[Federal Register Volume 76, Number 71 (Wednesday, April 13, 2011)]
[Rules and Regulations]
[Pages 20498-20500]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-8196]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0703; Directorate Identifier 2009-NM-093-AD; 
Amendment 39-16654; AD 2011-08-04]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. 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.

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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:

    There have been four reports of loose or detached main landing 
gear torque link apex pin locking plate and the locking plate 
retainer bolt. This condition could result in torque link apex pin 
disengagement, heavy vibration during landing, damage to main 
landing gear components and subsequent main landing gear collapse.
* * * * *
We are issuing this AD to require actions to correct the unsafe 
condition on these products.

[[Page 20499]]


DATES: This AD becomes effective May 18, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 18, 
2011.

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; phone: 516-228-7355; fax: 516-794-5531; e-mail: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a supplemental notice of proposed rulemaking (NPRM) to 
amend 14 CFR part 39 to include an AD that would apply to the specified 
products. That supplemental NPRM was published in the Federal Register 
on January 11, 2011 (76 FR 1556). That supplemental NPRM proposed to 
correct an unsafe condition for the specified products. The MCAI 
states:

    There have been four reports of loose or detached main landing 
gear torque link apex pin locking plate and the locking plate 
retainer bolt. This condition could result in torque link apex pin 
disengagement, heavy vibration during landing, damage to main 
landing gear components and subsequent main landing gear collapse.
    Investigation has determined that incorrect stack-up tolerances 
of the apex joint or improper installation of the locking plate and 
apex nut could result in torque link apex pin disengagement. This 
directive mandates [a one-time detailed] inspection of the torque 
link apex joint [for correct installation and damage, and corrective 
actions if necessary] and replacement of the torque link apex nut.

The corrective actions include re-installing parts that are not 
correctly installed and replacing damaged parts. 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 received no comments on the supplemental NPRM or on the 
determination of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed in the 
supplemental NPRM.

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

    Based on the service information, we estimate that this AD will 
affect about 361 products of U.S. registry. We also estimate that it 
will take about 5 work-hours 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 the AD on U.S. 
operators to be $153,425, or $425 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

    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.

Sec.  39.13  [Amended]

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

2011-08-04 Bombardier, Inc.: Amendment 39-16654. Docket No. FAA-
2009-0703; Directorate Identifier 2009-NM-093-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective May 18, 
2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the Bombardier airplanes identified in 
paragraphs (c)(1) and (c)(2) of this AD, certificated in any 
category.
    (1) Model CL-600-2C10 (Regional Jet Series 700, 701 & 702) 
airplanes, serial numbers (S/Ns) 10003 and subsequent.

[[Page 20500]]

    (2) Model CL-600-2D15 (Regional Jet Series 705) airplanes and 
Model CL-600-2D24 (Regional Jet Series 900) airplanes, S/Ns 15001 
and subsequent.

Subject

    (d) Air Transport Association (ATA) of America Code 32: Landing 
gear.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    There have been four reports of loose or detached main landing 
gear torque link apex pin locking plate and the locking plate 
retainer bolt. This condition could result in torque link apex pin 
disengagement, heavy vibration during landing, damage to main 
landing gear components and subsequent main landing gear collapse.
    Investigation has determined that incorrect stack-up tolerances 
of the apex joint or improper installation of the locking plate and 
apex nut could result in torque link apex pin disengagement. This 
directive mandates [a one-time detailed] inspection of the torque 
link apex joint [for correct installation and damage, and corrective 
actions if necessary] and replacement of the torque link apex nut.

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.

Inspection for Part Number (P/N) and Serial Number (S/N)

    (g) For all airplanes identified in paragraphs (c)(1) and (c)(2) 
of this AD: Within 900 flight hours after the effective date of this 
AD, inspect the main landing gear (MLG) shock strut assemblies to 
determine whether an MLG shock strut assembly having P/Ns 49000-11 
through 49000-22 inclusive and a S/N 0001 through 0284 inclusive is 
installed. A review of airplane maintenance records is acceptable in 
lieu of this inspection if the part and serial numbers of the MLG 
shock strut assembly can be conclusively determined from that 
review.

Inspection of the Torque Link Apex Joint

    (h) For any MLG shock strut assembly having P/Ns 49000-11 
through 49000-22 inclusive and a S/N 0001 through 0284 inclusive 
found installed during the inspection or records check required by 
paragraph (g) of this AD: Within 900 flight hours after the 
effective date of this AD, perform a one-time detailed inspection 
and all applicable corrective actions on the torque link apex joint, 
in accordance with Part A of the Accomplishment Instructions of 
Bombardier Service Bulletin 670BA-32-019, Revision A, dated 
September 18, 2008, except as provided by paragraph (l) of this AD. 
Do all applicable corrective actions before further flight.

Replacement or Rework of the Apex Nut

    (i) For any MLG shock strut assembly identified during the 
inspection or records check required by paragraph (g) of this AD: 
Within 4,500 flight hours after the effective date of this AD, 
replace or rework the apex nut, in accordance with Part B of the 
Accomplishment Instructions of Bombardier Service Bulletin 670BA-32-
019, Revision A, dated September 18, 2008.

Parts Installation

    (j) As of the effective date of this AD, no person may install, 
on any airplane, a replacement MLG shock strut assembly identified 
in paragraph (j)(1) or (j)(2) of this AD, unless it has been 
reworked in accordance with paragraph B. of Part B of the 
Accomplishment Instructions of Bombardier Service Bulletin 670BA-32-
019, Revision A, dated September 18, 2008.
    (1) Part numbers 49000-11 through 49000-22 inclusive, and with a 
serial number in the range of S/Ns 0001 through 0284 inclusive (the 
serial number can start with ``MA,'' ``MAL,'' or ``MA-'').
    (2) Part numbers 49050-5 through 49050-10 inclusive, and with a 
serial number in the range of S/Ns 1001 through 1114 inclusive (the 
serial number can start with ``MA,'' ``MAL,'' or ``MA-'').

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (k) Inspections, corrective actions, replacements, and rework 
accomplished before the effective date of this AD in accordance with 
Bombardier Service Bulletin 670BA-32-019, dated March 16, 2006, are 
considered acceptable for compliance with the corresponding actions 
specified in this AD.
    (l) The inspections specified in paragraph (h) of this AD are 
not required if the actions specified in paragraph (i) of this AD 
have already been accomplished; or if Bombardier Repair Engineering 
Order 670-32-11-0022, dated October 22, 2005, or Goodrich Service 
Concession Request SCR 0056-05, dated October 22, 2005; has been 
incorporated.

FAA AD Differences

    Note 1: The MCAI specifies to inspect only airplanes having 
certain serial numbers that are part of the MCAI applicability. 
Because the affected part could be rotated onto any of the airplanes 
listed in the applicability, this AD requires that the inspection be 
done on all airplanes. We have coordinated this with the Transport 
Canada Civil Aviation (TCCA).

Other FAA AD Provisions

    (m) 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, notify 
your appropriate principal inspector, or lacking a principal 
inspector, the manager of the local flight standards district 
office/certificate holding 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.

Special Flight Permits

    (n) 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

    (o) Refer to MCAI Canadian Airworthiness Directive CF-2009-20, 
dated May 1, 2009; and Bombardier Service Bulletin 670BA-32-019, 
Revision A, dated September 18, 2008; for related information.

Material Incorporated by Reference

    (p) You must use Bombardier Service Bulletin 670BA-32-019, 
Revision A, dated September 18, 2008, 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 Cote-Vertu Road West, Dorval, Quebec H4S 1Y9, 
Canada; phone: 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 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 March 23, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-8196 Filed 4-12-11; 8:45 am]
BILLING CODE 4910-13-P