Airworthiness Directives; Bombardier, Inc. Airplanes, 51050-51053 [2013-19157]
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2013–16–07 Eurocopter France Helicopters:
Amendment 39–17545; Docket No.
FAA–2013–0353; Directorate Identifier
2008–SW–029–AD.
(a) Applicability
This AD applies to Eurocopter France
(Eurocopter) models AS332C, AS332L,
AS332L1, AS332L2, and EC225LP
helicopters, serial numbers (S/N) up to and
including 2680 and S/N 9000 through 9009,
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as
interference between the tail gearbox (TGB)
attachment bolt and the structure fitting. This
condition could result in insufficient
tightening of the TGB casing, damage to the
TGB attachment, cracking under the
attachment bolt, loss of the TGB and
consequently, loss of helicopter control.
(c) Effective Date
This AD becomes effective September 24,
2013.
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(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
Within 50 hours time-in-service (TIS):
(1) Inspect the TGB aft attachment fitting
to measure the dimension for a blind hole as
follows:
(i) Remove the TGB attachment bolt (c) but
retain washer (d) as depicted in Detail A,
Figure 1, of Eurocopter Emergency Alert
Service Bulletin (EASB) No. 53.01.58 and
EASB No. 53A012, both Revision 1, and both
dated January 4, 2008.
(ii) Use a depth gauge to measure
dimension ‘‘x’’ between the top face of the
washer (d) and the bottom of aft fitting (a) as
depicted in Detail A, Figure 1, of the EASB.
(2) If the measurement is equal to or greater
than 81 mm, then the blind hole is present.
Install the TGB attachment bolt (c) with its
washer (d) as depicted in Detail A, Figure 1,
of EASB No. 53.01.58 or No. 53A012. Lock
with lockwire.
(3) If the measurement is less than 81 mm,
then the blind hole is missing. Inspect the
end of the threaded section of bolt (c) for
chafing or a contact mark, as depicted in
Area 1, Figure 1, of the EASB.
(i) If there is no chafing and no contact
marks, install bolt (c) with washer (d) and
additional washer (2) as depicted in Detail B,
Figure 1, of EASB No. 53.01.58 or No.
53A012.
(ii) If there is chafing or a contact mark,
replace the TGB attachment bolt (c) with an
airworthy bolt and install with washer (d)
and additional washer (2) as depicted in
Detail B, Figure 1, of EASB No. 53.01.58 or
No. 53A012. Lock with lockwire.
(iii) Within the next 825 hours TIS, replace
the TGB aft attachment fitting with an
airworthy attachment fitting.
(4) Inspect the right and left attachment
points of the TGB forward attachment to
measure the dimension for a blind hole, as
follows:
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(i) Remove both TGB attachment bolts (c)
but retain washers (d), as depicted in Detail
A, Figure 2, of EASB No. 53.01.58 or No.
53A012.
(ii) Use a depth gauge to measure
dimension ‘‘x’’ between the top face of
washer (d) and the bottom of forward fitting
(b) at the right and left attachment points, as
depicted in Detail A, Figure 2, of EASB No.
53.01.58 or No. 53A012.
(5) If both measurements are equal to or
greater than 81 mm, then the blind hole is
present. Install TGB attachment bolt (c) with
its washer (d), as depicted in Detail A, Figure
2, of EASB No. 53.01.58 or No. 53A012. Lock
with lockwire.
(6) If one or both measurements are less
than 81 mm, then the blind hole is missing.
Inspect the end of the threaded section of
each bolt (c) for chafing or a contact mark,
as depicted in Area 1, Figure 2 of EASB No.
53.01.58 or No. 53A012.
(i) If there is no chafing and no contact
marks, for each attachment point, install bolt
(c) with washer (d) and additional washer (2),
as depicted in Detail B, Figure 2, of EASB No.
53.01.58 or No. 53A012.
(ii) If there is chafing or a contact mark,
replace each the TGB attachment bolt (c)
with an airworthy bolt and install bolt (1)
with washer (d) and additional washer (2), as
depicted in Detail B, Figure 2, of EASB No.
53.01.58 or No. 53A012. Lock with lockwire.
(iii) Within the next 825 hours TIS, replace
the TGB forward attachment fitting with an
airworthy attachment fitting.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Gary Roach,
Aviation Safety Engineer, Regulations and
Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, TX 76137;
telephone (817) 222–5110; email
gary.b.roach@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
(g) Additional Information
The subject of this AD is addressed in the
´ ´
Direction Generale de L’Aviation Civile
(DGAC) France AD No F–2007–027, dated
January 2, 2008. You may view the DGAC AD
in the AD Docket on the Internet at https://
www.regulations.gov.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6520, Tail Rotor Gearbox.
(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.
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(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Eurocopter EASB No. 53.01.58, Revision
1, dated January 4, 2008.
(ii) Eurocopter EASB No. 53A012, Revision
1, dated January 4, 2008.
Note 1 to paragraph (i)(2): Eurocopter
EASB No. 53.01.58 and No. 53A012, both
Revision 1, and both dated January 4, 2008,
are co-published as one document along with
Eurocopter EASB No. 53.00.58 and No.
53A011, also both Revision 1, and both dated
January 4, 2008, which are not incorporated
by reference in this AD.
(3) For Eurocopter service information
identified in this AD, contact American
Eurocopter Corporation, 2701 N. Forum
Drive, Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax (972)
641–3775; or at https://www.eurocopter.com/
techpub.
(4) You may view this service information
that is incorporated by reference in the AD
Docket on the Internet at https://
www.regulations.gov.
(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 July 31,
2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2013–19159 Filed 8–19–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0297; Directorate
Identifier 2012–NM–205–AD; Amendment
39–17550; AD 2013–16–12]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model DHC–8–102,
–103, and –106 airplanes. This AD was
prompted by a report of cracking in a
lower longeron in a nacelle. This AD
requires repetitive inspections for
cracking of the lower longerons in the
nacelles, and replacement with new
longerons or repair if necessary.
SUMMARY:
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Additionally, this AD specifies an
optional terminating action. We are
issuing this AD to detect and correct
such cracking, which could result in
degradation of the structural integrity of
the nacelle and possible collapse of the
main landing gear (MLG).
DATES: This AD becomes effective
September 24, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 24, 2013.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Jeffrey Zimmer, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
New York 11590; telephone (516) 228–
7306; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
Part 39 to include an AD that would
apply to the specified products. The
NPRM was published in the Federal
Register on April 9, 2013 (78 FR 21079).
The NPRM proposed to correct an
unsafe condition for the specified
products. Transport Canada Civil
Aviation (TCCA), which is the aviation
authority for Canada, has issued
Canadian Airworthiness Directive CF–
2012–27, dated November 2, 2012
(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 has been one in-service report where
a nacelle lower longeron was found to be
cracked during a routine maintenance
inspection. The investigation determined that
the crack initiated from the right-hand side
(RHS) drain hole. Fatigue testing has
indicated that both the RHS and left-hand
side (LHS) longerons are vulnerable to fatigue
cracking. Failure of the nacelle lower
longeron would result in a degradation of the
structural integrity of the nacelle and could
potentially lead to collapse of the main
landing gear (MLG).
This [Canadian] AD mandates initial and
repeat inspections [for cracking] of the RHS
and LHS nacelle lower longerons until the
terminating action is accomplished.
The initial inspection may be either a
detailed inspection or a bolt-hole eddy
current (BHEC) inspection. The
repetitive inspection is a BHEC
inspection. The corrective action is
replacement of the longeron with a new
longeron or repair. The optional
terminating action is replacement of the
nacelle lower longerons, and cold
working of the drain holes. You may
obtain further information by examining
the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (78
FR 21079, April 9, 2013) or on the
determination of the cost to the public.
Changes to Service Information
References
Bombardier, Inc. has issued revised
service information, which specifies
that no additional actions are necessary
to address the identified unsafe
condition. We have revised this AD to
reference Bombardier Service Bulletin
8–54–39, Revision B, dated March 13,
2013, as the appropriate source of
service information for accomplishing
the required actions.
We have also added Bombardier
Service Bulletin 8–54–39, Revision A,
dated August 2, 2012, to paragraph (k)
of this AD, which provides credit for
actions performed before the effective
date of this AD.
Conclusion
We reviewed the available data 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 (78 FR
21079, April 9, 2013) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 21079,
April 9, 2013).
Costs of Compliance
We estimate that this AD affects 51
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Repetitive Inspections
21 work-hours × $85 per hour = $1,785
per inspection cycle.
We estimate the following costs to do
any necessary replacements that would
Cost per
product
Parts cost
$0
Cost on U.S. operators
$1,785 per inspection
cycle.
be required based on the results of the
inspection. We have no way of
$91,035 per inspection cycle.
determining the number of aircraft that
might need these replacements:
ON-CONDITION COSTS
Labor cost
Parts cost
Cost per
product
Replacement ....................................
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Action
100 work-hours × $85 per hour = $8,500 .................................................
$23,849
$32,349
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
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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,
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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
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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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the MCAI, 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
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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.
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2013–16–12 Bombardier, Inc.: Amendment
39–17550. Docket No. FAA–2013–0297;
Directorate Identifier 2012–NM–205–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective September 24, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc. Model
DHC–8–102, –103 airplanes, and airplanes
converted to Model DHC–8–106 in
accordance with Bombardier Service Bulletin
8–92–07 or Bombardier Service Bulletin 8–
92–08, serial numbers 003 through 287
inclusive, with pre-modification 8/1593
nacelle lower longeron installed; certificated
in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 54, Nacelles/pylons.
(e) Reason
This AD was prompted by a report of
cracking in a lower longeron in a nacelle. We
are issuing this AD to detect and correct such
cracking, which could result in degradation
of the structural integrity of the nacelle and
possible collapse of the main landing gear
(MLG).
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Initial Inspection
At the applicable time specified in
paragraph (g)(1), (g)(2), (g)(3), or (g)(4) of this
AD: Do a detailed visual inspection or a bolthole eddy current (BHEC) test for cracking of
each nacelle lower longeron, in accordance
with the Accomplishment Instructions of
Bombardier Service Bulletin 8–54–39,
Revision B, dated March 13, 2013.
(1) For Model DHC–8–102 and -103
airplanes that have accumulated 35,000 total
flight cycles or less as of the effective date
of this AD: Within 5,000 flight cycles after
the effective date of this AD, but not to
exceed 36,000 total flight cycles.
(2) For Model DHC–8–102 and -103
airplanes that have accumulated more than
35,000 total flight cycles as of the effective
date of this AD: Within 1,000 flight cycles
after the effective date of this AD.
(3) For Model DHC–8–106 airplanes with
the Pre-Modification 8/1641 configuration,
within 500 flight cycles after the effective
date of this AD.
(4) For Model DHC–8–106 airplanes with
the Post-Modification 8/1641 configuration,
within 5,000 flight cycles after the effective
date of this AD.
(h) Repetitive BHEC Testing
After accomplishment of the actions
required by paragraph (g) of this AD, at the
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applicable time specified in paragraph (h)(1)
or (h)(2) of this AD: Do repetitive BHEC
testing for cracking of each nacelle lower
longeron, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–54–39, Revision B, dated
March 13, 2013, until the terminating action
specified in paragraph (j) of this AD is done.
(1) For Model DHC–8–102 and -103
airplanes, at intervals not to exceed 2,500
flight cycles.
(2) For Model DHC–8–106 airplanes, at
intervals not to exceed 1,854 flight cycles.
(i) Replacement or Repair of Crack Longeron
If any cracking is found during any
inspection required by paragraph (g) or (h) of
this AD: Before further flight, replace any
cracked nacelle lower longeron with a new
longeron, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–54–39, Revision B, dated
March 13, 2013; or repair the longeron using
a method approved by either the Manager,
New York ACO, ANE–170, FAA, or
Transport Canada Civil Aviation (TCCA) (or
its delegated agent).
(j) Optional Terminating Action
Accomplishment of the actions specified in
paragraphs (j)(1) and (j)(2) of this AD
constitutes terminating action for the
repetitive BHEC testing specified in
paragraph (h) of this AD for that longeron
only.
(1) Replacement of the nacelle lower
longeron, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–54–39, Revision B, dated
March 13, 2013.
(2) Cold working of the drain holes, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–54–39, Revision B, dated March 13, 2013.
(k) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (h) of this AD, if those
actions were performed before the effective
date of this AD using Bombardier Service
Bulletin 8–54–39, dated March 14, 2012; or
using Bombardier Service Bulletin 8–54–39,
Revision A, dated August 2, 2012; which are
not incorporated by reference in this AD.
(l) 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 manager of the ACO, send it to ATTN:
Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, New York
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
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approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information Canadian
Airworthiness Directive CF–2012–27, dated
November 2, 2012, for related information,
which can be found in the AD docket on the
Internet at https://www.regulations.gov.
(2) Service information identified in this
AD that is not incorporated by reference may
be obtained at the address specified in
paragraphs (n)(3) and (n)(4) of this AD. You
may review copies of 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.
(n) Material Incorporated by Reference
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(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) Bombardier Service Bulletin 8–54–39,
Revision B, dated March 13, 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 review copies of the 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.
Issued in Renton, Washington, on August
1, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–19157 Filed 8–19–13; 8:45 am]
BILLING CODE 4910–13–P
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Jkt 229001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1180; Directorate
Identifier 2012–CE–032–AD; Amendment
39–17539; AD 2013–16–01]
RIN 2120–AA64
Airworthiness Directives; Beechcraft
Corporation and Hawker Beechcraft
Corporation
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Beechcraft Corporation (type certificate
previously held by Hawker Beechcraft
Corporation) Models 58, 95–C55, E55,
and 56TC airplanes; and Hawker
Beechcraft Corporation Models 58P and
58TC airplanes (both type certificates
previously held by Raytheon Aircraft
Company). This AD was prompted by
reports of elevator balance weights
becoming loose or failing because the
balance weight material was under
strength and did not meet material
specifications. This AD requires
inspections of elevator balance weights
and replacement of defective elevator
balance weights. We are issuing this AD
to correct the unsafe condition on these
products.
DATES: This AD is effective September
24, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of September 24, 2013.
ADDRESSES: For service information
identified in this AD, contact Beechcraft
Corporation, B091–A04, 10511 E.
Central Ave., Wichita, Kansas 67206;
telephone: 1 (800) 429–5372 or (316)
676–3140; fax: (316) 676–8027; email:
tmdc@beechcraft.com; or Internet:
https://www.beechcraft.com/
customer_support/technical_and_
field_support. You may review copies of
the referenced service information at the
FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106.
For information on the availability of
this material at the FAA, call (816) 329–
4148.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
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51053
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 (phone: 800–647–5527) is
Document 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: T.
N. Baktha, Senior Aerospace Engineer,
FAA, Wichita ACO, 1801 Airport Road,
Room 100, Wichita, Kansas 67209;
telephone: (316) 946–4155; fax: (316)
946–4107; email: t.n.baktha@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
Part 39 to include an airworthiness
directive (AD) that would apply to the
specified products. The NPRM (77 FR
66566, November 6, 2012) proposed to
require inspections of elevator balance
weights and replacement of defective
elevator balance weights. We followed
the NPRM with a supplemental notice
of proposed rulemaking (SNPRM) that
published in the Federal Register on
May 15, 2013 (78 FR 28540). The
SNPRM proposed to prohibit the
installation of designated spare parts
and to clarify applicability.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the SNPRM
(78 FR 28540, May 15, 2013) or on the
determination of the cost to the public.
Conclusion
We reviewed the relevant data 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 SNPRM (78 FR
28540, May 15, 2013) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM.
Costs of Compliance
We estimate that this AD affects 1,326
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
E:\FR\FM\20AUR1.SGM
20AUR1
]]>Agencies
[Federal Register Volume 78, Number 161 (Tuesday, August 20, 2013)]
[Rules and Regulations]
[Pages 51050-51053]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-19157]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0297; Directorate Identifier 2012-NM-205-AD;
Amendment 39-17550; AD 2013-16-12]
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-8-102, -103, and -106 airplanes. This AD was
prompted by a report of cracking in a lower longeron in a nacelle. This
AD requires repetitive inspections for cracking of the lower longerons
in the nacelles, and replacement with new longerons or repair if
necessary.
[[Page 51051]]
Additionally, this AD specifies an optional terminating action. We are
issuing this AD to detect and correct such cracking, which could result
in degradation of the structural integrity of the nacelle and possible
collapse of the main landing gear (MLG).
DATES: This AD becomes effective September 24, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September
24, 2013.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Jeffrey Zimmer, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7306; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
Part 39 to include an AD that would apply to the specified products.
The NPRM was published in the Federal Register on April 9, 2013 (78 FR
21079). The NPRM proposed to correct an unsafe condition for the
specified products. Transport Canada Civil Aviation (TCCA), which is
the aviation authority for Canada, has issued Canadian Airworthiness
Directive CF-2012-27, dated November 2, 2012 (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 has been one in-service report where a nacelle lower
longeron was found to be cracked during a routine maintenance
inspection. The investigation determined that the crack initiated
from the right-hand side (RHS) drain hole. Fatigue testing has
indicated that both the RHS and left-hand side (LHS) longerons are
vulnerable to fatigue cracking. Failure of the nacelle lower
longeron would result in a degradation of the structural integrity
of the nacelle and could potentially lead to collapse of the main
landing gear (MLG).
This [Canadian] AD mandates initial and repeat inspections [for
cracking] of the RHS and LHS nacelle lower longerons until the
terminating action is accomplished.
The initial inspection may be either a detailed inspection or a
bolt-hole eddy current (BHEC) inspection. The repetitive inspection is
a BHEC inspection. The corrective action is replacement of the longeron
with a new longeron or repair. The optional terminating action is
replacement of the nacelle lower longerons, and cold working of the
drain holes. You may obtain further information by examining the MCAI
in the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (78 FR 21079, April 9,
2013) or on the determination of the cost to the public.
Changes to Service Information References
Bombardier, Inc. has issued revised service information, which
specifies that no additional actions are necessary to address the
identified unsafe condition. We have revised this AD to reference
Bombardier Service Bulletin 8-54-39, Revision B, dated March 13, 2013,
as the appropriate source of service information for accomplishing the
required actions.
We have also added Bombardier Service Bulletin 8-54-39, Revision A,
dated August 2, 2012, to paragraph (k) of this AD, which provides
credit for actions performed before the effective date of this AD.
Conclusion
We reviewed the available data 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 (78 FR 21079, April 9, 2013) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 21079, April 9, 2013).
Costs of Compliance
We estimate that this AD affects 51 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Repetitive Inspections............. 21 work-hours x $85 per $0 $1,785 per inspection $91,035 per inspection cycle.
hour = $1,785 per cycle.
inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the inspection. We have
no way of determining the number of aircraft that might need these
replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replacement............................... 100 work-hours x $85 per hour = $23,849 $32,349
$8,500.
----------------------------------------------------------------------------------------------------------------
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
[[Page 51052]]
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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the MCAI, 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 AD:
2013-16-12 Bombardier, Inc.: Amendment 39-17550. Docket No. FAA-
2013-0297; Directorate Identifier 2012-NM-205-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective September
24, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc. Model DHC-8-102, -103
airplanes, and airplanes converted to Model DHC-8-106 in accordance
with Bombardier Service Bulletin 8-92-07 or Bombardier Service
Bulletin 8-92-08, serial numbers 003 through 287 inclusive, with
pre-modification 8/1593 nacelle lower longeron installed;
certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 54, Nacelles/
pylons.
(e) Reason
This AD was prompted by a report of cracking in a lower longeron
in a nacelle. We are issuing this AD to detect and correct such
cracking, which could result in degradation of the structural
integrity of the nacelle and possible collapse of the main landing
gear (MLG).
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Initial Inspection
At the applicable time specified in paragraph (g)(1), (g)(2),
(g)(3), or (g)(4) of this AD: Do a detailed visual inspection or a
bolt-hole eddy current (BHEC) test for cracking of each nacelle
lower longeron, in accordance with the Accomplishment Instructions
of Bombardier Service Bulletin 8-54-39, Revision B, dated March 13,
2013.
(1) For Model DHC-8-102 and -103 airplanes that have accumulated
35,000 total flight cycles or less as of the effective date of this
AD: Within 5,000 flight cycles after the effective date of this AD,
but not to exceed 36,000 total flight cycles.
(2) For Model DHC-8-102 and -103 airplanes that have accumulated
more than 35,000 total flight cycles as of the effective date of
this AD: Within 1,000 flight cycles after the effective date of this
AD.
(3) For Model DHC-8-106 airplanes with the Pre-Modification 8/
1641 configuration, within 500 flight cycles after the effective
date of this AD.
(4) For Model DHC-8-106 airplanes with the Post-Modification 8/
1641 configuration, within 5,000 flight cycles after the effective
date of this AD.
(h) Repetitive BHEC Testing
After accomplishment of the actions required by paragraph (g) of
this AD, at the applicable time specified in paragraph (h)(1) or
(h)(2) of this AD: Do repetitive BHEC testing for cracking of each
nacelle lower longeron, in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin 8-54-39, Revision B,
dated March 13, 2013, until the terminating action specified in
paragraph (j) of this AD is done.
(1) For Model DHC-8-102 and -103 airplanes, at intervals not to
exceed 2,500 flight cycles.
(2) For Model DHC-8-106 airplanes, at intervals not to exceed
1,854 flight cycles.
(i) Replacement or Repair of Crack Longeron
If any cracking is found during any inspection required by
paragraph (g) or (h) of this AD: Before further flight, replace any
cracked nacelle lower longeron with a new longeron, in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
8-54-39, Revision B, dated March 13, 2013; or repair the longeron
using a method approved by either the Manager, New York ACO, ANE-
170, FAA, or Transport Canada Civil Aviation (TCCA) (or its
delegated agent).
(j) Optional Terminating Action
Accomplishment of the actions specified in paragraphs (j)(1) and
(j)(2) of this AD constitutes terminating action for the repetitive
BHEC testing specified in paragraph (h) of this AD for that longeron
only.
(1) Replacement of the nacelle lower longeron, in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
8-54-39, Revision B, dated March 13, 2013.
(2) Cold working of the drain holes, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 8-54-39,
Revision B, dated March 13, 2013.
(k) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(h) of this AD, if those actions were performed before the effective
date of this AD using Bombardier Service Bulletin 8-54-39, dated
March 14, 2012; or using Bombardier Service Bulletin 8-54-39,
Revision A, dated August 2, 2012; which are not incorporated by
reference in this AD.
(l) 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 manager of the ACO, send it
to ATTN: Program Manager, Continuing Operational Safety, FAA, New
York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 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
[[Page 51053]]
approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
Canadian Airworthiness Directive CF-2012-27, dated November 2, 2012,
for related information, which can be found in the AD docket on the
Internet at https://www.regulations.gov.
(2) Service information identified in this AD that is not
incorporated by reference may be obtained at the address specified
in paragraphs (n)(3) and (n)(4) of this AD. You may review copies of
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.
(n) 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) Bombardier Service Bulletin 8-54-39, Revision B, dated March
13, 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 review copies of the 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 August 1, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-19157 Filed 8-19-13; 8:45 am]
BILLING CODE 4910-13-P
