
[Federal Register Volume 82, Number 156 (Tuesday, August 15, 2017)]
[Proposed Rules]
[Pages 38626-38629]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-16777]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0775; Product Identifier 2017-NM-048-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc., Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2016-25-
18, for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 
airplanes. AD 2016-25-18 requires an inspection for discrepancies of 
the attachment points of the links between the engine rear mount 
assemblies, and corrective actions if necessary. Since we issued AD 
2016-25-18, we have determined that replacement of certain nuts and 
bolts in the engine rear mount assemblies is necessary. This proposed 
AD would require an inspection of certain attachment points, corrective 
action if necessary, and replacement of certain bolts and nuts in the 
engine rear mount assemblies. This proposed AD also adds airplanes to 
the applicability. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by September 29, 
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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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 
Standards Branch, 1601 Lind Avenue SW., Renton, WA. 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 by searching for and locating Docket No. FAA-2017-
0775; or in person at the Docket Management Facility 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: Aziz Ahmed, Airframe Engineer, 
Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516-228-7329; 
fax: 516-794-5531.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0775; 
Product Identifier 2017-NM-048-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

    On December 2, 2016, we issued AD 2016-25-18, Amendment 39-18744 
(81 FR 90961, December 16, 2016) (``AD 2016-25-18''), for certain 
Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. AD 2016-
25-18 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. AD 2016-25-18 
requires an inspection for discrepancies of the attachment points of 
the links between the engine rear mount assemblies, and corrective 
actions if necessary. We issued AD 2016-25-18 to detect and correct 
broken engine attachment hardware, which could result in separation of 
an engine from the airplane.
    Since we issued AD 2016-25-18, we have determined that replacement 
of certain nuts and bolts in the engine rear mount assemblies is 
necessary.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD CF-2016-23R1, dated 
February 20, 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-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.
    As an interim corrective action, Bombardier issued Service 
Bulletins (SBs) 700-71-002, 700-71-6002, 700-71-5002,

[[Page 38627]]

and 700-1A11-71-002 to inspect the attachment points of the links 
between the engine rear mount assemblies, and install replacement 
hardware if required.
    The original version of this [Canadian] AD was issued to mandate 
incorporation of the above Bombardier SBs to inspect and maintain 
integrity of the affected engine rear mount assembly.
    Revision 1 of this [Canadian] AD is issued to mandate 
incorporation of the Bombardier SBs 700-71-003, 700-71-6003, 700-71-
5003, and 700-1A11-71-003 to replace the existing bolts and self-
locking nuts with new bolts and nuts, as a final corrective action.

The MCAI also adds airplanes having serial numbers 9764, 9766, and 9771 
through 9785 inclusive to the applicability. Those airplanes are also 
affected by the identified unsafe condition. You may examine the MCAI 
in the AD docket on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2017-0775.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued the following service information.
     Bombardier Service Bulletin 700-71-002, Revision 01, dated 
June 30, 2016.
     Bombardier Service Bulletin 700-71-5002, Revision 01, 
dated June 30, 2016.
     Bombardier Service Bulletin 700-71-6002, Revision 01, 
dated June 30, 2016.
     Bombardier Service Bulletin 700-1A11-71-002, Revision 01, 
dated June 30, 2016.
    This 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.
    Bombardier has also issued the following service information. The 
service information describes procedures for nut and bolt replacement. 
These documents are distinct since they apply to different airplane 
models and serial numbers.
     Bombardier Service Bulletin 700-71-003, dated December 5, 
2016.
     Bombardier Service Bulletin 700-71-5003, dated December 5, 
2016.
     Bombardier Service Bulletin 700-71-6003, dated December 5, 
2016.
     Bombardier Service Bulletin 700-1A11-71-003, dated 
December 5, 2016.
    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 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.

Costs of Compliance

    We estimate that this proposed AD affects 97 airplanes of U.S. 
registry.
    The actions required by AD 2016-25-18, and retained in this 
proposed AD take about 1 work-hour per product, at an average labor 
rate of $85 per work-hour. Based on these figures, the estimated cost 
of the actions that are required by AD 2016-25-18 is $85 per product.
    The retained on-condition costs in this proposed AD take about 2 
work-hours per product, at an average labor rate of $85 per work-hour. 
Required parts cost about $730 per product. Based on these figures, the 
estimated cost of the on-condition actions that are required by AD 
2016-25-18 is $900 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for other retained on-condition actions specified in AD 
2016-25-18.
    We also estimate that it would take about 4 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost up to 
$14,940 per product. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be up to $1,482,160, or up to 
$15,280 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.
    According to the manufacturer, some of the costs of this proposed 
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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

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);
    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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator,

[[Page 38628]]

the FAA proposes to amend 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 removing Airworthiness Directive (AD) 
2016-25-18, Amendment 39-18744 (81 FR 90961, December 16, 2016), and 
adding the following new AD:

Bombardier, Inc.: Docket No. FAA-2017-0775; Product Identifier 2017-
NM-048-AD.

(a) Comments Due Date

    We must receive comments by September 29, 2017.

(b) Affected ADs

    This AD replaces AD 2016-25-18, Amendment 39-18744 (81 FR 90961, 
December 16, 2016) (``AD 2016-25-18'').

(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 9785 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) Retained Inspection, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2016-25-18, with no changes. For airplanes having S/Ns 9002 through 
9763 inclusive, 9765, 9767 through 9770 inclusive, and 9998: Within 
500 flight hours or 4 months, whichever occurs first after January 
3, 2017 (the effective date of AD 2016-25-18), 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. Accomplishing the actions required by paragraphs (j) and (k) of 
this AD terminates the requirements of this paragraph.
    (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) Retained Corrective Action for Paragraph (g) of This AD, With No 
Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2016-25-18, with no changes. 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. Accomplishing the actions required by paragraphs (j) and 
(k) of this AD terminates the requirements of this paragraph.

(i) Retained Exception to Service Information Specifications, With No 
Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2016-25-18, with no changes. Where the applicable Bombardier service 
bulletin specified in paragraphs (g)(1) through (g)(4) of this AD 
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 
(o)(2) of this AD.

(j) New Requirement of This AD: Gap Measurement

    Within 1,000 flight hours or 12 months, whichever occurs first 
after the effective date of this AD: Measure the gaps between the 
applicable shouldered bushing fitted on the mount beam and the 
washer; and between the applicable engine ring lug and the head of 
the mount pin to determine if the gaps are within acceptable limits; 
in accordance with Part A of the Accomplishment Instructions of the 
applicable service information specified in paragraphs (j)(1) 
through (j)(4) of this AD. Accomplishing the actions required by 
paragraphs (j) and (k) of this AD terminates the requirements of 
paragraphs (g) and (h) of this AD.
    (1) Bombardier Service Bulletin 700-71-003, dated December 5, 
2016 (for Bombardier Model BD-700-1A10 airplanes).
    (2) Bombardier Service Bulletin 700-71-6003, dated December 5, 
2016 (for Bombardier Model BD-700-1A10 airplanes).
    (3) Bombardier Service Bulletin 700-71-5003, dated December 5, 
2016 (for Bombardier Model BD-700-1A11 airplanes).
    (4) Bombardier Service Bulletin 700-1A11-71-003, dated December 
5, 2016 (for Bombardier Model BD-700-1A11 airplanes).

(k) New Requirement of This AD: Nut and Bolt Replacement, and Gap 
Measurement

    Within 1,000 flight hours or 12 months, whichever occurs first 
after the effective date of this AD: Replace the nuts having part 
number (P/N) AS54365 and the bolts having P/N AS54020 and AS54002 in 
the engine rear mount assembly with new nuts and new bolts; and do 
the gap measurement to determine if the gap is within acceptable 
limits; in accordance with Part B of the Accomplishment Instructions 
the applicable service information specified in paragraphs (j)(1) 
through (j)(4) of this AD.

(l) New Requirement of This AD: Corrective Action

    If any gap is detected, during any measurement required by 
paragraph (j) or (k) of this AD, that is not within the applicable 
limits specified in the service information specified in paragraphs 
(j)(1) through (j)(4) of this AD, before further flight repair using 
a method approved by the Manager, New York ACO Branch, FAA; or 
Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.'s TCCA 
Design Approval Organization (DAO).

(m) No Reporting Required

    Although the service information identified in paragraphs (j)(1) 
through (j)(4) of this AD specifies to submit certain information to 
the manufacturer, this AD does not include that requirement.

(n) 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 January 3, 2017 (the effective date of AD 2016-25-18), in 
accordance with the Accomplishment Instructions of the applicable 
service information specified in paragraphs (n)(1) through (n)(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.

(o) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York ACO Branch, 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 manager of the certification 
office, send it to ATTN: Program Manager, Continuing Operational 
Safety, FAA, New York ACO Branch, 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.

[[Page 38629]]

    (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 
Branch, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO. If approved by 
the DAO, the approval must include the DAO-authorized signature.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive 2016-23R1, dated February 
20, 2017, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2017-0775.
    (2) For more information about this AD, contact Aziz Ahmed, 
Airframe Engineer, Airframe and Mechanical Systems Section, FAA, New 
York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
telephone: 516-228-7329; fax: 516-794-5531.
    (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. You may view this service information at the 
FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on August 2, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-16777 Filed 8-14-17; 8:45 am]
BILLING CODE 4910-13-P


