COMMENTS DUE DATE
(a) We must receive comments by February 18, 2010.
AFFECTED ADS
(b) None.
APPLICABILITY
(c) This AD applies to Bombardier, Inc. (Type Certificate previously held
by Canadair) Model CL-600-2B16 (CL-604) airplanes; certificated in any
category; serial numbers 5408 through 5665 inclusive.
SUBJECT
(d) Air Transport Association (ATA) of America Code 24: Electrical Power.
REASON
(e) The mandatory continuing airworthiness information (MCAI) states:
Two cases of a crack on a "dry" ADG (Air Driven Generator) (Hamilton
Sundstrand part number in the 761339 series) in the aft area of the strut
and generator housing assembly, have been reported on CL-600-2B19
aircraft. The same part number is also installed on CL-600-2B16 (CL-604)
aircraft. Investigation determined that the crack was in an area of the
strut where the wall thickness of the casting was below specification, due
to a manufacturing anomaly in a specific batch of ADGs. Structural failure
and departure of the ADG during deployment could possibly result in damage
to the aircraft structure. If deployment were activated by a dual engine
shutdown, ADG structural failure would also result in loss of hydraulics
for the flight controls.
This directive gives instructions to check the part number of the
installed ADG and, for ADGs with a part number in the 761339 series, the
serial numbers of the ADG and the strut and generator housing assembly are
also to be checked. If these serial numbers are within specified ranges *
* *, initial and subsequent repeat fluorescent penetrant inspections of
the ADG strut are required.
This directive also gives instructions to perform a fluorescent penetrant
inspection after each unscheduled in-flight ADG deployment and a [general]
visual inspection after each unscheduled on-ground ADG deployment.
Instructions regarding re-identification (where applicable) and
replacement parts are also included.
The unsafe condition is possible loss of control of the airplane.
ACTIONS AND COMPLIANCE
(f) Unless already done, do the following actions.
(1) Within 400 flight hours after the effective date of this AD, inspect
to determine the part number of the installed ADG and accomplish the
actions required by paragraph (f)(1)(i) or (f)(1)(ii) of this AD, as
applicable. A review of airplane maintenance records is acceptable in
lieu of this inspection if the part number of the ADG can be
conclusively determined from that review.
(i) If the part number of the ADG is 604-90800-23 (Hamilton Sundstrand
part number 1711405), the strut wall thickness is within specification
and no further action is required by this paragraph.
(ii) If the part number of the ADG is 604-90800-1, -17 or -19 (Hamilton
Sundstrand part number in the 761339 series), inspect to determine
the ADG serial number and do the applicable action required by
paragraph (f)(1)(ii)(A), (f)(1)(ii)(B), or (f)(1)(ii)(C) of this AD.
A review of airplane maintenance records is acceptable in lieu of
this inspection if the serial number of the ADG can be conclusively
determined from that review.
(A) If the serial number of the ADG is 2000 or higher, the strut wall
thickness is within specification and only re-identification is req-
uired. Do the actions required by paragraph (f)(8) of this AD.
(B) If the serial number of the ADG is in the range 0101 through 1999
inclusive, and the symbol 24-3 is marked in the serial number block of
the identification plate, the strut wall thickness is within
specification and only re-identification is required. Do the actions
required by paragraph (f)(8) of this AD.
(C) If the serial number of the ADG is in the range 0101 through 1999
inclusive, and the symbol 24-3 is not marked in the serial number
block of the identification plate, inspect to determine the serial
number of the strut and generator housing assembly and do the
applicable action required by paragraph (f)(1)(ii)(C)(1) or
(f)(1)(ii)(C)(2) of this AD, as applicable.
NOTE 1: Guidance on serial number location can be found in Figure 1, Sheet
1, of Hamilton Sundstrand Service Bulletin ERPS10AG-24-3, Revision 3,
dated March 12, 2009.
(1) If the serial number of the strut and generator housing assembly is in
the range 0001 through 2503 inclusive, the fluorescent penetrant
inspection specified in paragraph (f)(2) of this AD is required. For
airplanes on which an unscheduled in-flight or on-ground ADG
deployment has occurred after accomplishing the actions required by
this paragraph, do the actions required by paragraph (f)(6), (f)(7),
or (f)(8) of this AD, as applicable.
(2) If the serial number of the strut and generator housing assembly is
2504 or higher, the strut wall thickness is within specification and
only re-identification is required. Do the actions required by
paragraph (f)(8) of this AD.
(2) For airplanes having a strut and generator housing assembly identified
in paragraph (f)(1)(ii)(C)(1), except for airplanes with serial
numbers 5611 through 5665 on which Bombardier conducted the initial
fluorescent penetrant inspection prior to aircraft delivery and on
which the ADG has not been replaced since aircraft delivery: Within
400 flight hours after the effective date of this AD, do a fluorescent
penetrant inspection of the ADG strut, and replace the ADG, as
applicable, in accordance with paragraphs 2.A., 2.C., and 2.D. of the
Accomplishment Instructions in Bombardier Alert Service Bulletin A604
-24-017, Revision 01, dated January 15, 2007. If the ADG is replaced
by an ADG with part number 604-90800-23 (Hamilton Sundstrand part
number 1711405), no further action is required by this paragraph.
Accomplishing the requirements in paragraph (f)(4) of this AD is
required for airplanes on which each ADG has been inspected in
accordance with this paragraph.
(3) Accomplishment of the fluorescent penetrant inspection before the eff-
ective date of this AD in accordance with the applicable service
information identified in the Table 1 of this AD is acceptable for
compliance with the requirements of paragraph (f)(2) of this AD.
TABLE 1--ACCEPTABLE SERVICE INFORMATION
------------------------------------------------------------------------
DOCUMENT REVISION DATE
------------------------------------------------------------------------
Bombardier Alert Service Original........ May 6, 2005.
Bulletin 604-24-017.
Hamilton Sundstrand Service Original........ April 14, 2005.
Bulletin ERPS10AG-24-3.
Hamilton Sundstrand Service Revision 1...... April 19, 2005.
Bulletin ERPS10AG-24-3.
Hamilton Sundstrand Service Revision 2...... November 14, 2006.
Bulletin ERPS10AG-24-3.
Hamilton Sundstrand Service Revision 3...... March 12, 2009.
Bulletin ERPS10AG-24-3.
--------------------------------------------------------------------------
NOTE 2: In Hamilton Sundstrand Service Bulletin ERPS10AG-24-3, the fluor-
escent penetrant inspection is referred to as a "penetrant check."
(4) As of the effective date of this AD, for airplanes on which the in-
spection required by paragraph (f)(2) of this AD has been done and on
which a scheduled ADG operational test is performed: Before further
flight after each test, do a general visual inspection of the ADG
strut for cracks, and replace the ADG if any crack is found, in
accordance with paragraphs 2.A., 2.C., and 2.D. of the Accomplishment
Instructions in Bombardier Alert Service Bulletin A604-24-017,
Revision 01, dated January 15, 2007. If the ADG is replaced by an ADG
with part number 604-90800-23 (Hamilton Sundstrand part number
1711405), no further action is required by this paragraph.
(5) As of the effective date of this AD, for airplanes identified in
paragraph (f)(1)(ii)(C)(1) of this AD on which an unscheduled in
-flight ADG deployment occurs: Before further flight after each
deployment, do a general visual inspection of the ADG strut for
cracks, and replace the ADG if any crack is found, in accordance with
paragraphs 2.A., 2.B., and 2.D. of the Accomplishment Instructions in
Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated
January 15, 2007. [If the ADG is replaced by an ADG with part number
604-90800-23 (Hamilton Sundstrand part number 1711405), no further
action is required by this paragraph.] The general visual inspection
required by this paragraph is not required if the fluorescent
penetrant inspection required by paragraph (f)(6) of this AD is
performed before further flight.
(6) For airplanes identified in paragraph (f)(1)(ii)(C)(1) of this AD on
which an unscheduled in-flight ADG deployment occurs: Within 3 days or
10 hours time-in-service, whichever comes first, after each
deployment, perform a fluorescent penetrant inspection of the ADG
strut, and replace the ADG, as applicable, in accordance with
paragraphs 2.A., 2.C., and 2.D. of the Accomplishment Instructions in
Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated
January 15, 2007. If the ADG is replaced by an ADG with part number
604-90800-23 (Hamilton Sundstrand part number 1711405), no further
action is required by this paragraph.
(7) For airplanes identified in paragraph (f)(1)(ii)(C)(1) of this AD on
which an unscheduled on-ground ADG deployment task is done: Before
further flight after each deployment, do a general visual inspection
of the ADG strut for cracks, and replace the ADG if any crack is
found, in accordance with paragraphs 2.A., 2.B., and 2.D. of the
Accomplishment Instructions in Bombardier Alert Service Bulletin A604
-24-017, Revision 01, dated January 15, 2007. If the ADG is replaced
by an ADG with part number 604-90800-23 (Hamilton Sundstrand part
number 1711405), no further action is required by this paragraph.
(8) For airplanes identified in paragraphs (f)(1)(ii)(A), (f)(1)(ii)(B),
and (f)(1)(ii)(C)(2) of this AD: Within 400 flight hours after the
effective date of this AD, re-identify the ADG, in accordance with the
Accomplishment Instructions in Bombardier Service Bulletin 604-24-019,
dated October 1, 2007. Following re-identification, no further action
is required by this paragraph.
NOTE 3: Paragraph (f)(8) of this AD is applicable only if required by
paragraph (f)(1)(ii)(A), (f)(1)(ii)(B), or (f)(1)(ii)(C)(2) of this AD.
The strut wall thickness of the ADGs specified in these paragraphs is not
below specification.
(9) As of the effective date of this AD, no person may install an ADG
having part number 604-90800-1, -17, or -19 (Hamilton Sundstrand part
number in the 761339 series) on any airplane if the serial number of
the ADG is in the range 0101 through 1999 strut and the serial number
of the generator housing assembly is in the range 0001 through 2503.
NOTE 4: The Bombardier CL-604 Illustrated Parts Catalog specifies that,
for an ADG with a Hamilton Sundstrand part number in the 761339 series,
future procurement is to be an ADG with Hamilton Sundstrand part number
1711405.
(10) Although Bombardier Alert Service Bulletin A604-24-017, Revision 01,
dated January 15, 2007; and Service Bulletin 604-24- 019, dated
October 1, 2007; specify submitting certain information to the
manufacturer, this AD does not require that submission.
FAA AD DIFFERENCES
NOTE 5: This AD differs from the MCAI and/or service information as
follows: Although the MCAI or service information tells you to submit
information to the manufacturer, paragraph (f)(10) of this AD specifies
that such submittal is not required.
OTHER FAA AD PROVISIONS
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Air-
craft Certification Office (ACO), FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. Send information to ATTN: Program Manager, Continued
Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone (516) 228- 7300; fax (516) 794
-5531. Before using any approved AMOC on any airplane to which the
AMOC applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office. The
AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain corrective
actions from a manufacturer or other source, use these actions if they
are FAA-approved. Corrective actions are considered FAA-approved if
they are approved by the State of Design Authority (or their delegated
agent). You are required to assure the product is airworthy before it
is returned to service.
RELATED INFORMATION
(h) Refer to MCAI Canadian Airworthiness Directive CF-2009-24, issued May
19, 2009; Bombardier Alert Service Bulletin A604-24-017, Revision 01,
dated January 15, 2007; and Bombardier Service Bulletin 604-24-019,
dated October 1, 2007; for related information.
Issued in Renton, Washington, on December 23, 2009. Ali Bahrami, Manager,
Transport Airplane Directorate, Aircraft Certification Service.
DATES: We must receive comments on this proposed AD by February 18, 2010.
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
14 CFR Part 39
[Docket No. FAA-2009-1227; Directorate Identifier 2009-NM-119-AD] RIN
2120-AA64
AIRWORTHINESS DIRECTIVES; Bombardier, Inc. (Type Certificate Previously
Held by Canadair) Model CL-600-2B16 (CL-604) Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
--------------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an aviation
product. The MCAI describes the unsafe condition as: Two cases of a crack
on a "dry" ADG (Air Driven Generator) (Hamilton Sundstrand part number in
the 761339 series) in the aft area of the strut and generator housing
assembly, have been reported on CL-600-2B19 aircraft. The same part number
is also installed on CL-600-2B16 (CL-604) aircraft. Investigation
determined that the crack was in an area of the strut where the wall
thickness of the casting was below specification, due to a manufacturing
anomaly in a specific batch of ADGs. Structural failure and departure of
the ADG during deployment could possibly result in damage to the aircraft
structure. If deployment were activated by a dual engine shutdown, ADG
structural failure would also result in loss of hydraulics for the flight
controls. The unsafe condition is possible loss of control of the
airplane. The proposed AD would require actions that are intended to
address the unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by February 18, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the
instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except
Federal holidays.
For service information identified in this proposed AD, contact
Bombardier, Inc., 400 Cote-Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514-855-5000; fax 514-855-7401; e-mail
thd.crj@aero.bombardier.com; Internet http://www.bombardier.com. You may
review copies of the referenced service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For
information on the availability of this material at the FAA, call 425-227
-1221 or 425-227-1152.
EXAMINING THE AD DOCKET
You may examine the AD docket on the Internet at http://www.regulations.
gov; or in person at the Docket Operations office between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone (800) 647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Craig Yates, Aerospace Engineer, Airframe
and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York
11590; telephone (516) 228-7355; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
COMMENTS INVITED
We invite you to send any written relevant data, views, or arguments about
this proposed AD. Send your comments to an address listed u nder the ADD-
RESSES section. Include "Docket No. FAA-2009-1227; Directorate Identifier
2009-NM-119-AD" at the beginning of your comments. We specifically invite
comments on the overall regulatory, economic, environmental, and energy
aspects of this proposed AD. We will consider all comments received by the
closing date and may amend this proposed AD based on those comments.
We have lengthened the 30-day comment period for proposed ADs that address
MCAI originated by aviation authorities of other countries to provide
adequate time for interested parties to submit comments. The comment
period for these proposed ADs is now typically 45 days, which is
consistent with the comment period for domestic transport ADs.
We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
DISCUSSION
Transport Canada Civil Aviation (TCCA), which is the airworthiness author-
ity for Canada, has issued Canadian Airworthiness Directive CF-2009-24,
issued May 19, 2009 (referred to after this as "the MCAI"), to correct an
unsafe condition for the specified products. The MCAI states:
Two cases of a crack on a "dry" ADG (Air Driven Generator) (Hamilton
Sundstrand part number in the 761339 series) in the aft area of the strut
and generator housing assembly, have been reported on CL-600-2B19
aircraft. The same part number is also installed on CL-600-2B16 (CL-604)
aircraft. Investigation determined that the crack was in an area of the
strut where the wall thickness of the casting was below specification, due
to a manufacturing anomaly in a specific batch of ADGs. Structural failure
and departure of the ADG during deployment could possibly result in damage
to the aircraft structure. If deployment were activated by a dual engine
shutdown, ADG structural failure would also result in loss of hydraulics
for the flight controls.
This directive gives instructions to check the part number of the
installed ADG and, for ADGs with a part number in the 761339 series, the
serial numbers of the ADG and the strut and generator housing assembly are
also to be checked. If these serial numbers are within specified ranges *
* *, initial and subsequent repeat fluorescent penetrant inspections of
the ADG strut are required.
This directive also gives instructions to perform a fluorescent penetrant
inspection after each unscheduled in-flight ADG deployment and a [general]
visual inspection after each unscheduled on-ground ADG deployment.
Instructions regarding re-identification (where applicable) and replace-
ment parts are also included.
The unsafe condition is possible loss of control of the airplane. You may
obtain further information by examining the MCAI in the AD docket.
RELEVANT SERVICE INFORMATION
Bombardier has issued Alert Service Bulletin A604-24-017, Revision 01,
dated January 15, 2007; and Service Bulletin 604-24-019, dated October 1,
2007. The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
FAA'S DETERMINATION AND REQUIREMENTS OF THIS PROPOSED AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant to
our bilateral agreement with the State of Design Authority, we have been
notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
DIFFERENCES BETWEEN THIS AD AND THE MCAI OR SERVICE INFORMATION
We have reviewed the MCAI and related service information and, in general,
agree with their substance. But we might have found it necessary to use
different words from those in the MCAI to ensure the AD is clear for U.S.
operators and is enforceable. In making these changes, we do not intend to
differ substantively from the information provided in the MCAI and related
service information.
We might also have proposed different actions in this AD from those in the
MCAI in order to follow FAA policies. Any such differences are highlighted
in a NOTE within the proposed AD.
COSTS OF COMPLIANCE
Based on the service information, we estimate that this proposed AD would
affect about 378 products of U.S. registry. We also estimate that it would
take about 2 work-hours per product to comply with the basic requirements
of this proposed AD. The average labor rate is $80 per work-hour. Required
parts would cost about $0 per product. Where the service information lists
required parts costs that are covered under warranty, we have assumed that
there will be no charge for these costs. As we do not control warranty
coverage for affected parties, some parties may incur costs higher than
estimated here. Based on these figures, we estimate the cost of the prop-
osed AD on U.S. operators to be $60,480, or $160 per product.
AUTHORITY FOR THIS RULEMAKING
Title 49 of the United States Code specifies the FAA's authority to issue
rules on aviation safety. Subtitle I, section 106, describes the authority
of the FAA Administrator. "Subtitle VII: Aviation Programs," describes in
more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in "Subtitle
VII, Part A, Subpart III, Section 44701: General requirements." Under that
section, Congress charges the FAA with promoting safe flight of civil
aircraft in air commerce by prescribing regulations for practices,
methods, and procedures the Administrator finds necessary for safety in
air commerce. This regulation is within the scope of that authority
because it addresses an unsafe condition that is likely to exist or devel-
op on products identified in this rulemaking action.
REGULATORY FINDINGS
We determined that this proposed AD would not have federalism implications
under Executive Order 13132. This proposed AD would 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 responsib-
ilities among the various levels of government.
For the reasons discussed above, I certify 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 Proc-
edures (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 Regul-
atory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to comply with
this proposed AD and placed it in the AD docket.
LIST OF SUBJECTS IN 14 CFR PART 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference,
Safety.
THE PROPOSED AMENDMENT
Accordingly, under the authority delegated to me by the Administrator, the
FAA proposes to amend 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. The FAA amends Sec. 39.13 by adding the following new AD: