Airworthiness Directives; Bombardier, Inc. Airplanes, 55353-55358 [2016-19480]
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Federal Register / Vol. 81, No. 161 / Friday, August 19, 2016 / Rules and Regulations
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their comment on special conditions no.
25–612–SC. We provided a detailed
response in special conditions no. 25–
612–SC and have now clearly defined
the applicability for these Boeing 737–
8 special conditions. One aspect of
Boeing’s comment that we did not
address in special conditions no. 25–
612–SC is that some design changes
may not change a lithium battery
installation but affect it, which results
in these special conditions being
applicable. For example, adding a heat
source next to a lithium battery can
increase its possibility of entering into
thermal runaway. Lithium battery
installations affected by design changes
must meet these special conditions.
Some examples of changes that affect
lithium battery installations are those
that:
• Increase the temperatures or
pressures in a battery,
• Increase the electrical load on a
battery,
• Increase potential for imbalance
between battery cells,
• Modify protective circuitry for a
lithium battery,
• Increase the airplane level risk due
to the location of an existing lithium
battery. An example is installation of a
new oxygen line next to an existing part
that has a lithium battery. The airplane
level risk may increase due to the
potential hazard of a lithium battery fire
in the proximity of oxygen.
The FAA has determined that
‘‘uncontrolled’’ in special condition 2
should be ‘‘uncontrollable’’ to more
accurately describe the concern. This
revision does not change the intended
meaning of this special condition.
Except as discussed above, the special
conditions are adopted as proposed.
Applicability
As discussed above, these special
conditions are applicable to the Model
737–8 airplane. Should the applicant
apply at a later date for a change to the
type certificate to include another
model incorporating the same novel or
unusual design feature, or should any
other model already included on the
same type certificate be modified to
incorporate the same novel or unusual
design feature, these special conditions
would apply to that model as well.
These special conditions are only
applicable to design changes applied for
after the effective date of the special
conditions. The existing airplane fleet
and follow-on deliveries of airplanes
with previously certified nonrechargeable lithium battery
installations are not affected.
These special conditions are not
applicable to previously certified non-
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rechargeable lithium battery
installations where the only change is
either cosmetic or relocating the
installation to improve the safety of the
airplane and occupants. The FAA
determined that this exclusion is in the
public interest because the need to meet
all of the special conditions might
otherwise deter such design changes
that involve relocating batteries. A
cosmetic change is a change in
appearance only, and does not change
any function or safety characteristic of
the battery installation.
Conclusion
This action affects only certain novel
or unusual design features on one model
of airplane. It is not a rule of general
applicability.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
■ The authority citation for these
special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Special Conditions
Accordingly, the following special
conditions are part of the type
certification basis for the Boeing Model
737–8 airplane.
Non-Rechargeable Lithium Battery
Installations
In lieu of § 25.1353(b)(1) through
(b)(4) at Amendment 25–123, each nonrechargeable lithium battery installation
must:
1. Maintain safe cell temperatures and
pressures under all foreseeable
operating conditions to prevent fire and
explosion.
2. Prevent the occurrence of selfsustaining, uncontrollable increases in
temperature or pressure.
3. Not emit explosive or toxic gases,
either in normal operation or as a result
of its failure, that may accumulate in
hazardous quantities within the
airplane.
4. Meet the requirements of § 25.863.
5. Not damage surrounding structure
or adjacent systems, equipment, or
electrical wiring from corrosive fluids or
gases that may escape in such a way as
to cause a major or more-severe failure
condition.
6. Have provisions to prevent any
hazardous effect on airplane structure or
systems caused by the maximum
amount of heat it can generate due to
any failure of it or its individual cells.
7. Have a failure sensing and warning
system to alert the flightcrew if its
failure affects safe operation of the
airplane.
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55353
8. Have a means for the flightcrew or
maintenance personnel to determine the
battery charge state if the battery’s
function is required for safe operation of
the airplane.
Note: A battery system consists of the
battery and any protective, monitoring, and
alerting circuitry or hardware inside or
outside of the battery. It also includes vents
(where necessary) and packaging. For the
purpose of these special conditions, a
‘‘battery’’ and ‘‘battery system’’ are referred to
as a battery.
Issued in Renton, Washington, on August
12, 2016.
Michael Kaszycki,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–19856 Filed 8–18–16; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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 Aframe 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
SUMMARY:
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Federal Register / Vol. 81, No. 161 / Friday, August 19, 2016 / Rules and Regulations
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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
thd.qseries@aero.bombardier.com;
Internet https://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: jean.breed@goodrich.com;
Internet: https://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 https://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 https://
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.
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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 Aframe 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 Aframe 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 Aframe 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
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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.
• 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.
• Rework of the left-hand (LH) side
and right-hand (RH) side nacelle Aframe 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.
• Repetitive detailed inspections of
the nacelle A-frame structure and the
MLG stabilizer brace for insufficient
clearance and damage, and repair if
necessary.
• 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.
• Installation of new stop brackets
and a shim on each MLG stabilizer brace
assembly.
• 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 https://
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.
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Federal Register / Vol. 81, No. 161 / Friday, August 19, 2016 / Rules and Regulations
address the unsafe condition; therefore,
there are no changes necessary in those
paragraphs in this regard. However, we
Horizon Air asked that the following
revised service information be included have revised paragraph (k) of this AD to
specify doing only the actions provided
in the proposed AD for the applicable
in ‘‘Part B—Procedure,’’ of the
actions:
• Bombardier Service Bulletin 84–54– Accomplishment Instructions of
Bombardier Service Bulletin 84–32–114,
20, Revision C, dated March 5, 2015.
• Bombardier Service Bulletin 84–32– Revision B, dated February 3, 2015, for
the required actions specified in that
112, Revision C, dated April 2, 2015.
• Bombardier Service Bulletin 84–32– paragraph.
114, Revision B, dated February 3, 2015. Request To Clarify a Certain Reference
• Goodrich Service Bulletin 46400–
Horizon Air asked that we revise the
32–102 R2, Revision 2, dated February
paragraph references in paragraph (l)(1)
17, 2015.
of the proposed AD for clarity. Horizon
Horizon Air pointed out that several
Air stated that paragraph (l)(1) of the
of the service documents specified in
proposed AD refers to Bombardier
the proposed AD have been updated,
ModSum IS4Q5450002, Revision B,
and asserted that the proposed AD
dated June 22, 2012, as acceptable for
should be revised to reference the
compliance with the actions specified in
updated service information. Horizon
paragraph (g) of the proposed AD.
Air also asked that credit be given for
Horizon Air noted that for greater
actions done using the previous
clarity, the reference should be to
revisions of the revised service
paragraph (g)(2) of the proposed AD.
information.
We agree with the commenter’s
We agree with the commenter’s
request for the reasons provided. We
requests. No new work is specified by
have changed paragraph (l)(1) of this AD
the revised service information;
to specify that installing specified
therefore, we have revised the ‘‘Related
fasteners on the MLG A-frame, in both
Service Information under 1 CFR part
LH and RH nacelles, in accordance with
51’’ section and the applicable
Bombardier ModSum IS4Q5450002,
requirements of this AD to refer to the
Revision B, dated June 22, 2012, is
updated service information. We have
acceptable for compliance with the
also revised paragraph (m) of this AD to
actions specified in paragraph (g)(2) of
provide credit for certain actions
this AD.
required by this AD, if those actions
were performed before the effective date Conclusion
of this AD using earlier revisions of the
We reviewed the relevant data,
service information identified
considered the comments received, and
previously.
determined that air safety and the
public interest require adopting this AD
Request To Omit Job Set-Up and Close
with the changes described previously
Out Actions
and minor editorial changes. We have
Horizon Air asked that we not
determined that these minor changes:
mandate the ‘‘Job Set-up’’ and ‘‘Close
• Are consistent with the intent that
Out’’ sections of the Accomplishment
was proposed in the NPRM for
Instructions of certain service
correcting the unsafe condition; and
information referenced in the NPRM.
• Do not add any additional burden
Horizon Air stated that these
upon the public than was already
instructions do not directly correct the
proposed in the NPRM.
unsafe condition, but they do restrict an
We also determined that these
operator’s ability to perform other
changes will not increase the economic
maintenance in conjunction with the
burden on any operator or increase the
instructions that correct the unsafe
scope of this AD.
condition. Horizon Air added that only
Related Service Information Under
the section in the Accomplishment
1 CFR Part 51
Instructions that directly corrects the
unsafe condition should be required.
Bombardier has issued the following
We agree with the commenter’s
service information.
request to exclude the ‘‘Job Set-up’’ and
• ModSum IS4Q2400028, Revision B,
‘‘Close Out’’ sections of the
dated December 11, 2012; and ModSum
Accomplishment Instructions of certain IS4Q2400029, Revision A, dated July 6,
service information identified in this
2012. These modsums describe
AD. Paragraphs (g), (h), (i), and (j) of this procedures for rerouting certain
AD already identify the specific sections electrical harnesses and installing
of the Accomplishment Instructions of
grommets.
• ModSum IS4Q5450002, Revision B,
the applicable service information for
dated June 22, 2012. This modsum
doing only the actions that directly
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Request To Incorporate Revised Service
Information and Provide Credit
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describes procedures for installing
specified fasteners on the MLG A-frame,
in both the LH and RH nacelles.
• 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.
• 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.
• 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.
• 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.
• Service Bulletin 84–54–20, Revision
C, dated March 5, 2015. This service
information describes procedures for
detailed inspections of the nacelle Aframe 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.
• 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/Aframe structure and MLG stabilizer
brace assembly and to make sure no
fouling condition exists, and repair.
Goodrich has issued the following
service information.
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• 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.
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.
jstallworth on DSK7TPTVN1PROD with RULES
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;
14:10 Aug 18, 2016
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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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
Authority for This Rulemaking
VerDate Sep<11>2014
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.
[Amended]
2. The FAA amends § 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.
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(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
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Federal Register / Vol. 81, No. 161 / Friday, August 19, 2016 / Rules and Regulations
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.
jstallworth on DSK7TPTVN1PROD with RULES
(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
VerDate Sep<11>2014
14:10 Aug 18, 2016
Jkt 238001
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.
PO 00000
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Fmt 4700
Sfmt 4700
55357
(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.
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Federal Register / Vol. 81, No. 161 / Friday, August 19, 2016 / Rules and Regulations
(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 https://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.
jstallworth on DSK7TPTVN1PROD with RULES
(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
thd.qseries@aero.bombardier.com; Internet
https://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:
jean.breed@goodrich.com; Internet: https://
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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
VerDate Sep<11>2014
14:10 Aug 18, 2016
Jkt 238001
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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–4226; Directorate
Identifier 2015–NM–095–AD; Amendment
39–18616; AD 2016–17–03]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2003–25–
07 for certain Airbus Model A319 and
A320 series airplanes, and AD 2005–13–
39 for certain Airbus Model A321 series
airplanes. AD 2003–25–07 required a
revision to the airplane flight manual
(AFM) and replacement of both elevator
aileron computers (ELACs) having L80
standards with new ELACs having L81
standards. AD 2005–13–39 required a
revision to the AFM, replacement of
existing ELACs with ELACs having L83
or L91 standards, as applicable; and a
concurrent action. Since we issued AD
2003–25–07 and AD 2005–13–39, we
have determined that new ELAC
standards must be incorporated. The
ELAC standards have been upgraded to
version L97+, which implements
enhanced angle-of-attack (AOA)
monitoring to better detect AOA
blockage, including multiple AOA
blockages. This AD requires replacing
existing ELACs with new ELACs having
L97+ standards or revising the software
in an existing ELAC to the L97+
standards, as applicable, which
terminates the requirements of AD
2003–25–07 and AD 2005–13–39. This
AD also expands the applicability to
include all Airbus Model A318, A319,
A320, and A321 series airplanes. We are
issuing this AD to prevent inadvertent
activation of the AOA protections.
Inadvertent activation of the AOA
protections could result in a continuous
nose-down pitch rate that could result
in reduced controllability of the
airplane.
DATES: This AD is effective September
23, 2016.
SUMMARY:
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 23, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 9, 2005 (70 FR 38580, July
5, 2005).
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of January 22, 2004 (68 FR
70431, December 18, 2003).
ADDRESSES: For service information
identified in this final rule, contact
Airbus, Airworthiness Office—EIAS, 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5
61 93 36 96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
4226.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
4226; 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 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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2003–25–07,
Amendment 39–13390 (68 FR 70431,
December 18, 2003) (‘‘AD 2003–25–
07’’); and AD 2005–13–39, Amendment
E:\FR\FM\19AUR1.SGM
19AUR1
]]>Agencies
[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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 thd.qseries@aero.bombardier.com; Internet
https://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: jean.breed@goodrich.com; Internet: https://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 https://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 https://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.
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.
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.
Repetitive detailed inspections of the nacelle A-frame
structure and the MLG stabilizer brace for insufficient clearance and
damage, and repair if necessary.
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.
Installation of new stop brackets and a shim on each MLG
stabilizer brace assembly.
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 https://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:
Bombardier Service Bulletin 84-54-20, Revision C, dated
March 5, 2015.
Bombardier Service Bulletin 84-32-112, Revision C, dated
April 2, 2015.
Bombardier Service Bulletin 84-32-114, Revision B, dated
February 3, 2015.
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:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
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.
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.
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.
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.
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.
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.
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.
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.
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]]
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 https://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 thd.qseries@aero.bombardier.com; Internet
https://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:
jean.breed@goodrich.com; Internet: https://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: https://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
