Skip to Content

Proposed Rule

Airworthiness Directives; Bombardier, Inc. Model CL-215-1A10 (CL-215), CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) Airplanes

Document Details

Information about this document as published in the Federal Register.

Published Document

This document has been published in the Federal Register. Use the PDF linked in the document sidebar for the official electronic format.

Start Preamble

AGENCY:

Federal Aviation Administration (FAA), DOT.

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

Seven cases of on-ground hydraulic accumulator screw cap or end cap failure have been experienced * * * resulting in loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure. * * *

* * * * *

A detailed analysis of the systems and structure in the potential line of trajectory of a failed screw cap/end cap for each accumulator has been conducted. It has identified that the worst-case scenarios would be impact damage to various components, potentially resulting in fuel spillage, uncommanded flap movement, or loss of aileron control [and consequent reduced controllability of the airplane].

* * * * *

The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.

Start Printed Page 68729

DATES:

We must receive comments on this proposed AD by December 27, 2010.

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 W12-40, 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 Côte-Vertu Road West, Dorval, Québec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-7401; e-mail thd.crj@aero.bombardier.com; 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.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Christopher Alfano, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228-7340; fax (516) 794-5531.

End Further Info End Preamble Start Supplemental Information

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-2010-1108; Directorate Identifier 2010-NM-151-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

Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF-2009-42R1, dated May 14, 2010 (referred to after this as “the MCAI”), to correct an unsafe condition for the specified products. The MCAI states:

* * * * *

Seven cases of on-ground hydraulic accumulator screw cap or end cap failure have been experienced on CL-600-2B19 (CRJ) aircraft, resulting in loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure. To date, the lowest number of flight cycles accumulated at the time of failure has been 6991.

Although there have been no failures to date on any CL-215-1A10 (CL-215) or CL-215-6B11 (CL-215T and CL-415) aircraft, similar accumulators, Part Number (P/N) 08-8423-010 (MS28700-3), to those installed on the CL-600-2B19, are installed on the aircraft listed in the Applicability section of this directive [MCAI].

A detailed analysis of the systems and structure in the potential line of trajectory of a failed screw cap/end cap for each accumulator has been conducted. It has identified that the worst-case scenarios would be impact damage to various components, potentially resulting in fuel spillage, uncommanded flap movement, or loss of aileron control [and consequent reduced controllability of the airplane].

This directive [MCAI] mandates repetitive [ultrasonic] inspections of the accumulators for cracks and replacement of any accumulator in which a crack is detected.

* * * * *

You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Bombardier has issued Service Bulletins 215-541, 215-3155, and 215-4414, all Revision 1, all dated March 12, 2010. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.

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

We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.

We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD.

Costs of Compliance

Based on the service information, we estimate that this proposed AD would affect about 6 products of U.S. registry. We also estimate that it would take about 7 work-hours per product to comply with the 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 $3,570, or $595 per product per inspection cycle.

In addition, we estimate that any necessary follow-on actions would take about 6 work-hours and require parts costing $4,055, for a cost of $4,565 per product. We have no way of determining the number of products that may need these actions.

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, Start Printed Page 68730Part 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 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.

Start List of Subjects

List of Subjects in 14 CFR Part 39

End List of Subjects

The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

Start Part

PART 39—AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Start Authority

Authority: 49 U.S.C. 106(g), 40113, 44701.

End Authority
[Amended]

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

Bombardier, Inc.: Docket No. FAA-2010-1108; Directorate Identifier 2010-NM-151-AD.

Comments Due Date

(a) We must receive comments by December 27, 2010.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Bombardier, Inc. airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD.

(1) Model CL-215-1A10 (CL-215) airplanes, serial numbers 1001 through 1990 inclusive;

(2) Model CL-215-6B11 (CL-215T Variant) airplanes, serial numbers 1056 through 1125 inclusive;

(3) Model CL-215-6B11 (CL-415 Variant) airplanes, serial numbers 2001 through 2990 inclusive.

Subject

(d) Air Transport Association (ATA) of America Code 27: Flight controls; and 32: Landing gear.

Reason

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

Seven cases of on-ground hydraulic accumulator screw cap or end cap failure have been experienced * * * resulting in loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure. * * *

* * * * *

A detailed analysis of the systems and structure in the potential line of trajectory of a failed screw cap/end cap for each accumulator has been conducted. It has identified that the worst-case scenarios would be impact damage to various components, potentially resulting in fuel spillage, uncommanded flap movement, or loss of aileron control [and consequent reduced controllability of the airplane].

* * * * *

Compliance

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

Inspection To Determine Flight Hours

(g) Within 50 flight hours after the effective date of this AD, inspect to determine the number of flight cycles accumulated by each of the applicable accumulators (i.e., brake, aileron, elevator, and rudder accumulators) having part number (P/N) 08-8423-010 (MS28700-3) installed on the airplane. A review of airplane maintenance records is acceptable in lieu of this inspection if the number of flight cycles accumulated can be conclusively determined from that review.

Initial Ultrasonic Inspection

(h) For Model CL-215-1A10 (CL-215) and CL-215-6B11 (CL-215T) airplanes: Do an ultrasonic inspection for cracking of the accumulator at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, in accordance with Part B of the Accomplishment Instructions of the applicable service bulletin listed in Table 1 of this AD.

Table 1—Service Bulletins

For model—Use Bombardier Service Bulletin—Revision—Dated—
CL-215-1A10 (CL-215)215-5411March 12, 2010.
CL-215-6B11 (CL-215T)215-31551March 12, 2010.
CL-600-6B11 (CL-415)215-44141March 12, 2010.

(1) For any accumulator on which the inspection required by paragraph (g) of this AD shows an accumulation of more than 875 total flight cycles or on which it is not possible to determine the number of total accumulated flight cycles, do the inspection within 125 flight cycles after the effective date of this AD.

(2) For any accumulator on which the inspection required by paragraph (g) of this AD shows an accumulation of 875 total flight cycles or fewer, do the inspection before the accumulation of 1,000 flight cycles on the accumulator.

(i) For Model CL-215-6B11 (CL-415) airplanes, do an ultrasonic inspection for cracking of the accumulator at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, in accordance with Part B of the Accomplishment Instructions of the applicable service bulletin listed in Table 1 of this AD.

(1) For any accumulator on which the inspection required by paragraph (g) of this AD shows an accumulation of more than 750 flight cycles or on which it is not possible to determine the number of total accumulated flight cycles, do the inspection within 250 flight cycles after the effective date of this AD.

(2) For any accumulator on which the inspection required by paragraph (g) of this AD shows an accumulation of 750 total flight cycles or fewer, do the inspection before the accumulation of 1,000 flight cycles on the accumulator.

Repetitive Inspections

(j) If no cracking is found during any inspection required by paragraph (h) or (i) of this AD, repeat the inspection thereafter at intervals not to exceed 750 flight cycles. Start Printed Page 68731

(k) If any cracking is found during any inspection required by paragraph (h) or (i) of this AD, before further flight, replace the accumulator with a serviceable accumulator, in accordance with Part B of the Accomplishment Instructions of the applicable service bulletin listed in Table 1 of this AD. Doing the replacement does not end the inspection requirements of this AD. Repeat the inspections required by paragraph (h) or (i) of this AD at intervals not to exceed 750 flight cycles.

Parts Installation

(l) As of the effective date of this AD, no person may install an accumulator (P/N) 08-8423-010 (MS28700-3) on any airplane unless the accumulator has been inspected in accordance with the requirements of this AD.

Credit for Actions Accomplished in Accordance With Previous Service Information

(m) Inspections accomplished before the effective date of this AD in accordance with the applicable service bulletin listed in Table 2 of this AD are considered acceptable for compliance with the corresponding action specified in this AD.

Table 2—Credit Service Bulletins

For model—Use Bombardier Service Bulletin—Dated—
CL-215-1A10 (CL-215)215-541July 9, 2009.
CL-215-6B11 (CL-215T)215-3155July 9, 2009.
CL-600-6B11 (CL-415)215-4414July 9, 2009.

FAA AD Differences

Note 1:

This AD differs from the MCAI and/or service information as follows:

No differences.

Other FAA AD Provisions

(n) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE-170, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone 516-228-7300; fax 516-794-5531. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards 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.

(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056.

Related Information

(o) Refer to MCAI Transport Canada Civil Aviation Airworthiness Directive CF-2009-42R1, dated May 14, 2010; and the service bulletins listed in Table 1 of this AD; for related information.

Start Signature

Issued in Renton, Washington, on November 2, 2010.

Dionne Palermo,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Part End Supplemental Information

[FR Doc. 2010-28275 Filed 11-8-10; 8:45 am]

BILLING CODE 4910-13-P