[Federal Register Volume 60, Number 244 (Wednesday, December 20, 1995)]
[Rules and Regulations]
[Pages 65521-65523]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-30961]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-238-AD; Amendment 39-9465; AD 95-26-07]
Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional
Jet Series 100) Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain Bombardier Model CL-600-2B19 series airplanes.
This action requires revising the Limitations Section of the Airplane
Flight Manual to provide the flight crew with procedures to check the
travel range of the aileron. This action also requires inspection for
damage of the shear pins of the aileron flutter damper and aileron
hinge fittings, and various follow-on actions. This amendment is
prompted by reports of failure of shear pins in the aileron flutter
damper. The actions specified in this AD are intended to prevent damage
to the aileron hinge fittings due to failed shear pins, which
subsequently could cause reduced controllability of the airplane.
DATES: Effective January 4, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 4, 1996.
Comments for inclusion in the Rules Docket must be received on or
before February 20, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-238-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
The service information referenced in this AD may be obtained from
Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station
Centre-ville, Quebec H3C 3G9, Canada. This information may be examined
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW.,
Renton, Washington; or at the FAA, New York Aircraft Certification
Office, Engine and Propeller Directorate, 10 Fifth Street, Third Floor,
Valley Stream, New York; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Franco Pieri, Aerospace Engineer,
Airframe Branch, ANE-172, FAA, Engine and Propeller Directorate, New
York Aircraft Certification Office, 10 Fifth Street, Third Floor,
Valley Stream, New York 11581; telephone (516) 256-7526; fax (516) 568-
2716.
SUPPLEMENTARY INFORMATION: Transport Canada Aviation, which is the
airworthiness authority for Canada, recently notified the FAA that an
unsafe condition may exist on certain Bombardier Model CL-600-2B19
(Regional Jet Series 100) series airplanes. Transport Canada Aviation
advises that it has received reports indicating that the shear pins of
the aileron flutter damper had failed. Investigation revealed that the
shear pins had sheared off and migrated out, which subsequently damaged
the aileron hinge fittings. This condition, if not corrected, could
result in reduced controllability of the airplane.
Bombardier has issued Canadair Regional Jet Alert Service Bulletin
S.B. A601R-27-058, Revision ``A,'' dated September 8, 1995, which
describes procedures for:
1. A visual inspection to detect damage of the shear link, the
shear pin, and the aileron attachment fitting;
2. Repair of the aileron attachment fitting, if necessary;
3. For airplanes on which any damaged shear pin is found, removal
of the aileron flutter dampers, the shear links, the pivots, and the
attaching hardware;
4. For certain airplanes on which no damaged shear pin is found,
repetitive visual inspections to detect damage of the shear link, the
shear pin, and the aileron attachment fitting until the aileron flutter
dampers are removed.
[[Page 65522]]
Transport Canada Aviation classified the alert service bulletin as
mandatory, and issued Canadian airworthiness directive CF-95-14, dated
September 11, 1995, in order to assure the continued airworthiness of
these airplanes in Canada.
This airplane model is manufactured in Canada and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, Transport Canada Aviation has kept
the FAA informed of the situation described above. The FAA has examined
the findings of Transport Canada Aviation, reviewed all available
information, and determined that AD action is necessary for products of
this type design that are certificated for operation in the United
States.
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, this AD is being issued to prevent damage to the
aileron hinge fittings due to the failure of the shear pins, which
could cause subsequent reduced controllability of the airplane. This AD
requires revising the Limitations Section of the FAA-approved Airplane
Flight Manual to provide the flight crew with procedures to check the
travel range of the aileron prior to the first flight of the day. Such
checks are necessary to verify proper operation of the aileron control
system. The FAA has determined that these checks may be properly
performed by pilots because the checks do not require the use of tools,
precision measuring equipment, training, pilot logbook endorsements, or
the use of reference to technical data that are not contained in the
body of the AD.
This AD also requires a visual inspection to detect damage of the
shear link, the shear pin, and the aileron attachment fitting; and
repair of the aileron attachment fitting, if necessary. This AD also
requires removal of the aileron flutter dampers, the shear links, the
pivots, and the attaching hardware for airplanes on which any damage to
the shear pin is detected. For certain airplanes on which no damaged
shear pin is found, this AD provides for accomplishment of the visual
inspections on a repetitive basis until the aileron flutter dampers are
removed. These actions are required to be accomplished in accordance
with the alert service bulletin described previously.
Operators should note that, although the relevant Transport Canada
Aviation airworthiness directive requires the visual inspection of all
aileron flutter damper shear pins and aileron hinge fittings within 7
calendar days or at the next scheduled shear pin replacement, this AD
requires that inspection to be performed within 30 days. The FAA has
determined that an interval of 30 days will address the identified
unsafe condition in a timely manner. In recent communications with
Transport Canada Aviation and the manufacturer, the FAA finds that the
unsafe condition was not as urgent as it initially appeared to be. In
developing an appropriate compliance time for this AD, the FAA
considered not only the manufacturer's recommendation, but also the
average utilization of the affected fleet and the time necessary to
perform the required actions (10 work hours). In light of all these
factors, the FAA finds 30 days to be an appropriate compliance time for
initiating the required actions in that it represents the maximum
interval of time allowable for affected airplanes to continue to
operate without compromising safety.
This is considered to be interim action. Once a terminating
modification is developed, approved, and available, the FAA may
consider additional rulemaking.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications shall identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 95-NM-238-AD.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will not have substantial direct
effects 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. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, may be obtained from the Rules Docket at the
location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
[[Page 65523]]
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-26-07 Bombardier, Inc. (Formerly Canadair): Amendment 39-9465.
Docket 95-NM-238-AD.
Applicability: Model CL-600-2B19 (Regional Jet Series 100)
series airplanes, serial numbers 7003 through 7079 inclusive;
certificated in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
modified, altered, or repaired in the area subject to the
requirements of this AD. For airplanes that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must use the authority
provided in paragraph (e) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition; or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent damage to the aileron hinge fittings due to failure
of the shear pins, which could cause subsequent reduced
controllability of the airplane; accomplish the following:
(a) Within 7 days after the effective date of this AD, revise
the Limitations Section of the FAA-approved Airplane Flight Manual
(AFM) to include the following. This may be accomplished by
inserting a copy of this AD in the AFM.
``Before engine start, prior to the first flight of each day,
the flight crew or certificated maintenance personnel shall perform
a check of the travel range of the aileron as follows:
Aileron--Check travel range (to approx \1/2\ travel) using each
hydraulic system in turn, with the other hydraulic systems
depressurized.''
Note 2: This AFM revision may also be accomplished by inserting
a copy of Temporary Revision RJ/45, dated September 7, 1995, in the
AFM. When this temporary revision has been incorporated into general
revisions of the AFM, the general revisions may be inserted in the
AFM, provided the information contained in the general revisions is
identical to that specified in Temporary Revision RJ/45.
Note 3: Operators should note that operation of the aircraft
remains restricted to the altitude and airspeed limits currently
specified in the FAA-approved AFM, Revision 34, Chapter 5, Abnormal
Procedures, Section 13, Hydraulic Power, Paragraphs ``A'' through
``C'' and ``M'' through ``O.''
(b) Perform a visual inspection to detect damage of the shear
link, the shear pin, and the aileron attachment fitting, in
accordance with Canadair Regional Jet Alert Service Bulletin S.B.
A601R-27-058, Revision `A,' dated September 8, 1995, and at the time
specified in paragraph (b)(1) or (b)(2) of this AD, as applicable.
(1) For airplanes having serial numbers 7003 through 7054
inclusive: Inspect at the next scheduled shear pin replacement, but
no later than 30 days after the effective date of the AD.
(2) For airplanes having serial numbers 7055 through 7079
inclusive: Inspect at the next scheduled shear pin replacement, but
no later than 400 flight hours after the effective date of the AD.
(c) If no shear pin is found to be damaged during the inspection
required by paragraph (b) of this AD, accomplish the requirements of
either paragraph (c)(1) or (c)(2), as applicable, at the times
specified:
(1) For airplanes having serial numbers 7003 through 7054
inclusive: At the next scheduled shear pin replacement, but no later
than 400 flight hours after accomplishing the inspection specified
in paragraph (b) of this AD, remove the aileron flutter dampers,
shear link, and pivot, in accordance with Canadair Regional Jet
Alert Service Bulletin S.B. A601R-27-058, Revision `A,' dated
September 8, 1995. Following removal of the flutter dampers, the
shear pin replacement in accordance with the FAA-approved
maintenance program is not required.
(2) For airplanes having serial numbers 7055 through 7079
inclusive: Repeat the inspection required by paragraph (b) of this
AD at intervals not to exceed 400 flight hours. At the next
scheduled shear pin replacement, but no later than 1,500 landings
after accomplishing the initial inspection specified in paragraph
(b) of this AD, remove the aileron flutter dampers, shear link, and
pivot, in accordance with Canadair Regional Jet Alert Service
Bulletin S.B. A601R-27-058, Revision `A,' dated September 8, 1995.
Following removal of the flutter dampers, the shear pin replacement
in accordance with the FAA-approved maintenance program is not
required.
(d) If any shear pin is found to be damaged during the
inspection required by paragraph (b) of this AD, prior to further
flight, remove the aileron flutter dampers, shear link, and pivot,
in accordance with Canadair Regional Jet Alert Service Bulletin S.B.
A601R-27-058, Revision `A,' dated September 8, 1995. Following
removal of the flutter dampers, shear pin replacement in accordance
with the FAA-approved maintenance program is not required.
(e) If any aileron hinge fitting is found to be damaged during
the inspection required by paragraph (b) of this AD, prior to
further flight, repair in accordance with Canadair Regional Jet
Alert Service Bulletin S.B. A601R-27-058, Revision `A,' dated
September 8, 1995.
(f) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, New York Aircraft Certification
Office (ACO), FAA, Engine and Propeller Directorate. Operators shall
submit their requests through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, New York ACO.
Note 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the New York ACO.
(g) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
(h) The inspections, removal, and repair shall be done in
accordance with Canadair Regional Jet Alert Service Bulletin S.B.
A601R-27-058, Revision `A,' dated September 8, 1995. This
incorporation by reference was approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. Copies may be obtained from Bombardier, Inc., Canadair,
Aerospace Group, P.O. Box 6087, Station Centreville, Quebec H3C 3G9,
Canada. Copies may be inspected at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
FAA, New York Aircraft Certification Office, Engine and Propeller
Directorate, 10 Fifth Street, Third Floor, Valley Stream, New York;
or at the Office of the Federal Register, 800 North Capitol Street
NW., suite 700, Washington, DC.
(i) This amendment becomes effective on January 4, 1996.
Issued in Renton, Washington, on December 13, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-30961 Filed 12-19-95; 8:45 am]
BILLING CODE 4910-13-U
