[Federal Register Volume 81, Number 136 (Friday, July 15, 2016)]
[Proposed Rules]
[Pages 45995-45997]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-16732]



[[Page 45995]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8178; Directorate Identifier 2015-NM-197-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: We propose to adopt a new airworthiness directive (AD) for 
certain Bombardier, Inc. Model DHC-8-400 series airplanes. This 
proposed AD was prompted by a determination by the manufacturer that 
shims might not have been installed between certain longerons and 
longeron joint fittings. This proposed AD would require repetitive 
inspections of the external surface of the fuselage skin panel for 
loose or working fasteners, and corrective action if necessary; a 
detailed visual inspection of the longeron joint fittings for the 
existence of shims and, if necessary, repetitive inspections of the 
longeron and the longeron joint fittings for any cracking, and 
corrective action if necessary. This proposed AD would also provide 
terminating action for certain repetitive inspections. We are proposing 
this AD to detect and correct missing shims between the longerons and 
longeron joint fittings. Such missing shims could result in a gapping 
condition and lead to stress corrosion cracking of the longeron joint 
fittings, and could adversely affect the structural integrity of the 
wing-to-fuselage attachment joints.

DATES: We must receive comments on this proposed AD by August 29, 2016.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this NPRM, 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 [email protected]; Internet http://www.bombardier.com. You may view this referenced service information at 
the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
WA. For information on the availability of this material at the FAA, 
call 425-227-1221.

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-2016-
8178; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, 
NY 11590; telephone 516-228-7329; fax 516-794-5531.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-8178; 
Directorate Identifier 2015-NM-197-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on 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 proposed AD.

Discussion

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2015-22, dated August 3, 2015 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for certain Bombardier, Inc. Model DHC-8-400 series 
airplanes. The MCAI states:

    The aeroplane manufacturer has determined that shims may not 
have been installed between the longerons and longeron joint 
fittings at fuselage station X373-380, stringers 7 on the left and 
right hand side, on certain aeroplanes. The missing shims could 
result in a gapping condition and could lead to stress corrosion 
cracking of the longeron joint fittings.
    Failure of the longeron joint fitting could compromise the 
structural integrity of the wing-to-fuselage attachment joint.
    This [Canadian] AD mandates inspections in the area of the 
longeron joint fittings.

Corrective actions include replacing any loose or working fasteners 
(fasteners that show signs of wear or fatigue corrosion), repairing any 
structural damage, and replacing any cracked longeron or longeron with 
an amplitude of 50% or more of the calibration signal. 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-2016-8178.

Related Service Information Under 1 CFR Part 51

    Bombardier, Inc. has issued Bombardier Service Bulletin 84-53-65, 
dated February 27, 2015. The service information describes procedures 
for inspections of the external surface of the fuselage skin panel for 
loose or working fasteners; a detailed visual inspection of the 
longeron joint fittings for the existence of shims; high frequency eddy 
current (HFEC) inspections of the longeron and the longeron joint 
fittings for any cracking; and replacement of longeron fittings, shims, 
and fasteners. 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 and Requirements of This Proposed AD

    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 pertinent information and determined an unsafe

[[Page 45996]]

condition exists and is likely to exist or develop on other products of 
the same type design.

Costs of Compliance

    We estimate that this proposed AD affects 76 airplanes of U.S. 
registry.
    We also estimate that it would take about 2 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $12,920, or $170 
per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 3 work-hours for the inspection for missing shims, 9 work-
hours for the replacement of longeron fittings and shims, and 1 work-
hour for a reporting requirement; and would require parts costing 
$3,222; for a cost of up to $4,327 per product. We have no way of 
determining the number of aircraft that might need these actions. We 
have received no definitive data that would enable us to provide cost 
estimates for repair of loose or working fasteners or structural damage 
specified in this proposed AD.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this proposed AD 
is 2120-0056. The paperwork cost associated with this proposed AD has 
been detailed in the Costs of Compliance section of this document and 
includes time for reviewing instructions, as well as completing and 
reviewing the collection of information. Therefore, all reporting 
associated with this proposed AD is mandatory. Comments concerning the 
accuracy of this burden and suggestions for reducing the burden should 
be directed to the FAA at 800 Independence Ave. SW., Washington, DC 
20591, ATTN: Information Collection Clearance Officer, AES-200.

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.

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-2016-8178; Directorate Identifier 
2015-NM-197-AD.

(a) Comments Due Date

    We must receive comments by August 29, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc. Model DHC-8-400, -401, and -
402 airplanes, certificated in any category, serial numbers 4156 
through 4453 inclusive, 4456, and 4457.

(d) Subject

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

(e) Reason

    This AD was prompted by a determination by the manufacturer that 
shims might not have been installed between the longerons and 
longeron joint fittings at station X373-380, stringer 7, on the left 
and right sides of the airplane. We are issuing this AD to detect 
and correct missing shims between the longerons and longeron joint 
fittings. Such missing shims could result in a gapping condition and 
lead to stress corrosion cracking of the longeron joint fittings, 
and could adversely affect the structural integrity of the wing-to-
fuselage attachment joints.

(f) Compliance

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

(g) Inspection of the External Surface of the Fuselage Skin Panels

    At the time specified in paragraph (g)(1) or (g)(2) of this AD, 
as applicable, do a detailed visual inspection of the external 
surface of the fuselage skin panel for loose or working fasteners 
(fasteners that show signs of wear or fatigue corrosion) and 
structural damage, in accordance with paragraph 3.B. of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-53-65, 
dated February 27, 2015.
    (1) For airplanes that have accumulated less than 10,000 total 
flight hours, or less than 5 years in service since new, as of the 
effective date of this AD: Prior to accumulating 12,000 total flight 
hours or 6 years in service since new, whichever occurs first.
    (2) For airplanes that have accumulated 10,000 total flight 
hours or more, or 5 years or more in service since new, as of the 
effective date of this AD: Within 2,000 flight hours or 12 months 
after the effective date of this AD, whichever occurs first.

(h) Corrective Actions

    If any loose or working fastener or any structural damage is 
found during any inspection required by this AD: Before further 
flight, repair using a method approved by the Manager, New York 
Aircraft Certification Office (ACO), FAA; or Transport Canada Civil 
Aviation (TCCA); or Bombardier, Inc.'s TCCA Design Approval 
Organization (DAO); and therafter do the inspections required by 
paragraph (i) of this AD. Accomplishment of a repair in accordance 
with a method approved by the Manager, New York ACO, FAA; or TCCA; 
or

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Bombardier, Inc.'s TCCA DAO terminates the repetitive inspections 
required by paragraph (i) of this AD for the repaired area only.

(i) Repetitive Detailed Visual Inspections

    Repeat the detailed visual inspection required by the 
introductory text to paragraph (g) of this AD at intervals not to 
exceed 12 months or 2,000 flight cycles, whichever occurs first 
after accomplishment of the most recent inspection, until the 
actions required by the introductory text to paragraph (j) of this 
AD are done.

(j) Inspection for Missing Shims

    At the time specified in paragraph (j)(1) or (j)(2) of this AD, 
as applicable, do a detailed visual inspection of the longeron joint 
fittings for the existence of shims, in accordance with paragraph 
3.C. of the Accomplishment Instructions of Bombardier Service 
Bulletin 84-53-65, dated February 27, 2015.
    (1) For airplanes that have accumulated less than 10,000 total 
flight hours, or less than 5 years in service since new, as of the 
effective date of this AD: Prior to accumulating 18,000 total flight 
hours or 9 years in service since new, whichever occurs first.
    (2) For airplanes that have accumulated 10,000 total flight 
hours or more, or 5 years or more in service since new, as of the 
effective date of this AD: Within 8,000 flight hours or 4 years 
after the effective date of this AD, whichever occurs first; but not 
to exceed 30,000 total flight hours or 144 months in service since 
new, whichever occurs first.

(k) Airplanes With Installed Shims: No Further Action Required

    If the inspection required by the introductory text to paragraph 
(j) of this AD reveals that shims are installed in the longeron 
joint fittings, no further action is required by this AD.

(l) Airplanes With Missing Shims: High Frequency Eddy Current (HFEC) 
Inspections and Corrective Actions

    If the inspection required by the introductory text to paragraph 
(j) of this AD reveals that any shim is missing from the longeron 
joint fittings: Before further flight, do an HFEC inspection of the 
longeron and the longeron joint fittings for any cracking, in 
accordance with paragraph 3.D. of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-53-65, dated February 27, 2015.
    (1) If any crack is found, or any indication is found with an 
amplitude of 50% or more of the calibration signal: Before further 
flight, replace the longeron joint fittings, in accordance with 
paragraph 3.E. of the Accomplishment Instructions of Bombardier 
Service Bulletin 84-53-65, dated February 27, 2015.
    (2) After each inspection required by the introductory text to 
paragraph (l) and paragraph (l)(1) of this AD, report the inspection 
results at the applicable time specified in paragraph (l)(2)(i) or 
(l)(2)(ii) of this AD to Bombardier, Inc., Q-Series Technical Help 
Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; 
telephone 416-375-4000; fax 416-375-4539; email 
[email protected]; Internet http://www.bombardier.com.
    (i) If the inspection was done on or after the effective date of 
this AD: Within 30 days after that inspection.
    (ii) If the inspection was done before the effective date of 
this AD: Within 30 days after the effective date of this AD.
    (3) If any crack, or any indication with an amplitude of 50% or 
more of the calibration signal is not found: Repeat the HFEC 
inspection required by the introductory text to paragraph (l) of 
this AD at intervals not to exceed 12,000 flight hours or 6 years, 
whichever occurs first after accomplishment of the most recent HFEC 
inspection, in accordance with paragraph 3.D. of the Accomplishment 
Instructions of Bombardier Service Bulletin 84-53-65, dated February 
27, 2015. If any crack is found, or any indication is found with an 
amplitude of 50% or more of the calibration signal: Before further 
flight, replace the longeron joint fittings, in accordance with 
paragraph 3.E. of the Accomplishment Instructions of Bombardier 
Service Bulletin 84-53-65, dated February 27, 2015.

(m) Terminating Action for Repetitive HFEC Inspections

    Replacement of the longeron joint fittings, in accordance with 
paragraph 3.E. of the Accomplishment Instructions of Bombardier 
Service Bulletin 84-53-65, dated February 27, 2015, constitutes 
terminating action for the repetitive HFEC inspections required by 
paragraph (l)(3) of this AD.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York ACO, ANE-170, 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 ACO, send it to ATTN: Program 
Manager, Continuing Operational Safety, FAA, New York ACO, 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. The AMOC approval letter must 
specifically reference this AD.
    (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, 
ANE-170, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO. If approved 
by the DAO, the approval must include the DAO-authorized signature.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2015-22, dated August 3, 
2015, 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-2016-8178.
    (2) 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 [email protected]; Internet 
http://www.bombardier.com. You may view this service information at 
the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at 
the FAA, call 425-227-1221.

    Issued in Renton, Washington, on July 8, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-16732 Filed 7-14-16; 8:45 am]
 BILLING CODE 4910-13-P