Airworthiness Directives; Bombardier, Inc. Airplanes, 30185-30187 [2012-12336]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 77, Number 99 (Tuesday, May 22, 2012)]
[Rules and Regulations]
[Pages 30185-30187]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-12336]



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Federal Register / Vol. 77, No. 99 / Tuesday, May 22, 2012 / Rules 
and Regulations

[[Page 30185]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0042; Directorate Identifier 2011-NM-154-AD; 
Amendment 39-17057; AD 2012-10-08]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for 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. That 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. This new AD continues to require 
the actions in the existing AD, and adds the previously omitted part 
and serial numbers. 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.

DATES: This AD becomes effective June 26, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 18, 2011 
(76 FR 20498, April 13, 2011).

ADDRESSES: You may examine the AD docket on the Internet at https://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: 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: 
Stephen.Kowalski@faa.gov.

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 February 6, 2012 (77 
FR 5730), and proposed to supersede AD 2011-08-04, Amendment 39-16654 
(76 FR 20498, April 13, 2011). That 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 
[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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (77 FR 5730, February 6, 
2012) or on the determination of the cost to the public.

Explanation of Changes Made to This AD

    We have revised certain headers throughout this AD. We have also 
revised the heading for and the wording in paragraph (n) of this AD; 
this change has not affected the intent of that paragraph.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously--except for minor editorial changes. We have determined that 
these changes:
     Are consistent with the intent that was proposed in the 
NPRM (77 FR 5730, February 6, 2012) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 5730, February 6, 2012).

Difference 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 AD continues to require that the inspection be done 
on all airplanes. We have coordinated this difference with the TCCA.

Costs of Compliance

    We estimate that this AD will affect about 361 products of U.S. 
registry.
    The actions that are required by AD 2011-08-04, Amendment 39-16654 
(76 FR 20498, April 13, 2011), and retained in this AD take 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 will take about 5 work-hours per product to 
comply with the new 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.

[[Page 30186]]

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 that 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);
    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 AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://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 (77 FR 5730, February 6, 
2012), 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 removing airworthiness directive (AD) 
2011-08-04, Amendment 39-16654 (76 FR 20498, April 13, 2011), and 
adding the following new AD:

2012-10-08 Bombardier, Inc.: Amendment 39-17057. Docket No. FAA-
2012-0042; Directorate Identifier 2011-NM-154-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective June 26, 
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.

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

    This paragraph restates the requirements of paragraph (g) of AD 
2011-08-04, Amendment 39-16654 (76 FR 20498, April 13, 2011). 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), inspect the MLG shock strut assemblies to determine whether an 
MLG shock strut assembly having a P/N 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) Retained Inspection of the Torque Link Apex Joint for Model CL-600-
2C10 Airplanes

    This paragraph restates the requirements of paragraph (h) of AD 
2011-08-04, Amendment 39-16654 (76 FR 20498, April 13, 2011). For 
any MLG shock strut assembly having a P/N 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 (the effective 
date of AD 2011-08-04), 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) Retained Replacement or Rework of the Apex Nut for Model CL-600-
2C10 Airplanes

    This paragraph restates the requirements of paragraph (i) of AD 
2011-08-04, Amendment 39-16654 (76 FR 20498, April 13, 2011). 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 (the effective date of AD 2011-08-
04), 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) Retained Parts Installation

    For all airplanes: As of May 18, 2011 (the effective date of AD 
2011-08-04, Amendment 39-16654 (76 FR 20498, April 13, 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-'').

[[Page 30187]]

    (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-'').

(k) New 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 Previous Actions

    (1) This paragraph provides credit for inspections, corrective 
actions, replacements, and rework required by paragraphs (g), (h), 
and (i) of this AD, if those actions were performed before May 18, 
2011 (the effective date of AD 2011-08-04, Amendment 39-16654 (76 FR 
20498, April 13, 2011)), using Bombardier Service Bulletin 670BA-32-
019, dated March 16, 2006.
    (2) This paragraph provides credit for inspections, corrective 
actions, replacements, and rework required by paragraphs (k), (l), 
and (m) of this AD, if those actions were performed before the 
effective date of this AD using Bombardier Service Bulletin 670BA-
32-019, dated March 16, 2006.

(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.

(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.

 (s) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the following service 
information under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
May 18, 2011 (76 FR 20498, April 13, 2011).
    (i) Bombardier Service Bulletin 670BA-32-019, Revision A, dated 
September 18, 2008.
    (4) 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; email: 
thd.crj@aero.bombardier.com; Internet: https://www.bombardier.com.
    (5) 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.
    (6) 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 an NARA facility, call 202-741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on May 10, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-12336 Filed 5-21-12; 8:45 am]
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