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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0581; Directorate Identifier 2014-NM-167-AD;
Amendment 39-17999; AD 2014-17-51]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), 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-600-2B16 airplanes. This emergency AD was
sent previously to all known U.S. owners and operators of these
airplanes. This AD requires inspecting the inboard flap fasteners of
the hinge-box forward fitting at Wing Station (WS) 76.50 and WS 127.25
to determine the orientation and condition of the fasteners, as
applicable, and replacement or repetitive inspections of the fasteners
if necessary. This AD also provides for optional terminating action for
the requirements of the AD. This AD was prompted by reports of
fractured fastener heads on the inboard flap hinge-box forward fitting
at WS 76.50 due to incorrect installation. We are issuing this AD to
detect and correct incorrectly oriented or fractured fasteners, which
could
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 the flap surface, and consequent loss of
control of the airplane.
DATES: This AD is effective November 12, 2014 to all persons except
those persons to whom it was made immediately effective by Emergency AD
2014-17-51, issued on August 19, 2014, which contained the requirements
of this amendment.
The Director of the Federal Register approved the incorporation by
reference of certain publications identified in this AD as of November
12, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of March
6, 2014 (79 FR 9389, February 19, 2014).
We must receive comments on this AD by December 12, 2014.
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 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
thd.crj@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 by searching for and locating Docket No. FAA-2014-
0581; 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
(phone: 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,
Propulsion and Services Branch, ANE-173, 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:
Discussion
On August 19, 2014, we issued Emergency AD 2014-17-51, which
requires inspecting the inboard flap fasteners of the hinge-box forward
fitting at WS 76.50 and WS 127.25 to determine the orientation and
condition of the fasteners, as applicable, and replacement or
repetitive inspections of the fasteners if necessary. Emergency AD
2014-17-51 also provides for optional terminating action for the
requirements of the AD. This emergency AD was sent previously to all
known U.S. owners and operators of these airplanes. This action was
prompted by reports of fractured fastener heads on the inboard flap
hinge-box forward fitting at Wing Station (WS) 76.50 due to incorrect
installation. This condition, if not corrected, could 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 the flap surface, and consequent loss of
control of the airplane.
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Emergency Airworthiness
Directive CF-2014-27, dated August 15, 2014 (referred to after this as
the Mandatory Continuing Airworthiness Information, or ``the MCAI''),
to correct an unsafe condition on certain Model CL-600-2B16 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
adversely affect the continued safe operation of the aeroplane.
The original issue of AD CF-2013-39 [dated December 6, 2013]
[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.
After the issuance of AD CF-2013-39, 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.
This [Canadian] AD is issued to reduce the initial and
repetitive inspection intervals previously mandated in AD CF-2013-
39, and to impose replacement of the incorrectly oriented fasteners
within 24 months. The CL-600-1A11, -2A12 and -2B16 (601-3A/-3R
Variant) aeroplanes are addressed through AD CF-2013-39R1 [dated
August 15, 2014].
You may examine the MCAI on the Internet at http://www.regulations.gov
by searching for and locating Docket No. FAA-2014-0581.
Relevant Service Information
We reviewed the following service information:
Bombardier Alert Service Bulletin A604-57-006, Revision
01, dated September 26, 2013, including Appendices 1 and 2, dated
September 26, 2013.
Bombardier Alert Service Bulletin A604-57-006, Revision
02, dated January 22, 2014, including Appendices 1 and 2, dated
September 26, 2013.
Bombardier Alert Service Bulletin A605-57-004, Revision
01, dated September 26, 2013, including Appendices 1 and 2, dated
September 26, 2013.
Bombardier Alert Service Bulletin A605-57-004, Revision
02, dated January 22, 2014, including Appendices 1 and 2, dated
September 26, 2013.
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
Revision 02 of the service information instructs operators to
contact Bombardier for repair procedures for certain configurations;
paragraph (k)(2) of this AD addresses this issue.
FAA's Determination and AD Requirements
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 the same type design.
Accomplishment of the requirements of this AD constitutes
terminating action for the requirements of AD 2014-03-17, Amendment 39-
17754 (79 FR 9389, February 19, 2014), for the airplanes identified in
paragraph (c) of this AD.
FAA AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19,
2014), corresponds to Canadian AD CF-2013-39, dated December 6, 2013.
FAA AD 2014-03-17 applies to Bombardier, Inc. Model CL-600-1A11 (CL-
600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and
CL-604 Variants) airplanes. Because of the urgency of this unsafe
condition for the CL-604 Variant airplanes, we have determined that it
is necessary to issue an emergency AD, only for CL-604 Variant
airplanes, to reduce the compliance times for the inspection required
by AD 2014-03-17.
Explanation of Applicability
This AD applies to Bombardier, Inc. Model CL-600-2B16 airplanes
with certain serial numbers. The CL-605 is a marketing designation for
the Challenger CL-600-2B16, CL-604 Variant, with Modsums 604DX10000,
604DX20000, and 604DX30000 incorporated, beginning with serial numbers
5701 and subsequent. All CL-604 and CL-605 airplanes are type certified
as CL-600-2B16 airplanes. Therefore this AD applies to all CL-600-2B16
models in the specified serial-number range.
Differences Between This AD and the MCAI/Service Information
Canadian Airworthiness Directive CF-2014-27, dated August 15, 2014,
specifies to replace all forward and aft fasteners at WS 76.50 and
127.25 within 24 months, if any incorrectly installed fasteners are
found. We are considering requiring this replacement, which would
terminate the actions required by this AD. 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
replacement.
Although the service information identified previously specifies
that operators may contact the manufacturer for disposition of certain
repair conditions, this AD requires operators to repair those
conditions in accordance with a method approved by the FAA, or TCCA, or
Bombardier, Inc.'s TCCA Design Approval Organization (DAO).
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
incorrect installation of the fasteners attaching the inboard flap
hinge-box forward fitting may result in their premature failure, and
possible detachment of the flap hinge box and the flap surface, and
loss of control of the airplane. Therefore, we find that notice and
opportunity for prior public comment are impracticable and that good
cause exists for making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send any written data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include the docket number FAA-2014-0581 and
Directorate Identifier 2014-NM-167-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 because of 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 285 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
|
Action
|
Labor cost
|
Parts cost
|
Cost per
product
|
Cost on
U.S.
operators
|
| Inspection |
1 work-hour x $85 per hour =
$85 |
$0
|
$85
|
$24,225
|
We estimate the following costs to
do any necessary replacements
that would be required based on the results of the inspection. We have
no way of determining the number of aircraft that might need these
replacements:
On-Condition Costs
|
Action
|
Labor cost
|
Parts cost
|
Cost per
product
|
| Fastener replacement |
Up to 58 work-hours x $85 per
hour = $4,930 |
$0
|
$4,930
|
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
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 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
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]
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
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