[Federal Register Volume 84, Number 130 (Monday, July 8, 2019)]
[Rules and Regulations]
[Pages 32255-32257]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-14412]



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 Rules and Regulations
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains regulatory documents 
 having general applicability and legal effect, most of which are keyed 
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  Federal Register / Vol. 84, No. 130 / Monday, July 8, 2019 / Rules 
and Regulations  

[[Page 32255]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0189; Product Identifier 2019-NM-001-AD; Amendment 
39-19672; AD 2019-12-17]
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 DHC-8-102, -103, and -106 airplanes; 
Model DHC-8-200 series airplanes; and Model DHC-8-300 series airplanes. 
This AD was prompted by the reported loss of an elevator spring tab 
balance weight prior to takeoff. This AD requires inspecting the two 
balance weights and the two hinge arms on each elevator spring tab, and 
corrective actions if necessary. The FAA is issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective August 12, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 12, 
2019.

ADDRESSES: For service information identified in this final rule, 
contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt 
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; 
fax 416-375-4539; email thd.qseries@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. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0189.

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-
0189; 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

    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 DHC-8-102, -103, and -106 airplanes; Model DHC-8-200 series 
airplanes; and Model DHC-8-300 series airplanes. The NPRM published in 
the Federal Register on April 4, 2019 (84 FR 13148). The NPRM was 
prompted by the reported loss of an elevator spring tab balance weight 
prior to takeoff. The NPRM proposed to require inspecting the two 
balance weights and the two hinge arms on each elevator spring tab, and 
corrective actions if necessary.
    The FAA is issuing this AD to address tolerance stack-up between 
the balance weight and the hinge arm that can allow the attachment 
bolts to fret with the hinge arm and result in wear, fracture, and loss 
of the spring tab balance weight. Loss of the spring tab balance weight 
can lead to unacceptable flutter margins and loss of the airplane.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD CF-2018-30, dated November 
7, 2018 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain Bombardier, Inc., Model DHC-8-102, -103, and -106 
airplanes; Model DHC-8-200 series airplanes; and Model DHC-8-300 series 
airplanes. The MCAI states:

    One operator has reported the loss of an elevator spring tab 
balance weight prior to takeoff. An investigation found that 
clearances, due to tolerance stack-up between balance weight and 
hinge arm, allow the attachment bolts to fret with the hinge arm 
causing wear and potentially progressing to fracture and loss of the 
spring tab balance weight. The loss of a spring tab balance weight 
could result in unacceptable flutter margins and loss of the 
aeroplane.
    This [Canadian] AD mandates a one-time [detailed] inspection to 
verify the spring tab balance weights are securely attached on both 
the left hand and right hand spring tab assemblies. If any of the 
balance weights are found loose, instructions are given to repair 
any damage to the hinge arm, and to add a solid shim between balance 
weight and hinge arm to eliminate any potential gap, and to specify 
balance weight attachment hardware that has low susceptibility to 
hydrogen embrittlement.

    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-
0189.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The FAA has considered the comment 
received. The Air Line Pilots Association, International stated that it 
agrees with the intent of the NPRM.

Conclusion

    The FAA reviewed the relevant data, considered the comment 
received, 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 Service Bulletin 8-55-27, Revision A, dated

[[Page 32256]]

August 15, 2018. This service information describes procedures for 
inspecting the two balance weights and the two hinge arms on each 
elevator spring tab, and corrective actions including inspecting the 
holes in the hinge arm, inspecting the hinge arm for corrosion and 
chafing, installing bushings and a solid shim, replacing the hinge arm, 
repairing damage to the hinge arm, and permanently securing the mass 
balance.
    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 47 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
2 work-hours x $85 per hour = $170...........................              $0             $170           $7,990
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary on-
condition actions 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 these on-condition actions:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
           Labor cost               Parts cost       Cost per  product
------------------------------------------------------------------------
Up to 18 work-hours x $85 per                 $0  Up to $1,530.
 hour = $1,530.
------------------------------------------------------------------------

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 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

    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

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):

2019-12-17 Bombardier, Inc.: Amendment 39-19672; Docket No. FAA-
2019-0189; Product Identifier 2019-NM-001-AD.

(a) Effective Date

    This AD is effective August 12, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc., Model DHC-8-102, -103, -
106, -201, -202, -301, -311, and -315 airplanes, certificated in any 
category, serial numbers 003 through 672 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 55, Stabilizers.

(e) Reason

    This AD was prompted by the reported loss of an elevator spring 
tab balance weight prior to takeoff. The FAA is issuing this AD to 
address tolerance stack-up between the balance weight and the hinge 
arm that can allow the attachment bolts to fret with the hinge arm 
and result in wear, fracture, and loss of the spring tab balance 
weight. Loss of the spring tab balance weight can lead to 
unacceptable flutter margins and loss of the airplane.

(f) Compliance

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

[[Page 32257]]

(g) Inspection and Corrective Actions

    Within 600 flight hours after the effective date of this AD, 
perform a detailed inspection of the two balance weights and a 
detailed inspection of the two hinge arms on each elevator spring 
tab (left hand and right hand), in accordance with Section 3.B, Part 
A, of the Accomplishment Instructions of Bombardier Service Bulletin 
8-55-27, Revision A, dated August 15, 2018.
    (1) If any of the balance weight attachment locknuts, part 
number (P/N) MS 21042-4, is found fractured, loose, or missing: 
Before further flight conduct the rectification in accordance with 
Section 3.B, Part B, of the Accomplishment Instructions of 
Bombardier Service Bulletin 8-55-27, Revision A, dated August 15, 
2018.
    (2) If the balance weight is found not secure: Within 60 flight 
hours after the inspection required by paragraph (g) of this AD, 
repair any damage to the hinge arm and permanently secure the mass 
balance, in accordance with Section 3.B, Part B, of the 
Accomplishment Instructions of Bombardier Service Bulletin 8-55-27, 
Revision A, dated August 15, 2018.
    (3) If the balance weight is found secure: Within 5,000 flight 
hours after the inspection required by paragraph (g) of this AD, 
repair any damage to the hinge arm and permanently secure the mass 
balance, in accordance with Section 3.B, Part B, of the 
Accomplishment Instructions of Bombardier Service Bulletin 8-55-27, 
Revision A, dated August 15, 2018.
    (4) Where Bombardier Service Bulletin 8-55-27, Revision A, dated 
August 15, 2018, specifies to contact Bombardier for appropriate 
action: Before further flight, accomplish corrective actions in 
accordance with the procedures specified in paragraph (i)(2) of this 
AD.

(h) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g), (g)(2), (g)(3), and (g)(4) of this AD, if those 
actions were performed before the effective date of this AD using 
Section 3.B of the Accomplishment Instructions of Bombardier Service 
Bulletin 8-55-27, dated April 17, 2018, provided that within 600 
flight hours after the effective date of this AD, a detailed visual 
inspection of the balance weight locknuts, P/N MS 21042-4, is 
performed in accordance with Section 3.B, Part C, of the 
Accomplishment Instructions of Bombardier Service Bulletin 8-55-27, 
Revision A, dated August 15, 2018, and the rectification is 
performed before further flight for any fractured, loose, or missing 
balance weight attachment locknuts, P/N MS 21042-4, in accordance 
with Section 3.B, Part B, of the Accomplishment Instructions of 
Bombardier Service Bulletin 8-55-27, Revision A, dated August 15, 
2018.

(i) 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.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian AD CF-2018-30, dated November 7, 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-2019-0189.
    (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) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (k)(3) and (k)(4) of this AD.

(k) 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 8-55-27, Revision A, dated 
August 15, 2018.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt 
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; 
fax 416-375-4539; email thd.qseries@aero.bombardier.com; internet 
http://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, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on June 21, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-14412 Filed 7-5-19; 8:45 am]
BILLING CODE 4910-13-P


