Document ID: FAA-2010-0550-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 and 440) Airplanes; et al.
Posted Date: 2010-06-18T04:00Z

[Federal Register: June 18, 2010 (Volume 75, Number 117)]
[Proposed Rules]               
[Page 34657-34661]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18jn10-18]                         

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0550; Directorate Identifier 2009-NM-124-AD]
RIN 2120-AA64

 
Airworthiness Directives; Bombardier, Inc. Model CL-600-2B19 
(Regional Jet Series 100 & 440) Airplanes; Model CL-600-2C10 (Regional 
Jet Series 700, 701, & 702) Airplanes; Model CL-600-2D15 (Regional Jet 
Series 705) Airplanes; and Model CL-600-2D24 (Regional Jet Series 900) 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

[[Page 34658]]

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 is also installed on 
CL-600-2C10, -2D15 and -2D24 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 was activated by a dual engine shutdown, ADG 
structural failure would also result in loss of hydraulics for the 
flight controls. 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 August 2, 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.

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-2010-0550; 
Directorate Identifier 2009-NM-124-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, which is the aviation authority 
for Canada, has issued Canadian Airworthiness Directive CF-2009-27, 
dated June 8, 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 is also installed on CL-600-
2C10, -2D15 and -2D24 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 was 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 strut and generator 
housing assembly are also to be checked. If these serial numbers are 
within specified ranges ***, a one-time fluorescent penetrant 
inspection of the ADG strut is required [and replacement of the ADG 
if necessary].
    Note: For ADGs with serial numbers in the *** specified ranges, 
subsequent fluorescent penetrant inspections are required after each 
scheduled in-flight or on-ground functional check of the ADG and 
also after each unscheduled in-flight ADG deployment. These 
inspection requirements are not mandated in this directive but are 
specified in the approved maintenance program.

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Bombardier has issued Alert Service Bulletin A601R-24-120, Revision 
C, dated April 20, 2009; and Alert Service Bulletin A670BA-24-020, 
Revision C, dated April 20, 2009. 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

[[Page 34659]]

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 1,073 products of U.S. registry. We also estimate 
that it would take about 1 work-hour per product to comply with the 
basic requirements of this proposed AD. The average labor rate is $85 
per work-hour. Based on these figures, we estimate the cost of the 
proposed AD on U.S. operators to be $91,205, or $85 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.: Docket No. FAA-2010-0550; Directorate Identifier 
2009-NM-124-AD.

Comments Due Date

    (a) We must receive comments by August 2, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bombardier, Inc. Model CL-600-2B19 
(Regional Jet Series 100 & 440) airplanes, serial numbers 7305 
through 8051 inclusive; Model CL-600-2C10 (Regional Jet Series 700, 
701, & 702) airplanes, serial numbers 10003 through 10260 inclusive; 
and Model CL-600-2D15 (Regional Jet Series 705) airplanes and Model 
CL-600-2D24 (Regional Jet Series 900) airplanes, serial numbers 
15001 through 15106 inclusive; certificated in any category.

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 is also installed on CL-600-
2C10, -2D15 and -2D24 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 was 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 strut and generator 
housing assembly are also to be checked. If these serial numbers are 
within specified ranges ***, a one-time fluorescent penetrant 
inspection of the ADG strut is required [and replacement of the ADG 
if necessary].

    Note: For ADGs with serial numbers in the * * * specified 
ranges, subsequent fluorescent penetrant inspections are required 
after each scheduled in-flight or on-ground functional check of the 
ADG and also after each unscheduled in-flight ADG deployment. These 
inspection requirements are not mandated in this directive but are 
specified in the approved maintenance program.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Actions

    (g) Do the following actions.
    (1) Within 1,000 flight hours after the effective date of this 
AD or before the first scheduled ADG functional test after the 
effective date of this AD, whichever occurs first, inspect to 
determine the part number of the installed ADG. A review of the 
airplane maintenance records is acceptable in lieu of this 
inspection if the part number can be conclusively determined from 
that review.
    (i) If a Hamilton Sundstrand ADG having part number 1711405 is 
installed, the strut thickness is within specification and no 
further action is required by this AD.
    (ii) If a Hamilton Sundstrand ADG having a part number in the 
761339 series is installed, within 1,000 flight hours after the 
effective date of this AD or before the first scheduled ADG 
functional test after the effective date of this AD, whichever 
occurs first, inspect to determine the serial number of the ADG. A 
review of the airplane maintenance records is acceptable in lieu of 
this inspection if the serial number 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 no further action is 
required by this AD.
    (B) If the serial number of the ADG is in the range 0101 through 
1999 and symbol ``24-3'' is marked in the serial number block of the 
identification plate, the strut wall thickness is within 
specification, no further action is required by this AD.
    (C) If the serial number of the ADG is in the range 0101 through 
1999 and the symbol

[[Page 34660]]

``24-3'' is not marked in the serial block of the identification 
plate, within 1,000 flight hours after the effective date of this AD 
or before the first scheduled ADG functional test after the 
effective date of this AD, whichever occurs first, inspect to 
determine the serial number of the strut and generator housing 
assembly. A review of the airplane maintenance records is acceptable 
in lieu of this inspection if the serial number can be conclusively 
determined from that review.
    (1) If the serial number of the strut and generator housing 
assembly is in the range 0001 through 2503, do a fluorescent 
penetrant inspection in accordance with paragraph (g)(2) of this AD 
at the times specified in paragraph (g)(2) of this AD.
    (2) If the serial number of the strut and generator housing 
assembly is 2504 or higher, the strut wall thickness is within 
specification and no further action is required by this AD.
    (3) If the serial number of the strut and generator housing 
assembly is not inspected or it is not possible to determine the 
serial number, do a fluorescent penetrant inspection in accordance 
with paragraph (g)(2) of this AD at the times specified in paragraph 
(g)(2) of this AD.
    (2) For ADGs having a strut and generator assembly identified in 
paragraph (g)(1)(ii)(C)(1) or (g)(1)(ii)(C)(3) of this AD: Within 
1,000 flight hours after the effective date of this AD or before the 
first scheduled ADG functional test after the effective date of this 
AD, whichever occurs first, do a fluorescent penetrant inspection 
for cracking of the ADG strut, and if any crack is found, before 
further flight, replace the ADG with a serviceable ADG, in 
accordance with the Accomplishment Instructions of Bombardier Alert 
Service Bulletin A601R-24-120, Revision C, dated April 20, 2009 (for 
Model CL-600-2B19 airplanes); or Bombardier Alert Service Bulletin 
A670BA-24-020, Revision C, dated April 20, 2009 (for Model CL-600-
2C10, CL-600-2D15, and CL-600-2D24 airplanes).
    (3) Fluorescent penetrant inspections accomplished before the 
effective date of this AD in accordance with any applicable service 
bulletin specified in Table 1 of this AD are considered acceptable 
for compliance with the corresponding fluorescent penetrant 
inspection specified in this AD.

                                        Table 1--Credit Service Bulletins
----------------------------------------------------------------------------------------------------------------
      Bombardier, Inc. Model--             Service Bulletin--            Revision--               Dated--
----------------------------------------------------------------------------------------------------------------
CL-600-2B19 airplanes...............  Bombardier Alert Service      Original............  April 20, 2005.
                                       Bulletin A601R-24-120.
CL-600-2B19 airplanes...............  Bombardier Alert Service      A...................  December 1, 2005.
                                       Bulletin A601R-24-120.
CL-600-2B19 airplanes...............  Bombardier Alert Service      B...................  December 7, 2006.
                                       Bulletin A601R-24-120.
CL-600-2C10 airplanes and CL-600-     Bombardier Alert Service      Original............  April 20, 2005.
 2D24 airplanes.                       Bulletin A670BA-24-020.
CL-600-2C10 airplanes; and CL-600-    Bombardier Alert Service      A...................  May 17, 2005.
 2D15 and CL-600-2D24 airplanes.       Bulletin A670BA-24-020.
CL-600-2C10 airplanes; and CL-600-    Bombardier Alert Service      B...................  December 7, 2006.
 2D15 and CL-600-2D24 airplanes.       Bulletin A670BA-24-020.
CL-600-2B19 airplanes; CL-600-2C10    Hamilton Sundstrand Service   Original............  April 14, 2005.
 airplanes; and CL-600-2D15 and CL-    Bulletin ERPS10AG-24-3.
 600-2D24 airplanes.
CL-600-2B19 airplanes; CL-600-2C10    Hamilton Sundstrand Service   1...................  April 19, 2005.
 airplanes; and CL-600-2D15 and CL-    Bulletin ERPS10AG-24-3.
 600-2D24 airplanes.
CL-600-2B19 airplanes; CL-600-2C10    Hamilton Sundstrand Service   2...................  November 14, 2006.
 airplanes; and CL-600-2D15 and CL-    Bulletin ERPS10AG-24-3.
 600-2D24 airplanes.
Bombardier, Inc. CL-600-2B19          Hamilton Sundstrand Service   3...................  March 12, 2009.
 airplanes; CL-600-2C10 airplanes;     Bulletin ERPS10AG-24-3.
 and CL-600-2D15 and CL-600-2D24
 airplanes.
----------------------------------------------------------------------------------------------------------------

    Note 1: For additional guidance on the ADGs specified in 
paragraphs (g)(1)(ii)(C)(1)and (g)(1)(ii)(C)(3) of this AD and the 
repetitive fluorescent penetrant inspections specified as part of 
the periodic ADG functional check procedure, refer to the applicable 
tasks identified in Table 2 of this AD. These tasks can be found in 
Part 2 -Airworthiness Requirements, Appendix A--Certification 
Maintenance Requirements (CMR) of the Bombardier (Canadair) Regional 
Jet Maintenance Requirements Manual, and the Bombardier CRJ Series 
Regional Jet Aircraft Maintenance Manual (AMM).

    Table 2--Guidance for the Periodic ADG Functional Check Procedure
------------------------------------------------------------------------
     Bombardier, Inc. Model--                Task Number (No.)--
------------------------------------------------------------------------
CL-600-2B19 airplanes.............  CMR Task No. C24-20-129-01 and AMM
                                     Task No: 24-23-01-720-803.
CL-600-2C10 airplanes.............  CMR Task No. 24-23-00-102 and AMM
                                     Task No. 24-23-01-720-802.
CL-600-2D15 and CL-600-2D24         CMR Task No. 24-23-00-102 and AMM
 airplanes.                          Task No. 24-23-01-720-802.
------------------------------------------------------------------------

    Note 2:  For additional guidance on the ADGs specified in 
paragraph (g)(1)(ii)(C)(1), and the fluorescent penetrant inspection 
necessary following each future unscheduled in-flight ADG 
deployment, refer to following task specified in Table 3 of this AD.

  Table 3--Guidance for Inspection Following Unscheduled In-Flight ADG
                               Deployment
------------------------------------------------------------------------
            Bombardier, Inc. Model--                  AMM Task No.--
------------------------------------------------------------------------
CL-600-2B19 airplanes, serial numbers 7305              05-51-19-210-801
 through 8051 inclusive........................
CL-600-2C10 airplanes, serial numbers 10003             05-51-19-210-801
 through 10260 inclusive.......................
CL-600-2D15 and CL-600-2D24 airplanes, serial           05-51-19-210-801
 numbers 15001 through 15106 inclusive.........
------------------------------------------------------------------------

[[Page 34661]]

    Note 3: In Hamilton Sundstrand Service Bulletin ERPS10AG-24-3, 
the fluorescent penetrant inspection is referred to as a ``Penetrant 
Check.''

FAA AD Differences

    Note 4:  This AD differs from the MCAI and/or service 
information as follows: No differences.

Other FAA AD Provisions

    (h) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office (ACO), ANE-170, 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, Continuing 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.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.
    (4) Special Flight Permits: Special flight permits, as described 
in section 21.197 and section 21.199 of the Federal Aviation 
Regulations (14 CFR 21.197 and 21.199), are not allowed.

Related Information

    (i) Refer to MCAI Canadian Airworthiness Directive CF-2009-27, 
dated June 8, 2009; Bombardier Alert Service Bulletin A601R-24-120, 
Revision C, dated April 20, 2009; and Bombardier Alert Service 
Bulletin A670BA-24-020, Revision C, dated April 20, 2009; for 
related information.

    Issued in Renton, Washington, on June 10, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-14769 Filed 6-17-10; 8:45 am]
BILLING CODE 4910-13-P