[Federal Register Volume 60, Number 166 (Monday, August 28, 1995)]
[Rules and Regulations]
[Pages 44419-44421]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-20632]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-139-AD; Amendment 39-9344; AD 95-17-14]
Airworthiness Directives; Bombardier Model CL-600-1A11 (CL-600),
CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A and -3R) 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, CL-600-2A12, and
CL-600-2B16 series airplanes. This action requires functional testing
of the brake of the horizontal stabilizer trim actuator (HSTA); and
exercising the pitch trim system, revising the FAA-approved Airplane
Flight Manual (AFM), operational testing of the HSTA, and replacing the
HSTA or horizontal stabilizer trim control unit, if necessary. This
amendment is prompted by reports of overspeed annunciation of the pitch
trim due to slippage of the no-back device on the HSTA. The actions
specified in this AD are intended to prevent uncommanded movement of
the HSTA due to failure of the no-back device on the HSTA to operate
properly; this condition could adversely affect the controllability of
the airplane.
DATES: Effective September 12, 1995.-
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 12, 1995.-
Comments for inclusion in the Rules Docket must be received on or
before October 27, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-139-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: Peter Cuneo, Aerospace Engineer,
Systems and Equipment Branch, ANE-173, FAA, New York Aircraft
Certification Office, Engine and Propeller Directorate, 10 Fifth
Street, Third Floor, Valley Stream, New York 11581; telephone (516)
256-7506; 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-600-1A11 (CL-
600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A and -3R) series
airplanes. Transport Canada Aviation advises that it has received
reports of overspeed annunciation of the pitch trim. Each time such
annunciation occurred, the horizontal stabilizer trim actuator (HSTA)
mechanical brake prevented uncommanded movement of the HSTA, i.e., HSTA
runaway. Investigation has revealed that the reported overspeed
annunciation of the pitch trim may be attributed to slippage of the no-
back device on the HSTA. Further investigation revealed that the no-
back device on the HSTA failed to operate properly at low temperatures,
but operated properly at ambient temperatures above zero degrees
centigrade. This condition, if not corrected, could result in
uncommanded movement of the HSTA, which could adversely affect the
controllability of the airplane. -
Bombardier has issued Alert Service Bulletins A600-0645 (for Model
CL-600-1A11 series airplanes), and A601-0443 (for Model CL-600-2A12 and
CL-600-2B16 series airplanes), both dated January 11, 1995, which
describe procedures for an operational test of the HSTA brake, and
replacement of the HSTA or horizontal stabilizer trim control unit
(HSTCU) with a serviceable unit. Transport Canada Aviation approved
these service bulletins and issued Canadian airworthiness directive CF-
95-02, dated February 28, 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,
[[Page 44420]]
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 uncommanded
movement of the HSTA. This AD requires repetitive functional testing of
the HSTA brake for all airplanes. If certain conditions are found to
exist during the functional tests, this AD also requires exercising of
the pitch trim system, revising the Limitations Section of the FAA-
approved Airplane Flight Manual (AFM), operational testing of the HSTA,
and replacing the HSTA or HSTCU with a serviceable unit. Accomplishment
of the replacement terminates the requirement to exercise the pitch
trim system and revise the AFM.
-Operational testing of the HSTA and replacement of the HSTA or
HSTCU are required to be accomplished in accordance with the applicable
alert service bulletin 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 rule to clarify this long-standing requirement. -
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-139-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:
PART 39--AIRWORTHINESS DIRECTIVES -
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended] -
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-17-14 Bombardier, Inc. (Formerly Canadair): Amendment 39-9344.
Docket 95-NM-139-AD. -
Applicability: Model CL-600-1A11 (CL-600) series airplanes
having serial numbers 1004 through 1085 inclusive; Model CL-600-2A12
(CL-601) series airplanes having serial numbers 3001 through 3066
inclusive; and Model CL-600-2B16 (CL-601-3A and -3R) series
airplanes having serial numbers 5001 through 5137 inclusive, and
5139 through 5299 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 uncommanded movement of the horizontal stabilizer
trim actuator (HSTA), accomplish the following: -
(a) Within 20 hours time-in-service after the effective date of
this AD, perform the following ``Functional Test Procedures of the
HSTA Brake'': -
(1) Press the CHAN 1 INOP/CHAN 2 INOP switch/light and then the
OVSP/CHNG CHAN switch/light on the center pedestal control panel. -
[[Page 44421]]
(2) Set and hold the pitch trim switch on the pilot's control
wheel until the stabilizer is in full NOSE UP position. -
(3) Set and hold the pitch trim switch on the pilot's control
wheel to NOSE DOWN position and, while the stabilizer is moving,
press the PITCH TRIM DISC switch on the pilot's control wheel when
the needle on the stabilizer trim position indicator reaches the
first marking of the take-off configuration green band. Verify that
both CHAN INOP lights are on. -
(4) Verify that the stabilizer over-travel is less than one
degree, as read on the stabilizer trim position indicator on the
center instrument panel.
-Note 2: One increment on the stabilizer trim position indicator
is equal to one degree of stabilizer travel.
(i) If the stabilizer over-travel is less than or equal to one
degree, the pitch trim brake performance meets the ground
performance requirements and is considered serviceable.
-(ii) If the stabilizer over-travel is more than one degree,
dispatch is prohibited. Correction is required prior to further
flight, in accordance with Bombardier Alert Service Bulletin A600-
0645, dated January 11, 1995 (for Model CL-600-1A11 series
airplanes), or A601-0443, dated January 11, 1995 (for Model CL-600-
2A12 and CL-600-2B16 series airplanes), as applicable.
-(b) For airplanes on which the stabilizer over-travel is shown
to be equal to or less than 1 degree during the functional test
required by paragraph (a) of this AD, and no overspeed annunciation
has been reported previously, repeat the functional test thereafter
at intervals not to exceed 100 hours time-in-service.
-(c) For airplanes on which the stabilizer over-travel is shown
to be equal to or less than 1 degree during the functional test
required by paragraph (a) of this AD, and overspeed annunciation has
been reported previously, accomplish paragraphs (c)(1), (c)(2),
(c)(3), and (c)(4) of this AD.
-(1) Prior to each flight, exercise the pitch trim system by
accomplishing the following: ``Command full NOSE DOWN, then full
NOSE UP and re-position.''
-(2) Prior to further flight following accomplishment of the
functional test required by paragraph (a) of this AD, revise the
Limitations Section of the FAA-approved Airplane Flight Manual (AFM)
to include the following information. This may be accomplished by
inserting a copy of this AD in the AFM.
``1. Do not engage autopilot at an altitude below 1,000 feet
AGL.
``2. Monitor 8 CH annunciator for FLT CONT light.
``3. Maximum flap setting to be used is Flap 20 degrees.''
-(3) Within 50 hours time-in-service after the effective date of
this AD, perform an operational test to identify the unserviceable
HSTA or horizontal stabilizer trim control unit (HSTCU) and replace
it with a serviceable unit, in accordance with Bombardier Alert
Service Bulletin A600-0645, dated January 11, 1995 (for Model CL-
600-1A11 series airplanes), or A601-0443, dated January 11, 1995
(for Model CL-600-2A12 and CL-600-2B16 series airplanes), as
applicable. Replacement of the unserviceable unit with a serviceable
unit constitutes terminating action for the requirements of
paragraphs (c)(1) and (c)(2) of this AD. Following such replacement,
exercise of the pitch trim system may be discontinued and the
limitation may be removed from the AFM.
-(4) Thereafter at intervals not to exceed 100 hours time-in-
service repeat the functional test of the HSTA brake as specified in
paragraph (a) of this AD.
-(d) For airplanes on which the stabilizer over-travel is shown
to be more than 1 degree during the functional test required by
paragraph (a) of this AD, accomplish the requirements of paragraphs
(d)(1) and (d)(2) of this AD.
-(1) Prior to further flight, perform an operational test to
identify the unserviceable HSTA or HSTCU and replace it with a
serviceable unit, prior to further flight, in accordance with
Bombardier Alert Service Bulletin A600-0645, dated January 11, 1995
(for Model CL-600-1A11 series airplanes), or A601-0443, dated
January 11, 1995 (for Model CL-600-2A12 and CL-600-2B16 series
airplanes), as applicable.
-(2) Thereafter at intervals not to exceed 100 hours time-in-
service repeat the functional test of the HSTA brake as specified in
paragraph (a) in this AD.
-(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 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 3: 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 operational test and replacement shall be done in
accordance with Bombardier Alert Service Bulletin A600-0645, dated
January 11, 1995, or Bombardier Alert Service Bulletin A601-0443,
dated January 11, 1995, 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 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.
-(h) This amendment becomes effective on September 12, 1995.
Issued in Renton, Washington, on August 15, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-20632 Filed 8-25-95; 8:45 am]
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