[Federal Register Volume 63, Number 110 (Tuesday, June 9, 1998)]
[Proposed Rules]
[Pages 31377-31380]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-15252]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-116-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 and 200) Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain Bombardier Model 
CL-600-2B19 (Regional Jet Series 100 and 200) airplanes, that currently 
requires repetitive inspections to detect discrepancies of the shock 
strut end caps and attachment pins of the main landing gear (MLG), and 
replacement of discrepant parts with new parts. It also requires a 
check for and replacement of certain pins that currently may be 
installed on some airplanes. This action would add a requirement for 
the installation of new, improved MLG shock strut upper and lower 
attachment pins, which would constitute terminating action for the 
repetitive inspections. This action also would reduce the applicability 
of the existing AD by removing certain airplanes. This proposal is 
prompted by issuance of mandatory continuing airworthiness information 
by a foreign civil airworthiness authority. The actions specified by 
the proposed AD are intended to prevent failure of attachment pins and 
the attachment pin end caps, which could result in failure of the MLG.

DATES: Comments must be received by July 9, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 97-NM-116-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00

[[Page 31378]]

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; or 
Messier-Dowty Inc., 574 Monarch Avenue, Ajax, Ontario L1S 2GB, 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, 181 South Franklin Avenue, Valley Stream, New York.

FOR FURTHER INFORMATION CONTACT: George Duckett, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft 
Certification Office, Engine and Propeller Directorate, 10 Fifth 
Street, Third Floor, Valley Stream, New York 11581; telephone (516) 
256-7525; fax (516) 256-2716.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 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 97-NM-116-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-114, Attention: Rules 
Docket No. 97-NM-116-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On October 24, 1996, the FAA issued AD 96-22-14, amendment 39-9803 
(61 FR 57319, November 6, 1996), applicable to certain Bombardier Model 
CL-600-2B19 (Regional Jet Series 100 and 200) airplanes, to require 
repetitive inspections to detect discrepancies of the shock strut end 
caps and attachment pins of the main landing gear (MLG), and 
replacement of discrepant parts with new parts. It also requires a 
check for and replacement of certain pins that currently may be 
installed on some airplanes.
    That action was prompted by reports of corrosion, wear, and loss of 
chrome plating on the upper and lower attachment pins of the shock 
strut of the MLG, and reports of cracks in the lower attachment pins 
and the end cap of upper attachment pins. The requirements of that AD 
are intended to prevent failure of the attachment pin and the 
attachment pin end caps, which could result in failure of the MLG.

Actions Since Issuance of Previous Rule

    In the preamble to AD 96-22-14, the FAA specified that the actions 
required by that AD were considered ``interim action'' and that once a 
terminating modification is developed, approved, and available, the FAA 
may consider additional rulemaking action. The manufacturer now has 
developed such a modification, and the FAA has determined that further 
rulemaking action is indeed necessary; this proposed AD follows from 
that determination.

Relevant Service Information

    The manufacturer has issued Canadair Regional Jet Service Bulletin 
S.B. 601R-32-065, dated November 11, 1996. The Canadair service 
bulletin references Messier-Dowty Service Bulletin M-DT 17002-32-12, 
dated November 6, 1996, as an additional source of service information. 
These service bulletins describe procedures for the installation of 
new, improved MLG shock strut upper and lower attachment pins. The 
effectivity listing of the Canadair service bulletin limits the 
accomplishment of the installation to those airplanes on which the 
installation was not accomplished during production. Accomplishment of 
the installation eliminates the need for the repetitive inspections 
required by AD 96-22-14.
    Transport Canada Aviation (TCA), which is the airworthiness 
authority for Canada, classified the Canadair service bulletin as 
mandatory and issued Canadian airworthiness directive CF-96-12R1, dated 
January 29, 1997, in order to assure the continued airworthiness of 
these airplanes in Canada.

FAA's Conclusions

    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, 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 certificated for 
operation in the United States.

Explanation of Requirements of Proposed 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, the proposed AD would supersede AD 96-22-14 to 
continue to require the repetitive inspections to detect discrepancies 
of the shock strut end caps and attachment pins of the MLG. It also 
continues to require a check for and replacement of certain pins that 
currently may be installed on some airplanes. This new proposed AD 
would add a requirement for the installation of new, improved MLG shock 
strut upper and lower attachment pins, which would constitute 
terminating action for the repetitive inspections. In addition, this 
action would reduce the applicability of the existing AD by removing 
certain airplanes.
    The actions would be required to be accomplished in accordance with 
the service bulletin described previously.

Cost Impact

    There are approximately 41 Model CL-600-2B19 (Regional Jet Series 
100 and 200) airplanes of U.S. registry that would be affected by this 
proposed AD.
    The actions that are currently required by AD 96-22-14, and 
retained in this proposed AD, take approximately 25 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 $61,500, or $1,500 per 
airplane.

[[Page 31379]]

    The new actions that are proposed in this AD action would take 
approximately 13 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts would be supplied by 
the manufacturer at no cost to the operators. Based on these figures, 
the cost impact of the new actions proposed by this AD on U.S. 
operators is estimated to be $31,980, or $780 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or proposed 
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 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.

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. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-9803 (61 FR 
57319, November 6, 1996), and by adding a new airworthiness directive 
(AD), to read as follows:

Bombardier, Inc. (Formerly Canadair): Docket 97-NM-116-AD. 
Supersedes AD 96-22-14, Amendment 39-9803.

    Applicability: Model CL-600-2B19 (Regional Jet Series 100 and 
200) airplanes, serial numbers 7003 through 7157 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 (f) 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 failure of attachment pins and the attachment pin end 
caps of the main landing gear (MLG), which could result in failure 
of the MLG, accomplish the following:

Restatement of the Requirements of AD 96-22-14

    (a) Serial Number Check. For airplanes having serial numbers 
7003 through 7126 inclusive: Within 150 landings after November 21, 
1996 (the effective date of AD 96-22-14, amendment 39-9803), check 
the serial number of each MLG shock strut lower attachment pin, part 
number 17144-1, in accordance with paragraphs 2.A. and 2.B. of the 
Accomplishment Instructions of Canadair Regional Jet Alert Service 
Bulletin S.B. A601R-32-062, Revision `C,' dated September 18, 1996; 
and paragraphs 2.A.(4), 2.B.(4), and 2.C.(3) of the Accomplishment 
Instructions of Messier-Dowty Service BulletinM-DT 17002-32-10, 
Revision 3, dated September 6, 1996.
    (1) If the serial number is within the range of DCL206 through 
DCL259 inclusive, prior to further flight, remove the pin and 
install a new pin having a serial number outside (either higher or 
lower) of that range, in accordance with the service bulletins. 
Thereafter, inspect that replacement pin in accordance with 
paragraphs (b) and (c) of this AD.
    (2) If the serial number is outside of the range (higher or 
lower) of DCL206 through DCL259 inclusive, thereafter inspect the 
pin in accordance with paragraphs (b) and (c) of this AD.
    (b) In-Situ Visual Inspection. Within 150 landings after 
November 21, 1996, perform an in-situ visual inspection to detect 
discrepancies of the left- and right-hand shock strut of the MLG, in 
accordance with paragraphs 2.C. and 2.D. of the Accomplishment 
Instructions of Canadair Regional Jet Alert Service Bulletin S.B. 
A601R-32-062, Revision `C,' dated September 18, 1996; and paragraph 
2.B.(1) of the Accomplishment Instructions of Messier-Dowty Service 
Bulletin M-DT 17002-32-10, Revision 3, dated September 6, 1996.

    Note 2: In-situ visual inspections that have been accomplished 
prior to November 21, 1996, in accordance with Messier-Dowty Service 
Bulletin M-DT 17002-32-10, dated June 13, 1996; Revision 1, dated 
June 29, 1996; or Revision 2, dated July 17, 1996; are considered 
acceptable for compliance with paragraph (b) of this amendment.
    (1) If no discrepancy is detected, repeat the in-situ visual 
inspection thereafter at intervals not to exceed every ``A'' check 
or 400 landings, whichever occurs later.
    (2) If any discrepancy is detected, prior to further flight, 
replace the discrepant part with a new part in accordance with the 
service bulletins. Thereafter, repeat the in-situ visual inspection 
at intervals not to exceed every ``A'' check or 400 landings, 
whichever occurs later.
    (c) Detailed Inspection. Within 3,000 landings since the date of 
airplane manufacture, or within 400 landings after November 21, 
1996, whichever occurs later, perform a detailed inspection to 
detect discrepancies of the shock strut end caps and attachment pins 
of the MLG, in accordance with paragraphs 2.E. and 2.F. of the 
Accomplishment Instructions of Canadair Regional Jet Alert Service 
Bulletin S.B. A601R-32-062, Revision `C,' dated September 18, 1996; 
and paragraph 2.B.(2) of the Accomplishment Instructions of Messier-
Dowty Service Bulletin M-DT 17002-32-10, Revision 3, dated September 
6, 1996. Non-destructive testing (NDT) must be accomplished in 
accordance with the instructions provided or references referred to 
in these service bulletins. Where instructions in those documents 
specify dye penetrant inspections (DPI), accomplish fluorescent 
penetrant (Type 1) inspections, sensitivity level 3 or higher, using 
material qualified to Military Standard MIL-I-25135.

    Note 3: Detailed inspections accomplished prior to November 21, 
1996, in accordance with Messier-Dowty Service Bulletin M-DT 17002-
32-10, dated June 13, 1996; Revision 1, dated June 29, 1996; or 
Revision 2, dated July 17, 1996; are considered acceptable for 
compliance with paragraph (c) of this amendment.

    (1) If no discrepancy is detected, repeat the detailed 
inspection thereafter at intervals not to exceed 2,000 landings.
    (2) If any discrepancy is detected, prior to further flight, 
replace the discrepant part with a new part in accordance with the 
service bulletins. Repeat the detailed inspection thereafter at 
intervals not to exceed 2,000 landings.
    (d) As of November 21, 1996, no person shall install on any 
airplane an MLG shock strut lower attachment pin, part number 17144-
1, that has a serial number that is within the range of DCL206 
through DCL259 inclusive.

[[Page 31380]]

New Requirements of This AD

    (e) Within 6 months after the effective date of this AD, install 
new MLG shock strut upper and lower attachment pins in accordance with 
Canadair Regional Jet Service Bulletin S.B. 601R-32-065, dated November 
11, 1996. Accomplishment of this installation constitutes terminating 
action for the repetitive inspections required by paragraphs (b) and 
(c) of this AD.

    Note 4: The Canadair service bulletin references Messier-Dowty 
Service Bulletin M-DT 17002-32-12, dated November 6, 1996, as an 
additional source of service information to accomplish the 
installation.

    (f)(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.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 96-22-14, amendment 39-9803, are approved as 
alternative methods of compliance with this AD.

    Note 5: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the New York ACO.

    (g) 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.
    Note 6: The subject of this AD is addressed in Canadian 
airworthiness directive CF-96-12R1, dated January 29, 1997.

    Issued in Renton, Washington, on June 3, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-15252 Filed 6-8-98; 8:45 am]
BILLING CODE 4910-13-U