Airworthiness Directives: Bombardier, Inc. (Type Certificate Previously Held by Canadair) Model CL-600-2B16 (CL-604) Airplanes
Federal Register: January 4, 2010 (Volume 75, Number 1)
Proposed Rules
Page 91-94
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
DOCID:fr04ja10-22
Page 91
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 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec
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 under the ADDRESSES 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 authority 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 replacement 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.
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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 proposed 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 develop 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 responsibilities 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 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.
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:
Bombardier, Inc. (Type Certificate Previously Held by Canadair):
Docket No. FAA-2009-1227; Directorate Identifier 2009-NM-119-AD.
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.
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(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 required. 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 effective 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 fluorescent penetrant inspection is referred to as a ``penetrant check.''
(4) As of the effective date of this AD, for airplanes on which the inspection 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.
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(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 Aircraft 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.
FR Doc. E9-31137 Filed 12-31-09; 8:45 am
BILLING CODE 4910-13-P
