Airworthiness Directives: Bombardier Model DHC-8 Series Airplanes

Federal Register: January 12, 2009 (Volume 74, Number 7)

Proposed Rules

Page 1164-1166

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

DOCID:fr12ja09-14

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 14 CFR Part 39

Docket No. FAA-2008-1361; Directorate Identifier 2008-NM-140-AD

RIN 2120-AA64

Airworthiness Directives; Bombardier Model DHC-8-102, -103, and - 106 Airplanes and DHC-8-200, -300, and -400 Series Airplanes

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:

A fuselage spoiler cable disconnect sensing device was installed in production on later DHC-8 Series 100/200/300 aircraft, and on all

DHC-8 Series 400 aircraft. On earlier DHC-8 Series 100/200/300 aircraft, its installation was mandated by [Canadian] Airworthiness

Directive CF-2006-13 [which corresponds to FAA AD 2007-21-16].

However, several incorrectly assembled spoiler cable disconnect sensing devices have recently been discovered on in-service aircraft. A pulley and plastic spacer had been inadvertently interchanged during assembly of the device in production, resulting in the spoiler cable sliding on the spacer rather than on the pulley, as designed.

Continued operation with an incorrectly assembled spoiler cable disconnect sensing device could result in impaired operation of the sensing device and/or an eventual fuselage spoiler cable disconnect, with possible reduced controllability of the aircraft.

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

DATES: We must receive comments on this proposed AD by February 11, 2009.

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 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec

H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-7401; e-mail thd.qseries@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 or 425-227-1152.

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.

FOR FURTHER INFORMATION CONTACT: Dan Parrillo, Aerospace Engineer,

Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft

Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New

York 11590; telephone (516) 228-7305; fax (516) 794-5531.

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-2008-1361;

Directorate Identifier 2008-NM-140-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- 2008-28, dated July 10, 2008 (referred to after this as ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states:

A fuselage spoiler cable disconnect sensing device was installed in production on later DHC-8 Series 100/200/300 aircraft, and on all

DHC-8 Series 400 aircraft. On earlier DHC-8 Series 100/200/300 aircraft, its installation was mandated by [Canadian] Airworthiness

Directive CF-2006-13 [which corresponds to FAA AD 2007-21-16].

However, several incorrectly assembled spoiler cable disconnect sensing devices have recently been discovered on in-service aircraft. A pulley and plastic spacer had been inadvertently interchanged during assembly of the device in production, resulting in the spoiler cable sliding on the spacer rather than on the pulley, as designed.

Continued operation with an incorrectly assembled spoiler cable disconnect sensing device could result in impaired operation of the sensing device and/or an eventual fuselage spoiler cable disconnect, with possible reduced controllability of the aircraft.

Required actions include inspecting the fuselage spoiler cable disconnect sensing device and, if necessary, inspecting components for wear and damage, replacing worn or damaged components, and correctly re-assembling the sensing device. You may obtain further information by examining the MCAI in the AD docket.

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Relevant Service Information

Bombardier has issued Service Bulletins 84-27-34, dated October 3, 2007, and 8-27-107, dated October 16, 2007. 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 145 products 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 proposed AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of the proposed

AD on U.S. operators to be $11,600, or $80 per product.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation

Programs,'' describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in

``Subtitle VII, Part A, Subpart III, section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

Regulatory Findings

We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not 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.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the

Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows:

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

Sec. 39.13 [Amended] 2. The FAA amends Sec. 39.13 by adding the following new AD:

Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2008- 1361; Directorate Identifier 2008-NM-140-AD.

Comments Due Date

(a) We must receive comments by February 11, 2009.

Affected ADs

(b) None.

Applicability

(c) This AD applies to the following Bombardier Model DHC-8 airplanes, certificated in any category.

(1) Model DHC-8-102, -103, -106, -201, -202, -301, -311, and - 315 airplanes, serial numbers 003 through 644 inclusive.

(2) Model DHC-8-400, -401 and -402 airplanes, serial numbers 4003, 4004, 4006, and 4008 through 4164 inclusive.

Subject

(d) Air Transport Association (ATA) of America Code 27: Flight controls.

Reason

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

A fuselage spoiler cable disconnect sensing device was installed in production on later DHC-8 Series 100/200/300 aircraft, and on all

DHC-8 Series 400 aircraft. On earlier DHC-8 Series 100/200/300 aircraft, its installation was mandated by [Canadian] Airworthiness

Directive CF-2006-13 [which corresponds to FAA AD 2007-21-16].

However, several incorrectly assembled spoiler cable disconnect sensing devices have recently been discovered on in-service aircraft. A pulley and plastic spacer had been inadvertently interchanged during assembly of the device in production, resulting in the spoiler cable sliding on the spacer rather than on the pulley, as designed.

Continued operation with an incorrectly assembled spoiler cable disconnect sensing device could result in impaired operation of the sensing device and/or an eventual fuselage spoiler cable disconnect, with possible reduced controllability of the aircraft.

Required actions include inspecting the fuselage spoiler cable disconnect sensing device and, if necessary, inspecting components for wear and damage, replacing worn or damaged components, and correctly re-assembling the sensing device.

Actions and Compliance

(f) Unless already done, do the following.

(1) For Bombardier Model DHC-8-102, -103, -106, -201, -202, - 301, -311, and -315 airplanes, serial numbers 003 through 561 inclusive: Do the actions required by paragraph (f)(1)(i) or

(f)(1)(ii) of this AD, as applicable, in accordance with paragraph 3.B., Part A, of Bombardier Service Bulletin 8-27-107, dated October 16, 2007.

(i) For airplanes on which fuselage spoiler cable disconnect sensing device, Modsum 8Q100898, has been installed as of the effective date of this AD: Within 1,000 flight hours after the effective date of this AD, inspect the fuselage spoiler cable disconnect sensing device for correct assembly.

(ii) For airplanes on which fuselage spoiler cable disconnect sensing device, Modsum 8Q100898, has not been installed as of the effective date of this AD: Concurrently with

Page 1166

the installation of Modsum 8Q100898, inspect the fuselage spoiler cable disconnect sensing device for correct assembly.

Note 1: AD 2007-21-16 requires the installation of Modsum 8Q100898.

(2) For Bombardier Model -102, -103, -106, -201, -202, -301, - 311, and -315 airplanes, serial numbers 562 through 644 inclusive:

Within 1,000 flight hours after the effective date of this AD, inspect the fuselage spoiler cable disconnect sensing device for correct assembly in accordance with paragraph 3.B., Part A, of

Bombardier Service Bulletin 8-27-107, dated October 16, 2007.

Note 2: The fuselage spoiler cable disconnect sensing device was installed in production on the airplanes identified in paragraph

(f)(2) of this AD.

(3) For Bombardier Model DHC 8-400, -401, and -402 airplanes, serial numbers 4003, 4004, 4006, and 4008 through 4164 inclusive:

Within 1,000 flight hours after the effective date of this AD, inspect the fuselage spoiler cable disconnect sensing device for correct assembly in accordance with paragraph 3.B., Part A, of

Bombardier Service Bulletin 84-27-34 dated October 3, 2007.

Note 3: The fuselage spoiler cable disconnect sensing device was installed in production on the airplanes identified in paragraph

(f)(3) of this AD.

(4) For all airplanes: If an incorrectly assembled sensing device is detected during any inspection required by paragraphs

(f)(1), (f)(2), or (f)(3) of this AD, before further flight, inspect the components, replace worn or damaged components, and correctly re-assemble the sensing device. Do the actions in accordance with paragraph 3.B., Part B, of Bombardier Service Bulletin 8-27-107, dated October 16, 2007; or Bombardier Service Bulletin 84-27-34, dated October 3, 2007; as applicable.

FAA AD Differences

Note 4: This AD differs from the MCAI and/or service information as follows: No difference.

Other FAA AD Provisions

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

(1) Alternative Methods of Compliance (AMOCs): The Manager, New

York Aircraft Certification Office, 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: Dan Parrillo, Aerospace

Engineer, Airframe and Propulsion Branch, ANE-171, FAA, New York

Aircraft Certification Office, 1600 Stewart Avenue, Suite 410,

Westbury, New York 11590; telephone (516) 228-7305; fax (516) 794- 5531. Before using any approved AMOC on any airplane to which the

AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(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, the

Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120- 0056.

Related Information

(h) Refer to MCAI Canadian Airworthiness Directive CF-2008-28, dated July 10, 2008; Bombardier Service Bulletin 84-27-34, dated

October 3, 2007; and Bombardier Service Bulletin 8-27-107 dated

October 16, 2007; for related information.

Issued in Renton, Washington, on December 18, 2008.

Stephen P. Boyd,

Assistant Manager, Transport Airplane Directorate, Aircraft

Certification Service.

FR Doc. E9-323 Filed 1-9-09; 8:45 am

BILLING CODE 4910-13-P