[Federal Register: May 7, 2004 (Volume 69, Number 89)]
[Rules and Regulations]
[Page 25485-25488]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07my04-4]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-175-AD; Amendment 39-13628; AD 2004-09-37]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-1A11 (CL-600),
CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-
604) Series 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 transport category airplanes,
that currently requires a detailed inspection to detect cracks of the
vane brackets of the inboard flap actuator beam, and follow-on
repetitive detailed inspections or corrective actions, as applicable.
That AD also provides for two optional terminating actions for the
detailed inspection(s). This action requires performing one or the
other of the terminating actions. The actions specified by this AD are
intended to detect and correct gaps between the flap vane bracket and
the adjacent lower skin and between the flap vane bracket and vane
actuator beam, and premature cracking of the flap vane brackets, which
could result in failure of the flap vane bracket(s) when the flaps are
extended and the flap vane is aerodynamically loaded, and consequent
reduced controllability of the airplane. This action is intended to
address the identified unsafe condition.
DATES: Effective June 11, 2004.
The incorporation by reference of certain publications listed in
the regulations was previously approved by the Director of the Federal
Register as of May 8, 2003 (68 FR 19940, April 23, 2003).
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, New York Aircraft Certification
Office, 1600 Stewart Avenue, suite 410, Westbury, New York; or at the
National Archives and Records Administration (NARA). For information on
the availability of this material at NARA, call (202) 741-6030, or go
to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
FOR FURTHER INFORMATION CONTACT: Serge Napoleon, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New
York 11590; telephone (516) 228-7312; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 2003-08-12,
amendment 39-13125 (68 FR 19940, April 23, 2003), which is applicable
to certain Bombardier transport category airplanes, was published in
the Federal Register on February 13, 2004 (69 FR 7170). That action
proposed to continue to require a detailed inspection to detect cracks
of the vane brackets of the inboard flap actuator beam, and follow-on
repetitive detailed inspections or corrective actions, as applicable.
That action also proposed to require performing one or the other of two
terminating actions.
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 411 airplanes of U.S. registry that will be
affected by this AD.
The detailed inspection that is currently required by AD 2003-08-
12, amendment 39-13125, takes approximately 11 work hours per airplane
to accomplish, at an average labor rate of $65 per work hour. Based on
these figures, the cost impact of the currently required actions on
U.S. operators is estimated to be $293,865, or $715 per airplane, per
inspection cycle.
The terminating corrective actions specified in Part B of the
Accomplishment Instructions of the applicable alert service bulletin
identified in Table 2 of this AD, take approximately 24 work hours per
airplane to accomplish the inspections and between 4 and 48 work hours
per airplane to accomplish the replacement of the vane bracket(s), at
an average labor rate of $65 per work hour. Required parts will cost
between $535 and $6,414 for the vane brackets. Based on these figures,
the cost impact of the terminating corrective actions on U.S. operators
is estimated to be between $967,905 and $4,559,634, or between $2,355
and $11,094 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. The cost
impact figures discussed in AD rulemaking actions represent only the
time necessary to perform the specific actions actually required by the
AD. These figures typically do not include incidental costs, such as
the time required to gain access and close up, planning time, or time
necessitated by other administrative actions.
The optional terminating corrective actions specified in Part C of
the Accomplishment Instructions of the applicable alert service
bulletin identified in Table 2 of this AD, take approximately 80 work
hours per airplane to accomplish, at an average labor rate of $65 per
work hour. Required parts will cost approximately $6,414 for the vane
brackets. Based on these figures, the cost impact of the terminating
corrective actions on U.S. operators is estimated to be $4,773,354 or
between $11,614 per airplane.
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.
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
[[Page 25486]]
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
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 39-13125 (68 FR
19940, April 23, 2003), and by adding a new airworthiness directive
(AD), amendment 39-13628, to read as follows:
2004-09-37 Bombardier, Inc.: Amendment 39-13628. Docket 2003-NM-175-
AD. Supersedes AD 2003-08-12, Amendment 39-13125.
Applicability: This AD applies to the airplanes listed in Table
1 of this AD, certificated in any category. Table 1 is as follows:
Table 1.--Applicability
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Model Serial Nos.
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CL-600-1A11 (CL-600) series airplanes....... 1004 through 1085 inclusive.
CL-600-2A12 (CL-601) series airplanes....... 3001 through 3066 inclusive.
CL-600-2B16 (CL-601-3A and CL-601-3R) series 5001 through 5194 inclusive.
airplanes.
CL-600-2B16 (CL-604) series airplanes....... 5301 through 5499 inclusive.
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Compliance: Required as indicated, unless accomplished
previously.
To detect and correct gaps between the flap vane bracket and the
adjacent lower skin and between the flap vane bracket and vane
actuator beam, and premature cracking of the flap vane brackets,
which could result in failure of the flap vane bracket(s) when the
flaps are extended and the flap vane is aerodynamically loaded, and
consequent reduced controllability of the airplane; accomplish the
following:
Note 1: Where there are differences between this AD and the
applicable Bombardier alert service bulletin specified in Table 2 of
this AD, the AD prevails.
Restatement of Requirements of AD 2003-08-12
Inspection
(a) Do a detailed inspection to detect cracks of the vane
brackets of the inboard flap actuator beam, per Part A of the
Accomplishment Instructions of the applicable Bombardier alert
service bulletin specified in Table 2 of this AD; at the applicable
time indicated in Table 3 of this AD. Table 2 is as follows:
Table 2.--Alert Service Bulletins
------------------------------------------------------------------------
Bombardier alert
Model service bulletin Excluding
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CL-600-1A11 (CL-600) series A600-0699, Revision Service Bulletin
airplanes. 01, dated July 8, Incorporation
2002. Sheet, Flap Vane
Bracket Inspection
Program page, and
Minimum Edge
Distance Inspection
pages.
CL-600-2A12 (CL-601) series A601-0532, Revision Service Bulletin
airplanes, and CL-600-2B16 01, dated July 8, Incorporation
(CL-601-3A and CL-601-3R) 2002. Sheet, Flap Vane
series airplanes. Bracket Inspection
Program page, and
Minimum Edge
Distance Inspection
pages.
CL-600-2B16 (CL-604) series A604-27-007, Service Bulletin
airplanes. Revision 01, dated Incorporation
July 8, 2002. Sheet, Flap Vane
Bracket Inspection
Program page, and
Minimum Edge
Distance Inspection
pages.
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Table 3 is as follows:
Table 3.--Compliance Times
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For airplanes that have accumulated-- The compliance time is--
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1,200 total landings or less as of May Before the accumulation of
8, 2003 (the effective date of AD 2003- 1,300 total landings.
08-12).
More than 1,200 total landings, but Within 100 landings after May
less than 3,000 total landings as of 8, 2003 (the effective date of
May 8, 2003 (the effective date of AD AD 2003-08-12).
landings after 2003-08-12).
3,000 total landings or more as of May Within 50 landings after May 8,
8, 2003 (the effective date of AD 2003- 2003 (the effective date of AD
08-12). 2003-08-12).
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[[Page 25487]]
Note 2: 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.''
No Crack Findings: Repetitive Inspections
(b) If no crack is detected during the detailed inspection
required by paragraph (a) of this AD, repeat that inspection
thereafter at intervals not to exceed 100 landings.
Crack Findings: Corrective Actions
(c) If any crack is detected during the detailed inspection
required by paragraph (a) of this AD, before further flight, do the
actions specified in paragraph (e) or (f) of this AD.
New Requirements of This AD
Terminating Actions
(d) Do the actions specified in paragraph (e) or (f) of this AD,
at the applicable time listed in Table 4--Compliance Time--
Terminating Actions.
Table 4.--Compliance Time--Terminating Actions
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For airplanes that have accumulated-- The compliance time is--
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Less than 2,000 total landings as of Within 600 total landings after
the effective date of this AD. the effective date of this AD.
2,000 or more total landings as of the Within 400 total landings after
effective date of this AD. the effective date of this AD.
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(e) Do the actions specified in paragraphs (e)(1), (e)(2), and
(e)(3) of this AD per Part B of the Accomplishment Instructions of
the applicable alert service bulletin identified in Table 2 of this
AD, unless otherwise specified in this AD. Accomplishment of these
actions constitutes compliance with the requirements of paragraphs
(a), (b), and (c) of this AD.
(1) Do a detailed inspection to detect gaps at flap stations
60.0, 98.5, and 137.0 between the vane bracket(s) and adjacent lower
skin and vane actuator beam. If any gap is in excess of the limits
specified in the applicable alert service bulletin, before further
flight, repair per a method approved by either the Manager, New York
Aircraft Certification Office (ACO), FAA; or Transport Canada Civil
Aviation (TCCA) (or its delegated agent).
(2) Measure the minimum edge distance (MED) for the fastener
holes in all flap vane brackets and actuator beams. If the MED
requirements for any bracket or actuator beam do not meet the
allowable values specified in Figure 2 of the applicable alert
service bulletin, before further flight, replace the out-of-
tolerance bracket and/or actuator beam with a new bracket and/or
actuator beam that meets the MED requirements specified in Figure 2
of the applicable alert service bulletin.
(3) Do a nondestructive test (NDT) inspection on all vane
brackets for cracks. If any crack is found, before further flight,
accomplish the corrective actions (e.g., remove gaps, ensure that
the MED requirements for the replacement brackets meet the allowable
values specified in Figure 2 of the applicable alert service
bulletin, and replace any cracked vane bracket with a new bracket
that meets the MED requirements specified in Figure 2 of the
applicable alert service bulletin). Although the applicable alert
service bulletin describes procedures for identifying and returning
all cracked vane brackets to Bombardier, this AD does not require
such actions.
(f) In lieu of the actions specified in paragraph (e) of this
AD, do the actions specified in paragraphs (f)(1) and (f)(2) of this
AD per Part C of the Accomplishment Instructions of the applicable
alert service bulletin identified in Table 2 of this AD.
Accomplishment of these actions constitutes compliance with the
requirements of paragraphs (a), (b), and (c) of this AD.
(1) Replace all 12 vane brackets with new brackets that meet the
MED requirements specified in Figure 2 of the applicable alert
service bulletin (including removal of any gap between the vane
brackets and the adjacent lower skin and actuator beams).
(2) Measure the MED for the fastener holes in all replacement
flap vane brackets and actuator beams (including a detailed
inspection for gaps).
(i) If the MED requirements for any bracket or actuator beam do
not meet the allowable values specified in Figure 2 of the
applicable alert service bulletin, before further flight, replace
the out-of-tolerance bracket and/or actuator beam with a new bracket
and/or actuator beam that meets the MED requirements specified in
Figure 2 of the applicable alert service bulletin.
(ii) If any gap is detected, before further flight, repair the
gap.
Other Means of Acceptable Compliance With Paragraph (f) of This AD
(g) Accomplishment of the inspections and modifications per Part
B or Part C of the applicable alert service bulletin listed in Table
5 of this AD; and the MED dimension checks for the flap brackets and
the actuator beams as specified in drawing K600-14251, including any
required rework; is considered acceptable for compliance with the
requirements of paragraph (f) of this AD. Table 5 of this AD is as
follows:
Table 5.--Acceptable Basic Issue Alert Service Bulletins
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Use bombardier alert service
For model-- bulletin--
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CL-600-1A11 (CL-600) series airplanes.. A600-0699, Basic Issue, dated
November 29, 2001.
CL-600-2A12 (CL-601) series airplanes, A601-0532, Basic Issue, dated
and CL-600-2B16 (CL-601-3A and CL-601- November 29, 2001.
3R) series airplanes.
CL-600-2B16 (CL-604) series airplanes.. A604-27-007, Basic Issue, dated
November 29, 2001.
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Time Limits/Maintenance Checks
(h) After doing the actions specified in paragraph (e) or (f) of
this AD, revise the Airworthiness Limitation section (ALS) of the
Instructions for Continued Airworthiness to state the following
(this may be accomplished by inserting a copy of this AD in the
ALS): ``Do the applicable Time Limits/Maintenance Checks (TLMC)
inspection task for the flap vane brackets at the times specified in
the following table:''
Table.--Compliance Time for TLMCs
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Condition of brackets and gaps Compliance time
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No gap or crack in any flap vane Continue using existing TLMC
bracket. bracket schedule as published
in the applicable ALS.
[[Page 25488]]
No crack in any flap vane bracket, but For Model CL-600-1A11 (CL-600),
shims added. CL-600-2A12 (CL-601), and CL-
600-2B16 (CL-601-3A and CL-601-
3R) series airplanes:
Repeat inspections remain at
600 landings from rework.
For Model CL-600-2B16 (CL-604)
series airplanes:
Repeat inspections remain at
1,800 landings from rework.
All 12 flap vane brackets have been For Model CL-600-1A11 (CL-600),
replaced. CL-600-2A12 (CL-601), and CL-
600-2B16 (CL-601-3A and CL-601-
3R) series airplanes:
New threshold of 7,000 landings
from installation of new flap
vane brackets. Repeat
inspections remain at 600
landings.
For Model CL-600-2B16 (CL-604)
series airplanes:
New threshold of 7,200 landings
from installation of new flap
vane brackets. Repeat
inspections remains at 1,800
landings.
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(i) After doing the requirements of paragraph (h) of this AD,
except as provided in paragraph (j) of this AD, no alternative
inspection times may be approved for these flap vane brackets.
Alternative Methods of Compliance
(j) In accordance with 14 CFR 39.19, the Manager, New York ACO,
FAA, is authorized to approve alternative methods of compliance
(AMOCs) for this AD.
Incorporation by Reference
(k) Unless otherwise specified in this AD, the actions shall be
done in accordance with the following Bombardier alert service
bulletins as listed in Table 6 of this AD, as applicable. Table 6 of
this AD is as follows:
Table 6.--Alert Service Bulletins
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Bombardier alert service bulletin Excluding
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A600-0699, Revision 01, dated July 8, Service Bulletin Incorporation
2002. Sheet, Flap Vane Bracket
Inspection Program page, and
Minimum Edge Distance
Inspection pages.
A601-0532, Revision 01, dated July 8, Service Bulletin Incorporation
2002. Sheet, Flap Vane Bracket
Inspection Program page, and
Minimum Edge Distance
Inspection pages
A604-27-007, Revision 01, dated July 8, Service Bulletin Incorporation
2002. Sheet, Flap Vane Bracket
Inspection Program page, and
Minimum Edge Distance
Inspection pages.
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This incorporation by reference was previously approved by the
Director of the Federal Register as of May 8, 2003 (68 FR 19940,
April 23, 2003). Copies of the service bulletins 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, 1600 Stewart Avenue, suite 410, Westbury, New
York; or at the National Archives and Records Administration (NARA).
For information on the availability of this material at NARA, call
(202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Note 3: The subject of this AD is addressed in Canadian
airworthiness directives CF-2002-36 and CF-2002-37, both effective
August 30, 2002.
Effective Date
(1) This amendment becomes effective on June 11, 2004.
Issued in Renton, Washington, on April 28, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-10375 Filed 5-6-04; 8:45 am]
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