AD Amdt-39-10615

[Federal Register Volume 63, Number 122 (Thursday, June 25, 1998)]
[Rules and Regulations]
[Pages 34574-34576]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-16448]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-83-AD; Amendment 39-10615; AD 98-13-24]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional 
Jet Series 100) Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet 
Series 100) airplanes, that currently requires a revision to the 
Airplane Flight Manual (AFM) to prohibit the use of mach trim and to 
add speed restrictions if the autopilot is disengaged or inoperative. 
That AD also requires installation of an associated placard. This 
amendment adds requirements for replacement of the horizontal 
stabilizer trim control unit (HSTCU) with a new HSTCU, and reactivation 
of the mach trim engage/disengage switch/light (if deactivated). 
Accomplishment of these actions terminates the requirements of the 
existing AD. This amendment also limits the applicability of the 
existing AD. This amendment is prompted by issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified by this AD are intended to prevent 
deficiencies of the HSTCU, which could result in a nose-up trim runaway 
when a single component in the mach trim circuit fails.

DATES: Effective July 30, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 30, 1998.

ADDRESSES: The service information referenced in this AD 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 Federal Aviation Administration 
(FAA), Transport Airplane Directorate, Rules Docket, 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: Peter Cuneo, Aerospace Engineer, 
Systems and Flight Test 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) 256-7506; 
fax (516) 568-2716.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 95-13-04, 
amendment 39-9325 (60 FR 38668, July 28, 1995), which is applicable to 
certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) 
airplanes, was published in the Federal Register on April 14, 1998 (63 
FR 18160). The action proposed to continue to require a revision to the 
AFM to prohibit the use of mach trim and to add speed restrictions if 
the autopilot is disengaged or inoperative, and to require installation 
of an associated placard. The action proposed to add requirements for 
replacement of the horizontal stabilizer trim control unit (HSTCU) with 
a new HSTCU, and reactivation of the mach trim engage/disengage switch/
light (if deactivated). Accomplishment of these actions would terminate 
the requirements of the existing AD. That AD also proposed to limit the 
applicability of the existing AD.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Corrections to the Proposal

    In paragraph (b) of the proposed rule, the FAA inadvertently 
referenced Bombardier Service Bulletin S.B. 601R-27-053, dated May 27, 
1996; and Revision A, dated August 26, 1996; for accomplishment of the 
proposed actions. Paragraph (b) of this final rule has been revised to 
reference only Bombardier Service Bulletin S.B. 601R-27-053, Revision 
B, dated February 21, 1997. In addition, NOTE 3 has been added to 
reference the original issue and Revision A of the service bulletin as 
acceptable means of compliance for operators that have accomplished the 
applicable actions prior to the issuance of this AD.
    The FAA has become aware of a typographical error that appeared in 
paragraph (d)(2) of the proposal. The AD

[[Page 34575]]

number referenced in that paragraph appeared incorrectly as AD 93-13-
04. Paragraph (d)(2) of this final rule has been revised to correctly 
specify that AD number as AD 95-13-04.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule with the changes previously described. 
The FAA has determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Cost Impact

    There are approximately 54 Bombardier Model CL-600-2B19 (Regional 
Jet Series 100) airplanes of U.S. registry that will be affected by 
this AD.
    The actions that are currently required by AD 95-13-04, and 
retained in this AD, take approximately 2 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the currently required actions on 
U.S. operators is estimated to be $6,480, or $120 per airplane.
    The new actions that are required by this new AD will take 
approximately 3 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will be provided by the 
manufacturer at no cost to the operators. Based on these figures, the 
cost impact of the new requirements of this AD on U.S. operators is 
estimated to be $9,720, or $180 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted.

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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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 removing amendment 39-9325 (60 FR 
38668, July 28, 1995), and by adding a new airworthiness directive 
(AD), amendment 39-10615, to read as follows:

98-13-24  Bombardier, Inc. (Formerly Canadair): Amendment 39-10615. 
Docket 97-NM-83-AD. Supersedes AD 95-13-04, Amendment 39-9325.

    Applicability: Model CL-600-2B19 (Regional Jet Series 100) 
airplanes, serial numbers 7003 through 7112 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 (d)(1) 
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 deficiencies of the horizontal stabilizer trim 
control unit (HSTCU), which could result in a nose-up trim runaway 
when a single component in the mach trim circuit fails, accomplish 
the following:

Restatement of Requirements of AD 95-13-04

    (a) Within 24 hours after August 14, 1995 (the effective date of 
AD 95-13-04, amendment 39-9325), accomplish the requirements of 
paragraphs (a)(1), (a)(2), and (a)(3) of this AD.
    (1) Install a placard adjacent to the primary flight display 
next to the airspeed limitation placard, to read:

``USE OF MACH TRIM IS PROHIBITED. IF THE AUTOPILOT IS DISENGAGED OR 
INOPERATIVE, RESTRICT SPEED TO 250 KIAS OR 0.7 MACH.''

    (2) Revise the Limitations section of the FAA-approved Airplane 
Flight Manual (AFM) to include the following information. The 
requirements of this paragraph may be accomplished by inserting a 
copy of this AD, or Canadair Regional Jet Temporary Revision No. TR 
RJ/43, into the AFM.

``USE OF MACH TRIM IS PROHIBITED. IF THE AUTOPILOT IS DISENGAGED OR 
INOPERATIVE, RESTRICT SPEED TO 250 KIAS OR 0.7 MACH.''

    Note 2: When the temporary revision has been incorporated in the 
general revisions of the AFM, the general revisions may be inserted 
in the AFM, provided the information contained in the general 
revision is identical to that specified in Canadair Regional Jet 
Temporary Revision No. TR RJ/43.

    (3) Revise the Limitations section of the FAA-approved AFM to 
include the following information. The requirements of this 
paragraph may be accomplished by inserting a copy of this AD into 
the AFM.
    ``Prior to the accomplishment of Bombardier Alert Service 
Bulletin S.B. A601R-27-054, dated June 12, 1995, when the Mach trim 
system is disengaged, the ``MACH TRIM'' caution message will be 
displayed on the Engine Indication and Crew Alerting System (EICAS), 
and the Mach trim engage/disengage switch ``INOP'' legend will be 
illuminated. The EICAS message may be scrolled out of view prior to 
takeoff, but the switch ``INOP'' light will remain illuminated.''

New Requirements of This AD

    (b) Within 18 months after the effective date of this AD, 
replace the HSTCU with a new HSTCU having part number 601R92301-9, 
and reactivate the mach trim switch/light (if deactivated), in 
accordance with Bombardier Service Bulletin S.B. 601R-27-053, 
Revision B, dated February 21, 1997. Accomplishment of this 
modification constitutes terminating action for the requirements of 
paragraph (a) of this AD; after the modification has been 
accomplished, the previously required AFM limitation may be removed.

    Note 3: Accomplishment of paragraph (b) of this AD, prior to the 
effective date of this AD, in accordance with Bombardier Service 
Bulletin S.B. 601R-27-053, dated May 27, 1996; or Revision A, dated 
August 26, 1996; is considered acceptable for compliance with the 
applicable actions specified in this amendment.

    (c) As of the effective date of this AD, no person shall install 
on any airplane any

[[Page 34576]]

HSTCU having part number 601R92301-5, 601R92301-7, or 601R92301-951.
    (d)(1) 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.
    (d)(2) Alternative methods of compliance approved previously in 
accordance with AD 95-13-04, amendment 39-9325, are approved as 
alternative methods of compliance with this AD.

    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.

    (e) 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.
    (f) The actions shall be done in accordance with Bombardier 
Service Bulletin S.B. 601R-27-053, Revision B, dated February 21, 
1997. 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, 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 5: The subject of this AD is addressed in Canadian 
airworthiness directive CF-95-08R2, dated July 23, 1996.

    (g) This amendment becomes effective on July 30, 1998.

    Issued in Renton, Washington, on June 15, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-16448 Filed 6-24-98; 8:45 am]
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