
[Federal Register: May 18, 2010 (Volume 75, Number 95)]
[Proposed Rules]               
[Page 27665-27667]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18my10-13]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0515; Directorate Identifier 2009-NM-196-AD]
RIN 2120-AA64

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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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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:

    Several cases have been reported of cracks in the joint 
extrusions securing the outer bondment to the acoustic panel of the 
nacelle transcowl assemblies. Although there is no effect on flight 
safety (thrust reverser stowed), thrust reverser deployment under 
rejected take-off or emergency landing load conditions could 
potentially result in acoustic panel failure and possible runway 
debris.
* * * * *

The loss of an acoustic panel during rejected take-off or emergency 
landing load conditions could leave debris on the runway. This debris, 
if not removed, creates an unsafe condition for other airplanes during 
take-off or landing, as those airplanes could impact debris on the 
runway and sustain damage. 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 July 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-2010-0515; 
Directorate Identifier 2009-NM-196-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory,

[[Page 27666]]

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 aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2009-33, dated July 28, 2009 (referred to after this as ``the MCAI''), 
to correct an unsafe condition for the specified products. The MCAI 
states:

    Several cases have been reported of cracks in the joint 
extrusions securing the outer bondment to the acoustic panel of the 
nacelle transcowl assemblies. Although there is no effect on flight 
safety (thrust reverser stowed), thrust reverser deployment under 
rejected take-off or emergency landing load conditions could 
potentially result in acoustic panel failure and possible runway 
debris.
    This directive mandates inspection, repair (if necessary) and 
reinforcement of the transcowl assemblies.

The loss of an acoustic panel during rejected take-off or emergency 
landing load conditions could leave debris on the runway. This debris, 
if not removed, creates an unsafe condition for other airplanes during 
take-off or landing, as those airplanes could impact debris on the 
runway and sustain damage. The inspection is a detailed visual 
inspection of the outboard edge of the transcowl joint extrusion for 
evidence of cracking. The repair consists of doing an eddy current or 
liquid penetrant inspection for cracking, and depending on the results, 
either removing the affected joint extrusion area and replacing with 
packers, or contacting Bombardier for repair instructions and doing the 
repair. The reinforcement of the transcowl assemblies includes 
installing new support channels. You may obtain further information by 
examining the MCAI in the AD docket.

Relevant Service Information

    Bombardier has issued Service Bulletin 670BA-78-008, Revision A, 
dated July 10, 2009; and Task 05-51-27-210-801 of Part 2, Volume 1, of 
the Bombardier CRJ Series Regional Jet Aircraft Maintenance Manual 
(AMM), CSP B-001, Revision 28, dated January 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 
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 361 products of U.S. registry. We also estimate that 
it would take about 8 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 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 $245,480, or $680 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:

[[Page 27667]]

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-2010-0515; Directorate Identifier 
2009-NM-196-AD.

Comments Due Date

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

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD, certificated in any category.
    (1) Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 
701, & 702) airplanes, serial numbers 10003 through 10265 inclusive.
    (2) Bombardier, Inc. Model CL-600-2D15 (Regional Jet Series 705) 
and Model CL-600-2D24 (Regional Jet Series 900) airplanes, serial 
numbers 15001 through 15192 inclusive.

Subject

    (d) Air Transport Association (ATA) of America Code 78: Engine 
exhaust.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Several cases have been reported of cracks in the joint 
extrusions securing the outer bondment to the acoustic panel of the 
nacelle transcowl assemblies. Although there is no effect on flight 
safety (thrust reverser stowed), thrust reverser deployment under 
rejected take-off or emergency landing load conditions could 
potentially result in acoustic panel failure and possible runway 
debris.
* * * * *
The loss of an acoustic panel during rejected take-off or emergency 
landing load conditions could leave debris on the runway. This 
debris, if not removed, creates an unsafe condition for other 
airplanes during take-off or landing, as those airplanes could 
impact debris on the runway and sustain damage.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Within 5,000 flight hours or 24 months after the effective 
date of this AD, whichever occurs first, inspect for the part number 
and serial number of each transcowl assembly, and, as applicable, 
the repair status of each transcowl assembly.
    (i) If all transcowl assemblies installed on any airplane 
applicable to this AD meet one of the conditions as listed in 
paragraph (f)(1)(i)(A), (f)(1)(i)(B), or (f)(1)(i)(C) of this AD, no 
further action is required by this AD.
    (A) Part number (P/N) KCN624-2003-3, -5, or -7.
    (B) P/Ns CN624-2001-XXX or KCN624-2001-X (XXX and X mean various 
dash numbers), with serial number (S/N) SB0965 or higher.
    (C) P/Ns CN624-2001-XXX or KCN624-2001-X (XXX and X mean various 
dash numbers), and repaired in accordance with one of the Bombardier 
repair engineering orders (REOs) listed in paragraph 1.D of 
Bombardier Service Bulletin 670BA-78-008, Revision A, dated July 10, 
2009.
    (ii) If one or more of the transcowl assemblies have P/N CN624-
2001-XXX or KCN624-2001-X (XXX and X mean various dash numbers), 
with S/N SB0964 or lower, and have not been repaired in accordance 
with one of the Bombardier REOs listed in paragraph 1.D of 
Bombardier Service Bulletin 670BA-78-008, Revision A, dated July 10, 
2009, do the actions specified in paragraph (f)(3) of this AD.
    (2) As of the effective date of this AD, following any high-
energy stop or rejected take-off (RTO), perform a detailed visual 
inspection of each transcowl assembly (left, right, upper, and 
lower) before further flight, in accordance with Task 05-51-27-210-
801 of Part 2, Volume 1, of the Bombardier CRJ Series Regional Jet 
Aircraft Maintenance Manual (AMM), CSP B-001, Revision 28, dated 
January 20, 2009. If any crack is found on one or more transcowl 
assemblies, before further flight, repair and reinforce the cracked 
part(s) in accordance with paragraph (f)(3) of this AD. Doing the 
requirements of paragraph (f)(3) of this AD terminates the 
requirements of paragraph (f)(2) of this AD.
    (3) Except as required by paragraph (f)(2) of this AD, within 
5,000 flight hours or 24 months after the effective date of this AD, 
whichever comes first, do a detailed visual inspection for cracking 
on each transcowl, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 670BA-78-008, Revision 
A, dated July 10, 2009. If any cracking of the joint extrusion is 
found, before further flight, repair and reinforce the joint 
extrusion on each transcowl, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 670BA-78-008, Revision 
A, dated July 10, 2009. If no cracking is found, before further 
flight, reinforce the joint extrusion on each transcowl, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 670BA-78-008, Revision A, dated July 10, 2009. 
Accomplishment of the actions specified in this paragraph terminate 
the requirements of paragraphs (f)(1)(ii) and (f)(2) of this AD.
    (4) Inspections, repairs, and reinforcement of the joint 
extrusion on each transcowl is also acceptable for compliance with 
the requirements of paragraph (f) of this AD if done before the 
effective date of this AD in accordance with Bombardier Service 
Bulletin 670BA-78-008, dated September 19, 2008.
    (5) After accomplishing the inspection required by paragraph 
(f)(1) of this AD, no replacement or spare transcowl assembly having 
P/N CN624-2001-XXX or KCN624-2001-X (XXX and X mean various dash 
numbers), with S/N SB0964 or lower, may be installed on any airplane 
unless the transcowl assembly has been repaired in accordance with 
one of the Bombardier REOs listed in paragraph 1.D of Bombardier 
Service Bulletin 670BA-78-008, Revision A, dated July 10, 2009.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: No differences.

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, 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, 1600 Stewart Avenue, Suite 40, 
Westbury, NY 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.

Related Information

    (h) Refer to MCAI Canadian Airworthiness Directive CF-2009-33, 
dated July 28, 2009; Bombardier Service Bulletin 670BA-78-008, 
Revision A, dated July 10, 2009; and Task 05-51-27-210-801 of Part 
2, Volume 1, of the Bombardier CRJ Series Regional Jet Aircraft 
Maintenance Manual, CSP B-001, Revision 28, dated January 20, 2009; 
for related information.

    Issued in Renton, Washington, on May 7, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-11889 Filed 5-17-10; 8:45 am]
BILLING CODE 4910-13-P

