[Federal Register Volume 61, Number 216 (Wednesday, November 6, 1996)]
[Rules and Regulations]
[Pages 57319-57322]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-27922]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-NM-208-AD; Amendment 39-9803; AD 96-22-14]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional
Jet Series 100 and 200) 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 (Regional Jet
Series 100 and 200) airplanes. This action requires repetitive
inspections to detect discrepancies of the shock strut end caps and
attachment pins of the main landing gear (MLG), and replacement of
discrepant parts with new parts. It also requires a check for and
replacement of certain pins that currently may be installed on some
airplanes. This amendment is prompted by reports of corrosion, wear,
and loss of chrome plating on the upper and lower attachment pins of
the shock strut of the MLG, and reports of cracks in the lower
attachment pins and the end cap of upper attachment pins. The actions
specified in this AD are intended to prevent failure of attachment pin
and the attachment pin's end cap, which could result in failure of the
MLG.
DATES: Effective November 21, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 21, 1996.
Comments for inclusion in the Rules Docket must be received on or
before January 6, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-208-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
The service information referenced in this AD may be obtained from
Bombardier Inc., Bombardier Regional Aircraft Division, Canadair
Administrative Center, 400 Cote Vertu Road West, Dorval, Quebec, Canada
H4S 1Y9; and Messier-Dowty CSC, P.O. Box 49, Sterling, Virginia, 20167.
This information may be examined at the FAA, Transport Airplane
Directorate,
[[Page 57320]]
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: George Duckett, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, Engine and Propeller Directorate, 10 Fifth
Street, Third Floor, Valley Stream, New York 11581; telephone (516)
256-7525; 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 and 200) airplanes. Transport Canada Aviation
advises that it has received several reports of cracks in the lower
attachment pins and one of the two end caps, which retain the upper
attachment of the shock strut. The cause of such cracking is unknown at
this time. Cracking in the subject attachment pin could result in
failure of the pin and consequent failure of the MLG. Cracking in the
subject end cap could result in loss of the end cap and possible loss
of the retaining pin holding the upper end of the shock strut to the
main fitting; this situation ultimately could result in failure of the
MLG.
Explanation of Relevant Service Information
Bombardier has issued Canadair Regional Jet Alert Service Bulletin
S.B. A601R-32-062, Revision `C', dated September 18, 1996. In addition,
Messier-Dowty has issued Service Bulletin M-DT 17002-32-10, Revision 3,
dated September 6, 1996. For certain airplanes, these service bulletins
describe procedures for performing a check to determine the serial
number of the lower attachment pin of the shock strut of each main
landing gear, removal of certain pins, and the installation of new
pins, if necessary. These service bulletins also describe procedures
for performing repetitive in-situ and detailed inspections to detect
corrosion, wear, loss of chrome plating, and cracking of the MLG shock
strut upper and lower attachment pins and pin end caps. They also
describe procedures for replacement of discrepant parts with new parts.
Transport Canada Aviation classified these service bulletins as
mandatory and issued Canadian airworthiness directive CF-96-12, dated
July 23, 1996, in order to assure the continued airworthiness of these
airplanes in Canada.
FAA's Conclusions
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.
Explanation of Requirements of Rule
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 failure of the
attachment pins and end caps of the MLG, which could result in failure
of the MLG. For certain airplanes, this AD requires a check to
determine the serial number of the lower attachment pin of the shock
strut of each main landing gear, removal of certain pins, and the
installation of new pins, if necessary. This AD also requires
repetitive in-situ visual and detailed inspections to detect
discrepancies of the left and right-hand shock struts of the MLG, and
replacement of discrepant parts with new parts. Those actions are
required to be accomplished in accordance with the service bulletins
described previously.
Interim Action
This is considered to be interim action. The manufacturer has
advised that it currently is developing a modification that will
positively address the unsafe condition addressed by this AD. Once this
modification is developed, approved, and available, the FAA may
consider additional rulemaking.
Determination of Rule's Effective Date
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 96-NM-208-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
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
[[Page 57321]]
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:
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. Section 39.13 is amended by adding the following new
airworthiness directive:
96-22-14 Bombardier, Inc. (Formerly Canadair): Amendment 39-9803.
Docket 96-NM-208-AD.
Applicability: Model CL-600-2B19 (Regional Jet Series 100 and
200) airplanes; serial numbers 7003 through 7160, 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 request approval for an
alternative method of compliance in accordance with paragraph (e) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the attachment pins and end caps of the
main landing gear (MLG), which could result in failure of the MLG,
accomplish the following:
(a) Serial Number Check. For airplanes having serial numbers
7003 through 7126, inclusive: Within 150 landings after the
effective date of this AD, check the serial number of each MLG shock
strut lower attachment pin, part number 17144-1, in accordance with
paragraphs 2.A. and 2.B. of the Accomplishment Instructions of
Canadair Regional Jet Alert Service Bulletin S.B. A601R-32-062,
Revision 'C', dated September 18, 1996; and paragraphs 2.A.(4),
2.B.(4), and 2.C.(3) of the Accomplishment Instructions of Messier-
Dowty Service Bulletin M-DT 17002-32-10, Revision 3, dated September
6, 1996.
(1) If the serial number is within the range of DCL206 through
DCL259, inclusive, prior to further flight, remove the pin and
install a new pin having a serial number outside (either higher or
lower) of that range, in accordance with the service bulletins.
Thereafter, inspect that replacement pin in accordance with
paragraphs (b) and (c) of this AD.
(2) If the serial number is outside of the range (higher or
lower) of DCL206 through DCL259, thereafter inspect the pin in
accordance with paragraphs (b) and (c) of this AD.
(b) In-Situ Visual Inspection. Within 150 landings after the
effective date of this AD, perform an in-situ visual inspection to
detect discrepancies of the left- and right-hand shock strut of the
MLG, in accordance with paragraphs 2.C. and 2.D. of the
Accomplishment Instructions of Canadair Regional Jet Alert Service
Bulletin S.B. A601R-32-062, Revision 'C', dated September 18, 1996;
and paragraph 2.B.(1) of the Accomplishment Instructions of Messier-
Dowty Service Bulletin M-DT 17002-32-10, Revision 3, dated September
6, 1996.
Note 2: In-situ visual inspections that have been accomplished
prior to the effective date of this amendment in accordance with
Messier-Dowty Service Bulletin M-DT 17002-32-10, dated June 13,
1996; Revision 1, dated June 29, 1996; or Revision 2, dated July 17,
1996; are considered acceptable for compliance with paragraph (b) of
this amendment.
(1) If no discrepancy is detected, repeat the in-situ visual
inspection thereafter at intervals not to exceed every ``A'' check
or 400 landings, whichever occurs later.
(2) If any discrepancy is detected, prior to further flight,
replace the discrepant part with a new part in accordance with the
service bulletins. Thereafter, repeat the in- situ visual inspection
at intervals not to exceed every ``A'' check or 400 landings,
whichever occurs later.
(c) Detailed Inspection. Within 3,000 landings since the date of
airplane manufacture, or within 400 landings after the effective
date of this AD, whichever occurs later, perform a detailed
inspection to detect discrepancies of the shock strut end caps and
attachment pins of the MLG, in accordance with paragraphs 2.E. and
2.F. of the Accomplishment Instructions of Canadair Regional Jet
Alert Service Bulletin S.B. A601R-32-062, Revision `C', dated
September 18, 1996; and paragraph 2.B.(2) of the Accomplishment
Instructions of Messier-Dowty Service Bulletin M-OT 17002-32-10,
Revision 3, dated September 6, 1996. Non-destructive testing (NDT)
must be accomplished in accordance with the instructions provided or
references referred to in these service bulletins. Where
instructions in those documents specify dye penetrant inspections
(DPI), accomplish fluorescent penetrant (Type 1) inspections,
sensitivity level 3 or higher, using material qualified to Military
Standard MIL-I-25135.
Note 3: Detailed inspections accomplished prior to the effective
date of this amendment in accordance with Messier-Dowty Service
Bulletin M-DT 17002-32-10, dated June 13, 1996; Revision 1, dated
June 29, 1996; or Revision 2, dated July 17, 1996; are considered
acceptable for compliance with paragraph (c) of this amendment.
(1) If no discrepancy is detected, repeat the detailed
inspection thereafter at intervals not to exceed 2,000 landings.
(2) If any discrepancy is detected, prior to further flight,
replace the discrepant part with a new part in accordance with the
service bulletins. Repeat the detailed inspection thereafter at
intervals not to exceed 2,000 landings.
(d) As of the effective date of this AD, no person shall install
on any airplane an MLG shock strut lower attachment pin, part number
17144-1, that has a serial number that is within the range of DCL206
through DCL259, inclusive.
(e) 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 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.
(f) 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.
(g) The specified actions shall be done in accordance with
Messier-Dowty Service Bulletin No. M-DT 17002-32-10, Revision 3,
dated September 6, 1996, and Canadair Regional Jet Alert Service
Bulletin S.B. A601R-32-062, Revision `C', dated September 18, 1996.
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., Bombardier Regional
Aircraft Division, Canadair Administrative Center, 400 Cote Vertu
Road West, Dorval, Quebec, Canada H4S 1Y9. 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 November 21, 1996.
[[Page 57322]]
Issued in Renton, Washington, on October 24, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-27922 Filed 11-5-96; 8:45 am]
BILLING CODE 4910-13-U