURE 2 TO PARAGRAPH (I) – MODIFICATION SERVICE INFORMATION
______________________________________________________________________
AIRPLANE MODEL SERVICE INFORMATION
______________________________________________________________________
BD-700-1A10 airplanes having Bombardier Service Bulletin
serial numbers 9002 through 700-53-052, Basic Issue, dated
9312 inclusive, 9314 through October 1, 2018
9380 inclusive, and 9384
through 9429 inclusive
BD-700-1A10 airplanes having Bombardier Service Bulletin
serial numbers 9313, 9381, and 700-53-6010, Basic Issue, dated
9432 through 9844 inclusive October 1, 2018.
BD-700-1A11 airplanes having Bombardier Service Bulletin
serial numbers 9127 through 700-1A11-53-027, Basic Issue,
9383 inclusive, 9389 through dated October 1, 2018
9400 inclusive, 9404 through
9431 inclusive, and 9998
BD-700-1A11 airplanes having Bombardier Service Bulletin
serial numbers 9386, 9401, and 700-53-5011, Basic Issue, dated
9445 through 9840 inclusive October 1, 2018
______________________________________________________________________
(j) ALTERNATIVE MODIFICATION
Airplanes that have been modified as specified by any modification
identified in paragraphs (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 termi-
nates 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 Bombardier,
Inc.'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 AD 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 9-avs-nyaco-cos@faa.gov.
(n) 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 700-53-052, Basic Issue, dated October 1,
2018.
(ii) Bombardier Service Bulletin 700-53-054, Basic Issue, dated October 1,
2018.
(iii) Bombardier Service Bulletin 700-53-5011, Basic Issue, dated October
1, 2018
(iv) Bombardier Service Bulletin 700-53-5013, Basic Issue, dated October
1, 2018.
(v) Bombardier Service Bulletin 700-53-6010, Basic Issue, dated October 1,
2018.
(vi) Bombardier Service Bulletin 700-53-6012, Basic Issue, dated October
1, 2018.
(vii) Bombardier Service Bulletin 700-1A11-53-027, Basic Issue, dated
October 1, 2018.
(viii) Bombardier Service Bulletin 700-1A11-53-029, Basic Issue, dated
October 1, 2018.
(3) For service information identified in this AD, contact Bombardier,
Inc., 400 Cote-Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; tele-
phone 514-855-5000; fax 514-855-7401; email thd.crj@aero.bombardier.
com; internet https://www.bombardier.com.
(4) 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.
(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 March 10, 2020. Lance T. Gant, Director, Compliance & Airworthi-
ness Division, Aircraft Certification Service.
FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer, Air-
frame 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 9-avs-nyaco-cos@faa.gov.
|
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0876; Product Identifier 2019-NM-070-AD; Amendment
39-19877; AD 2020-05-27]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
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 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 AD requires repetitive inspections of the rudder quadrant
box assembly for any cracking, and modification of the rudder quadrant
box assembly. The FAA issuing this AD to address the unsafe condition
on these products.
DATES: This AD is effective May 7, 2020.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of May 7, 2020.
ADDRESSES: For service information identified in this final rule,
contact Bombardier, Inc., 400 Cote-Vertu Road West, Dorval,
Quebec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email thd.crj@aero.bombardier.com; 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. It is also available on the internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2019-0876.
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 final rule, the regulatory evaluation, 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: 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 9-avs-nyaco-cos@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD CF-2019-11, dated March
22, 2019 (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 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.
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 and BD-700-1A11 airplanes. The NPRM published
in the Federal Register on December 16, 2019 (84 FR 68370). The NPRM
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
NPRM proposed to require repetitive inspections of the rudder quadrant
box assembly for any cracking, and modification of the rudder quadrant
box assembly. 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.
See the MCAI for additional background information.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The FAA received no comments on the NPRM or
on the determination of the cost to the public.
Conclusion
The FAA reviewed the relevant data and determined that air safety
and the public interest require adopting this final rule as proposed,
except for minor editorial changes. The FAA has determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
Bombardier has issued the following service information.
Bombardier Service Bulletin 700-53-054, Basic Issue, dated
October 1, 2018.
Bombardier Service Bulletin 700-53-5013, Basic Issue,
dated October 1, 2018.
Bombardier Service Bulletin 700-53-6012, Basic Issue,
dated October 1, 2018.
Bombardier Service Bulletin 700-1A11-53-029, Basic Issue,
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, Basic Issue, dated
October 1, 2018.
Bombardier Service Bulletin 700-53-6010, Basic Issue,
dated October 1, 2018.
Bombardier Service Bulletin 700-1A11-53-027, Basic Issue,
dated October 1, 2018.
Bombardier Service Bulletin 700-53-5011, Basic Issue,
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.
Costs of Compliance
The FAA estimates that this AD affects 123 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
|
| 2 work-hours x $85 per hour =
$170 per inspection cycle |
$0 |
$170 per inspection cycle |
$20,910 per inspection cycle |
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
|
Labor cost
|
Parts cost
|
Cost per
product
|
| 46 work-hours x $85 per hour
= $3,910 |
$355
|
$4,265
|
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 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.
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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
|