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

[Federal Register Volume 75, Number 190 (Friday, October 1, 2010)]
[Rules and Regulations]
[Pages 60604-60608]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-24482]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0550; Directorate Identifier 2009-NM-124-AD; 
Amendment 39-16454; AD 2010-20-19]
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), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This 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.
* * * * *

[[Page 60605]]

We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective November 5, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 5, 
2010.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on June 18, 2010 (75 FR 
34657). That NPRM proposed 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 [Transport Canada Civil Aviation (TCCA)] 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 [TCCA] directive 
but are specified in the approved maintenance program.

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

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. Air Line Pilots 
Association, International supports the NPRM.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD as proposed.

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 required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect 1,073 products of U.S. 
registry. We also estimate that it will take about 1 work-hour per 
product to comply with the basic requirements of this AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this AD to the 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 AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify this AD:
    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 AD and placed it in the AD docket.

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 the NPRM, 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


[[Page 60606]]




Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2010-20-19 Bombardier, Inc.: Amendment 39-16454. Docket No. FAA-
2010-0550; Directorate Identifier 2009-NM-124-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
5, 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 [Transport Canada Civil Aviation (TCCA)] 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 [TCCA] 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 ``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--                  Date--
----------------------------------------------------------------------------------------------------------------
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.

[[Page 60607]]

 
CL-600-2B19 airplanes; CL-600-     Hamilton Sundstrand       Original...........  April 14, 2005.
 2C10 airplanes; and CL-600-2D15    Service Bulletin
 and CL-600-2D24 airplanes.         ERPS10AG-24-3.
CL-600-2B19 airplanes; CL-600-     Hamilton Sundstrand       1..................  April 19, 2005.
 2C10 airplanes; and CL-600-2D15    Service Bulletin
 and CL-600-2D24 airplanes.         ERPS10AG-24-3.
CL-600-2B19 airplanes; CL-600-     Hamilton Sundstrand       2..................  November 14, 2006.
 2C10 airplanes; and CL-600-2D15    Service Bulletin
 and CL-600-2D24 airplanes.         ERPS10AG-24-3.
Bombardier, Inc. CL-600-2B19       Hamilton Sundstrand       3..................  March 12, 2009.
 airplanes; CL-600-2C10             Service Bulletin
 airplanes; and CL-600-2D15 and     ERPS10AG-24-3.
 CL-600-2D24 airplanes.
----------------------------------------------------------------------------------------------------------------


    Note 1: 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 may be found in the applicable tasks 
identified in Table 2 of this AD. These tasks can be found in Part 
2--Airworthiness Limitations, Appendix A--Certification Maintenance 
Requirements (CMR), of the Bombardier CL-600-2C10, CL-600-2D15, and 
CL-600-2D24 Maintenance Requirements Manual; and the Canadair CRJ 
Series Regional Jet Aircraft Maintenance Manual (AMM); as 
applicable.


    Table 2--Guidance for the Periodic ADG Functional Check Procedure
------------------------------------------------------------------------
        Bombardier, Inc. Model--                  Task number--
------------------------------------------------------------------------
CL-600-2B19 airplanes..................  CMR Task C24-20-129-01 and AMM
                                          Task 24-23-01-720-803
CL-600-2C10 airplanes..................  CMR Task 24-23-00-102 and AMM
                                          Task 24-23-01-720-802
CL-600-2D15 and CL-600-2D24 airplanes..  CMR Task 24-23-00-102 and AMM
                                          Task 24-23-01-720-802
------------------------------------------------------------------------


    Note 2:  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 can be 
found in the tasks specified in Table 3 of this AD.


  Table 3--Guidance for Inspection Following Unscheduled In-Flight ADG
                               Deployment
------------------------------------------------------------------------
          Bombardier, Inc. Model--                    AMM task--
------------------------------------------------------------------------
CL[dash]600-2B19 airplanes, serial numbers   05-51-19-210-801
 7305 through 8051 inclusive.
CL-600-2C10 airplanes, serial numbers 10003  05-51-19-210-801
 through 10260 inclusive.
CL[dash]600[dash]2D15 and CL-600-2D24        05-51-19-210-801
 airplanes, serial numbers 15001 through
 15106 inclusive.
------------------------------------------------------------------------


    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.

Material Incorporated by Reference

    (j) You must use Bombardier Alert Service Bulletin A601R-24-120, 
Revision C, dated April 20, 2009; or Bombardier Alert Service 
Bulletin A670BA-24-020, Revision C, dated April 20, 2009; as 
applicable; to do the actions required by this AD, unless the AD 
specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this 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 [email protected]; Internet http://www.bombardier.com.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the

[[Page 60608]]

availability of this material at the FAA, call 425-227-1221.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on September 21, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-24482 Filed 9-30-10; 8:45 am]
BILLING CODE 4910-13-P

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