Airworthiness Directives; Bombardier, Inc. Airplanes, 13528-13530 [2014-04822]

Download as PDF 13528 Federal Register / Vol. 79, No. 47 / Tuesday, March 11, 2014 / Rules and Regulations Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2010–11–51, Amendment 39–16396 (75 FR 50874, August 18, 2010), and adding the following new AD: ■ 2014–05–07 Airbus Helicopters (Type Certificate Previously Held by Eurocopter France): Amendment 39– 17780; FAA–2013–0477; Directorate Identifier 2011–SW–015–AD. (a) Applicability This AD applies to Model AS350B, BA, B1, B2, C, D, and D1 helicopters and Model AS355E, F, F1, F2, and N helicopters, with a tail gearbox (TGB) control lever, part number (P/N) 350A33–1058–00, P/N 350A33–1058–01, P/N 350A33–1058–02, or P/N 350A33–1058–03, both with and without an ‘‘X’’ marked near the P/N, installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a crack in the TGB control lever. This condition could result in failure of the TGB control lever, loss of tail rotor control, and subsequent loss of control of the helicopter. (c) Affected ADs This AD supersedes AD 2010–11–51, Amendment 39–16396 (75 FR 50874, August 18, 2010). (d) Effective Date This AD becomes effective April 15, 2014. mstockstill on DSK4VPTVN1PROD with RULES (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (f) Required Actions (1) For helicopters with a lever not marked with an ‘‘X’’ near the P/N, within 10 hours time-in-service (TIS), and thereafter at intervals not to exceed 10 hours TIS, using a mirror and appropriate light source, visually inspect the TGB control lever for a crack as shown in area ‘‘A’’ of Figure 2 of Eurocopter Emergency Alert Service Bulletin No. 05.00.62, Revision 2, dated March 1, 2011 (EASB No. 05.00.62), for Model AS350 helicopters, and Eurocopter Emergency Alert Service Bulletin No. 05.00.57, Revision 2, dated March 1, 2011 (EASB No. 05.00.57), for Model AS355 helicopters. If there is a crack, before further flight, replace each cracked TGB control lever with a TGB control lever with a P/N not listed in paragraph (a) of this AD. (2) For Model AS355N helicopters, within 110 hours TIS, or if the helicopter has reached 100 or more hours TIS, within the next 10 hours TIS, and thereafter at intervals not to exceed 110 hours TIS, using a mirror and appropriate light source, inspect each TGB control lever for a crack as shown in area ‘‘C’’ of Figure 8 of EASB No. 05.00.62 or EASB No. 05.00.57, as applicable to your model helicopter. VerDate Mar<15>2010 16:00 Mar 10, 2014 Jkt 232001 (3) Within 660 hours TIS, replace each TGB control lever with a reworked TGB control lever marked with an ‘‘X’’ near the P/ N or with a TGB control lever with a P/N not listed in paragraph (a) of this AD. (4) For all model helicopters except Model AS355N, within 660 hours TIS, or if the helicopter has reached 605 or more hours TIS within the next 55 hours TIS, and thereafter at intervals not to exceed 660 hours TIS, using a mirror and appropriate light source, inspect each TGB control lever for a crack as shown in area ‘‘C’’ of Figure 8 of EASB No. 05.00.62 or EASB No. 05.00.57, as applicable to your model helicopter. (5) If there is a crack, before further flight, replace each cracked TGB control lever with a TGB control lever with a P/N not listed in paragraph (a) of this AD. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety Management Group, 2601 Meacham Blvd., Fort Worth, TX 76137, telephone (817) 222–5110, email robert.grant@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (h) Related Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) Emergency AD No. 2011–0038–E, dated March 4, 2011, and superseded EASA Emergency AD No. 2010–0082–E, dated April 27, 2010. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA–2013–0477. (i) Subject Joint Aircraft Service Component (JASC) Code: 6720 Tail Rotor Control System. (j) 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 the AD specifies otherwise. (i) Eurocopter Emergency Alert Service Bulletin (EASB), No. 05.00.62, Revision 2, dated March 1, 2011. (ii) Eurocopter EASB No. 05.00.57, Revision 2, dated March 1, 2011. Note 1 to paragraph (j)(2): Eurocopter EASB No. 05.00.62, Revision 2, dated March 1, 2011, and Eurocopter EASB No. 05.00.57, Revision 2, dated March 1, 2011, are copublished as one document along with Eurocopter EASB No. 05.00.38, Revision 2, dated March 1, 2011, and Eurocopter EASB No. 05.00.35, Revision 2, dated March 1, PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 2011, which are not incorporated by reference in this AD. (3) For Eurocopter service information identified in this AD, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641– 3775; or at http:// www.airbushelicopters.com/techpub. (4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222–5110. (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/ibrlocations.html. Issued in Fort Worth, Texas, on February 26, 2014. Bruce E. Cain, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2014–04729 Filed 3–10–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0798; Directorate Identifier 2013–NM–087–AD; Amendment 39–17796; AD 2014–05–23] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD–100–1A10 (Challenger 300) airplanes. This AD was prompted by multiple reports of erratic electrical status indications on the push button annunciators and the engine instrument and crew alerting system. Certain of those reported incidents resulted in the airplane experiencing a momentary loss of electrical power and loss of flight displays. This AD requires modification of the direct current power centers. We are issuing this AD to prevent loss of electrical power, which could result in the loss of flight displays and reduced controllability of the airplane. DATES: This AD becomes effective April 15, 2014. SUMMARY: E:\FR\FM\11MRR1.SGM 11MRR1 Federal Register / Vol. 79, No. 47 / Tuesday, March 11, 2014 / Rules and Regulations mstockstill on DSK4VPTVN1PROD with RULES The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 15, 2014. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-0798; 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 ˆ ´ Cote-Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855– 5000; fax 514–855–7401; email thd.crj@ aero.bombardier.com; 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. FOR FURTHER INFORMATION CONTACT: Assata Dessaline, Aerospace Engineer, Systems and Flight Test Branch, ANE– 172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone (516) 228–7301; fax (516) 794–5531. 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 BD–100–1A10 (Challenger 300) airplanes. The NPRM published in the Federal Register on September 25, 2013 (78 FR 58965). The NPRM was prompted by multiple reports of erratic electrical status indications on the push button annunciators and the engine instrument and crew alerting system. Certain of those reported incidents resulted in the airplane experiencing a momentary loss of electrical power and loss of flight displays. The NPRM proposed to require modification of the direct current power centers. We are issuing this AD to prevent loss of electrical power, which could result in the loss of flight displays and reduced controllability of the airplane. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2013–05, dated February 22, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition VerDate Mar<15>2010 16:00 Mar 10, 2014 Jkt 232001 for the specified products. The MCAI states: There have been multiple in-service reports of erratic electrical status indications on the Push Button Annunciators (PBA) and the Engine Instrument & Crew Alerting System (EICAS) while on-ground and during flight. Three of those reported incidents resulted in the aeroplane experiencing momentary loss of electrical power and loss of flight displays. The investigation revealed that improper insertion of a Printed Circuit Board (PCB) in a Direct Current Power Center (DCPC) may lead to erroneous electrical status indications on the PBAs and EICAS. The erroneous indications could mislead the pilots into turning off active generators and leading to partial or complete loss of electrical power. Loss of electrical power could result in the loss of flight displays and reduced controllability of the aeroplane. Further investigation determined that the design of the existing DCPC covers does not ensure that the PCBs will remain inserted into the motherboard of the DCPC. This [TCCA] AD mandates the modification of each DCPC to ensure that properly closed covers will retain the PCBs within the motherboards. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2013-07980001. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (78 FR 58965, September 25, 2013) 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 (78 FR 58965, September 25, 2013) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (78 FR 58965, September 25, 2013). Costs of Compliance We estimate that this AD affects 92 airplanes of U.S. registry. We also estimate that it will take about 7 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $1,568 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $198,996, or $2,163 per product. PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 13529 According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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-2013-0798; 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 E:\FR\FM\11MRR1.SGM 11MRR1 13530 Federal Register / Vol. 79, No. 47 / Tuesday, March 11, 2014 / Rules and Regulations 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 1. The authority citation for part 39 continues to read as follows: ■ [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2014–05–23 Bombardier, Inc.: Amendment 39–17796. Docket No. FAA–2013–0798; Directorate Identifier 2013–NM–087–AD. (a) Effective Date This airworthiness directive (AD) becomes effective April 15, 2014. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc. Model BD–100–1A10 (Challenger 300) airplanes, certificated in any category, serial numbers 20003 and subsequent. (d) Subject Air Transport Association (ATA) of America Code 24, Electrical power. mstockstill on DSK4VPTVN1PROD with RULES (e) Reason This AD was prompted by multiple reports of erratic electrical status indications on the push button annunciators and the engine instrument and crew alerting system. Certain of those reported incidents resulted in the airplane experiencing a momentary loss of electrical power and loss of flight displays. We are issuing this AD to prevent loss of electrical power, which could result in the loss of flight displays and reduced controllability of the airplane. (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) Direct Current Power Centers (DCPC) Modification For airplanes having serial numbers 20003 through 20405 inclusive: Within 800 flight hours after the effective date of this AD or within 24 months after the effective date of this AD, whichever occurs first, modify the VerDate Mar<15>2010 16:00 Mar 10, 2014 Jkt 232001 (h) Parts Installation Limitation As of the effective date of this AD, no person may install a DCPC having a part number specified in paragraphs (h)(1) through (h)(9) of this AD on any airplane, unless the DCPC serial number has a suffix ‘‘R’’ beside the serial number. (1) 970GC02Y04. (2) 970GC02Y05. (3) 970GC02Y06. (4) 975GC02Y04. (5) 975GC02Y05. (6) 975GC02Y06. (7) 320GC03Y04. (8) 320GC03Y05. (9) 320GC03Y06. (i) Other FAA AD Provisions Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 left-hand DCPC, right-hand DCPC, and auxiliary DCPC, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 100–24–23, dated November 26, 2012. 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, 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) 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 FAAapproved 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. (j) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2013–05, dated February 22, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2013-0798-0001. (k) 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. PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 (i) Bombardier Service Bulletin 100–24–23, dated November 26, 2012. (ii) Reserved. (3) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; email thd.crj@ aero.bombardier.com; 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/ibrlocations.html. Issued in Renton, Washington, on February 26, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–04822 Filed 3–10–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0977; Directorate Identifier 2013–NM–190–AD; Amendment 39–17795; AD 2014–05–22] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 717–200 airplanes. This AD was prompted by multiple reports of cracking in the overwing frames. This AD requires repetitive inspections for cracking in the overwing frames, and corrective actions if necessary. We are issuing this AD to detect and correct such cracking, which could result in a severed frame and might increase the loading of adjacent frames, resulting in damage to the adjacent structure and consequent loss of structural integrity of the airplane. DATES: This AD is effective April 15, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 15, 2014. SUMMARY: E:\FR\FM\11MRR1.SGM 11MRR1

Agencies

[Federal Register Volume 79, Number 47 (Tuesday, March 11, 2014)]
[Rules and Regulations]
[Pages 13528-13530]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04822]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0798; Directorate Identifier 2013-NM-087-AD; 
Amendment 39-17796; AD 2014-05-23]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes. This AD 
was prompted by multiple reports of erratic electrical status 
indications on the push button annunciators and the engine instrument 
and crew alerting system. Certain of those reported incidents resulted 
in the airplane experiencing a momentary loss of electrical power and 
loss of flight displays. This AD requires modification of the direct 
current power centers. We are issuing this AD to prevent loss of 
electrical power, which could result in the loss of flight displays and 
reduced controllability of the airplane.

DATES: This AD becomes effective April 15, 2014.

[[Page 13529]]

    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 15, 
2014.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0798; 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 
thd.crj@aero.bombardier.com; 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.

FOR FURTHER INFORMATION CONTACT: Assata Dessaline, Aerospace Engineer, 
Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone (516) 228-7301; fax (516) 794-5531.

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 BD-100-1A10 (Challenger 300) airplanes. The NPRM published in the 
Federal Register on September 25, 2013 (78 FR 58965). The NPRM was 
prompted by multiple reports of erratic electrical status indications 
on the push button annunciators and the engine instrument and crew 
alerting system. Certain of those reported incidents resulted in the 
airplane experiencing a momentary loss of electrical power and loss of 
flight displays. The NPRM proposed to require modification of the 
direct current power centers. We are issuing this AD to prevent loss of 
electrical power, which could result in the loss of flight displays and 
reduced controllability of the airplane.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2013-05, dated February 22, 2013 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for the specified products. The MCAI 
states:

    There have been multiple in-service reports of erratic 
electrical status indications on the Push Button Annunciators (PBA) 
and the Engine Instrument & Crew Alerting System (EICAS) while on-
ground and during flight. Three of those reported incidents resulted 
in the aeroplane experiencing momentary loss of electrical power and 
loss of flight displays.
    The investigation revealed that improper insertion of a Printed 
Circuit Board (PCB) in a Direct Current Power Center (DCPC) may lead 
to erroneous electrical status indications on the PBAs and EICAS. 
The erroneous indications could mislead the pilots into turning off 
active generators and leading to partial or complete loss of 
electrical power. Loss of electrical power could result in the loss 
of flight displays and reduced controllability of the aeroplane.
    Further investigation determined that the design of the existing 
DCPC covers does not ensure that the PCBs will remain inserted into 
the motherboard of the DCPC.
    This [TCCA] AD mandates the modification of each DCPC to ensure 
that properly closed covers will retain the PCBs within the 
motherboards.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0798-0001.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (78 FR 58965, September 
25, 2013) 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 (78 FR 58965, September 25, 2013) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 58965, September 25, 2013).

Costs of Compliance

    We estimate that this AD affects 92 airplanes of U.S. registry.
    We also estimate that it will take about 7 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $1,568 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $198,996, or $2,163 per product.
    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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-2013-0798; 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

[[Page 13530]]

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.


Sec.  39.13  [Amended]

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

2014-05-23 Bombardier, Inc.: Amendment 39-17796. Docket No. FAA-
2013-0798; Directorate Identifier 2013-NM-087-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective April 15, 
2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc. Model BD-100-1A10 
(Challenger 300) airplanes, certificated in any category, serial 
numbers 20003 and subsequent.

(d) Subject

    Air Transport Association (ATA) of America Code 24, Electrical 
power.

(e) Reason

    This AD was prompted by multiple reports of erratic electrical 
status indications on the push button annunciators and the engine 
instrument and crew alerting system. Certain of those reported 
incidents resulted in the airplane experiencing a momentary loss of 
electrical power and loss of flight displays. We are issuing this AD 
to prevent loss of electrical power, which could result in the loss 
of flight displays and reduced controllability of the airplane.

(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) Direct Current Power Centers (DCPC) Modification

    For airplanes having serial numbers 20003 through 20405 
inclusive: Within 800 flight hours after the effective date of this 
AD or within 24 months after the effective date of this AD, 
whichever occurs first, modify the left-hand DCPC, right-hand DCPC, 
and auxiliary DCPC, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 100-24-23, dated 
November 26, 2012.

(h) Parts Installation Limitation

    As of the effective date of this AD, no person may install a 
DCPC having a part number specified in paragraphs (h)(1) through 
(h)(9) of this AD on any airplane, unless the DCPC serial number has 
a suffix ``R'' beside the serial number.

(1) 970GC02Y04.
(2) 970GC02Y05.
(3) 970GC02Y06.
(4) 975GC02Y04.
(5) 975GC02Y05.
(6) 975GC02Y06.
(7) 320GC03Y04.
(8) 320GC03Y05.
(9) 320GC03Y06.

(i) 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, 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) 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.

(j) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
Canadian Airworthiness Directive CF-2013-05, dated February 22, 
2013, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0798-0001.

(k) 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) Bombardier Service Bulletin 100-24-23, dated November 26, 
2012.
    (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 thd.crj@aero.bombardier.com; 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 February 26, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-04822 Filed 3-10-14; 8:45 am]
BILLING CODE 4910-13-P