[Federal Register Volume 84, Number 174 (Monday, September 9, 2019)]
[Proposed Rules]
[Pages 47170-47172]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-19295]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0675; Product Identifier 2019-NM-068-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 DHC-8-401 and -402 airplanes. This 
proposed AD was prompted by a report that certain fuselages were 
delivered with non-conforming keel tension fittings and stringer end 
fittings. This proposed AD would require a detailed visual inspection 
of stringer end fittings and keel fittings for loose or working 
fasteners, signs of wear, and corrosion, and repair if necessary; and a 
general visual inspection of the keel tension fitting and stringer end 
fittings, as applicable and repairs and replacement of the keel and 
stringer end fittings if necessary. 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 October 24, 
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 Bombardier, Inc., service information identified in this NPRM, 
contact De Havilland Aircraft of Canada Ltd., Q-Series Technical Help 
Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; phone: 
416-375-4000; fax: 416-375-4539; email: [email protected]; internet: 
https://dehavilland.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-
0675; 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 Propulsion Section, FAA, New York ACO Branch, 1600 Stewart 
Avenue, Suite 410, Westbury, NY 11590; phone: 516-228-7330; fax: 516-
794-5531; email: [email protected].

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-2019-0675; 
Product Identifier 2019-NM-068-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 http://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 AD CF-2019-06, dated February 
18, 2019 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain Bombardier, Inc., Model DHC-8-401 and -402 
airplanes. The MCAI states:

    A disclosure letter from a supplier identified a number of 
fuselages that were delivered with non-conforming keel tension 
fittings and stringer end fittings. Left unaddressed, these non-
conformances can lead to premature cracking in several locations, 
corrosion, and compromise the structural integrity of the fuselage 
joints.
    This [Canadian] AD requires a one-time inspection of the non-
conforming fittings [and repair if necessary], and later [an 
inspection of the fittings and, if necessary,] replacement of the 
fittings [or repair].

    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-
0675.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued the following service information.
     Service Bulletin 84-53-74, dated August 29, 2018. This 
service information describes procedures for a general visual 
inspection of the keel and stringer end fittings, repair, and 
replacement of the keel and stringer end fittings.

[[Page 47171]]

     Service Bulletin 84-53-75, dated August 29, 2018. This 
service information describes procedures for a detailed visual 
inspection of stringer end fittings and keel fittings, in the passenger 
compartment at stations X373.15 and X428.50, for loose or working 
fasteners, signs of wear, and corrosion.
    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.

Costs of Compliance

    The FAA estimates that this proposed AD affects 1 airplane of U.S. 
registry. The FAA estimates 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
----------------------------------------------------------------------------------------------------------------
33 work-hours x $85 per hour = $2,805........................              $0           $2,805           $2,805
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data that would enable the 
agency to provide cost estimates for the on-condition replacements 
specified in this proposed AD.

              Estimated Costs of On-Condition Replacements
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                                                             Cost per
              Labor cost                   Parts cost        product
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46 work-hours x $85 per hour = $3,910.         $54,649          $58,559
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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 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-2019-0675; Product Identifier 2019-
NM-068-AD.

(a) Comments Due Date

    The FAA must receive comments by October 24, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc., Model DHC-8-401 and -402 
airplanes, certificated in any category, serial numbers 4327, 4330, 
4337, 4342, 4350, 4352, 4362, 4367, 4372, 4375, 4376, 4378, 4383, 
4384, 4385, 4388, 4391, 4392, 4396, and 4397.

[[Page 47172]]

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a report that certain fuselages were 
delivered with non-conforming keel tension fittings and stringer end 
fittings. The FAA is issuing this AD to address non-conforming keel 
tension fittings and stringer end fittings which could lead to 
premature cracking in several locations, corrosion, and compromise 
the structural integrity of the fuselage joints.

(f) Compliance

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

(g) Detailed Visual Inspection of the Stringer End Fittings and Keel 
Fittings and Repair

    Within 8,000 flight hours or 5 years after the effective date of 
this AD, whichever occurs first: Do a detailed visual inspection of 
the stringer end fittings and keel fittings at fuselage stations 
X373.15 and X428.50 for loose and working fasteners, signs of wear, 
and corrosion in accordance with paragraph 3.B. of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-53-75, 
dated August 29, 2018. If any loose or working fasteners, signs of 
wear, or corrosion are found during any inspection required by this 
paragraph, before further flight, repair 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. Doing the actions specified in 
Bombardier Service Bulletin 84-53-66 does not constitute compliance 
with the actions specified in this paragraph.

(h) General Visual Inspection, Repair, and Replacement of the Stringer 
End Fittings and Keel Fittings

    Except for airplanes identified in paragraph (i) of this AD: 
Before accumulating 40,000 total flight cycles or within 12 months 
after the effective date of this AD, whichever occurs later, do the 
inspections specified in paragraphs (h)(1) and (2) of this AD.
    (1) Do a general visual inspection of the keel tension fittings 
at fuselage stations X373.15 and X428.50 for non-conformance 
conditions (oversize, elongated, and off angle conditions) in 
accordance with paragraph 3.B. of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-53-74, dated August 29, 2018. If any 
non-conformance condition is found, before further flight, replace 
the keel tension fittings at fuselage stations X373.15 and X428.50, 
including doing all applicable repairs, in accordance with paragraph 
3.B. of the Accomplishment Instructions of Bombardier Service 
Bulletin 84-53-74, dated August 29, 2018; except where Bombardier 
Service Bulletin 84-53-74, dated August 29, 2018, specifies to 
contact Bombardier, before further flight, repair using a method 
approved by the Manager, New York ACO Branch, FAA; or TCCA; or 
Bombardier, Inc.'s TCCA DAO. If approved by the DAO, the approval 
must include the DAO-authorized signature.
    (2) Do a general visual inspection of the stringer end fittings 
at fuselage stations X373.15 and X428.50 for non-conformance 
conditions (i.e., excessive depth Hi-Lite fastener hole chamfers and 
installation too close to the fillet radius), in accordance with 
paragraph 3.B. of the Accomplishment Instructions of Bombardier 
Service Bulletin 84-53-74, dated August 29, 2018. If any non-
conformance condition is found, before further flight, replace the 
stringer end fittings at fuselage stations X373.15 and X428.50, 
including doing all applicable repairs and an eddy current or 
fluorescent dye penetrant inspection for cracks of all blended areas 
and fasteners, in accordance with paragraph 3.B. of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-53-74, 
dated August 29, 2018; except where Bombardier Service Bulletin 84-
53-74, dated August 29, 2018, specifies to contact Bombardier, 
before further flight, repair using a method approved by the 
Manager, New York ACO Branch, FAA; or TCCA; or Bombardier, Inc.'s 
TCCA DAO. If approved by the DAO, the approval must include the DAO-
authorized signature.

(i) Rework for Airplanes That Have Accomplished Bombardier Service 
Bulletin 84-53-69 Prior to the Effective Date of This AD

    For airplanes on which the actions specified in Bombardier 
Service Bulletin 84-53-69 have been accomplished prior to the 
effective date of this AD: Before accumulating 40,000 total flight 
cycles or within 12 months after the effective date of this AD, 
whichever occurs later, do a general visual inspection of the 
stringer end fittings at fuselage stations X373.15 and X428.50 for 
non-conformance conditions (i.e., excessive depth Hi-Lite fastener 
hole chamfers and installation too close to the fillet radius) in 
accordance with paragraph 3.B. of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-53-74, dated August 29, 2018. If any 
non-conformance condition is found, before further flight, replace 
the stringer end fittings at fuselage stations X373.15 and X428.50, 
including doing all applicable repairs and an eddy current or 
fluorescent dye penetrant inspection for cracks of all blended areas 
and fasteners, in accordance with paragraph 3.B. of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-53-74, 
dated August 29, 2018; except where Bombardier Service Bulletin 84-
53-74, dated August 29, 2018, specifies to contact Bombardier, 
before further flight, repair using a method approved by the 
Manager, New York ACO Branch, FAA; or TCCA; or Bombardier, Inc.'s 
TCCA DAO. If approved by the DAO, the approval must include the DAO-
authorized signature.

(j) Corrective Action for Eddy Current and Fluorescent Dye Penetrant 
Inspections

    If, during any eddy current or fluorescent dye penetrant 
inspection required by paragraph (h)(2) or (i) of this AD, any 
cracking is found, before further flight, repair using a method 
approved by the Manager, New York ACO Branch, FAA; or TCCA; or 
Bombardier, Inc.'s TCCA DAO. If approved by the DAO, the approval 
must include the DAO-authorized signature.

(k) 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; phone: 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 TCCA; or Bombardier, Inc.'s TCCA DAO. If approved by 
the DAO, the approval must include the DAO-authorized signature.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian AD CF-2019-06, dated February 18, 2019, 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-2019-0675.
    (2) For more information about this AD, contact Andrea Jimenez, 
Aerospace Engineer, Airframe and Propulsion Section, FAA, New York 
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
phone: 516-228-7330; fax: 516-794-5531; email: [email protected].
    (3) For Bombardier, Inc., service information identified in this 
AD, contact De Havilland Aircraft of Canada Ltd., Q-Series Technical 
Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; 
phone: 416-375-4000; fax: 416-375-4539; email: [email protected]; 
internet: https://dehavilland.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 August 30, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-19295 Filed 9-6-19; 8:45 am]
 BILLING CODE 4910-13-P