[Federal Register Volume 62, Number 222 (Tuesday, November 18, 1997)]
[Rules and Regulations]
[Pages 61436-61438]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-30104]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-285-AD; Amendment 39-10209; AD 97-24-02]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-1A11, -2A12,
and -2B16 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-600-1A11, -2A12, and -2B16
series airplanes. This action requires repetitive inspections to detect
cracks of a certain bulkhead web of the fuselage at certain locations,
and repair, if necessary. This amendment is prompted by issuance of
mandatory continuing airworthiness information by a foreign civil
airworthiness authority. The actions specified in this AD are intended
to detect and correct cracking in the pressure bulkhead at frame
station (FS) 409.00, which could result in uncontrolled
depressurization of the airplane and/or reduced structural integrity of
the fuselage.
DATES: Effective December 3, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 3, 1997.
Comments for inclusion in the Rules Docket must be received on or
before December 18, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 97-NM-285-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
Centreville, Montreal, 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, Engine and Propeller
Directorate, New York Aircraft Certification Office, 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 and Propulsion Branch, ANE-171, 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 (TCA), which is
the airworthiness authority for Canada, recently notified the FAA that
an unsafe condition may exist on certain Bombardier Model CL-600-1A11,
-2A12, and -2B16 series airplanes. TCA advises that the structural
configuration of these airplanes at frame station (FS) 409.00 is
similar to that of Bombardier Model CL-600-2B19 (Regional Jet Series
100 and 200) series airplanes, which was shown to have a pressurization
problem caused by fatigue cracking in the underfloor pressure bulkhead
of the fuselage. TCA has received several reports of cracking at this
same location on Bombardier Model CL-600-1A11, -2A12, and -2B16 series
airplanes. This condition, if not corrected, could result in
uncontrolled depressurization of the airplane and/or reduced structural
integrity of the fuselage.
Other Relevant Rules
The FAA previously issued AD 97-14-11, amendment 39-10082 (62 FR
38206, July 17, 1997), which requires repetitive inspections to detect
cracks of a certain bulkhead web of the fuselage at certain locations,
and repair, if necessary. That AD applies to certain Bombardier Model
CL-600-2B19 (Regional Jet Series 100 and 200) series airplanes.
Explanation of Relevant Service Information
The manufacturer has issued Canadair Challenger Service Bulletin
601-0501, dated September 12, 1997 [for Model CL-600-2A12 (CL-601) and
CL-600-2B16 (CL-601-3A/-3R) series airplanes]; Service Bulletin 604-53-
007, dated September 30, 1997 [for Model CL-600-2B16 (CL-604) series
airplanes]; and Service Bulletin 600-0679, dated September 12, 1997
[for Model CL-600-1A11 (CL-600) series airplanes]. These service
bulletins describe procedures for repetitive detailed visual
inspections to detect fatigue cracking of the underfloor pressure
bulkhead at FS 409.00, and repair, if necessary. TCA classified these
service bulletins as mandatory and issued Canadian airworthiness
directive CF-97-16, dated September 25, 1997, in order to assure the
continued airworthiness of these airplanes in Canada.
FAA's Conclusions
These airplane models are manufactured in Canada and are 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, TCA has kept the FAA informed of the
situation described above. The FAA has examined the findings of TCA,
reviewed all available information, and determined that AD action is
necessary for products of this type design that are
[[Page 61437]]
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 requires accomplishment of the
inspections specified in the service bulletins described previously. In
addition, this AD requires repair, if necessary, in accordance with a
method approved by the FAA.
Operators should note that, while it is not the FAA's normal policy
to allow flight with known cracks, this AD does permit further flight
with cracking within certain limits. The results of a review, conducted
by the manufacturer, revealed that cracking in the underfloor pressure
bulkhead of the fuselage will not result in rapid decompression of the
airplane. Therefore, according to the review, if the crack size limits
are strictly observed and if repetitive inspections are performed at
the required intervals, cracks that grow beyond the limits will be
detected, and corrective action taken, before they can grow to a size
that would create an unacceptable risk of structural failure. Transport
Canada Aviation concurs with the findings of this review. In
consideration of these findings and based on the FAA's criteria for
flight with known cracking, the FAA has determined that further flight
with cracking within certain limits in the center pressure bulkhead is
permissible for an interim period.
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 15 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 97-NM-285-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 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:
97-24-02 Bombardier, Inc.: Amendment 39-10209. Docket 97-NM-285-AD.
Applicability: Model CL-600-1A11 (CL-600) series airplanes,
serial numbers 1004 through 1085 inclusive; Model CL-600-2A12 (CL-
601) series airplanes, serial numbers 3001 through 3066 inclusive;
Model CL-600-2B16 (CL-601-3A/-3R) series airplanes, serial numbers
5001 through 5194 inclusive; Model CL-600-2B16 (CL-604) series
airplanes, serial numbers 5301 through 5352 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
otherwise 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 (c) 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 detect and correct fatigue cracking in the underfloor
pressure bulkhead of the fuselage, which could result in
uncontrolled depressurization of the airplane and/or reduced
structural integrity of the fuselage, accomplish the following:
(a) For Model CL-600-1A11 (CL-600) airplanes: Prior to the
accumulation of 1,900 total landings, or within 100 landings after
the effective date of this AD, whichever occurs later, perform a
detailed visual inspection to detect cracks at frame station (FS)
409 of the bulkhead web [part number (P/N) 600-32014-71/-95/-105],
in accordance with Canadair Challenger Service
[[Page 61438]]
Bulletin 600-0679, dated September 12, 1997.
(1) If no crack is detected, repeat the detailed visual
inspection thereafter at intervals not to exceed 600 landings.
(2) If any crack is detected and if all three of the conditions
specified in paragraphs (a)(2)(i), (a)(2)(ii), and (a)(2)(iii) of
this AD are met, within 600 landings or 12 months after the crack is
detected, whichever occurs first, repair the cracking in accordance
with a method approved by the Manager, New York Aircraft
Certification Office (ACO), FAA, Engine and Propeller Directorate.
Until the repair is accomplished, repeat the detailed visual
inspection at intervals not to exceed 100 landings.
(i) No more than one crack exists at each corner radius, as
specified in the service bulletin; and
(ii) No crack extends under the angles having P/N 600-32014-13
and P/N 600-32014-15 on the aft side of the bulkhead web; and
(iii) No crack exists in angles having P/N 600-32014-13 and P/N
600-32014-15 on the aft side of the bulkhead web.
(3) If any cracking other than that identified in paragraph
(a)(2) of this AD is detected, prior to further flight, repair it in
accordance with a method approved by the Manager, New York ACO.
(b) For Model CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A/-3R),
and CL-600-2B16 (CL-604) series airplanes: Prior to the accumulation
of 1,100 total landings, or within 100 landings after the effective
date of this AD, whichever occurs later, perform a detailed visual
inspection to detect cracks at FS 409 of the bulkhead web (P/N 600-
32014-105/-137), in accordance with Canadair Challenger Service
Bulletin 601-0501, dated September 12, 1997 [for Model CL-600-2A12
(CL-601) and CL-600-2B16 (CL-601-3A/-3R) series airplanes); or
Canadair Challenger Service Bulletin 604-53-007, dated September 30,
1997 [for Model CL-600-2B16 (CL-604) series airplanes]; as
applicable.
(1) If no crack is detected, repeat the detailed visual
inspection thereafter at intervals not to exceed 600 landings.
(2) If any crack is detected and if all three of the conditions
specified in paragraphs (b)(2)(i), (b)(2)(ii), and (b)(2)(iii) of
this AD are met, within 600 landings or 12 months after the crack is
detected, whichever occurs first, repair the cracking in accordance
with a method approved by the Manager, New York ACO. Until the
repair is accomplished, repeat the detailed visual inspection at
intervals not to exceed 100 landings.
(i) No more than one crack exists at each corner radius, as
specified in the service bulletin; and
(ii) No crack extends under the angles having P/N 600-32014-113
and P/N 600-32014-115 on the aft side of the bulkhead web; and
(iii) No crack exists in angles having P/N 600-32014-113 and P/N
600-32014-115 on the aft side of the bulkhead web.
(3) If any cracking other than that identified in paragraph
(b)(2) of this AD is detected, prior to further flight, repair it in
accordance with a method approved by the Manager, New York ACO.
(c) 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 ACO. 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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the New York ACO.
(d) 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.
(e) The inspections shall be done in accordance with Canadair
Challenger Service Bulletin 600-0679, dated September 12, 1997;
Canadair Challenger Service Bulletin 601-0501, dated September 12,
1997; or Canadair Challenger Service Bulletin 604-53-007, dated
September 30, 1997; as applicable. 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
Centre-ville, Montreal, Quebec H3C 3G9, Canada. Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller
Directorate, New York Aircraft Certification Office, 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.
Note 3: The subject of this AD is addressed in Canadian
airworthiness directive CF-97-16, dated September 25, 1997.
(f) This amendment becomes effective on December 3, 1997.
Issued in Renton, Washington, on November 10, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-30104 Filed 11-17-97; 8:45 am]
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