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[Federal Register Volume 78, Number 235 (Friday, December 6, 2013)]
[Proposed Rules]
[Pages 73462-73465]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-29134]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-1024; Directorate Identifier 2013-NM-140-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-8-102, -103, -106, -201, -202, -301, 
-311, and -315 airplanes. This proposed AD was prompted by reports of a 
fractured wing-to-fuselage strut attachment joint bolt. This proposed 
AD would require doing a torque check of all wing-to-fuselage strut 
attachment joint bolts, and repairing or replacing if necessary. For 
certain airplanes this proposed AD would require a detailed inspection 
for corrosion, damage, and wear of each wing-to-fuselage strut 
attachment joint bolt and associated hardware, and replacing if 
necessary; and a borescope inspection for corrosion and damage of the 
bore hole and barrel nut threads, and repairing or replacing if 
necessary. We are proposing this AD to detect and correct fractured 
bolts, which could result in reduced structural integrity of the wing-
to-fuselage strut attachment joint and subsequent loss of the wing.

DATES: We must receive comments on this proposed AD by January 21, 
2014.

ADDRESSES: You may send comments 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 proposed 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

[[Page 73463]]

thd.qseries@aero.bombardier.com; 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; 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 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: Jeffrey Zimmer, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New 
York 11590; telephone (516) 228-7306; 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-2013-1024; 
Directorate Identifier 2013-NM-140-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-
2013-17R1, dated June 27, 2013 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for the specified products. The MCAI states:

    There have been two in-service reports of a wing-to-fuselage 
strut attachment joint bolt found fractured during routine 
maintenance. Laboratory examination of one fractured bolt revealed 
that the fracture was attributed to stress corrosion cracking.
    Failure of the bolts could compromise the structural integrity 
of the wing-to-fuselage strut attachment joint and could lead to a 
subsequent loss of the wing.
    This [Canadian] AD mandates the inspection and rectification, as 
required, of the wing-to-fuselage strut attachment joint bolts and 
associated hardware.
* * * * *
Required actions include doing a torque check of wing-to-fuselage strut 
attachment joint bolts, and repairing or replacing if necessary. For 
certain airplanes, required actions include a detailed inspection for 
corrosion, damage (including but not limited to scratching, cracking, 
pitting, cross threads, etc.), and wear of each wing-to-fuselage strut 
attachment joint bolt and associated hardware, and replacement if 
necessary; and a borescope inspection for corrosion and damage of the 
bore hole and barrel nut threads, and repair or replacement if 
necessary. You may examine the MCAI in the AD docket on the Internet at 
http://www.regulations.gov by searching for and locating it in Docket 
No. FAA-2013-1024.

Relevant Service Information

    Bombardier has issued Service Bulletin 8-57-47, Revision A, dated 
May 29, 2013. The actions described in this service information are 
intended to correct the unsafe condition identified in the MCAI.

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

Differences Between This Proposed AD and the MCAI or Service 
Information

    In many FAA transport ADs, when the service information specifies 
to contact the manufacturer for further instructions if certain 
discrepancies are found, we typically include in the AD a requirement 
to accomplish the action using a method approved by either the FAA or 
the State of Design Authority (or its delegated agent).
    We have recently been notified that certain laws in other countries 
do not allow such delegation of authority, but some countries do 
recognize design approval organizations. In addition, we have become 
aware that some U.S. operators have used repair instructions that were 
previously approved by a State of Design Authority or a Design Approval 
Holder (DAH) as a method of compliance with this provision in FAA ADs. 
Frequently, in these cases, the previously approved repair instructions 
come from the airplane structural repair manual or the DAH repair 
approval statements that were not specifically developed to address the 
unsafe condition corrected by the AD. Using repair instructions that 
were not specifically approved for a particular AD creates the 
potential for doing repairs that were not developed to address the 
unsafe condition identified by the MCAI AD, the FAA AD, or the 
applicable service information, which could result in the unsafe 
condition not being fully corrected.
    To prevent the use of repairs that were not specifically developed 
to correct the unsafe condition, this proposed AD would require that 
the repair approval specifically refer to the FAA AD. This change is 
intended to clarify the method of compliance and to provide operators 
with better visibility of repairs that are specifically developed and 
approved to correct the unsafe condition. In addition, we use the 
phrase ``its delegated agent, or by the DAH with State of Design 
Authority design organization approval, as applicable'' in this 
proposed AD to refer to a DAH authorized to approve required repairs 
for this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 94 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD.
    We also estimate that it would take about 107 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Required parts would cost 
about $5,476 per product. Based on these figures, we estimate the cost 
of this proposed AD on U.S. operators to be $1,369,674, or $14,571 per 
product.
    We have received no definitive data that would enable us to provide 
a cost estimate for the repairs or replacements specified in this 
proposed AD.

[[Page 73464]]

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 proposed 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 AD:

Bombardier, Inc.: Docket No. FAA-2013-1024; Directorate Identifier 
2013-NM-140-AD.

(a) Comments Due Date

    We must receive comments by January 21, 2014.

(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 57, Wings.

(e) Reason

    This AD was prompted by reports of a fractured wing-to-fuselage 
strut attachment joint bolt. We are issuing this AD to detect and 
correct fractured bolts, which could result in reduced structural 
integrity of the wing-to-fuselage strut attachment joint and 
subsequent loss of the wing.

(f) Compliance

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

(g) Torque Check

    At the applicable time specified in paragraph (g)(1) or (g)(2) 
of this AD: Do a torque check of the wing-to-fuselage strut 
attachment joint bolts, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 8-57-47, Revision A, 
dated May 29, 2013.
    (1) For airplanes that have accumulated fewer than 40,000 total 
flight cycles, and have less than 15 years in service since new, as 
of the effective date of this AD: Do the torque check before the 
accumulation of 42,000 total flight cycles, or within 16 years in 
service since new, whichever occurs first.
    (2) For airplanes that have accumulated 40,000 total flight 
cycles or more, or have 15 years or more in service since new, as of 
the effective date of this AD: Do the torque check within 2,000 
flight cycles or 12 months after the effective date of this AD, 
whichever occurs first.

(h) Inspection and Corrective Actions

    (1) If only one bolt fails the torque check, before further 
flight, replace the bolt, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 8-57-47, Revision A, 
dated May 29, 2013; and before further flight do the actions 
specified in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD.
    (2) If more than one bolt fails the torque check, 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 its delegated agent or by the Design Approval 
Holder with the TCCA design organization approval). For a repair 
method to be approved, the repair approval must specifically refer 
to this AD.
    (3) If all bolts pass the torque check, before further flight, 
do the actions specified in paragraphs (h)(3)(i) and (h)(3)(ii) of 
this AD, as applicable.
    (i) Do a detailed inspection for corrosion, damage (including 
but not limited to scratching, cracking, pitting, and cross threads, 
etc.), and wear, of each wing-to-fuselage strut attachment joint 
bolt and associated hardware, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 8-57-47, Revision A, 
dated May 29, 2013. If any bolt or hardware has corrosion, damage, 
or wear, before further flight, replace the affected part, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 8-57-47, Revision A, dated May 29, 2013.
    (ii) Do a borescope inspection for corrosion and damage 
(including but not limited to scratching, cracking, pitting, and 
cross threads, etc.) of the bore hole and barrel nut threads, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 8-57-47, Revision A, dated May 29, 2013, except as 
provided by paragraph (i) of this AD.
    (A) If any corrosion or damage is found in the barrel nut 
threads, before further flight, replace the barrel nut, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 8-57-47, Revision A, dated May 29, 2013, except as 
provided by paragraph (i) of this AD.
    (B) If any corrosion or damage is found in the bore of the hole, 
before further flight, repair, using a method approved by the 
Manager, New York ACO, FAA; or Transport Canada Civil Aviation 
(TCCA) (or its delegated agent or by the Design Approval Holder with 
the TCCA design organization approval). For a repair method to be 
approved, the repair approval must specifically refer to this AD.

(i) Exception to Service Information

    Where Bombardier Service Bulletin 8-57-47, Revision A, dated May 
29, 2013, specifies to contact the manufacturer for repair 
information, this AD requires repairing before further flight using 
a method approved by the Manager, New York ACO, FAA; or TCCA (or its 
delegated agent, or by the Design Approval Holder with TCCA design 
organization approval). For a repair method to be approved, the 
repair approval must specifically refer to this AD.

(j) Credit for Previous Actions

    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 8-57-47, dated March 16, 2012.

(k) 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

[[Page 73465]]

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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer, use these actions if they 
are FAA-approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or by the Design Approval Holder with a State of 
Design Authority's design organization approval). For a repair 
method to be approved, the repair approval must specifically refer 
to this AD. You are required to ensure the product is airworthy 
before it is returned to service.

(l) Special Flight Permits

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2013-17R1, dated June 27, 
2013, for related information, which can be found in the AD docket 
on the Internet at http://www.regulations.gov by searching for and 
locating it in Docket No. FAA-2013-1024.
    (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 thd.qseries@aero.bombardier.com; 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.

    Issued in Renton, Washington, on November 29, 2013.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-29134 Filed 12-5-13; 8:45 am]
BILLING CODE 4910-13-P
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