[Federal Register Volume 60, Number 33 (Friday, February 17, 1995)]
[Proposed Rules]
[Pages 9302-9304]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-4002]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-239-AD]
Airworthiness Directives; Bombardier Model CL-600-1A11 (CL-600),
-2A12 (CL-601), -2B16 (CL-601-3A, -3R), and -2B19 (Regional Jet Series
100) Series Airplanes, Equipped with Sundstrand Air Driven Generator
(ADG) Uplock Assembly
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Bombardier Model CL-600-
1A11, -2A12, -2B16, and -2B19 series airplanes. This proposal would
require an inspection to verify the proper operation of the uplock
latch of the air driven generator (ADG), and replacement of the uplock
latch with a serviceable part, if necessary. This proposal would also
require replacing the uplock assembly with a modified uplock assembly,
and performing a rigging inspection. This proposal is prompted by a
report indicating that, upon operation of the manual release system,
the ADG did not deploy due to failure of the shaft pin. The actions
specified by the proposed AD are intended to prevent failure of the
shaft pin, which could lead to the inability of the pilot to manually
deploy the ADG when necessary (i.e., when an airplane's primary
electrical power sources are lost and the ADG fails to deploy
automatically).
DATES: Comments must be received by March 31, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-239-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from Bombardier, Inc., Canadair, Aerospace Group, P.O. Box
6087, Station Centre-ville, 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.
FOR FURTHER INFORMATION CONTACT: Wing Chan, Electronics Engineer,
Systems and Equipment Branch, ANE-173, FAA, Engine and Propeller
Directorate, New York Aircraft Certification Office, 10 Fifth Street,
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7511;
fax (516) 568-2716.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such [[Page 9303]] 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
above. All communications received on or before the closing date for
comments, specified above, will be considered before taking action on
the proposed rule. The proposals contained in this notice may be
changed in light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 94-NM-239-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules
Docket No. 94-NM-239-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
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-600-1A11 (CL-600), -2A12 (CL-601), -2B16
(CL-601-3A, -3R), and -2B19 (Regional Jet Series 100) series airplanes,
equipped with a certain Sundstrand air driven generator (ADG) uplock
assembly. Transport Canada Aviation advises that, upon operation of the
manual release system, the air driven generator (ADG) did not deploy.
Investigation has revealed that the cause of this failure has been
attributed to a broken shaft pin in the ADG uplock assembly. Failure of
the shaft pin could lead to the inability of the pilot to manually
deploy the ADG when necessary (i.e., when an airplane's primary
electrical power sources are lost and the ADG fails to deploy
automatically). If this were to occur, all electrical power on the
airplane would be lost.
Bombardier has issued Canadair Regional Jet Alert Service Bulletin
S.B. A1601R-24-019, Revision `A', dated August 9, 1994 (for Model CL-
600-2B19 series airplanes); Canadair Challenger Service Bulletin 600-
0638, dated April 25, 1994 (for Model CL-600-1A11 series airplanes);
and Canadair Challenger Service Bulletin 601-0430, dated April 25, 1994
(for Model CL-600-2A12 and -2B16 series airplanes). These service
bulletins describe procedures for a one-time inspection to verify the
proper operation of the uplock latch of the ADG, and replacement of the
uplock latch with a serviceable part, if the uplock latch cannot be
activated. These service bulletins also describe procedures for
replacing the uplock assembly with a modified uplock assembly, and
performing a rigging inspection. Transport Canada Aviation classified
these service bulletins as mandatory and issued Canadian airworthiness
directive CF-94-14, dated September 7, 1994 (for Model CL-600-2B19
series airplanes); and Canadian airworthiness directive CF-94-13, dated
September 1, 1994 (for Model CL-600-1A11, -2A12, and -2B16 series
airplanes); 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, the Transport Canada Aviation has
kept the FAA informed of the situation described above. The FAA has
examined the findings of the 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, the proposed AD would require a one-time
inspection to verify the proper operation of the uplock latch of the
ADG, and replacement of the uplock latch with a serviceable part, if
the uplock latch cannot be activated. The proposed AD would also
require replacing the uplock assembly with a modified uplock assembly,
and performing a rigging inspection. The actions would be required to
be accomplished in accordance with the service bulletins described
previously.
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of compliance with the AD, in accordance with
the paragraph of each AD that provides for such approvals. A note has
been included in this notice to clarify this requirement.
The FAA estimates that 194 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 6 work
hours per airplane to accomplish the proposed actions, and that the
average labor rate is $60 per work hour. Required parts would be
supplied by the manufacturer at no cost to the operators. Based on
these figures, the total cost impact of the proposed AD on U.S.
operators is estimated to be $69,840, or $360 per airplane.
The total cost impact figure discussed above is based on
assumptions that no operator has yet accomplished any of the proposed
requirements of this AD action, and that no operator would accomplish
those actions in the future if this AD were not adopted.
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (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);
and (3) if promulgated, 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. A copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ``ADDRESSES.''
[[Page 9304]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
Bombardier Inc. (Formerly Canadair): Docket 94-NM-239-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 5150 inclusive; Model CL-500-2B19 (Regional Jet Series
100) series airplanes, serial numbers 7003 through 7040 inclusive;
equipped with Sundstrand air driven generator (ADG) uplock assembly
having part number 721863, 721863A, or 721863B; 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 (c) 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 failure of the shaft pin, which could lead to the
inability of the pilot to manually deploy the air driven generator
(ADG) when necessary (i.e., when an airplane's primary electrical
power sources are lost and the ADG fails to deploy automatically),
accomplish the following:
(a) For Model CL-600-2B19 (Regional Jet Series 100) series
airplanes equipped with Sundstrand ADG uplock assembly having P/N
721863B: Accomplish paragraphs (a)(1), (a)(2), and (a)(3), in
accordance with Canadair Alert Service Bulletin S.B. 1601R-24-019,
Revision `A', dated August 9, 1994.
(1) Within 600 flight hours after the effective date of this AD,
perform an inspection to verify the proper operation of the uplock
latch of the ADG, in accordance with the Accomplishment Instructions
of the service bulletin. If the uplock latch cannot be activated,
prior to further flight, replace the uplock latch with a serviceable
part in accordance with the service bulletin.
(2) Within 12 months after the effective date of this AD,
replace the uplock assembly with a modified uplock assembly, in
accordance with the Accomplishment Instructions of the service
bulletin.
(3) After accomplishment of paragraph (a)(1) or (a)(2) of this
AD, perform a rigging inspection in accordance with the
Accomplishment Instructions of the service bulletin.
(b) For Model CL-600-2A12, CL-2B16, and CL-600-1A11 series
airplanes: Accomplish paragraphs (b)(1), (b)(2), and (b)(3), in
accordance with Canadair Service Bulletin 600-0638, dated April 25,
1994 (for Model CL-600-1A11 series airplanes), or Canadair Service
Bulletin 601-0430, dated April 25, 1994 (for Model CL-600-2A12 and -
2B15 series airplanes), as applicable.
(1) Within 150 flight hours after the effective date of this AD,
perform an inspection to verify the proper operation of the uplock
latch of the ADG, in accordance with the Accomplishment Instructions
of the applicable service bulletin. If the uplock latch cannot be
activated, prior to further flight, replace the uplock latch with a
serviceable part, in accordance with the applicable service
bulletin.
(2) Within 12 months after the effective date of this AD,
replace the uplock assembly with a modified uplock assembly, in
accordance with the Accomplishment Instructions of the applicable
service bulletin.
(3) After accomplishment of paragraph (b)(1) or (b)(2) of this
AD, perform a rigging inspection in accordance with the
Accomplishment Instructions of the applicable service bulletin.
(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 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 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.
Issued in Renton, Washington, on February 13, 1995.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-4002 Filed 2-16-95; 8:45 am]
BILLING CODE 4910-13-U
