Airworthiness Directives; Bombardier, Inc. Airplanes, 38615-38617 [2015-16463]
Download as PDF
Federal Register / Vol. 80, No. 129 / Tuesday, July 7, 2015 / Rules and Regulations
https://www.regulations.gov in Docket No.
FAA–2014–0499.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6720, Tail Rotor Control
(i) 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 the AD specifies otherwise.
(i) Bell Helicopter Alert Service Bulletin
430–13–51, dated September 3, 2013.
(ii) Reserved.
(3) For Bell Helicopter Textron Canada
Limited service information identified in this
AD, contact Bell Helicopter Textron Canada
Limited, 12,800 Rue de l’Avenir, Mirabel,
Quebec J7J1R4; telephone (450) 437–2862 or
(800) 363–8023; fax (450) 433–0272; or at
https://www.bellcustomer.com/files/.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on June 24,
2015.
Bruce E. Cain,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2015–16469 Filed 7–6–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0569; Directorate
Identifier 2014–NM–047–AD; Amendment
39–18199; AD 2015–14–01]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
srobinson on DSK5SPTVN1PROD with RULES
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model DHC–8–400
series airplanes. This AD was prompted
by a report of loose bolts that are
SUMMARY:
VerDate Sep<11>2014
19:51 Jul 06, 2015
Jkt 235001
intended to secure the translating door
crank assembly to the outside handle
shaft. This AD requires a detailed
inspection for loose bolts on the aft
translating door crank assembly, and
removal and reinstallation of the bolts.
We are issuing this AD to prevent loose
bolts from falling out. If both bolts
become loose or fall out after the door
is closed and locked, the door cannot be
opened from inside or outside, which
could impede evacuation in the event of
an emergency.
DATES: This AD becomes effective
August 11, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 11, 2015.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0569; or in
person at the 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.
For service information identified in
this AD, contact Bombardier, Inc., QSeries 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. 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–2014–
0569.
FOR FURTHER INFORMATION CONTACT:
Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone 516–228–7318; 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 series airplanes. The NPRM
published in the Federal Register on
August 15, 2014 (79 FR 48105). The
NPRM was prompted by a report of
loose bolts that are intended to secure
the translating door crank assembly to
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38615
the outside handle shaft. The NPRM
proposed to require a detailed
inspection for loose bolts on the aft
translating door crank assembly, and
removal and reinstallation of the bolts.
We are issuing this AD to prevent loose
bolts from falling out. If both bolts
become loose or fall out after the door
is closed and locked, the door cannot be
opened from inside or outside, which
could impede evacuation in the event of
an emergency.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2014–08,
dated February 10, 2014 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
There was one in-service report where the
bolts securing the translating door crank
assembly to the outside handle shaft were
found loose. It was also found on another
translating door that sealant was missing on
these bolts. If both bolts become loose or fall
out after the door is closed and locked, the
door cannot be opened from inside or
outside.
The aft entry translating door and aft
service translating door are classified as
emergency exits. The inability to open an
emergency exit could impede evacuation in
the event of an emergency.
This [Canadian] AD mandates the
inspection of the translating door crank
assemblies for loose bolts, as well as
appropriate rectification [removal and
reinstallation of the bolts].
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-05690002.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comment received.
The following presents the comment
received on the NPRM (79 FR 48105,
August 15, 2014), and the FAA’s
response to the comment.
Request To Remove Certain
Requirements From the NPRM (79 FR
48105, August 15, 2014)
Horizon Air requested that the job setup and close-out procedures included in
Part A–INSPECTION, and Part B–
RECTIFICATION, of the
Accomplishment Instructions of
Bombardier Service Bulletin 84–52–75,
Revision A, dated July 11, 2013, be
removed as requirements in the NPRM
(79 FR 48105, August 15, 2014). The
commenter noted that only the
procedures included in paragraph B.
E:\FR\FM\07JYR1.SGM
07JYR1
srobinson on DSK5SPTVN1PROD with RULES
38616
Federal Register / Vol. 80, No. 129 / Tuesday, July 7, 2015 / Rules and Regulations
Procedure, of Part A and Part B of the
Accomplishment Instructions of
Bombardier Service Bulletin 84–52–75,
Revision A, dated July 11, 2013, provide
corrective actions to address the unsafe
condition. The commenter stated that
the job set-up and close-out procedures
do not directly correct the unsafe
condition and restrict an operators’
ability to perform maintenance in
conjunction with the detailed
inspection that would be required by
the proposed AD.
We partially agree with the
commenter’s request. We agree to
remove the job set-up procedures and
most of the steps in the job close-out
procedures from this AD because those
actions do not directly correct the
unsafe condition. We have revised
paragraph (g) of this AD to specify that
the inspection must be done in
accordance with paragraph 3.B.,
‘‘Procedure,’’ of Part A—INSPECTION,
of the Accomplishment Instructions of
Bombardier Service Bulletin 84–52–75,
Revision A, dated July 11, 2013.
We have also revised paragraphs (g)(1)
and (g)(2) of this AD to specify that the
corrective actions must be done in
accordance with paragraph 3.B.,
‘‘Procedure,’’ and steps 3.C.(4) and
3.C.(5) of paragraph 3.C., ‘‘Close Out,’’
of Part B—RECTIFICATION, of the
Accomplishment Instructions of
Bombardier Service Bulletin 84–52–75,
Revision A, dated July 11, 2013. The
intent of this final rule is to ensure that
the aft entry translating door and aft
service translating door are correctly
installed. Therefore, we consider the
operational tests in steps 3.C.(4) and
3.C.(5) of paragraph 3.C., ‘‘Close Out,’’
of Part B—RECTIFICATION, of the
Accomplishment Instructions of
Bombardier Service Bulletin 84–52–75,
Revision A, dated July 11, 2013, to be
required actions to ensure that these
doors operate properly. If maintenance
is done concurrently with the required
detailed inspection, it should not affect
an operator’s ability to return the
aircraft to service. If the required
detailed inspection cannot be completed
because the airplane is undergoing
maintenance, then the actions required
by this AD can be accomplished just
prior to the airplane being returned to
service. Concurrently performing
maintenance and doing the actions
required by this AD should not cause a
delay in an airplane’s return to service.
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
VerDate Sep<11>2014
19:51 Jul 06, 2015
Jkt 235001
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
48105, August 15, 2014) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 48105,
August 15, 2014).
Related Service Information Under 1
CFR Part 51
We reviewed Bombardier Service
Bulletin 84–52–75, Revision A, dated
July 11, 2013. This service information
describes procedures for a detailed
inspection for loose bolts on the aft
translating door crank assembly, and
removal and reinstallation of the bolts.
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 of
this AD.
Costs of Compliance
We estimate that this AD affects 82
airplanes of U.S. registry.
We also estimate that it will take
about 7 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
about $0 per product. Based on these
figures, we estimate the cost of this AD
on U.S. operators to be $48,790, or $595
per product.
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
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Fmt 4700
Sfmt 4700
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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/#!docketDetail;D=
FAA-2014-0569; 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 Operations office (telephone
800–647–5527) is in the ADDRESSES
section.
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
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2015–14–01 Bombardier, Inc.: Amendment
39–18199. Docket No. FAA–2014–0569;
Directorate Identifier 2014–NM–047–AD.
(a) Effective Date
This AD becomes effective August 11,
2015.
(b) Affected ADs
None.
E:\FR\FM\07JYR1.SGM
07JYR1
Federal Register / Vol. 80, No. 129 / Tuesday, July 7, 2015 / Rules and Regulations
(c) Applicability
This AD applies to Bombardier, Inc. Model
DHC–8–400, –401, and –402 airplanes,
certificated in any category, serial numbers
4001 through 4411 inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 52, Doors.
(e) Reason
This AD was prompted by a report of loose
bolts that are intended to secure the
translating door crank assembly to the
outside handle shaft. We are issuing this AD
to prevent loose bolts from falling out. If both
bolts become loose or fall out after the door
is closed and locked, the door cannot be
opened from inside or outside, which could
impede evacuation in the event of an
emergency.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
srobinson on DSK5SPTVN1PROD with RULES
(g) Inspection and Corrective Actions
Within 600 flight hours or 100 days,
whichever occurs first after the effective date
of this AD: Do a detailed inspection of the
aft translating door crank assembly for loose
bolts, in accordance with paragraph 3.B.,
‘‘Procedure,’’ of Part A—INSPECTION, of the
Accomplishment Instructions of Bombardier
Service Bulletin 84–52–75, Revision A, dated
July 11, 2013. Doing the applicable actions
specified in paragraph (g)(1) or (g)(2) of this
AD terminates the requirements of this
paragraph.
(1) If any loose bolt is found: Before further
flight, remove and reinstall the translating
door crank assembly bolt, in accordance with
paragraph 3.B., ‘‘Procedure,’’ and steps
3.C.(4) and 3.C.(5) of paragraph 3.C., ‘‘Close
Out,’’ of Part B—RECTIFICATION, of the
Accomplishment Instructions of Bombardier
Service Bulletin 84–52–75, Revision A, dated
July 11, 2013.
(2) If no loose bolt is found: Within 6,000
flight hours or 36 months, whichever occurs
first after the effective date of this AD,
remove and reinstall the translating door
crank assembly bolts, in accordance with
paragraph 3.B., ‘‘Procedure,’’ and steps
3.C.(4) and 3.C.(5) of paragraph 3.C., ‘‘Close
Out,’’ of Part B—RECTIFICATION, of the
Accomplishment Instructions of Bombardier
Service Bulletin 84–52–75, Revision A, dated
July 11, 2013.
(h) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g), (g)(1), and (g)(2)
of this AD, if those actions were performed
before the effective date of this AD using
Bombardier Service Bulletin 84–52–75, dated
July 27, 2012, which is not incorporated by
reference in this AD.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), ANE–170, FAA,
has the authority to approve AMOCs for this
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19:51 Jul 06, 2015
Jkt 235001
38617
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. The AMOC
approval letter must specifically reference
this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
Transport Canada Civil Aviation (TCCA), or
Bombardier, Inc.’s TCCA Design Approval
Organization (DAO). If approved by the DAO,
the approval must include the DAOauthorized signature.
Issued in Renton, Washington, on June 25,
2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
(j) Related Information
SUMMARY:
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2014–08, dated
February 10, 2014. This MCAI may be found
in the AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-0569-0002.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Bombardier Service Bulletin 84–52–75,
Revision A, dated July 11, 2013.
(ii) Reserved.
(3) For 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) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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[FR Doc. 2015–16463 Filed 7–6–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2434; Directorate
Identifier 2015–CE–023–AD; Amendment
39–18196; AD 2015–13–09]
RIN 2120–AA64
Airworthiness Directives; Piper
Aircraft, Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Piper Aircraft, Inc. Models PA–46–350P
and PA–46–500TP airplanes. This AD
requires installing cable ties around the
cabin altitude encoder and the
supporting structure, adding threadlocking compound to the threads of the
existing single fastener; and repetitively
inspecting the cable ties and the fastener
to ensure security and proper condition.
This AD was prompted by a report that
a cabin altitude encoder came free from
its mounting bracket, which interfered
with motion of the elevator flight
control. We are issuing this AD to
correct the unsafe condition on these
products.
This AD is effective July 13,
2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 13, 2015.
We must receive comments on this
AD by August 21, 2015.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
DATES:
E:\FR\FM\07JYR1.SGM
07JYR1
Agencies
[Federal Register Volume 80, Number 129 (Tuesday, July 7, 2015)]
[Rules and Regulations]
[Pages 38615-38617]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-16463]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0569; Directorate Identifier 2014-NM-047-AD;
Amendment 39-18199; AD 2015-14-01]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted
by a report of loose bolts that are intended to secure the translating
door crank assembly to the outside handle shaft. This AD requires a
detailed inspection for loose bolts on the aft translating door crank
assembly, and removal and reinstallation of the bolts. We are issuing
this AD to prevent loose bolts from falling out. If both bolts become
loose or fall out after the door is closed and locked, the door cannot
be opened from inside or outside, which could impede evacuation in the
event of an emergency.
DATES: This AD becomes effective August 11, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 11,
2015.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0569; or in person at the
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.
For 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. 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-2014-
0569.
FOR FURTHER INFORMATION CONTACT: Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516-228-7318; 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 series airplanes. The NPRM published in the Federal
Register on August 15, 2014 (79 FR 48105). The NPRM was prompted by a
report of loose bolts that are intended to secure the translating door
crank assembly to the outside handle shaft. The NPRM proposed to
require a detailed inspection for loose bolts on the aft translating
door crank assembly, and removal and reinstallation of the bolts. We
are issuing this AD to prevent loose bolts from falling out. If both
bolts become loose or fall out after the door is closed and locked, the
door cannot be opened from inside or outside, which could impede
evacuation in the event of an emergency.
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2014-08, dated February 10, 2014 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for the specified products. The MCAI
states:
There was one in-service report where the bolts securing the
translating door crank assembly to the outside handle shaft were
found loose. It was also found on another translating door that
sealant was missing on these bolts. If both bolts become loose or
fall out after the door is closed and locked, the door cannot be
opened from inside or outside.
The aft entry translating door and aft service translating door
are classified as emergency exits. The inability to open an
emergency exit could impede evacuation in the event of an emergency.
This [Canadian] AD mandates the inspection of the translating
door crank assemblies for loose bolts, as well as appropriate
rectification [removal and reinstallation of the bolts].
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0569-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We have considered the comment received. The following
presents the comment received on the NPRM (79 FR 48105, August 15,
2014), and the FAA's response to the comment.
Request To Remove Certain Requirements From the NPRM (79 FR 48105,
August 15, 2014)
Horizon Air requested that the job set-up and close-out procedures
included in Part A-INSPECTION, and Part B-RECTIFICATION, of the
Accomplishment Instructions of Bombardier Service Bulletin 84-52-75,
Revision A, dated July 11, 2013, be removed as requirements in the NPRM
(79 FR 48105, August 15, 2014). The commenter noted that only the
procedures included in paragraph B.
[[Page 38616]]
Procedure, of Part A and Part B of the Accomplishment Instructions of
Bombardier Service Bulletin 84-52-75, Revision A, dated July 11, 2013,
provide corrective actions to address the unsafe condition. The
commenter stated that the job set-up and close-out procedures do not
directly correct the unsafe condition and restrict an operators'
ability to perform maintenance in conjunction with the detailed
inspection that would be required by the proposed AD.
We partially agree with the commenter's request. We agree to remove
the job set-up procedures and most of the steps in the job close-out
procedures from this AD because those actions do not directly correct
the unsafe condition. We have revised paragraph (g) of this AD to
specify that the inspection must be done in accordance with paragraph
3.B., ``Procedure,'' of Part A--INSPECTION, of the Accomplishment
Instructions of Bombardier Service Bulletin 84-52-75, Revision A, dated
July 11, 2013.
We have also revised paragraphs (g)(1) and (g)(2) of this AD to
specify that the corrective actions must be done in accordance with
paragraph 3.B., ``Procedure,'' and steps 3.C.(4) and 3.C.(5) of
paragraph 3.C., ``Close Out,'' of Part B--RECTIFICATION, of the
Accomplishment Instructions of Bombardier Service Bulletin 84-52-75,
Revision A, dated July 11, 2013. The intent of this final rule is to
ensure that the aft entry translating door and aft service translating
door are correctly installed. Therefore, we consider the operational
tests in steps 3.C.(4) and 3.C.(5) of paragraph 3.C., ``Close Out,'' of
Part B--RECTIFICATION, of the Accomplishment Instructions of Bombardier
Service Bulletin 84-52-75, Revision A, dated July 11, 2013, to be
required actions to ensure that these doors operate properly. If
maintenance is done concurrently with the required detailed inspection,
it should not affect an operator's ability to return the aircraft to
service. If the required detailed inspection cannot be completed
because the airplane is undergoing maintenance, then the actions
required by this AD can be accomplished just prior to the airplane
being returned to service. Concurrently performing maintenance and
doing the actions required by this AD should not cause a delay in an
airplane's return to service.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this AD as proposed except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 48105, August 15, 2014) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 48105, August 15, 2014).
Related Service Information Under 1 CFR Part 51
We reviewed Bombardier Service Bulletin 84-52-75, Revision A, dated
July 11, 2013. This service information describes procedures for a
detailed inspection for loose bolts on the aft translating door crank
assembly, and removal and reinstallation of the bolts. 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 of this AD.
Costs of Compliance
We estimate that this AD affects 82 airplanes of U.S. registry.
We also estimate that it will take about 7 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 about $0 per
product. Based on these figures, we estimate the cost of this AD on
U.S. operators to be $48,790, or $595 per product.
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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D= FAA-2014-0569; 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 Operations office
(telephone 800-647-5527) is in the ADDRESSES section.
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):
2015-14-01 Bombardier, Inc.: Amendment 39-18199. Docket No. FAA-
2014-0569; Directorate Identifier 2014-NM-047-AD.
(a) Effective Date
This AD becomes effective August 11, 2015.
(b) Affected ADs
None.
[[Page 38617]]
(c) Applicability
This AD applies to Bombardier, Inc. Model DHC-8-400, -401, and -
402 airplanes, certificated in any category, serial numbers 4001
through 4411 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 52, Doors.
(e) Reason
This AD was prompted by a report of loose bolts that are
intended to secure the translating door crank assembly to the
outside handle shaft. We are issuing this AD to prevent loose bolts
from falling out. If both bolts become loose or fall out after the
door is closed and locked, the door cannot be opened from inside or
outside, which could impede evacuation in the event of an emergency.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection and Corrective Actions
Within 600 flight hours or 100 days, whichever occurs first
after the effective date of this AD: Do a detailed inspection of the
aft translating door crank assembly for loose bolts, in accordance
with paragraph 3.B., ``Procedure,'' of Part A--INSPECTION, of the
Accomplishment Instructions of Bombardier Service Bulletin 84-52-75,
Revision A, dated July 11, 2013. Doing the applicable actions
specified in paragraph (g)(1) or (g)(2) of this AD terminates the
requirements of this paragraph.
(1) If any loose bolt is found: Before further flight, remove
and reinstall the translating door crank assembly bolt, in
accordance with paragraph 3.B., ``Procedure,'' and steps 3.C.(4) and
3.C.(5) of paragraph 3.C., ``Close Out,'' of Part B--RECTIFICATION,
of the Accomplishment Instructions of Bombardier Service Bulletin
84-52-75, Revision A, dated July 11, 2013.
(2) If no loose bolt is found: Within 6,000 flight hours or 36
months, whichever occurs first after the effective date of this AD,
remove and reinstall the translating door crank assembly bolts, in
accordance with paragraph 3.B., ``Procedure,'' and steps 3.C.(4) and
3.C.(5) of paragraph 3.C., ``Close Out,'' of Part B--RECTIFICATION,
of the Accomplishment Instructions of Bombardier Service Bulletin
84-52-75, Revision A, dated July 11, 2013.
(h) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g), (g)(1), and (g)(2) of this AD, if those actions were
performed before the effective date of this AD using Bombardier
Service Bulletin 84-52-75, dated July 27, 2012, which is not
incorporated by reference in this AD.
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office (ACO), ANE-170, FAA, has the
authority to approve AMOCs for this 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. The AMOC approval letter must specifically reference this
AD.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or Transport
Canada Civil Aviation (TCCA), or Bombardier, Inc.'s TCCA Design
Approval Organization (DAO). If approved by the DAO, the approval
must include the DAO-authorized signature.
(j) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directive CF-2014-08, dated February
10, 2014. This MCAI may be found in the AD docket on the Internet at
https://www.regulations.gov/#!documentDetail;D=FAA-2014-0569-0002.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Bombardier Service Bulletin 84-52-75, Revision A, dated July
11, 2013.
(ii) Reserved.
(3) For 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) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on June 25, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-16463 Filed 7-6-15; 8:45 am]
BILLING CODE 4910-13-P