[Federal Register Volume 80, Number 22 (Tuesday, February 3, 2015)]
[Rules and Regulations]
[Pages 5670-5674]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-01661]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0082; Directorate Identifier 2014-NM-233-AD; 
Amendment 39-18092; AD 2015-02-23]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and 
CL-600-2B16 (CL-601-3A, and CL-601-3R Variants) airplanes. This AD 
requires repetitive inspections for fractured or incorrectly oriented 
fasteners on the inboard flap hinge-box forward fittings on both wings, 
and replacement of all fasteners, if necessary. This AD was prompted by 
several reports of incorrectly oriented and fractured fasteners found 
on the inboard flap hinge-box forward fitting at wing station (WS) 
76.50. We are issuing this AD to detect and correct incorrectly 
oriented or fractured fasteners, which could result in detachment of 
the flap hinge-box and the flap surface, and consequent reduced 
controllability of the airplane.

DATES: This AD becomes effective February 18, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 18, 
2015.
    We must receive comments on this AD by March 20, 2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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.

[[Page 5671]]

    For service information identified in this AD, contact Bombardier, 
Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, 
Canada; telephone 514-855-5000; fax 514-855-7401; email 
<a href="/cdn-cgi/l/email-protection#a2d6cac68cc1d0c8e2c3c7d0cd8cc0cdcfc0c3d0c6cbc7d08cc1cdcf"><span class="__cf_email__" data-cfemail="73071b175d100119331216011c5d111c1e111201171a16015d101c1e">[email protected]</span></a>; 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. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-0082.

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-2015-
0082; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this 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, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone 516-228-7329; fax 516-794-5531.

SUPPLEMENTARY INFORMATION:

Discussion

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Emergency Airworthiness 
Directive CF-2013-39R2, dated December 12, 2014 (referred to after this 
as the Mandatory Continuing Airworthiness Information, or ``the 
MCAI''), to correct an unsafe condition on certain Bombardier, Inc. 
Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-
601-3A, and CL-601-3R Variants) airplanes. The MCAI states:

    There have been three in-service reports on 604 Variant 
aeroplanes of a fractured fastener head on the inboard flap hinge-
box forward fitting at Wing Station (WS) 76.50, found during a 
routine maintenance inspection. Investigation revealed that the 
installation of these fasteners on the inboard flap hinge-box 
forward fittings at WS 76.50 and WS 127.25, on both wings, does not 
conform to the engineering drawings. Incorrect installation may 
result in premature failure of the fasteners attaching the inboard 
flap hinge-box forward fitting. Failure of the fasteners could lead 
to the detachment of the flap hinge box and consequently the 
detachment of the flap surface. The loss of a flap surface could * * 
* [result in reduced controllability of the airplane].
    The original issue of this [Canadian] AD [dated December 6, 
2013] [http://www.regulations.gov/#!documentDetail;D=FAA-2014-0054-
0002] [which corresponds to FAA AD 2014-03-17, Amendment 39-17754 
(79 FR 9389, February 19, 2014)] mandated a detailed visual 
inspection (DVI) of each inboard flap hinge-box forward fitting, on 
both wings, and rectification as required. Incorrectly oriented 
fasteners require repetitive inspections until the terminating 
action is accomplished.
    Although there have been no reported fractured fastener heads 
found to date on any model CL-600-1A11, -2A12 or -2B16 (601-3A-3R 
Variant) aeroplanes, incorrectly oriented fasteners may also be 
installed.
    After the issuance of the original [Canadian] AD [dated August 
15, 2014], there has been one reported incident on a 604 Variant 
aeroplane where four fasteners were found fractured on the same flap 
hinge-box forward fitting. The investigation determined that the 
fasteners were incorrectly installed.
    Revision 1 of this [Canadian] AD was issued to remove the 604 
Variant aeroplanes from the Applicability section since they were 
addressed in [Canadian] AD CF-2014-27 [dated August 15, 2014] [which 
corresponds to FAA AD 2014-17-51, Amendment 39-17999 (79 FR 64088, 
October 28, 2014)] and to clarify paragraphs A.2. and C of this 
[Canadian] AD so that it matched the Bombardier Alert Service 
Bulletins.
    After the issuance of Revision 1 of this [Canadian] AD, there 
have been several reports of incorrectly oriented fasteners found on 
CL-600-1A11, and -2B16 (601-3A Variant) aeroplanes. Although there 
have been no reports of fractured fasteners found to date, 
incorrectly oriented fasteners could result in the premature failure 
of the forward flap hinge-box fitting.
    Revision 2 of this [Canadian] AD is issued to reduce the initial 
and repetitive inspection intervals and to impose replacement of the 
incorrectly oriented fasteners * * *. This [Canadian] AD also 
corrects various terminology errors which were found in previous 
French versions of this [Canadian] AD.

You may examine the MCAI on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2015-0082.

Related Rulemaking

    On February 3, 2014, we issued AD 2014-03-17, Amendment 39-17754 
(79 FR 9389, February 19, 2014) for Bombardier, Inc. Model CL-600-1A11 
(CL-600) airplanes, having serial numbers (S/Ns) 1004 through 1085 
inclusive; Model CL-600-2A12 (CL-601) airplanes, having S/Ns 3001 
through 3066 inclusive; and Model CL-600-2B16 (CL-601-3A, CL-601-3R, & 
CL-604 Variants) airplanes, having S/Ns 5001 through 5194 inclusive, 
5301 through 5665 inclusive, and 5701 through 5920 inclusive. AD 2014-
03-17 requires repetitive inspections for fractured or incorrectly 
oriented fasteners on the inboard flap hinge-box forward fittings on 
both wings, and fastener replacement if necessary, and was prompted by 
two reports of fractured fastener heads found on the inboard flap 
hinge-box forward fitting. AD 2014-03-17 was issued to detect and 
correct incorrectly oriented or fractured fasteners, which could result 
in detachment of the flap hinge-box and the flap surface, and 
consequent reduced controllability of the airplane.
    After we issued AD 2014-03-17, Amendment 39-17754 (79 FR 9389, 
February 19, 2014), we received a report of an additional incident of 
fractured fasteners on a Model CL-600-2B16 (CL-604 Variant) airplane. 
We then issued AD 2014-17-51, Amendment 39-17999 (79 FR 64088, October 
28, 2014), as a ``stand-alone'' AD to reduce compliance times for the 
initial and repetitive inspections only for Model CL-600-2B16 airplanes 
having S/Ns 5301 through 5665 inclusive, and 5701 through 5920 
inclusive. Issuing AD 2014-17-51 as a ``stand-alone'' AD instead of 
superseding AD 2014-03-17 was determined to be clearer and less 
burdensome for operators with airplanes unaffected by the reduced 
compliance times required by AD 2014-17-51.
    Since we issued AD 2014-17-51, Amendment 39-17999 (79 FR 64088, 
October 28, 2014), we received a report of incorrectly oriented 
fasteners on a Model CL-600-1A11 airplane and on a Model CL-600-2B16 
(601-3A Variant) airplane. Consequently, we determined it was necessary 
to issue this AD to reduce compliance times for the other airplane 
models not affected by AD 2014-17-51. Doing so reduces the potential 
complexity for two groups of airplanes (those that are and are not 
affected by AD 2014-17-51).

Related Service Information Under 1 CFR Part 51

    Bombardier has issued Alert Service Bulletins A600-0763, Revision 
02, dated December 9, 2014, including Appendices 1 and 2, dated 
September 26, 2013; and A601-0627, Revision 02, dated December 9, 2014, 
including Appendices 1 and 2, dated September 26, 2013. The service 
information describes procedures for repetitive inspections of the 
fasteners on the inboard flap hinge-box forward fittings on both wings, 
and replacement of all fasteners, if necessary. The actions described 
in this service information are

[[Page 5672]]

intended to correct the unsafe condition identified in the MCAI. This 
service information is reasonably available; see ADDRESSES for ways to 
access this service information.

FAA's Determination and Requirements of This 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because we 
have received several reports of incorrectly oriented and fractured 
fasteners found on the inboard flap hinge-box forward fitting at WS 
76.50. Incorrectly oriented or fractured fasteners could result in 
detachment of the flap hinge-box and the flap surface, and consequent 
reduced controllability of the airplane. Therefore, we determined that 
notice and opportunity for public comment before issuing this AD are 
impracticable and that good cause exists for making this amendment 
effective in fewer than 30 days.

Interim Action

    We consider this AD interim action. We are currently considering 
requiring replacement of incorrectly oriented fasteners, which will 
constitute terminating action for the repetitive inspections required 
by this AD action. However, the planned compliance time for the 
replacement would allow enough time to provide notice and opportunity 
for prior public comment on the merits of the modification.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2015-0082; Directorate 
Identifier 2014-NM-233-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this 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 AD.

Costs of Compliance

    We estimate that this AD affects 120 airplanes of U.S. registry.
    We also estimate that it will take about 1 work-hour per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD on U.S. operators to be $10,200, or $85 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 58 work-hours and require parts costing $753, for a cost of 
$5,683 per product. We have no way of determining the number of 
aircraft that might need this action.
    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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 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. 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.

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):

2015-02-23 Bombardier, Inc.: Amendment 39-18092. Docket No. FAA-
2015-0082; Directorate Identifier 2014-NM-233-AD.

(a) Effective Date

    This AD becomes effective February 18, 2015.

(b) Affected ADs

    This AD affects AD 2014-03-17, Amendment 39-17754 (79 FR 9389, 
February 19, 2014).

(c) Applicability

    This AD applies to the Bombardier, Inc. airplanes identified in 
paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in 
any category.
    (1) Bombardier, Inc. Model CL-600-1A11 (CL-600) airplanes, 
having serial numbers (S/Ns) 1004 through 1085 inclusive.
    (2) Bombardier, Inc. Model CL-600-2A12 (CL-601) airplanes, 
having S/Ns 3001 through 3066 inclusive.

[[Page 5673]]

    (3) Bombardier, Inc. Model CL-600-2B16 (CL-601-3A and CL-601-3R 
Variants) airplanes, having S/Ns 5001 through 5194 inclusive.

(d) Subject

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

(e) Reason

    This AD was prompted by several reports of incorrectly oriented 
and fractured fasteners found on the inboard flap hinge-box forward 
fitting at wing station (WS) 76.50. We are issuing this AD to detect 
and correct incorrectly oriented or fractured fasteners, which could 
result in detachment of the flap hinge-box and the flap surface, and 
consequent reduced controllability of the airplane.

(f) Compliance

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

(g) Inspection on Airplanes Not Previously Inspected

    For airplanes that have not been inspected as required by 
paragraph (g) of AD 2014-03-17, Amendment 39-17754 (79 FR 9389, 
February 19, 2014), as of the effective date of this AD: Within 10 
flight cycles after the effective date of this AD or 100 flight 
cycles after March 6, 2014 (the effective date of AD 2014-03-17), 
whichever occurs first, do a detailed visual inspection for 
incorrect orientation and any fractured or missing fastener heads of 
each inboard flap fastener of the hinge-box forward fitting at WS 
76.50 and WS 127.25, on both wings, in accordance with the 
Accomplishment Instructions of the applicable service information 
specified in paragraphs (g)(1) and (g)(2) of this AD. Accomplishing 
the inspection required by this paragraph terminates the 
requirements of paragraph (g) of AD 2014-03-17 for the inspected 
airplane only.
    (1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, 
Revision 02, dated December 9, 2014, including Appendices 1 and 2, 
dated September 26, 2013.
    (2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: 
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated 
December 9, 2014, including Appendices 1 and 2, dated September 26, 
2013.

(h) Corrective Actions for Paragraph (g) of This AD

    (1) If, during any inspection required by paragraph (g) of this 
AD, all fasteners are found correctly oriented and not fractured, 
and no fastener heads are missing (fasteners found intact): No 
further action is required by this AD.
    (2) If, during any inspection required by paragraph (g) of this 
AD, any fastener is found incorrectly oriented but no fasteners are 
fractured or are missing a fastener head (fasteners found intact), 
repeat the inspection required by paragraph (g) of this AD 
thereafter at intervals not to exceed 10 flight cycles until the 
replacement specified in paragraph (h)(3) or (k) of this AD is 
accomplished.
    (3) If, during any inspection required by paragraph (g) of this 
AD, any fastener is found fractured or has a missing fastener head: 
Before further flight, remove and replace all forward and aft 
fasteners (regardless of orientation or condition) at WS 76.50 and 
WS 127.25, on both wings, in accordance with the Accomplishment 
Instructions of the applicable service information specified in 
paragraphs (h)(3)(i) and (h)(3)(ii) of this AD, except as required 
by paragraph (m) of this AD. After accomplishing the replacement 
required by this paragraph, no further action is required by this 
AD.
    (i) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, 
Revision 02, dated December 9, 2014, including Appendices 1 and 2, 
dated September 26, 2013.
    (ii) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: 
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated 
December 9, 2014, including Appendices 1 and 2, dated September 26, 
2013.

(i) Inspection for Airplanes Previously Inspected and Found To Have 
Incorrectly Oriented Fastener(s)

    For airplanes on which an inspection required by paragraph (g) 
or (j) of AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 
19, 2014), has been done as of the effective date of this AD, and on 
which any incorrectly oriented fastener was found but no fasteners 
were fractured (fasteners found intact): Except as provided by 
paragraph (l) of this AD, within 10 flight cycles after the 
effective date of this AD, or within 100 flight cycles after 
accomplishing the most recent inspection required by AD 2014-03-17, 
whichever occurs first, do a detailed visual inspection for any 
fractured or missing fastener heads of each inboard flap fastener of 
the hinge-box forward fitting at WS 76.50 and WS 127.25, on both 
wings. Do the inspection in accordance with the Accomplishment 
Instructions of the applicable service information specified in 
paragraphs (i)(1) and (i)(2) of this AD. Accomplishing the 
inspection required by this paragraph terminates the requirements of 
paragraphs (g) and (j) of AD 2014-03-17 for the inspected airplane 
only.
    (1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, 
Revision 02, dated December 9, 2014, including Appendices 1 and 2, 
dated September 26, 2013.
    (2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: 
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated 
December 9, 2014, including Appendices 1 and 2, dated September 26, 
2013.

(j) Corrective Actions for Paragraph (i) of This AD

    (1) If, during any inspection required by paragraph (i) of this 
AD, no fasteners are found fractured or have missing fastener heads 
(fasteners are intact), repeat the inspection required by paragraph 
(i) of this AD thereafter at intervals not to exceed 10 flight 
cycles until the replacement specified in paragraph (j)(2) or (k) of 
this AD is accomplished.
    (2) If, during any inspection required by paragraph (i) of this 
AD, any fastener is found fractured or has a missing fastener head: 
Before further flight, remove and replace all forward and aft 
fasteners (regardless of orientation or condition) at WS 76.50 and 
WS 127.25, on both wings, in accordance with the Accomplishment 
Instructions of the applicable service information specified in 
paragraphs (j)(2)(i) and (j)(2)(ii) of this AD, except as required 
by paragraph (m) of this AD. After accomplishing the replacement 
required by this paragraph, no further action is required by this 
AD.
    (i) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, 
Revision 02, dated December 9, 2014, including Appendices 1 and 2, 
dated September 26, 2013.
    (ii) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: 
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated 
December 9, 2014, including Appendices 1 and 2, dated September 26, 
2013.

(k) Optional Terminating Action for Incorrectly Oriented Fasteners

    Replacement of all forward and aft fasteners (regardless of 
orientation or condition) at WS 76.50 and WS 127.25, on both wings, 
terminates the requirements of this AD. The replacement must be done 
in accordance with the Accomplishment Instructions of the applicable 
service information specified in paragraphs (k)(1) and (k)(2) of 
this AD, except as provided by paragraph (m) of this AD. Doing the 
replacement specified in this paragraph terminates the requirements 
of paragraphs (g) and (j) of AD 2014-03-17, Amendment 39-17754 (79 
FR 9389, February 19, 2014), only for the airplane on which the 
replacement was done.
    (1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004 
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763, 
Revision 02, dated December 9, 2014, including Appendices 1 and 2, 
dated September 26, 2013.
    (2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001 
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive: 
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated 
December 9, 2014,

[[Page 5674]]

including Appendices 1 and 2, dated September 26, 2013.

(l) Exception for Previously Replaced Fasteners

    Replacement of all fractured and incorrectly oriented forward 
and aft fasteners, as specified in paragraph (i) or (k) of AD 2014-
03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014), if done 
before the effective date of this AD, is considered acceptable for 
compliance with the requirements of this AD.

(m) Exception to the Service Information

    Where Bombardier Alert Service Bulletin A600-0763, Revision 02, 
dated December 9, 2014, including Appendices 1 and 2, dated 
September 26, 2013; and Bombardier Alert Service Bulletin A601-0627, 
Revision 02, dated December 9, 2014, including Appendices 1 and 2, 
dated September 26, 2013; specify to contact Bombardier for repair 
instructions, 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's TCCA 
Design Approval Organization (DAO).

(n) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g), (h), and (i) of this AD, if those actions were 
performed before the effective date of this AD using the applicable 
service information identified in paragraphs (n)(1) through (n)(4) 
of this AD.
    (1) Bombardier Alert Service Bulletin A600-0763, including 
Appendices 1 and 2, dated September 26, 2013, which was previously 
incorporated by reference on March 6, 2014 (79 FR 9389, February 19, 
2014).
    (2) Bombardier Alert Service Bulletin A600-0763, Revision 01, 
dated February 26, 2014, including Appendices 1 and 2, dated 
September 26, 2013, which is not incorporated by reference in this 
AD.
    (3) Bombardier Alert Service Bulletin A601-0627, including 
Appendices 1 and 2, dated September 26, 2013, which was previously 
incorporated by reference on March 6, 2014 (79 FR 9389, February 19, 
2014).
    (4) Bombardier Alert Service Bulletin A601-0627, Revision 01, 
dated February 26, 2014, including Appendices 1 and 2, dated 
September 26, 2013, which is not incorporated by reference in this 
AD.

(o) 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, Engine and Propeller Directorate, FAA; or TCCA; or 
Bombardier, Inc.'s TCCA DAO. If approved by the DAO, the approval 
must include the DAO-authorized signature.

(p) Special Flight Permits

    Special flight permits to operate the airplane to a location 
where the airplane can be repaired in accordance with sections 
21.197 and 31.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199) are not allowed.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Emergency Airworthiness Directive CF-2013-39R2, 
dated December 12, 2014, for related information. You may examine 
the MCAI on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2015-0082.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (r)(3) and (r)(4) of this AD.

(r) 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 Alert Service Bulletin A600-0763, Revision 02, 
dated December 9, 2014, including Appendices 1 and 2, dated 
September 26, 2013.
    (ii) Bombardier Alert Service Bulletin A601-0627, Revision 02, 
dated December 9, 2014, including Appendices 1 and 2, dated 
September 26, 2013.
    (3) For service information identified in this AD, contact 
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email <a href="/cdn-cgi/l/email-protection#e99d818dc78a9b83a9888c9b86c78b86848b889b8d808c9bc78a8684"><span class="__cf_email__" data-cfemail="8afee2eea4e9f8e0caebeff8e5a4e8e5e7e8ebf8eee3eff8a4e9e5e7">[email protected]</span></a>; Internet http://www.bombardier.com.
    (4) 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.
    (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 Renton, Washington, on January 20, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-01661 Filed 2-2-15; 8:45 am]
BILLING CODE 4910-13-P


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