[Federal Register Volume 77, Number 24 (Monday, February 6, 2012)]
[Proposed Rules]
[Pages 5730-5733]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-2619]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0042; Directorate Identifier 2011-NM-154-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to certain Bombardier, Inc. Model CL-600-2C10 
(Regional Jet Series 700, 701 & 702), CL-600-2D15 (Regional Jet Series 
705), and CL-600-2D24 (Regional Jet Series 900) airplanes. The existing 
AD currently requires a one-time inspection of the main landing gear 
(MLG) shock strut assemblies for part and serial numbers; for certain 
MLG shock strut assemblies, a one-time inspection of the torque link 
apex joint, and corrective actions if necessary; and, for certain MLG 
shock strut assemblies, replacement or rework of the apex nut. Since we 
issued that AD, we have determined that part and serial numbers for MLG 
shock strut assemblies for Model CL-600-2D15 and CL-600-2D24 airplanes 
were inadvertently omitted from certain requirements of the existing 
AD. This proposed AD would continue to require the actions in the 
existing AD, and would add the previously omitted part and serial 
numbers. We are proposing this AD to detect and correct improper 
assembly and damage of the MLG torque link apex joint, which could 
cause heavy vibration during landing, consequent damage to MLG 
components, and subsequent collapse of the MLG.

DATES: We must receive comments on this proposed AD by March 22, 2012.

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 W12-140, 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 Cote-Vertu Road West, Dorval, Quebec H4S 1Y9, 
Canada; phone: 514-855-5000; fax: 514-855-7401; email: 
[email protected]; 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.

[[Page 5731]]


FOR FURTHER INFORMATION CONTACT: Stephen Kowalski, 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) 228-7327; fax: (516) 794-5531; email: 
[email protected].

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-2012-0042; 
Directorate Identifier 2011-NM-154-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 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

    On March 23, 2011, we issued AD 2011-08-04, Amendment 39-16654 (76 
FR 20498, April 13, 2011). That AD required actions intended to address 
an unsafe condition on Bombardier, Inc. Model CL-600-2C10 (Regional Jet 
Series 700, 701 & 702), CL-600-2D15 (Regional Jet Series 705), and CL-
600-2D24 (Regional Jet Series 900) airplanes.
    Since we issued AD 2011-08-04, Amendment 39-16654 (76 FR 20498, 
April 13, 2011), we have determined that part and serial numbers for 
main landing gear (MLG) shock strut assemblies for Model CL-600-2D15 
(Regional Jet Series 705) airplanes and Model CL-600-2D24 (Regional Jet 
Series 900) airplanes were inadvertently omitted from paragraphs (g) 
and (h) of that AD. As a result, operators could be inspecting for part 
and serial numbers which they do not have, and would, therefore, not be 
required to accomplish the actions intended to correct the identified 
unsafe condition on those airplanes. Therefore, we have removed 
airplanes identified in paragraph (c)(2) of this AD from the 
requirements of paragraphs (g), (h), and (i) of this AD. We have added 
new requirements for those airplanes to inspect for the appropriate 
part numbers and serial numbers, and to do all applicable inspections 
and corrective actions.
    AD 2011-08-04, Amendment 39-16654 (76 FR 20498, April 13, 2011), 
referred to Transport Canada Civil Aviation (TCCA) (the aviation 
authority for Canada) Airworthiness Directive CF-2009-20, dated May 1, 
2009 (referred to after this as ``the MCAI''), 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 
[TCCA] 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.

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

    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 proposed AD would continue to require that the 
inspection be done on all airplanes. We have coordinated this with the 
TCCA.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 361 products of U.S. registry.
    The actions required by AD 2011-08-04, Amendment 39-16654 (76 FR 
20498, April 13, 2011), and retained in this proposed AD that about 5 
work-hours per product, at an average labor rate of $85 per work hour. 
Based on these figures, the estimated cost of the currently required 
actions is $153,425, or $425 per product.
    We estimate that it would take about 5 work-hours per product to 
comply with the new 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 $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 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 affect intrastate aviation in Alaska; and
    4. 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.

[[Page 5732]]

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 removing Amendment 39-16654 (76 FR 
20498, April 13, 2011) and adding the following new AD:

Bombardier, Inc.: Docket No. FAA-2012-0042; Directorate Identifier 
2011-NM-154-AD.

(a) Comments Due Date

    We must receive comments by March 22, 2012.

(b) Affected ADs

    This AD supersedes AD 2011-08-04, Amendment 39-16654 (76 FR 
20498, April 13, 2011).

(c) Applicability

    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.
    (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.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of loose or detached main 
landing gear (MLG) torque link apex pin locking plate and the 
locking plate retainer bolt in the torque link apex joint. We are 
issuing this AD to detect and correct improper assembly and damage 
of the MLG torque link apex joint, which could cause heavy vibration 
during landing, consequent damage to MLG components, and subsequent 
collapse of the MLG.

(f) Compliance

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

Restatement of Requirements of AD 2011-08-04, Amendment 39-16654 (76 FR 
20498, April 13, 2011)

(g) Inspection for Part Number (P/N) and Serial Number (S/N) for Model 
CL-600-2C10 Airplanes

    For airplanes identified in paragraph (c)(1) of this AD: Within 
900 flight hours after May 18, 2011 (the effective date of AD 2011-
08-04, Amendment 39-16654 (76 FR 20498, April 13, 2011)), 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.

(h) Inspection of the Torque Link Apex Joint for Model CL-600-2C10 
Airplanes

    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 May 18, 
2011, 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 (o) of this AD. Do all applicable 
corrective actions before further flight.

(i) Replacement or Rework of the Apex Nut for Model CL-600-2C10 
Airplanes

    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 May 18, 2011, 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.

(j) Parts Installation

    For all airplanes: As of May 18, 2011, 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-'').

New Requirements of This AD

(k) Inspection for Part Number and Serial Number for Model CL-600-2D15 
and CL-600-2D24 Airplanes

    For airplanes identified in paragraph (c)(2) of this AD: Within 
900 flight hours after the effective date of this AD, inspect the 
MLG shock strut assemblies to determine whether an MLG shock strut 
assembly having P/Ns 49050-5 through 49050-10 inclusive and a S/N 
0001 through 1114 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.

(l) Inspection of the Torque Link Apex Joint for Model CL-600-2D15 and 
CL-600-2D24 Airplanes

    For any MLG shock strut assembly having P/Ns 49050-5 through 
49050-10 inclusive and a S/N 0001 through 1114 inclusive found 
installed during the inspection or records check required by 
paragraph (k) 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 (o) of this AD. 
Do all applicable corrective actions before further flight.

(m) Replacement or Rework of the Apex Nut for Model CL-600-2D15 and CL-
600-2D24 Airplanes

    For any MLG shock strut assembly identified during the 
inspection or records check required by paragraph (k) of this AD: 
Within 900 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.

 (n) Credit for Actions Accomplished in Accordance With Previous 
Service Information

    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.

(o) Inspections Not Required Under Certain Conditions

    The inspections specified in paragraph (h) or (l) of this AD are 
not required if the actions specified in paragraph (i) or (m) of 
this AD, as applicable, 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.

[[Page 5733]]

(p) Other FAA AD Provisions

    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. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the ACO, send it 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.

(q) 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.

(r) Related Information

    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.


    Issued in Renton, Washington, on January 24, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-2619 Filed 2-3-12; 8:45 am]
BILLING CODE 4910-13-P