Document ID: FAA-2009-1227-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Bombardier, Inc. (Type Certificate Previously Held by Canadair) Model CL-600-2B16 (CL-604) Airplanes
Posted Date: 2010-01-04T05:00Z

[Federal Register Volume 75, Number 1 (Monday, January 4, 2010)]
[Proposed Rules]
[Pages 91-94]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-31137]

[[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.

[[Page 92]]

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.

[[Page 93]]

    (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.

[[Page 94]]

    (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