AD 98-04-45 SUPERSEDED

This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) series airplanes, that currently requires revisions to the Airplane Flight Manual (AFM) to advise the flight crew of the need to perform daily checks to verify proper operation of the elevator control system, and to restrict altitude and airspeed operations under certain conditions. That AD also requires removal of all elevator flutter dampers. That AD was prompted by reports that the installation of certain shear pins may jam or restrict movement of the elevator. The actions specified by that AD are intended to prevent such jamming or restricting movement of the elevator and the resultant adverse effect on the controllability of the airplane. This amendment adds inspections of certain airplanes to detect deformation or discrepancies of the flutter damper hinge fittings and lug of the horizontal stabilizer, the elevator hinge/damper fitting, and the shear pin lugs; and requires replacement of discrepant parts with serviceable parts. This amendment also requires installation of new elevator flutter dampers, and replacement of shear pins and shear links with new, improved pins and links.

Final rule

98-04-45 BOMBARDIER, INC. (Formerly Canadair): Amendment 39-10356. Docket 96-NM- 108-AD. Supersedes AD 94-24-02, Amendment 39-9075.

Applicability: Model CL-600-2B19 (Regional Jet Series 100) series airplanes, having serial numbers 7003 through 7054 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) 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 includespecific proposed actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To prevent failure of lugs and/or pins, which may increase the likelihood of jamming or restricting movement of the elevator and the resultant adverse effect on controllability of the airplane, accomplish the following: Restatement of Requirements of AD 94-01-09

(a) Within 30 days after January 26, 1994 (the effective date of AD 94-01-09, amendment 39-8791), revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following restrictions of altitude and airspeed operations under conditions of single or double hydraulic system failure; and advise the flight crew of these revised limits. Revision of the AFM may be accomplished by inserting a copy of this AD or AFM Revision 34, dated June 12, 1995, in the AFM.

SINGLE HYDRAULIC SYSTEM FAILURE

Altitude Limit
(Maximum)
Airspeed Limit
(Maximum)
31,000 feet(199 KIAS)
0.55 Mach
30,000 feet
(204 KIAS)
0.55 Mach
28,000 feet
(213 KIAS)
0.55 Mach
26,000 feet
(222 KIAS)
0.55 Mach
24,000 feet
(232 KIAS)
0.55 Mach
22,000 feet
(241KIAS)
0.55 Mach
20,000 feet
and below
252 KIAS

DOUBLE HYDRAULIC SYSTEM FAILURE

Altitude Limit
(Maximum)
Airspeed Limit
(Maximum)
10,000 feet
200 KIAS

NOTE 2: The restrictions described in the AFM Temporary Revision (TR) RJ/30, dated December 16, 1993; meet the requirements of this paragraph. Therefore, inserting a copy of TR RJ/30 in lieu of this AD in the AFM is considered an acceptable means of compliance with this paragraph. Restatement of Requirements of AD 94-24-02

(b) Within 7 days after December 14, 1994 (the effective date of AD 94-24-02, amendment 39-9075), accomplish the requirements of paragraph (b)(1) and (b)(2) of this AD:

(1) Until the requirements of paragraph (c)(2) of this AD are accomplished, remove the elevator dampers in accordance with Canadair Regional Jet Alert Service Bulletin S.B. A601R-27- 041, dated October 28, 1994.

(2) Revise the Limitations Section of the FAA-approved AFM to include the following, which advises the flight crew of daily checks to verify proper operation of the elevator control system. Revision of the AFM may be accomplished by inserting a copy of this AD or AFM Revision 32, dated March 30, 1995, in the AFM.

NOTE 3: The daily check described in the AFM Temporary Revision (TR) RJ/40, dated October 28, 1994, meets the requirements of this paragraph. Therefore, inserting a copy of TR RJ/40 into the AFM in lieu of this AD is considered an acceptable means of compliance with this paragraph.

"Elevator, Before Engine Start (First Flight of Day)

(1) Elevator........................................Check
Travel range (to
approximately 1/2
travel) using each
hydraulic system in
turn, with the other
hydraulic systems
depressurized."

New Requirements of this AD

(c) Within 12 months after the effective date of this AD, perform the requirements of paragraphs (c)(1) and (c)(2) of this AD, as applicable, in accordance with Canadair Regional Jet Service Bulletin S.B. 601R-27-040, Revision `B,' dated September 11, 1995.

(1) For airplanes having serial numbers 7003 through 7049, inclusive: Perform the inspections specified in paragraphs (c)(1)(i), (c)(1)(ii), and (c)(1)(iii) of this AD in accordance with Section 2.B., Part A, of the service bulletin.

(i) Remove the shear pins and shear links of the flutter dampers and perform a visual inspection to detect any deformation or discrepancy of the flutter damper hinge fitting and lug of the horizontal stabilizer. Prior to further flight, replace any deformed or discrepant part with a serviceable part in accordance with the service bulletin.

(ii) Perform a visual inspection to detect any deformation or discrepancy of the elevator hinge/damper fitting and shear pin lugs. Prior to further flight, replace any discrepant part with a serviceable part in accordance with the service bulletin.

(iii) Perform a fluorescent penetrant inspection and a dimensional inspection to detect any deformation or discrepancy of the shear pin lugs. If any deformation or discrepancy is found on the lugs, prior to further flight, replace the elevator with a new or serviceable elevator in accordance with the service bulletin.

(2) For airplanes having serial numbers 7003 through 7054, inclusive: Install new shear pins [part number (P/N) 601R24063-953] and new elevator flutter dampers (P/N 601R75142-7) in accordance with Section 2.B., Part B, of the service bulletin:

(d) 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 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 Canadair Regional Jet Service Bulletin S.B. 601R-27-040, Revision `B,' dated September 11, 1995, and Canadair Regional Jet Alert Service Bulletin S.B. A601R-27-041, dated October 28, 1994.

(1) The incorporation by reference of Canadair Regional Jet Service Bulletin S.B. 601R-27-040, Revision `B,' dated September 11, 1995, is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

(2) The incorporation by reference of Canadair Regional Jet Alert Service Bulletin S.B. A601R-27-041, dated October 28, 1994 was approved previously by the Director of the Federal Register as of December 14, 1994 (59 FR 60888, November 29, 1994).

(3) 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 5: The subject of this AD is addressed in Canadian airworthiness directive CF-94-21R1, dated November 3, 1995.

(g) This amendment becomes effective on April 3, 1998.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 94-24-02, amendment 39-9075 (59 FR 60888, November 29, 1994), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) series airplanes, was published in the Federal Register on February 3, 1997 (62 FR 4941). That action proposed to continue to require the removal of the originally installed elevator dampers. That action also proposed to continue to require revisions to the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to restrict altitude and airspeed operations under conditions of single or double hydraulic system failure, and to advise the flight crew of the need to perform daily checks to verify proper operation of the elevator control system.

For certain airplanes, this new action proposes to add inspections of certain airplanes to detect deformation or discrepancies of the flutter damper hinge fittings and lug of the horizontal stabilizer, the elevator hinge/damper fitting, and the shear pin lugs; and requires replacement of discrepant parts with serviceable parts. For those and other airplanes, the proposed AD also would require installation of new elevator flutter dampers, and replacement of shear pins and shear links with new, improved pins and links.

Interim Action
This is considered to be interim action until final action is identified, at which time the FAA may consider further rulemaking.

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.

Conclusion
The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

Cost Impact
There are approximately 21 Bombardier Model CL-600-2B19 (Regional Jet Series 100) series airplanes of U.S. registry that will be affected by this AD.

The actions that are currently required by AD 94-24-02, and retained in this AD, take approximately 6 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 previously required actions on U.S. operators is estimated to be $7,560, or $360 per airplane. The FAA estimates that all affected U.S. operators have previously accomplished these requirements, therefore, the future cost impact of these requirements is minimal.

For operators that are required to accomplish the inspections in this new AD, it will take approximately 26 work hours per airplane to accomplish them, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the new inspection requirements of this AD on U.S. operators is estimated to be $1,560 per airplane.

The installations that are required in this AD will take approximately 12 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 operator. Based on these figures, the cost impact of the installations required by this AD on U.S. operators is estimated to be $15,120, or $720 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.

39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-9075 (59 FR 60888, November 29, 1994), and by adding a new airworthiness directive (AD), amendment 39-10356 to read as follows:

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.

Franco Pieri, Aerospace Engineer, Airframe and
Propulsion Branch, ANE-171, New York Aircraft Certification Office, FAA, Engine and Propeller
Directorate, 10 Fifth Street, Third Floor, Valley Stream, New York 11581; telephone (516) 256-7526;
fax (516) 568-2716.