[Federal Register: May 29, 2003 (Volume 68, Number 103)]
[Rules and Regulations]
[Page 31956-31960]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29my03-7]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-03-AD; Amendment 39-13170; AD 2003-11-11]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-2B19 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain Bombardier Model CL-600-2B19 series
airplanes, that currently requires repetitive eddy current inspections
for cracking of the main landing gear (MLG) main fittings, and
replacement with new or serviceable MLG main fittings if necessary.
That AD also requires servicing the MLG shock struts; inspecting the
MLG shock struts for nitrogen pressure, visible chrome dimension, and
oil leakage; and performing corrective actions, if necessary. This
amendment clarifies the applicability, adds certain repetitive
inspections, reduces an initial inspection threshold, and removes a
provision to extend the repetitive interval for the eddy current
inspection.
[[Page 31957]]
This amendment is prompted by issuance of mandatory continuing
airworthiness information by a foreign civil airworthiness authority.
The actions specified in this AD are intended to prevent failure of the
MLG main fittings, which could result in collapse of the MLG upon
landing.
DATES: Effective June 13, 2003.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 13, 2003.
Comments for inclusion in the Rules Docket must be received on or
before June 30, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2003-NM-03-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232.
Comments may also be sent via the Internet using the following address:
9-anm-iarcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2003-NM-03-AD'' in the subject line and need not
be submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 for Windows or
ASCII text.
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 FAA, Transport Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington; or at the FAA, 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: Serge Napoleon, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 10 Fifth Street, Third Floor, Valley Stream, New
York 11581; telephone (516) 256-7512; fax (516) 568-2716.
SUPPLEMENTARY INFORMATION: On October 22, 2001, the FAA issued
airworthiness directive (AD) 2001-22-09, amendment 39-12488 (66 FR
54658, October 30, 2001). (A correction of that AD was published in the
Federal Register on November 26, 2001 (66 FR 58931), and a second
correction of that AD was published in the Federal Register on December
14, 2001 (66 FR 64739).) That AD is applicable to certain Bombardier
Model CL-600-2B19 series airplanes and currently requires repetitive
eddy current inspections for cracking of the main landing gear (MLG)
main fittings, and replacement with new or serviceable MLG main
fittings if necessary. That AD also requires servicing the MLG shock
struts; inspecting the MLG shock struts for nitrogen pressure, visible
chrome dimension, and oil leakage; and performing corrective actions,
if necessary. The actions required by that AD are intended to prevent
failure of the MLG main fittings, which could result in collapse of the
MLG upon landing.
Background
As described in the notice of proposed rulemaking (NPRM) for AD
2001-22-09, three cases of premature failure of the MLG main fittings
had been reported. The reports indicated that a circumferential crack
was found on the MLG main fittings at the radius between the fitting
cylinder area and the upper attachment lug for the shock strut. Further
investigation indicated that, under certain conditions, an incorrectly
serviced shock strut could lead to premature failure of the MLG main
fittings.
Actions Since Issuance of Previous Rule
Since the issuance of AD 2001-22-09, Transport Canada Civil
Aviation (TCCA), which is the airworthiness authority for Canada, has
advised us of reports of another premature failure of the MLG main
fittings. Subsequent laboratory examination has confirmed that the
failure was at the identical location of the previously reported
failures, except that this new incident resulted from a different
failure mode.
Since the findings of this latest premature failure of the MLG main
fittings, the following new service information has been issued:
The manufacturer issued Bombardier Alert Service Bulletin A601R-32-
079, Revision ``E,'' dated September 12, 2002; including Appendix 1,
Revision D, dated September 12, 2002; including Appendices 2 and 3,
dated September 12, 2002. The revised service bulletin describes
procedures for performing repetitive visual, eddy current, and
fluorescent penetrant inspections of the MLG fittings, and replacement
if necessary; servicing and inspecting the MLG shock struts; and
performing corrective actions if necessary. The major changes to
Bombardier Alert Service Bulletin A601R-32-079, Revision D, dated
December 1, 2000, which is cited as the appropriate source of service
information for accomplishment of AD 2001-22-09, include revising
certain compliance times, adding repetitive fluorescent penetrant
inspections, and removing the escalation of eddy current repetitive
inspections. TCCA classified this service bulletin as mandatory.
TCCA has issued Canadian airworthiness directive CF-1999-32R2,
dated September 19, 2002, to ensure the continued airworthiness of
these airplanes in Canada. The Canadian airworthiness directive removes
the procedure for escalation of the eddy current inspection interval
and adds a detailed visual inspection of the MLG main fittings to
supplement the eddy current inspection.
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, TCCA has kept us informed of the
situation described above. We have examined the findings of TCCA,
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 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, this AD supersedes AD 2001-22-09 to continue to
require certain requirements. Those requirements include performing
repetitive eddy current inspections for cracking of the MLG main
fittings; replacing with new or serviceable MLG main fittings if
necessary; servicing the MLG shock struts; inspecting the MLG shock
struts for nitrogen pressure, visible chrome dimension, and oil
leakage; and performing corrective actions if necessary.
This AD clarifies the applicability, adds certain repetitive
inspections, reduces an initial inspection threshold, and removes a
provision to extend the repetitive interval for the eddy current
inspection. The actions required by this AD must be accomplished per
the referenced service bulletin, as described previously.
[[Page 31958]]
Clarification of Compliance Time Related to the Components
The compliance times specified in AD 2001-22-09 did not specify
that the total flight cycles in paragraphs (a) and (b) of that AD are
related to the MLG or shock struts, as applicable. To clarify this, we
have revised certain paragraphs in this AD to specify that the
compliance time is related to the components referenced in those
paragraphs rather than to the airplane.
Clarification of Applicability
The Canadian airworthiness directive and Bombardier service
bulletin both include Messier Dowty part numbers (P/Ns) for the MLG
main fittings, which are comparable to the Bombardier P/Ns. For this
reason, we have determined that it is necessary to clarify the
applicability of this AD by referencing both Messier Dowty and
Bombardier P/Ns.
Clarification of Replacement Requirement
AD 2001-22-09 requires replacement of any cracked MLG main fitting
with a new or serviceable MLG, and the Bombardier service bulletin
specifies such replacement with either an MLG or MLG fitting. However,
in consonance with the Canadian airworthiness directive, this AD
requires replacing any cracked MLG main fitting with a new or
serviceable main fitting instead of replacing the entire MLG.
Explanation of Change to Existing AD
We have added paragraph (m)(2) of this AD to prohibit the use of
alternative methods of compliance issued per paragraph (e) of AD 2001-
22-09 that would have allowed escalation of the repetitive intervals
for the eddy current inspections from 500 to 1,000 flight cycles.
Interim Action
This is considered to be interim action until final action is
identified, at which time we may consider further rulemaking.
Determination of Rule's Effective Date
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.
Submit comments using the following format:
[sbull] Organize comments issue-by-issue. For example, discuss a
request to change the compliance time and a request to change the
service bulletin reference as two separate issues.
[sbull] For each issue, state what specific change to the AD is
being requested.
[sbull] Include justification (e.g., reasons or data) for each
request.
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 us 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 2003-NM-03-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
The regulations adopted herein will not have a substantial direct
effect 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, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
We have 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
0
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
0
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]
0
2. Section 39.13 is amended by removing amendment 39-12488 (66 FR
54658, October 30, 2001), corrected at 66 FR 58931, November 26, 2001;
and corrected at 66 FR 64739, December 14, 2001; and by adding a new
airworthiness directive (AD), amendment 39-13170, to read as follows:
2003-11-11 Bombardier, Inc.: Amendment 39-13170. Docket 2003-NM-03-
AD. Supersedes AD 2001-22-09, Amendment 39-12488.
Applicability: Model CL-600-2B19 series airplanes, certificated
in any category, having serial numbers 7003 and subsequent, equipped
with main landing gear (MLG) main fittings having part numbers (P/N)
601R85001-3 and 601R85001-4 (Messier Dowty, Inc. P/Ns 17064-101,
17064-102, 17064-103, and 17064-104).
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 (m)(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
[[Page 31959]]
been eliminated, the request should include specific proposed
actions to address it.
Compliance: Required as indicated, unless accomplished
previously.
Note 2: Where there are differences between the referenced
service bulletin and the AD, the AD prevails.
To prevent failure of the MLG main fittings, which could result
in collapse of the MLG upon landing, accomplish the following:
Service Bulletin References
(a) Accomplishment of the inspections and servicing, as
applicable, specified in paragraphs (c), (g), (h), and (i) of this
AD, per Bombardier Alert Service Bulletin A601R-32-079, dated
December 3, 1999; Revision ``A,'' dated January 7, 2000; Revision
``B,'' dated June 1, 2000; Revision ``C,'' dated October 26, 2000;
or Revision ``D,'' dated December 1, 2000; prior to the effective
date of this AD, is considered acceptable for compliance with the
requirements of paragraphs (c), (g), (h), and (i) of this AD.
(b) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Bombardier Alert Service Bulletin
A601R-32-079, Revision ``E,'' dated September 12, 2002; including
Appendix 1, Revision D, dated September 12, 2002; including
Appendices 2 and 3, dated September 12, 2002.
Initial Eddy Current Inspection
(c) Perform an eddy current inspection to detect cracking of the
MLG main fittings, per PART B of the service bulletin, at the
earlier of the times specified in paragraph (c)(1) or (c)(2) of this
AD.
(1) Prior to the accumulation of 1,500 total flight cycles on
the MLG, or within 150 flight cycles after December 4, 2001 (the
effective date of AD 2001-22-09, amendment 39-12488), whichever
occurs later.
(2) Prior to the accumulation of 1,000 total flight cycles on
the MLG, or within 150 flight cycles after the effective date of
this AD, whichever occurs later.
Repetitive Eddy Current Inspections
(d) Repeat the eddy current inspection specified in paragraph
(c) of this AD at the time specified in paragraph (d)(1), (d)(2), or
(d)(3), as applicable, except as provided by paragraph (d)(4) of
this AD, per PART B of the service bulletin.
(1) For airplanes on which the eddy current inspection required
by paragraph (c) of this AD is accomplished after the effective date
of this AD: Repeat the inspection at intervals not to exceed 500
flight cycles.
(2) For airplanes on which the repetitive eddy current
inspection required by AD 2001-22-09, amendment 39-12488, has been
accomplished, and on which the repetitive intervals have been
increased per paragraph (e) of AD 2001-22-09 before the effective
date of this AD: Repeat the inspection within 500 flight cycles
after the effective date of this AD, or within 1,000 flight cycles
since the last eddy current inspection, whichever occurs first, and
thereafter at intervals not to exceed 500 flight cycles.
(3) For airplanes on which the repetitive eddy current
inspection required by AD 2001-22-09 has been accomplished, and on
which the repetitive intervals have not been increased per paragraph
(e) of AD 2001-22-09 before the effective date of this AD: Repeat
the eddy current inspection at intervals not to exceed 500 flight
cycles.
(4) For airplanes on which an eddy current inspection has been
accomplished to confirm the detailed inspection required by
paragraph (j) of this AD: The next eddy current inspection must be
done within 500 flight cycles following the last detailed inspection
required by paragraph (j) of this AD, and thereafter at intervals
not to exceed 500 flight cycles.
Corrective Actions
(e) If no cracking of the MLG main fittings is suspected during
the next eddy current inspection required by paragraph (c) or (d) of
this AD, but the paint has been removed: Prior to further flight,
apply a new finish and install the harness clamp on the brake line
with the bolt, washers, nut, and cotter pin; per PART B of the
service bulletin.
(f) If any cracking of the MLG main fittings is found during any
eddy current inspection required by paragraph (c) or (d) of this AD:
Prior to further flight, replace any cracked MLG main fitting with a
new or serviceable part per the service bulletin.
Servicing the Shock Struts
(g) Prior to the accumulation of 1,500 total flight cycles on
the MLG shock struts, or within 500 flight cycles after December 4,
2001, whichever occurs later: Service (Oil and Nitrogen) the left
and right MLG shock struts per PART C (for airplanes on the ground)
or PART D (for airplanes on jacks) of the service bulletin.
Other Inspections
(h) Within 500 flight cycles after completing the actions
required by paragraph (g) of this AD: Inspect the MLG left and right
shock struts for nitrogen pressure, visible chrome dimension, and
oil leakage, in accordance with PART E of the service bulletin.
Thereafter, repeat the inspection at intervals not to exceed 500
flight cycles.
Corrective Actions for Certain Inspections
(i) If the chrome extension dimension of the shock strut
pressure reading is outside the limits specified in the Airplane
Maintenance Manual, Task 32-11-05-220-801, or any oil leakage is
found during any inspection required by paragraph (h) of this AD:
Prior to further flight, service the MLG shock strut in accordance
with PART C (for airplanes on the ground) or PART D (for airplanes
on jacks) of the service bulletin.
Detailed and Follow-on Inspections, and Corrective Action
(j) Prior to the accumulation of 1,000 total flight cycles on
the MLG, or within 250 flight cycles after the effective date of
this AD, whichever occurs later: Accomplish a detailed inspection of
the MLG main fittings to detect signs of cracking (including linear
paint cracks along the circumference of the main fitting tube, lack
of paint (paint peeling) or other paint damage, lack of adhesion or
paint bulging, and signs of corrosion), per PART A of the service
bulletin. Repeat the inspection thereafter at intervals not to
exceed 100 flight cycles.
Note 3: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
(k) If any linear paint crack along the circumference of the
main fitting tube, lack of paint (paint peeling) or other paint
damage, evidence of paint bulging due to lack of adhesion, or
evidence of corrosion is found during any inspection required by
paragraph (j) of this AD: Prior to further flight, accomplish either
an eddy current inspection to detect cracking, per PART B of the
service bulletin; or a fluorescent penetrant inspection to detect
cracking, per PART F of the service bulletin.
(1) If no cracking of the MLG main fittings is found during any
inspection required by paragraph (k) of this AD: Prior to further
flight, repaint and/or repair/rework any paint damage per PART B of
the service bulletin.
(2) If any cracking of the MLG main fittings is found during any
inspection required by paragraph (k) of this AD: Prior to further
flight, replace any cracked MLG main fitting with a new or
serviceable part per the service bulletin.
Reporting Requirement
(l) Within 30 days after each inspection and servicing required
by paragraphs (c), (d), (g), (h), (j), and (k) of this AD, report
all findings, positive or negative, to: Bombardier Aerospace, In-
Service Engineering, fax number 514-855-8501. Although the service
bulletin references completion of a ``Service Bulletin Comment
Sheet-Facsimile Reply Sheet,'' this AD does not require that action.
Information collection requirements contained in this regulation
have been approved by the Office of Management and Budget (OMB)
under the provisions of the Paperwork Reduction Act of 1980 (44
U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-
0056.
Alternative Methods of Compliance
(m)(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. 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 issued to allow escalation
of the repetitive intervals for the eddy current inspections from
500 to 1,000 flight cycles, per paragraph (e) of AD 2001-22-09, are
not approved as alternative methods of compliance with this AD.
Note 4: Information concerning the existence of approved
alternative methods of
[[Page 31960]]
compliance with this AD, if any, may be obtained from the New York
ACO.
Special Flight Permits
(n) 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.
Incorporation by Reference
(o) Unless otherwise specified by this AD, the actions shall be
done per Bombardier Alert Service Bulletin A601R-32-079, Revision
``E,'' dated September 12, 2002; including Appendix 1, Revision D,
dated September 12, 2002; including Appendices 2 and 3, dated
September 12, 2002; which includes the following effective pages:
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Revision Level
Page Number Shown on Page Date Shown on Page
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1-30............................ E................. September 12,
2002.
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Appendix 1
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A1-A10.......................... D................. September 12,
2002.
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Appendix 2
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A1-A2........................... Original.......... September 12,
2002.
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Appendix 3
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A1-A8........................... Original.......... September 12,
2002.
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This incorporation by reference is 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, 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, 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-1999-32R2, dated September 19, 2002.
Effective Date
(p) This amendment becomes effective on June 13, 2003.
Issued in Renton, Washington, on May 20, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-13120 Filed 5-28-03; 8:45 am]
BILLING CODE 4910-13-P