Document ID: FAA-2019-0876-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Bombardier, Inc., Airplanes
Posted Date: 2019-12-16T05:00Z

[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 
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.

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 9-avs-nyaco-cos@faa.gov.

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
----------------------------------------------------------------------------------------------------------------
2 work-hours x $85 per hour = $170 per       $0.................................        $170 per     $20,910 per
 inspection cycle.                                                                    inspection      inspection
                                                                                           cycle           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
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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 9-avs-nyaco-cos@faa.gov.
    (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 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.

    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