AD 2016-25-18

We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-700-1A10 and BD-700-1A11 airplanes. This AD requires an inspection for discrepancies of the attachment points of the links between the engine rear mount assemblies, and corrective actions if necessary. This AD was prompted by a report indicating that during maintenance, an engine mount pin was found backed out of the rear mount link, and the associated retaining bolt was also found fractured. 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):

2016-25-18 Bombardier Inc.: Amendment 39-18744; Docket No. FAA-2016- 9503; Directorate Identifier 2016-NM-179-AD.

(a) Effective Date

This AD becomes effective January 3, 2017.

(b) Affected ADs

None.

(c) Applicability

This AD applies to Bombardier Inc. Model BD-700-1A10 and BD-700- 1A11 airplanes, certificated in any category, serial numbers (S/Ns) 9002 through 9763 inclusive, 9765, 9767 through 9770 inclusive, and 9998.

(d) Subject

Air Transport Association (ATA) of America Code 72, Engine.

(e) Reason

This AD was prompted by a report indicating that during maintenance, an engine mount pin was found backed out of the rear mount link, and the associated retaining bolt was also found fractured at the groove that holds the locking spring. We are issuing this AD to detect and correct broken engine attachment hardware, which could result in separation of an engine from the airplane.

(f) Compliance

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

(g) Inspection

Within 500 flight hours or 4 months, whichever occurs first after the effective date of this AD: Do an inspection for discrepancies of the engine rear mount assemblies (including missing or broken bolts, missing nuts, incorrect torque values, and an incorrect gap between the bushing and washer); in accordance with Part A of the Accomplishment Instructions of the applicable service information specified in paragraphs (g)(1) through (g)(4) of this AD.
(1) Bombardier Service Bulletin 700-71-002, Revision 01, dated June 30, 2016 (for Bombardier Model BD-700-1A10 airplanes).
(2) Bombardier Service Bulletin 700-71-6002, Revision 01, dated June 30, 2016 (for Bombardier Model BD-700-1A10 airplanes).
(3) Bombardier Service Bulletin 700-71-5002, Revision 01, dated June 30, 2016 (for Bombardier Model BD-700-1A11 airplanes).
(4) Bombardier Service Bulletin 700-1A11-71-002, Revision 01, dated June 30, 2016 (for Bombardier Model BD-700-1A11 airplanes).

(h) Corrective Action

If any discrepancy is detected during the inspection required by paragraph (g) of this AD, before further flight, replace missing parts and correct noncompliant gaps and bolt torque, as specified in the Accomplishment Instructions of the applicable service information specified in paragraphs (g)(1) through (g)(4) of this AD, except as required by paragraph (i) of this AD.

(i) Exceptions to Service Information Specifications

Where the applicable Bombardier service bulletinprovides no instructions for corrective actions, or specifies to contact Bombardier for appropriate action, accomplish corrective actions in accordance with the procedures specified in paragraph (k)(2) of this AD.

(j) Credit for Previous Actions

This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (j)(1) through (j)(4) of this AD.
(1) Bombardier Service Bulletin 700-71-002, dated May 31, 2016.
(2) Bombardier Service Bulletin 700-71-6002, dated May 31, 2016.
(3) Bombardier Service Bulletin 700-71-5002, dated May 31, 2016.
(4) Bombardier Service Bulletin 700-1A11-71-002, dated May 31, 2016.

(k) 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

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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 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.

(l) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF-2016-23, dated July 28, 2016, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-9503.
(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD.

(m) 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 700-71-002, Revision 01, dated June 30, 2016.
(ii) Bombardier Service Bulletin 700-71-6002, Revision 01, dated June 30, 2016.
(iii) Bombardier Service Bulletin 700-71-5002, Revision 01, dated June 30, 2016.
(iv) Bombardier Service Bulletin 700-1A11-71-002, Revision 01, dated June 30, 2016.
(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

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for Canada, has issued Canadian AD CF-2016-23, dated July 28, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Bombardier, Inc. Model BD-700-1A10 and BD-700-1A11 airplanes. The MCAI states:

Bombardier reported that during maintenance of a BD-700 aeroplane, the engine mount pin, part number (P/N) BRR15838, was found backed out of the rear mount link. The retaining bolt, P/N AS54020, which passes through the engine mount pin was also found fractured at the groove which holds the locking spring. An investigation revealed the most probable root cause of failure to be a single axial tension static overload, with no evidence of fatigue contributing to the failure.
The above condition if not detected, may result in the loss of engine attachment tothe airframe.
Bombardier has issued Service Bulletins (SBs) 700-71-002, 700- 71-6002, 700-71-5002 and 700-1A11-71-002 to inspect the attachment points of the links between the engine rear mount assemblies, and installation of replacement hardware if required.
This [Canadian] AD mandates incorporation of the above Bombardier SBs to inspect [for discrepancies (including missing or broken bolts, missing nuts, incorrect torque values, and an incorrect gap between the bushing and washer), noncompliant gaps and torque values, broken or missing attachment hardware; and corrective actions, including installation of replacement hardware if necessary] and maintain integrity of the affected engine rear mount assembly. Bombardier is developing design changes for the parts in question. Further mandatory action may be required when the new parts become available.

You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 9503.

Related Service Information Under 1 CFR Part 51

We reviewed the following service information:
Bombardier Service Bulletin 700-71-002, Revision 01, dated June 30, 2016.
Bombardier Service Bulletin 700-71-6002, Revision 01, dated June 30, 2016.
Bombardier Service Bulletin 700-71-5002, Revision 01, dated June 30, 2016.
Bombardier Service Bulletin 700-1A11-71-002, Revision 01, dated June 30, 2016.
The service information describes procedures for an inspection for discrepancies of the attachment points of the links between the engine rear mount assemblies, and corrective actions. These documents are distinct since they apply to different airplane models and serial numbers. 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 AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of these same type designs.

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 broken engine attachment hardware could result in separation of an engine from the airplane. 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-2016-9503; Directorate Identifier 2016-NM-179-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 97 airplanes of U.S. registry.We estimate the following costs to comply with this AD:

Estimated Costs ----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Inspection............................ 1 work-hour x $85 per $0 $85 $8,245
hour = $85 per airplane. ----------------------------------------------------------------------------------------------------------------

We estimate the following costs to do any necessary corrective actions that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these corrective actions:

On-Condition Costs ----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Bolt and Nut Replacement...................... 1 work-hour x $85 per hour = $85 $730 $815

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Torque Change on Affected Bolts............... 1 work-hour x $85 per hour = $85 0 85 ----------------------------------------------------------------------------------------------------------------

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 available 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 thatthis 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.