[Federal Register Volume 85, Number 64 (Thursday, April 2, 2020)]
[Rules and Regulations]
[Pages 18431-18435]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-06786]


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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; 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.

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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 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 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. 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 [email protected].

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

[[Page 18432]]

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               $0  $170 per inspection cycle......................  $20,910 per inspection cycle.
 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
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
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 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

[[Page 18433]]

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

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):

2020-05-27 Bombardier, Inc.: Amendment 39-19877; Docket No. FAA-
2019-0876; Product Identifier 2019-NM-070-AD.

(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 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 flight cycles after 
the effective date of this AD.
[GRAPHIC] [TIFF OMITTED] TR02AP20.003

(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 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.

[[Page 18434]]

    (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.
[GRAPHIC] [TIFF OMITTED] TR02AP20.004

(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 
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 
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 [email protected].

(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.

[[Page 18435]]

    (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 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.
    (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 [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on March 10, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-06786 Filed 4-1-20; 8:45 am]
 BILLING CODE 4910-13-P