AD 2017-14-16

We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD requires removing the fasteners attaching the machined center fitting to the rear spar frame lower flange splice, inspecting the fasteners and fastener holes for damage, reworking and repairing the fastener holes, as applicable, and replacing the fasteners. This AD was prompted by a report indicating that certain fasteners attaching the machined rear spar center fitting to the frame were installed with a gap between the fastener head and the structure, or were installed tilted. We are issuing this AD to address the unsafe condition on these products.

Final rule; request for comments.

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 airworthiness directive (AD):

2017-14-16 Bombardier, Inc.: Amendment 39-18960; Docket No. FAA- 2017-0696; Directorate Identifier 2017-NM-070-AD.

(a) Effective Date

This AD becomes effective August 1, 2017.

(b) Affected ADs

None.

(c) Applicability

This AD applies to Bombardier, Inc., Model BD-100-1A10 airplanes, certificated in any category, serial numbers 20001 through 20433 inclusive.

(d) Subject

Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

This AD was prompted by a report indicating that certain fasteners attaching the machined rear spar center fitting to the frame were installed with a gap between the fastener head and the structure, or were installed tilted. We are issuing this AD to prevent failure of the fitting fasteners and consequent cracking within the fitting or frame, which could result in reduced structural integrity of the wing-to-fuselage attachment.

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(f) Compliance

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

(g) Replacement

Before the accumulation of 7,500 total flight cycles, or within 10 days after the effective date of this AD, whichever occurs later, do the actions required by paragraphs (g)(1) through (g)(4) of this AD, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 100-53-32, dated February 16, 2017.
(1) Remove the fasteners attaching the machined center fitting (part number 1005340715), wing-to-fuselage attachment and splice fitting at fuselage station 587, to the rear spar frame lower flange splice.
(2) Do a general visual inspection of the fasteners for damage and an eddy current inspection of the fastener holes for damage.
(3) Rework the fastener holes as applicable.
(4) Replace the fasteners with self-aligning fasteners and self- aligning collars.

(h) Exception to Service Information Specifications

If any damage of any fastener hole is found during any inspection required by paragraph (g)(2) of this AD, before further flight, repair using a method approved by the Manager, New York Aircraft Certification Office (ACO), ANE-170, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.'s TCCA Design Approval Organization (DAO).

(i) Reporting

Submit a report of the findings of the inspections required by paragraph (g)(2) of this AD, as specified in Appendix 1 of Bombardier Service Bulletin 100-53-32, dated February 16, 2017, to bbad_challenger_stress@aero.bombardier.com, at the applicabletime specified in paragraph (i)(1) or (i)(2) of this AD.
(1) If the inspection was done on or after the effective date of this AD: Submit the report within 10 days after the inspection.
(2) If the inspection was done before the effective date of this AD: Submit the report within 10 days after the effective date of this AD.

(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 New York 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 anyapproved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office.
(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 TCCA; or the TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature.
(3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200.

(k) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF-2017-12, dated March 10, 2017, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0696.
(2) For more information about this AD, contact Aziz Ahmed, Airframe Engineer, Airframe and Mechanical Systems Branch, ANE-171, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516-228-7329; fax: 516-794-5531.

(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) Bombardier Service Bulletin 100-53-32, dated February 16, 2017.
(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.

Discussion

Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian AD CF-2017-12, dated March 10, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Bombardier, Inc. Model BD-100-1A10 airplanes. The MCAI states:

During production, it was observed that some fasteners joining the machined rear spar center fitting were installed with a gap between the fastener head and the structure, and others were installed tilted. Improperly installed fasteners could cause a premature failure of the fitting fasteners and cracking within the fitting or frame, resulting in the loss of structural integrity of the wing to fuselage attachment.
This [Canadian] AD mandates the removal of all fasteners at the rear spar frame lower flange splice, inspection and rework [and repair] of the holes, and fastener replacement withself-aligning fasteners and self-aligning collars.

The inspections include a general visual inspection of the fasteners for damage (i.e., missing, broken, or deformed), and an eddy current inspection of the fastener holes for damage. Rework includes deburring and chamfering the holes.
You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0696.

Related Service Information Under 1 CFR Part 51

Bombardier, Inc., has issued Service Bulletin 100-53-32, dated February 16, 2017. The service information describes procedures for removing and replacing the fasteners attaching the machined center fitting to the rear spar frame lower flange splice. The service information also describes procedures for inspecting the fasteners and fastener holes and reworking the fastener holes. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This 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 issuing this

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AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.

FAA's Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because improperly installed fasteners could cause premature failure of the fitting fasteners and cracking within the fitting or frame, resulting in reduced structural integrity of the wing-to-fuselage attachment. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0696; Directorate Identifier 2017-NM-070-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this 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 AD.

Costs of Compliance

We estimate that this AD affects 187 airplanes of U.S. registry.
We also estimate that it will take about 37 work-hours per product to comply with the basic requirements of this AD and 1 work-hour per product for reporting. The average labor rate is $85 per work-hour. Required parts will cost about $15,150 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $3,437,060, or $18,380 per product.
We have received no definitive data that would enable us to provide cost estimates for other on-condition actions specified in this AD.
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.

Paperwork Reduction Act

A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120- 0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES-200.

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.

List of Subjects in 14 CFR Part 39

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