Airworthiness Directives; Bombardier, Inc. Airplanes

[Federal Register Volume 81, Number 161 (Friday, August 19, 2016)]
[Rules and Regulations]
[Pages 55353-55358]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-19480]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3986; Directorate Identifier 2015-NM-057-AD; 
Amendment 39-18613; AD 2016-16-15]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. This AD was 
prompted by reports of chafing damage due to insufficient clearance on 
the main landing gear (MLG) stabilizer brace, the nacelle A-frame 
structure, and the adjacent electrical wiring harnesses. An 
insufficient fillet radius may also exist on certain airplanes. This AD 
requires, depending on airplane configuration, an inspection of the 
nacelle A-frame structure for insufficient fillet radius; an inspection 
for cracking of affected structure, and rework or repair if necessary, 
and rework of the nacelle A-frame structure; repetitive inspections of 
the nacelle A-frame structure and the MLG stabilizer brace for 
insufficient clearance and damage, and repair if necessary, and rework 
of the nacelle A-frame structure, which would terminate the repetitive 
inspections; installation of new stop brackets and a shim on each MLG 
stabilizer brace assembly; and rework of the electrical wiring 
harnesses in the nacelle area. We are issuing this AD to

[[Page 55354]]

detect and correct chafing damage and subsequent premature cracking and 
fracture of the nacelle A-frame structure, which could result in 
failure of the MLG stabilizer brace and loss of the MLG down-lock 
indication, which could adversely affect the safe landing of the 
airplane.

DATES: This AD is effective September 23, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 23, 
2016.

ADDRESSES: For Bombardier service information identified in this final 
rule, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 
Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-
4000; fax 416-375-4539; email [email protected]; Internet 
http://www.bombardier.com. For Goodrich service information identified 
in this AD, contact Goodrich Corporation, Landing Gear, 1400 South 
Service Road, West Oakville, ON, Canada L6L 5Y7; phone: 905-825-1568; 
email: [email protected]; Internet: http://www.goodrich.com/TechPubs. 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-2015-
3986.

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-2015-
3986; 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 AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (telephone 
800-647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone 516-228-7329; fax 516-794-5531.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Bombardier, Inc. 
Model DHC-8-400, -401, and -402 airplanes. The NPRM published in the 
Federal Register on October 19, 2015 (80 FR 63147) (``the NPRM''). The 
NPRM was prompted by reports of chafing damage due to insufficient 
clearance on the MLG stabilizer brace, the nacelle A-frame structure, 
and the adjacent electrical wiring harnesses. An insufficient fillet 
radius may also exist on certain airplanes. The NPRM proposed to 
require, depending on airplane configuration, an inspection of the 
nacelle A-frame structure for insufficient fillet radius; an inspection 
for cracking of affected structure, and rework or repair if necessary, 
and rework of the nacelle A-frame structure; repetitive inspections of 
the nacelle A-frame structure and the MLG stabilizer brace for 
insufficient clearance and damage, and repair if necessary, and rework 
of the nacelle A-frame structure, which would terminate the repetitive 
inspections; installation of new stop brackets and a shim on each MLG 
stabilizer brace assembly; and rework of the electrical wiring 
harnesses in the nacelle area. We are issuing this AD to detect and 
correct chafing damage and subsequent premature cracking and fracture 
of the nacelle A-frame structure, which could result in failure of the 
MLG stabilizer brace and loss of the MLG down-lock indication, which 
could adversely affect the safe landing of the airplane.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2014-45, dated December 23, 2014 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition on certain Bombardier, Inc. Model DHC-8-
400, -401, and -402 airplanes. The MCAI states:

    The aeroplane manufacturer has discovered that an insufficient 
fillet radius may exist on the flange of the nacelle A-frame 
structure on certain aeroplanes. There have also been several in-
service reports of chafing damage on the main landing gear (MLG) 
stabilizer brace, the nacelle A-frame structure and its adjacent 
electrical wiring harnesses due to insufficient clearance.
    An insufficient fillet radius and chafing damage on the nacelle 
A-frame structure and MLG stabilizer brace could lead to premature 
cracking. Fracture of the nacelle A-frame structure or failure of 
the MLG stabilizer brace could adversely affect the safe landing of 
the aeroplane. The damage to the electrical wiring harnesses could 
result in the loss of the MLG downlock indication.
    This [Canadian] AD mandates the inspection and rework of the 
nacelle A-frame structure, and the rework of the forward MLG 
stabilizer brace assembly and the electrical harnesses in the 
nacelle area adjacent to the A-frame structure.

The following actions are required, depending on airplane 
configuration.
    <bullet> A detailed inspection of the nacelle A-frame structure for 
insufficient fillet radius, an eddy current or fluorescent dye 
penetrant inspection for cracking of affected structure, and rework or 
repair if necessary.
    <bullet> Rework of the left-hand (LH) side and right-hand (RH) side 
nacelle A-frame structure, including doing a measurement of the 
clearance between the fasteners/A-frame structure and MLG stabilizer 
brace assembly and making sure no fouling condition exists, and repair 
if necessary.
    <bullet> Repetitive detailed inspections of the nacelle A-frame 
structure and the MLG stabilizer brace for insufficient clearance and 
damage, and repair if necessary.
    <bullet> Rework of the nacelle A-frame structure, including a 
measurement of the clearance between the A-frame structure and MLG 
stabilizer brace assembly, and a fluorescent dye penetrant inspection 
or high frequency eddy current inspection for cracking and repair if 
necessary, which would terminate the repetitive inspections.
    <bullet> Installation of new stop brackets and a shim on each MLG 
stabilizer brace assembly.
    <bullet> Rework of the electrical wiring harnesses in the nacelle 
area. The rework includes a detailed inspection of the conduit assembly 
for certain conditions and repair if any condition is found, 
replacement of damaged conduit, a measurement of the clearance between 
the stabilizer brace and electrical harness on both LH and RH nacelles 
to make sure there is 0.100 inch (2.54 millimeters (mm)) minimum 
clearance between the MLG stabilizer brace, and a check for damage on 
the A-frame structure and MLG stabilizer brace and repair if necessary.

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-2015-
3986.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

[[Page 55355]]

Request To Incorporate Revised Service Information and Provide Credit

    Horizon Air asked that the following revised service information be 
included in the proposed AD for the applicable actions:
    <bullet> Bombardier Service Bulletin 84-54-20, Revision C, dated 
March 5, 2015.
    <bullet> Bombardier Service Bulletin 84-32-112, Revision C, dated 
April 2, 2015.
    <bullet> Bombardier Service Bulletin 84-32-114, Revision B, dated 
February 3, 2015.
    <bullet> Goodrich Service Bulletin 46400-32-102 R2, Revision 2, 
dated February 17, 2015.
    Horizon Air pointed out that several of the service documents 
specified in the proposed AD have been updated, and asserted that the 
proposed AD should be revised to reference the updated service 
information. Horizon Air also asked that credit be given for actions 
done using the previous revisions of the revised service information.
    We agree with the commenter's requests. No new work is specified by 
the revised service information; therefore, we have revised the 
``Related Service Information under 1 CFR part 51'' section and the 
applicable requirements of this AD to refer to the updated service 
information. We have also revised paragraph (m) of this AD to provide 
credit for certain actions required by this AD, if those actions were 
performed before the effective date of this AD using earlier revisions 
of the service information identified previously.

Request To Omit Job Set-Up and Close Out Actions

    Horizon Air asked that we not mandate the ``Job Set-up'' and 
``Close Out'' sections of the Accomplishment Instructions of certain 
service information referenced in the NPRM. Horizon Air stated that 
these instructions do not directly correct the unsafe condition, but 
they do restrict an operator's ability to perform other maintenance in 
conjunction with the instructions that correct the unsafe condition. 
Horizon Air added that only the section in the Accomplishment 
Instructions that directly corrects the unsafe condition should be 
required.
    We agree with the commenter's request to exclude the ``Job Set-up'' 
and ``Close Out'' sections of the Accomplishment Instructions of 
certain service information identified in this AD. Paragraphs (g), (h), 
(i), and (j) of this AD already identify the specific sections of the 
Accomplishment Instructions of the applicable service information for 
doing only the actions that directly address the unsafe condition; 
therefore, there are no changes necessary in those paragraphs in this 
regard. However, we have revised paragraph (k) of this AD to specify 
doing only the actions provided in ``Part B--Procedure,'' of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-32-114, 
Revision B, dated February 3, 2015, for the required actions specified 
in that paragraph.

Request To Clarify a Certain Reference

    Horizon Air asked that we revise the paragraph references in 
paragraph (l)(1) of the proposed AD for clarity. Horizon Air stated 
that paragraph (l)(1) of the proposed AD refers to Bombardier ModSum 
IS4Q5450002, Revision B, dated June 22, 2012, as acceptable for 
compliance with the actions specified in paragraph (g) of the proposed 
AD. Horizon Air noted that for greater clarity, the reference should be 
to paragraph (g)(2) of the proposed AD.
    We agree with the commenter's request for the reasons provided. We 
have changed paragraph (l)(1) of this AD to specify that installing 
specified fasteners on the MLG A-frame, in both LH and RH nacelles, in 
accordance with Bombardier ModSum IS4Q5450002, Revision B, dated June 
22, 2012, is acceptable for compliance with the actions specified in 
paragraph (g)(2) of this AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued the following service information.
    <bullet> ModSum IS4Q2400028, Revision B, dated December 11, 2012; 
and ModSum IS4Q2400029, Revision A, dated July 6, 2012. These modsums 
describe procedures for rerouting certain electrical harnesses and 
installing grommets.
    <bullet> ModSum IS4Q5450002, Revision B, dated June 22, 2012. This 
modsum describes procedures for installing specified fasteners on the 
MLG A-frame, in both the LH and RH nacelles.
    <bullet> ModSum IS4Q5450003, Revision C, dated November 29, 2012. 
This modsum describes procedures for trimming the horizontal and 
vertical stiffeners on the MLG A frame in both the LH and RH nacelles.
    <bullet> Service Bulletin 84-32-112, Revision C, dated April 2, 
2015. This service information describes procedures for incorporating 
Bombardier ModSum 4-902416 by installing new stop brackets and new stop 
shims for all MLG stabilizer brace assemblies.
    <bullet> Service Bulletin 84-32-114, Revision B, dated February 3, 
2015. This service information describes procedures for rework of the 
electrical wiring harnesses in the nacelle area. The rework includes a 
detailed inspection of the conduit assembly for certain conditions, and 
repair, replacement of damaged conduit, a measurement of the clearance 
to make sure there is 0.100 inch (2.54 mm) minimum clearance between 
the MLG stabilizer brace, and a check for damage on the A-frame 
structure and MLG stabilizer brace and repair.
    <bullet> Service Bulletin 84-54-19, dated April 18, 2013. This 
service information describes procedures for detailed inspections of 
the nacelle A-frame structure for insufficient fillet radius, an eddy 
current or fluorescent dye penetrant inspection for cracking of 
affected structure, and rework or repair.
    <bullet> Service Bulletin 84-54-20, Revision C, dated March 5, 
2015. This service information describes procedures for detailed 
inspections of the nacelle A-frame structure and the MLG stabilizer 
brace for insufficient clearance and damage, and repair. This service 
information also describes procedures for rework of the nacelle A-frame 
structure, including a measurement of the clearance between the A-frame 
structure and MLG stabilizer brace assembly, and a fluorescent dye 
penetrant inspection or high frequency eddy current inspection for 
cracking and repair, which would end the inspections.
    <bullet> Service Bulletin 84-54-21, dated May 9, 2013. This service 
information describes procedures for rework of the LH side and RH side 
nacelle A-frame structure, including a measurement of the clearance 
between the fasteners/A-frame structure and MLG stabilizer brace 
assembly and to make sure no fouling condition exists, and repair.
    Goodrich has issued the following service information.

[[Page 55356]]

    <bullet> Service Bulletin 46400-32-102 R2, Revision 2, dated 
February 17, 2015. This service information describes procedures for 
installing new stop brackets and new stop shims for all MLG stabilizer 
brace assemblies.
    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.

Costs of Compliance

    We estimate that this AD affects 80 airplanes of U.S. registry.
    We also estimate that it takes up to 50 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts will cost $8,452 per product. 
Based on these figures, we estimate the cost of this AD on U.S. 
operators to be up to $1,016,160, or $12,702 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

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):

2016-16-15 Bombardier, Inc.: Amendment 39-18613; Docket No. FAA-
2015-3986; Directorate Identifier 2015-NM-057-AD.

(a) Effective Date

    This AD is effective September 23, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc. Model DHC-8-400, -401, and -
402 airplanes, certificated in any category, serial numbers (S/Ns) 
4001 through 4431 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Reason

    This AD was prompted by reports of chafing damage due to 
insufficient clearance on the main landing gear (MLG) stabilizer 
brace, the nacelle A-frame structure, and the adjacent electrical 
wiring harnesses. An insufficient fillet radius might also exist on 
certain airplanes. We are issuing this AD to detect and correct 
chafing damage and subsequent premature cracking and fracture of the 
nacelle A-frame structure, which could result in failure of the MLG 
stabilizer brace and loss of the MLG down-lock indication, which 
could adversely affect the safe landing of the airplane.

(f) Compliance

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

(g) Inspection, Corrective Actions, and Rework

    For airplanes having S/Ns 4001 through 4055 inclusive: Do the 
actions required by paragraphs (g)(1) and (g)(2) of this AD.
    (1) Within 600 flight hours or 100 days after the effective date 
of this AD, whichever occurs first: Do a detailed inspection of the 
left-hand (LH) side and right-hand (RH) side nacelle A-frame 
structure for insufficient fillet radius, in accordance with ``Part 
A--Inspection'' of the Accomplishment Instructions of Bombardier 
Service Bulletin 84-54-19, dated April 18, 2013. If an insufficient 
fillet radius exists, before further flight, do an eddy current or 
fluorescent dye penetrant inspection for cracking, in accordance 
with ``Part A--Inspection'' of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-54-19, dated April 18, 2013.
    (i) If any cracking is found: 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).
    (ii) If no cracking is found: Before further flight, rework the 
structure, in accordance with ``Part B--Rectification'' of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-54-19, 
dated April 18, 2013.
    (2) Within 6,000 flight hours or 36 months after the effective 
date of this AD, whichever occurs first: Rework the LH side and RH 
side nacelle A-frame structure, including doing a measurement of the 
clearance between the fasteners/A-frame structure and MLG stabilizer 
brace assembly and making sure no fouling condition exists, in 
accordance with paragraph 3.B., ``Procedure,'' of the Accomplishment 
Instructions of Bombardier Service Bulletin 84-54-21, dated May 9, 
2013. If the clearance is found to be less than 0.100 inch (2.54 
millimeters (mm)) between the fasteners/A-frame structure and MLG 
stabilizer brace assembly after the rework is done, or a fouling 
condition exists during the extension of the MLG after rework is 
done, before further flight, repair using a method approved by the 
Manager, New York ACO, ANE-170, FAA; or TCCA; or Bombardier, Inc.'s 
TCCA DAO.

(h) Repetitive Inspections and Corrective Actions

    For airplanes having S/Ns 4056 through 4426 inclusive: Within 
600 flight hours or 100 days after the effective date of this AD, 
whichever occurs first, do a detailed inspection of the LH side and 
RH side nacelle A-frame structure and upper surface of the MLG 
stabilizer brace for insufficient clearance and damage (e.g., 
cracking), in accordance with ``Part A--Inspection'' of the 
Accomplishment Instructions of Bombardier Service Bulletin 84-54-20, 
Revision C, dated March 5, 2015. If no damage is found and clearance 
is sufficient: Repeat the inspection thereafter at intervals not to 
exceed 600 flight hours until the terminating action required by 
paragraph (i) of this AD has been done.
    (1) If a clearance less than 0.100 inch (2.54 mm) exists between 
the A-frame structure

[[Page 55357]]

and the MLG stabilizer brace assembly in the retracted position, 
after the rework is done, before further flight, repair using a 
method approved by the Manager, New York ACO, ANE-170, FAA; or TCCA; 
or Bombardier, Inc.'s TCCA DAO.
    (2) If any damage is found: Before further flight, repair using 
a method approved by the Manager, New York ACO, ANE-170, FAA; or 
TCCA; or Bombardier, Inc.'s TCCA DAO.

(i) Terminating Action for Certain Airplanes

    For airplanes having S/Ns 4056 through 4426 inclusive: Within 
6,000 flight hours or 36 months after the effective date of this AD, 
whichever occurs first, rework the LH side and RH side nacelle A-
frame structure, including doing a measurement of the clearance 
between the A-frame structure and MLG stabilizer brace assembly and 
doing a fluorescent dye penetrant inspection or high frequency eddy 
current inspection for cracking, in accordance with ``Part B--
Rework'' of the Accomplishment Instructions of Bombardier Service 
Bulletin 84-54-20, Revision C, dated March 5, 2015. Accomplishment 
of the actions required by this paragraph terminates the repetitive 
inspections required by paragraph (h) of this AD.
    (1) If a clearance less than 0.100 inch (2.54 mm) exists between 
the A-frame structure and the MLG stabilizer brace assembly in the 
retracted position, after the rework is done, before further flight, 
repair using a method approved by the Manager, New York ACO, ANE-
170, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO.
    (2) If any cracking is found: Before further flight, repair 
using a method approved by the Manager, New York ACO, ANE-170, FAA; 
or TCCA; or Bombardier, Inc.'s TCCA DAO.

(j) Modification of MLG Stabilizer Brace Assembly

    For airplanes having S/Ns 4001 through 4431 inclusive with a MLG 
stabilizer brace assembly having part number (P/N) 46400-27 
installed: Within 6,000 flight hours or 36 months after the 
effective date of this AD, whichever occurs first, incorporate 
Bombardier ModSum 4-902416 by installing new stop brackets and a new 
shim on each MLG stabilizer brace assembly, in accordance with 
paragraph 3.B., ``Procedure,'' of the Accomplishment Instructions of 
Bombardier Service Bulletin 84-32-112, Revision C, dated April 2, 
2015; and Goodrich Service Bulletin 46400-32-102 R2, Revision 2, 
dated February 17, 2015.

(k) Rework of the Electrical Wiring Harnesses

    For airplanes having S/Ns 4001 through 4411 inclusive: Within 
6,000 flight hours or 36 months after the effective date of this AD, 
whichever occurs first, rework the LH and RH sides of the electrical 
wiring harnesses in the nacelle area adjacent to the A-frame 
structure, including doing the actions specified in paragraphs 
(k)(1) through (k)(4) of this AD, in accordance with ``Part B--
Procedure'' of the Accomplishment Instructions of Bombardier Service 
Bulletin 84-32-114, Revision B, dated February 3, 2015. If any 
damage is found on the A-frame structure or MLG stabilizer brace, 
before further flight, repair using a method approved by the 
Manager, New York ACO, ANE-170, FAA; or TCCA; or Bombardier, Inc.'s 
TCCA DAO.
    (1) Doing a detailed inspection of the conduit assembly for the 
conditions specified in Bombardier Service Bulletin 84-32-114, 
Revision B, dated February 3, 2015, and, before further flight, 
repairing if any condition is found.
    (2) Replacing damaged conduit.
    (3) Measuring the clearance between the stabilizer brace and 
electrical harness on both LH and RH nacelles to make sure there is 
0.100 inch (2.54 mm) minimum clearance between the MLG stabilizer 
brace.
    (4) Checking for damage on the A-frame structure and MLG 
stabilizer brace.

(l) Optional Installations

    (1) Installing specified fasteners on the MLG A-frame, in both 
LH and RH nacelles, in accordance with Bombardier ModSum 
IS4Q5450002, Revision B, dated June 22, 2012, is acceptable for 
compliance with the actions specified in paragraph (g)(2) of this 
AD, provided the actions specified in Bombardier ModSum IS4Q5450002 
are done within the applicable compliance time specified in 
paragraph (g) of this AD, except where ModSum IS4Q5450002, Revision 
B, dated June 22, 2012, specifies to contact Bombardier for reduced 
clearances, before further flight, repair using a method approved by 
the Manager, New York ACO, ANE-170, FAA; or TCCA; or Bombardier, 
Inc.'s TCCA DAO.
    (2) Trimming the horizontal and vertical stiffeners on the MLG 
A-frame in both LH and RH nacelles, in accordance with Bombardier 
ModSum IS4Q5450003, Revision C, dated November 29, 2012, is 
acceptable for compliance with the actions specified in paragraph 
(i) of this AD, provided the actions specified in Bombardier ModSum 
IS4Q5450003 are done within the compliance time specified in 
paragraph (i) of this AD, except where ModSum IS4Q5450003, Revision 
C, released November 29, 2012, specifies to contact Bombardier for 
reduced clearances, before further flight, repair using a method 
approved by the Manager, New York ACO, ANE-170, FAA; or TCCA; or 
Bombardier, Inc.'s TCCA DAO.
    (3) Rerouting certain electrical harnesses and installing 
grommets, in accordance with Bombardier ModSum IS4Q2400028, Revision 
B, dated December 11, 2012 (for S/Ns 4001 through 4098 inclusive); 
or Bombardier ModSum IS4Q2400029, Revision A, dated July 6, 2012 
(for S/Ns 4090 through 4411 inclusive); is acceptable for compliance 
with the actions specified in paragraph (k) of this AD, provided the 
actions specified in the applicable modsum are done within the 
compliance time specified in paragraph (k) of this AD, except where 
Bombardier ModSum IS4Q2400028, Revision B, dated December 11, 2012; 
and Bombardier ModSum IS4Q2400029, Revision A, dated July 6, 2012; 
specify to contact Bombardier to report stabilizer brace or 
structural damaged findings, before further flight, repair using a 
method approved by the Manager, New York ACO, ANE-170, FAA; or TCCA; 
or Bombardier, Inc.'s TCCA DAO.

(m) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (i) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
specified in paragraph (m)(1)(i), (m)(1)(ii), or (m)(1)(iii) of this 
AD. This service information is not incorporated by reference in 
this AD.
    (i) Bombardier Service Bulletin 84-54-20, dated April 25, 2013.
    (ii) Bombardier Service Bulletin 84-54-20, Revision A, dated 
April 9, 2014.
    (iii) Bombardier Service Bulletin 84-54-20, Revision B, dated 
October 2, 2014.
    (2) This paragraph provides credit for actions required by 
paragraph (j) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
specified in paragraph (m)(2)(i), (m)(2)(ii), (m)(2)(iii), or 
(m)(2)(iv) of this AD. This service information is not incorporated 
by reference in this AD.
    (i) Bombardier Service Bulletin 84-32-112, dated December 20, 
2012.
    (ii) Bombardier Service Bulletin 84-32-112, Revision A, dated 
April 16, 2014.
    (iii) Bombardier Service Bulletin 84-32-112, Revision B, dated 
September 12, 2014.
    (iv) Goodrich Service Bulletin 46400-32-102 R1, Revision 1, 
dated June 24, 2013.
    (3) This paragraph provides credit for actions required by 
paragraph (k) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
specified in paragraph (m)(3)(i) or (m)(3)(ii) of this AD. This 
service information is not incorporated by reference in this AD.
    (i) Bombardier Service Bulletin 84-32-114, dated June 6, 2013.
    (ii) Bombardier Service Bulletin 84-32-114, Revision A, dated 
September 18, 2013.

(n) 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 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.
    (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 Bombardier, Inc.'s TCCA DAO. If approved 
by the DAO, the approval must include the DAO-authorized signature.

[[Page 55358]]

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2014-45, dated December 
23, 2014, 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-2015-3986.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (p)(3), (p)(4), and (p)(5) of this AD.

(p) 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 ModSum IS4Q2400028, Revision B, dated December 
11, 2012. (This document has 33 pages; the first page of the modsum 
indicates that there are 32 pages.)
    (ii) Bombardier ModSum IS4Q2400029, Revision A, dated July 6, 
2012.
    (iii) Bombardier ModSum IS4Q5450002, Revision B, dated June 22, 
2012.
    (iv) Bombardier ModSum IS4Q5450003, Revision C, dated November 
29, 2012.
    (v) Bombardier Service Bulletin 84-32-112, Revision C, dated 
April 2, 2015.
    (vi) Bombardier Service Bulletin 84-32-114, Revision B, dated 
February 3, 2015.
    (vii) Bombardier Service Bulletin 84-54-19, dated April 18, 
2013.
    (viii) Bombardier Service Bulletin 84-54-20, Revision C, dated 
March 5, 2015.
    (ix) Bombardier Service Bulletin 84-54-21, dated May 9, 2013.
    (x) Goodrich Service Bulletin 46400-32-102 R2, Revision 2, dated 
February 17, 2015.
    (3) For Bombardier service information identified in this AD, 
contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt 
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; 
fax 416-375-4539; email [email protected]; Internet 
http://www.bombardier.com.
    (4) For Goodrich service information identified in this AD, 
contact Goodrich Corporation, Landing Gear, 1400 South Service Road, 
West Oakville, ON, Canada L6L 5Y7; phone: 905-825-1568; email: 
[email protected]; Internet: http://www.goodrich.com/TechPubs.
    (5) 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.
    (6) 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 August 4, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-19480 Filed 8-18-16; 8:45 am]
 BILLING CODE 4910-13-P

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