Document ID: FAA-2019-0024-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Bombardier, Inc., Airplanes
Posted Date: 2019-02-28T05:00Z

[Federal Register Volume 84, Number 40 (Thursday, February 28, 2019)]
[Proposed Rules]
[Pages 6705-6707]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-03313]

 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 84, No. 40 / Thursday, February 28, 2019 / 
Proposed Rules  

[[Page 6705]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0024; Product Identifier 2018-NM-138-AD]
RIN 2120-AA64

Airworthiness Directives; Bombardier, Inc., Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Bombardier, Inc., Model CL-600-2A12 (601) airplanes. This 
proposed AD was prompted by a report of damage to the anti-rotation tab 
on a main landing gear (MLG) side brace fitting due to the installation 
of an incorrect side brace fitting shaft. This proposed AD would 
require an inspection of the MLG side brace fitting for damage, a 
verification of the side brace fitting shaft part number, and 
replacement of the side brace fitting shaft if necessary. It would also 
require the installation of an anti-rotation bracket. We are proposing 
this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by April 15, 2019.

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 http://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., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec 
H4S 1Y9, Canada; Widebody Customer Response Center North America toll-
free telephone 1-866-538-1247 or direct-dial telephone 1-514-855-2999; 
fax 514-855-7401; email ac.yul@aero.bombardier.com; internet http://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 http://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0024; 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 (phone: 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Kristopher Greer, Aerospace Engineer, 
Aviation Safety Section AIR-7B1, Boston ACO Branch, FAA, 1200 District 
Avenue, Burlington, MA 01803; telephone 781-238-7799.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite 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-2019-0024; 
Product Identifier 2018-NM-138-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM because 
of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD CF-2018-19, dated July 20, 
2018 (referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for 
certain Bombardier, Inc., Model CL-600-2A12 (601) airplanes. The MCAI 
states:

    There has been a report of damage to the anti-rotation tab on a 
Main Landing Gear (MLG) Side Brace fitting. Investigation of the 
report revealed that a Challenger model CL600 MLG Side Brace shaft 
had been installed on a Challenger model CL601 Side Brace fitting. 
Due to the difference in size, this will result in changes to the 
way the load is transferred between the shaft and the MLG Side Brace 
fitting and may result in premature cracking of the MLG Side Brace 
fitting. This condition, if not corrected, could lead to the 
collapse of the MLG resulting in structural damage to the wing spar 
and fuel tank.
    This [Canadian] AD mandates an inspection of the MLG Side Brace 
fitting and shaft to verify that the correct shaft part number (P/N) 
is installed and the fitting is not damaged [damage includes 
cracking, scratches, gouges, corrosion, defects, and incorrect inner 
diameter tolerance]. If the Challenger CL600 shaft is installed, 
this AD mandates replacement with the correct Challenger model CL601 
part. If the correct P/N is found installed, this [Canadian] AD also 
mandates the installation of a bracket to prevent the incorrect part 
from being installed in the future.

    You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0024.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued Service Bulletin 601-0624, Revision 2, dated 
January 29, 2018. This service information describes procedures for 
inspecting the MLG side brace fitting and side brace fitting shaft, 
installing a replacement side brace fitting shaft if necessary, and 
installing an anti-rotation bracket.
    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.

[[Page 6706]]

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, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
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.

Costs of Compliance

    We estimate that this proposed AD affects 9 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
4 work-hours x $85 per hour = $340...........................            $397             $737           $6,633
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
actions that would be required based on the results of any required 
actions. We have no way of determining the number of aircraft that 
might need these on-condition actions:

                                     Estimated Costs of On-Condition Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                                  Labor cost                                       Parts cost        product
----------------------------------------------------------------------------------------------------------------
8 work-hours x $85 per hour = $680............................................          $7,989           $8,669
----------------------------------------------------------------------------------------------------------------

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.
    We are 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 to the Director of the System Oversight 
Division.

Regulatory Findings

    We 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. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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-2019-0024; Product Identifier 2018-
NM-138-AD.

(a) Comments Due Date

    We must receive comments by April 15, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc., Model CL-600-2A12 (601) 
airplanes, certificated in any category, serial numbers (S/N) 3001 
through 3009 inclusive and 3011 through 3029 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by a report of damage to the anti-rotation 
tab on a main landing gear (MLG) side brace fitting due to the 
installation of an incorrect side brace fitting shaft. We are 
issuing this AD to address premature cracking of the MLG side brace 
fitting. This condition, if not corrected,

[[Page 6707]]

could lead to the collapse of the MLG, resulting in structural 
damage to the wing spar and fuel tank.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspection for Damage and Identification of the Side Brace Fitting 
Shaft Part Number

    Within 400 flight cycles or 12 months, whichever occurs first, 
after the effective date of this AD, do the actions specified in 
paragraphs (g)(1) and (g)(2) of this AD.
    (1) Identify the part number of the installed side brace fitting 
shaft.
    (2) Do a detailed visual inspection (DVI) of the side brace 
fitting for signs of damage, including cracking and gouges, in 
accordance with paragraph 2.B. of the Accomplishment Instructions of 
Bombardier Service Bulletin 601-0624, Revision 2, dated January 29, 
2018.

(h) Installation of Anti-Rotation Bracket

    (1) For airplanes on which a side brace fitting shaft having P/N 
600-10237-3 is installed and the actions required by paragraph (g) 
of this AD are done on or after the effective date of this AD: 
Before further flight, modify the MLG side brace fitting by 
installing the anti-rotation bracket in accordance with paragraph 
2.C. of the Accomplishment Instructions of Bombardier Service 
Bulletin 601-0624, Revision 2, dated January 29, 2018.
    (2) For airplanes on which a side brace fitting shaft having P/N 
600-10237-3 is installed and the actions required by paragraph (g) 
of this AD were done before the effective date of this AD: Within 6 
months after the effective date of this AD, modify the MLG side 
brace fitting by installing the anti-rotation bracket in accordance 
with paragraph 2.C. of the Accomplishment Instructions of Bombardier 
Service Bulletin 601-0624, Revision 2, dated January 29, 2018.

(i) Replacement of the Side Brace Fitting Shaft and Installation of the 
Anti-Rotation Bracket

    (1) For airplanes on which a side brace fitting shaft having P/N 
600-10237-1 or 600-10237-5 is installed and damage is found during 
the DVI of the side brace fitting: Before further flight, do a DVI 
of the anti-rotation tab and side brace fitting aft bushing for 
cracking, scratches, gouges, corrosion, and inner diameter 
tolerance, and a special detailed inspection (SDI) of the side brace 
fitting aft bore for cracks and defects; perform applicable repairs; 
replace the side brace fitting shaft with a side brace fitting shaft 
having P/N 600-10237-3; and install the anti-rotation bracket in 
accordance with paragraph 2.D. of the Accomplishment Instructions of 
Bombardier Service Bulletin 601-0624, Revision 2, dated January 29, 
2018.
    (2) For airplanes on which a side brace fitting shaft having P/N 
600-10237-1 or 600-10237-5 is installed and no damage is found 
during the DVI of the side brace fitting: Within 300 flight cycles 
or 12 months, whichever occurs first, after the inspection required 
by paragraph (g)(2) of this AD, do a DVI of the anti-rotation tab 
and side brace fitting aft bushing for cracking, scratches, gouges, 
corrosion, and inner diameter tolerance, and an SDI of the side 
brace fitting aft bore for cracks and defects; perform applicable 
repairs; replace the side brace fitting shaft with a side brace 
fitting shaft having P/N 600-10237-3; and install the anti-rotation 
bracket in accordance with paragraph 2.D. of the Accomplishment 
Instructions of Bombardier Service Bulletin 601-0624, Revision 2, 
dated January 29, 2018.

(j) Exceptions to Service Information

    Where Bombardier Service Bulletin 601-0624, Revision 2, dated 
January 29, 2018, specifies contacting Bombardier's Customer Support 
Engineering for repair instructions: This AD requires doing the 
repair before further flight using a method approved in accordance 
with the procedures specified in paragraph (l)(2) of this AD.

(k) Credit for Previous Actions

    (1) For an airplane on which a side brace fitting shaft having 
P/N 600-10237-3 is installed 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 
Bombardier Service Bulletin 601-0624, dated October 1, 2012; or 
Bombardier Service Bulletin 601-0624, Revision 1, dated March 29, 
2017.
    (2) This paragraph provides credit for actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Bombardier Service Bulletin 601-
0624, dated October 1, 2012; or Bombardier Service Bulletin 601-
0624, Revision 1, dated March 29, 2017, provided that the side brace 
fitting shaft was identified as having P/N 600-10237-3 and within 6 
months after the effective date of this AD, the MLG side brace 
fitting is modified by installing the anti-rotation bracket in 
accordance with paragraph 2.C. of the Accomplishment Instructions of 
Bombardier Service Bulletin 601-0624, Revision 2, dated January 29, 
2018.
    (3) This paragraph provides credit for actions required by 
paragraphs (g) and (i), if those actions were performed before the 
effective date of this AD, provided that any side brace fitting 
shaft having P/N 600-10237-1 or P/N 600-10237-5 was identified and 
replaced with a side brace fitting shaft having P/N 600-10237-3, and 
the anti-rotation bracket was installed in accordance with paragraph 
2.D. of the Accomplishment Instructions of Bombardier Service 
Bulletin 601-0624, Revision 1, dated March 29, 2017.

(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-2018-19, dated July 20, 2018, for related 
information. This MCAI may be found in the AD docket on the internet 
at http://www.regulations.gov by searching for and locating Docket 
No. FAA-2019-0024.
    (2) For more information about this AD, contact Kristopher 
Greer, Aerospace Engineer, Aviation Safety Section AIR-7B1, Boston 
ACO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; 
telephone 781-238-7799.
    (3) For information about AMOCs, contact Aziz Ahmed, Aerospace 
Engineer, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, 
Westbury, New York 11590; telephone: 516-287-7329; fax: 516-794-
5531; email: Aziz.Ahmed@faa.gov.
    (4) For service information identified in this AD, contact 
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; Widebody Customer Response Center 
North America toll-free telephone 1-866-538-1247 or direct-dial 
telephone 1-514-855-2999; fax 514-855-7401; email 
ac.yul@aero.bombardier.com; internet http://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 February 21, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-03313 Filed 2-27-19; 8:45 am]
 BILLING CODE 4910-13-P