[Federal Register Volume 80, Number 51 (Tuesday, March 17, 2015)]
[Rules and Regulations]
[Pages 13758-13760]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-05717]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0653; Directorate Identifier 2014-NM-057-AD; 
Amendment 39-18113; AD 2015-05-03]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. 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 certain 
Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) 
airplanes. This AD was prompted by reports of cracking on the skin 
panels and skin splice joints and angles at certain stringers at 
various locations between certain fuselage stations. This AD requires 
revising the maintenance or inspection program, as applicable, to 
incorporate new or revised maintenance requirements and airworthiness 
limitations, and incorporating structural repairs and modifications to 
preclude widespread fatigue damage (WFD). We are issuing this AD to 
detect and correct WFD, which could adversely affect the structural 
integrity of the airplane.

DATES: This AD becomes effective April 21, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 21, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0653 or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    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; email 
[email protected]; Internet http://www.bombardier.com. You 
may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2014-0653.

FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, 
NY 11590; telephone: 516-228-7329; fax: 516-794-5531; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Bombardier, Inc. 
Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. The NPRM 
published in the Federal Register on October 1, 2014 (79 FR 59157). The 
NPRM was prompted by reports of cracking on the skin panels and skin 
splice joints and angles at certain stringers at various locations 
between certain fuselage stations. The NPRM proposed to require 
revising the maintenance or inspection program, as applicable, to 
incorporate new or revised maintenance requirements and airworthiness 
limitations, and incorporating structural repairs and modifications to 
preclude WFD. We are issuing this AD to detect and correct WFD, which 
could adversely affect the structural integrity of the airplane.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2014-07, dated January 31, 2014 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Bombardier, Inc. Model CL-600-
2B19 (Regional Jet Series 100 & 440) airplanes. The MCAI states:

    Complete aeroplane fatigue testing on a CL-600-2B19 aeroplane by 
the aeroplane manufacturer revealed the onset of simultaneous 
cracking on the skin panels and skin splice joints and angles at 
stringers number 6 and 20 at various locations

[[Page 13759]]

between fuselage stations (FS) 409.00 to FS 589.00.
    Cracks at multiple locations may reduce the residual strength of 
the joint below the required levels if the cracks are not detectable 
under the existing maintenance program established at the time of 
certification. This multiple site damage (MSD) behavior, if not 
corrected, could lead to widespread fatigue damage (WFD) and 
adversely affect the structural integrity of the aeroplane and/or 
could result in rapid decompression of the aeroplane.
    A Temporary Revision (TR) has been made to the Maintenance 
Requirements Manual (MRM) to revise existing Airworthiness 
Limitations (AWL) tasks and introduce new inspection tasks for the 
detection of MSD. The aeroplane manufacturer is also developing a 
structural modification to preclude WFD from occurring in the fleet 
at these locations.
    This [Canadian] AD mandates the incorporation of the new and 
revised AWL tasks [into the maintenance program], and a structural 
modification to preclude WFD.

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0653-0003.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no valid comments on the NPRM (79 FR 59157, 
October 1, 2014) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 59157, October 1, 2014) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 59157, October 1, 2014).

Related Service Information Under 1 CFR Part 51

    We reviewed the following service information.
     Airworthiness Limitations (AWL) Task 53-41-109, 
Longitudinal Str. 6 splice at STR 6 and 20, of Appendix B, 
Airworthiness Limitations, of Part 2, Airworthiness Requirements, 
Revision 9, dated June 10, 2013, of the Bombardier CL-600-2B19 
Maintenance Requirements Manual, CSP A-053. This service information 
describes procedures for inspecting the longitudinal stringer 6 splice 
at stringers 6 and 20.
     AWL Task 53-41-110, Longitudinal Str. 6 splice butt strap 
at Str. 6, FS409.0 to FS617.0, of Appendix B, Airworthiness 
Limitations, of Part 2, Airworthiness Requirements, Revision 9, dated 
June 10, 2013, of the Bombardier CL-600-2B19 Maintenance Requirements 
Manual, CSP A-053. This service information describes procedures for 
inspecting the longitudinal stringer 6 splice butt at stringer 6 at 
fuselage station 409.0 to fuselage station 617.0.
     AWL Task 53-41-204, Frame splice angles at STR 6 and 20, 
of Appendix B, Airworthiness Limitations, of Part 2, Airworthiness 
Requirements, Revision 9, dated June 10, 2013, of the Bombardier CL-
600-2B19 Maintenance Requirements Manual, CSP A-053. This service 
information describes procedures for inspecting the frame splice angles 
at stringers 6 and 20.
     AWL Task 53-41-205, Longitudinal skin splice at STR 6 and 
20, of Appendix B, Airworthiness Limitations, of Part 2, Airworthiness 
Requirements, Revision 9, dated June 10, 2013, of the Bombardier CL-
600-2B19 Maintenance Requirements Manual, CSP A-053. This service 
information describes procedures for inspecting the longitudinal skin 
splice at stringers 6 and 20.
    This service information is reasonably available; see ADDRESSES for 
ways to access this service information.

Costs of Compliance

    We estimate that this AD affects 526 airplanes of U.S. registry.
    We also estimate that it would take about 1 work-hour per product 
to comply with the basic requirements of this AD. We have received no 
definitive data that would enable us to provide cost estimates for the 
repairs and modifications specified in this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD on U.S. operators to be $44,710, 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 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0653; or in person at the 
Docket Management Facility between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The AD docket contains this 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.

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.

[[Page 13760]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2015-05-03 Bombardier, Inc.: Amendment 39-18113. Docket No. FAA-
2014-0653; Directorate Identifier 2014-NM-057-AD.

(a) Effective Date

    This AD becomes effective April 21, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc. Model CL-600-2B19 (Regional 
Jet Series 100 & 440) airplanes, certificated in any category, 
serial numbers 7003 and subsequent.

(d) Subject

    Air Transport Association (ATA) of America Code 05, Periodic 
Inspections.

(e) Reason

    This AD was prompted by reports of cracking on the skin panels 
and skin splice joints and angles at certain stringers at various 
locations between certain fuselage stations. We are issuing this AD 
to detect and correct widespread fatigue damage, which could 
adversely affect the structural integrity of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Revision of Maintenance or Inspection Program

    Within 60 days after the effective date of this AD: Revise the 
maintenance or inspection program, as applicable, by incorporating 
the airworthiness limitations (AWL) tasks specified in paragraphs 
(g)(1) through (g)(4) of this AD. The initial compliance times for 
the tasks start from the applicable threshold times specified in 
Part 2 Airworthiness Requirements, Revision 9, dated June 10, 2013, 
of Appendix B, Airworthiness Limitations, of Bombardier CL-600-2B19, 
Maintenance Requirements Manual, CSP A-053; except that, for 
airplanes that have accumulated more than 38,000 total flight cycles 
as of the effective date of this AD, the initial compliance time for 
the AWL tasks is before the accumulation of 2,000 flight cycles 
after the effective date of this AD.
    (1) AWL Task 53-41-109, Longitudinal Str. 6 splice at STR 6 and 
20, of Appendix B, Airworthiness Limitations, of Part 2, 
Airworthiness Requirements, Revision 9, dated June 10, 2013, of the 
Bombardier CL-600-2B19, Maintenance Requirements Manual, CSP A-053.
    (2) AWL Task 53-41-110, Longitudinal Str. 6 splice butt strap at 
Str. 6, FS409.0 to FS617.0, of Appendix B, Airworthiness 
Limitations, of Part 2, Airworthiness Requirements, Revision 9, 
dated June 10, 2013, of the Bombardier CL-600-2B19, Maintenance 
Requirements Manual, CSP A-053.
    (3) AWL Task 53-41-204, Frame splice angles at STR 6 and 20, of 
Appendix B, Airworthiness Limitations, of Part 2, Airworthiness 
Requirements, Revision 9, dated June 10, 2013, of the Bombardier CL-
600-2B19, Maintenance Requirements Manual, CSP A-053.
    (4) AWL Task 53-41-205, Longitudinal skin splice at STR 6 and 
20., of Appendix B, Airworthiness Limitations, of Part 2, 
Airworthiness Requirements, Revision 9, dated June 10, 2013, of the 
Bombardier CL-600-2B19, Maintenance Requirements Manual, CSP A-053.

(h) No Alternative Actions or Intervals

    After the maintenance or inspection program has been revised as 
required by paragraph (g) of this AD, no alternative actions (e.g., 
inspections) or intervals may be used unless the actions or 
intervals are approved as an alternative method of compliance (AMOC) 
in accordance with the procedures specified in paragraph (j)(1) of 
this AD.

(i) Repairs and Modifications

    Before the accumulation of 60,000 total flight cycles: Install 
repairs and modifications to preclude widespread fatigue damage at 
locations specified in the tasks identified in paragraphs (g)(1) 
through (g)(4) of this AD, using a method approved by the Manager, 
New York ACO, ANE-170, FAA; or Transport Canada Civil Aviation 
(TCCA); or Bombardier, Inc.'s TCCA Design Approval Organization 
(DAO). If approved by the DAO, the approval must include the DAO-
authorized signature.

(j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York 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, NY 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) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, New York ACO, 
ANE-170, FAA; or Transport Canada Civil Aviation (TCCA); or 
Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If 
approved by the DAO, the approval must include the DAO-authorized 
signature.

(k) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
Canadian Airworthiness Directive CF-2014-07, dated January 31, 2014, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-
2014-0653-0003.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Appendix B, Airworthiness Limitations, of Part 2, 
Airworthiness Requirements, Revision 9, dated June 10, 2013, of the 
Bombardier CL-600-2B19 Maintenance Requirements Manual, CSP A-053:
    (A) Airworthiness Limitations (AWL) Task 53-41-109, Longitudinal 
Str. 6 splice at STR 6 and 20;
    (B) AWL Task 53-41-110, Longitudinal Str. 6 splice butt strap at 
Str. 6, FS409.0 to FS617.0;
    (C) AWL Task 53-41-204, Frame splice angles at STR 6 and 20; and
    (D) AWL Task 53-41-205, Longitudinal skin splice at STR 6 and 
20.
    (ii) Reserved.
    (3) 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; email [email protected]; Internet http://www.bombardier.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this 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/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 2, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-05717 Filed 3-16-15; 8:45 am]
 BILLING CODE 4910-13-P