Document ID: FAA-2016-9503-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Bombardier, Inc. Airplanes
Posted Date: 2016-12-16T05:00Z

[Federal Register Volume 81, Number 242 (Friday, December 16, 2016)]
[Rules and Regulations]
[Pages 90961-90964]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-29815]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9503; Directorate Identifier 2016-NM-179-AD; 
Amendment 39-18744; AD 2016-25-18]
RIN 2120-AA64

Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: 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.

DATES: This AD becomes effective January 3, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 3, 
2017.
    We must receive comments on this AD by January 30, 2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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 W12-140, 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 final rule, 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. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2016-9503.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9503; 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 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: Aziz Ahmed, Airframe Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, 
NY 11590; telephone: 516-228-7329; fax: 516-794-5531.

SUPPLEMENTARY INFORMATION: 

Discussion

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority

[[Page 90962]]

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 to the 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.
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    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

[[Page 90963]]

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

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 bulletin provides 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

[[Page 90964]]

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.

    Issued in Renton, Washington, on December 2, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-29815 Filed 12-15-16; 8:45 am]
 BILLING CODE 4910-13-P