Airworthiness Directives; SOCATA Airplanes, 51456-51459 [2015-20588]
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51456
Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations
(e) Required Actions
(1) Within 165 hours time-in-service (TIS),
visually inspect the swashplate assembly to
determine whether a ferrule is installed on
the rotating star. If the ferrule is not visible,
use a magnetic retriever positioned in Area
(X) as shown in the pictures under paragraph
3.B.2.b., Accomplishment Instructions, of
Airbus Helicopters Alert Service Bulletin
(ASB) No. EC130 62A010, ASB No. AS350
62.00.34, or ASB No. AS355 62.00.33, all
Revision 0, and all dated April 28, 2014,
whichever is applicable to your helicopter, to
determine whether the ferrule is installed.
The magnetic retriever will be magnetized if
a ferrule is installed.
(2) If a ferrule is not installed, no further
action is needed.
(3) If a ferrule is installed on the rotating
star, before further flight, dye-penetrant
inspect the rotating star for a crack in areas
‘‘Z’’ depicted in Figure 1 of Airbus
Helicopters ASB No. EC130 62A010, ASB
No. AS350 62.00.34, or ASB No. AS355
62.00.33, all Revision 0, and all dated April
28, 2014, as applicable to your model
helicopter.
(i) If the rotating star has a crack, before
further flight, remove from service the
rotating star; ferrule; and the screws, washers
and nuts used to attach the pitch change
rods, compass, and the rotating star deflector.
(ii) If the rotating star does not have a
crack, within 160 hours TIS, remove from
service the rotating star; ferrule; and the
screws, washers and nuts used to attach the
pitch change rods, compass, and the rotating
star deflector.
(4) Do not install a rotating star P/N
350A371003–04, 350A371003–05,
350A371003–06, 350A371003–07, or
350A371003–08 with a ferrule.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference 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) Airbus Helicopters Alert Service
Bulletin (ASB) No. EC130 62A010, Revision
0, dated April 28, 2014.
(ii) Airbus Helicopters ASB No. AS350
62.00.34, Revision 0, dated April 28, 2014.
(iii) Airbus Helicopters ASB No. AS355
62.00.33, Revision 0, dated April 28, 2014.
(3) For Airbus Helicopters service
information identified in this AD, contact
Airbus Helicopters, Inc., 2701 N. Forum
Drive, Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax (972)
641–3775; or at https://
www.airbushelicopters.com/techpub.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, Texas 76177. 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.
(f) Special Flight Permits
Special flight permits are prohibited.
[FR Doc. 2015–20587 Filed 8–24–15; 8:45 am]
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(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Robert Grant,
Aviation Safety Engineer, Safety Management
Group, FAA, 10101 Hillwood Pkwy., Fort
Worth, Texas 76177; telephone (817) 222–
5110; email asw-ftw-amoc@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.
(h) Additional Information
The subject of this AD is addressed in the
European Aviation Safety Agency (EASA) AD
No. 2014–0132R1, dated June 2, 2014. You
may view the EASA AD on the Internet at
https://www.regulations.gov in Docket No.
FAA–2015–0673.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6200, Main Rotor System.
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Issued in Fort Worth, Texas, on August 13,
2015.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2047; Directorate
Identifier 2015–CE–013–AD; Amendment
39–18243; AD 2015–17–10]
RIN 2120–AA64
Airworthiness Directives; SOCATA
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2007–04–
13 for certain SOCATA Model TBM 700
airplaness (type certificate previously
held by EADS SOCATA). This AD
results from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
SUMMARY:
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another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as cracks found on the main
landing gear cylinders. We are issuing
this AD to require actions to address the
unsafe condition on these products.
DATES: This AD is effective September
29, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 29, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of March 23, 2007 (72 FR
7576, February 16, 2007).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
2047; 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 20590.
For service information identified in
this AD, contact SOCATA, Direction des
Services, 65921 Tarbes Cedex 9, France;
telephone: 33 (0)5 62.41.73.00; fax: 33
(0)5 62.41.76.54; or SOCATA North
America, North Perry Airport, 7501 S
Airport Rd., Pembroke Pines, Florida
33023, telephone: (954) 893–1400; fax:
(954) 964–4141; Internet: https://
www.socata.com. You may view this
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. It is also available on the Internet
at https://www.regulations.gov by
searching for Docket No. FAA–2015–
2047.
FOR FURTHER INFORMATION CONTACT:
Albert J. Mercado, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4119; fax: (816) 329–4090; email:
albert.mercado@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to make
changes to an NPRM (80 FR 8821,
February 19, 2015), which would amend
14 CFR part 39 to add an AD that would
apply to certain SOCATA Model TBM
700 airplaness (type certificate
previously held by EADS SOCATA).
That SNPRM was published in the
Federal Register on June 11, 2015 (80
FR 33208), and proposed to supersede
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Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations
AD 2007–04–13, Amendment 39–14945,
(72 FR 7576, February 16, 2007) (‘‘AD
2007–04–13’’).
Since we issued AD 2007–04–13, it
has been determined that the time
between repetitive inspections should
be extended and an optional terminating
action for the repetitive inspections is
now available.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued AD No. 2006–
0085R2, dated January 16, 2015
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
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Cracks on several main landing gear (MLG)
cylinders have been reported in service.
This condition, if not to detected and
corrected, could lead to fatigue cracks in the
shock strut cylinder of the MLG, which could
result in a collapsed MLG during take-off or
landing runs, and possibly reduce the
structural integrity of the aeroplane.
To address this unsafe condition, EASA
issued AD 2006–0085 to require repetitive
special detailed inspections (SDI) for cracks
of the MLG shock strut cylinder and,
depending on findings, relevant investigative
and corrective actions.
After that AD was issued, SOCATA
performed an analysis to demonstrate that
the inspection interval could be extended,
and developed a reinforced MLG less prone
to fatigue, which is embodied in production
through SOCATA modification (MOD) 70–
0190–32 and can be introduced in service
through SOCATA Service Bulletin (SB) 70–
130–32 at Revision 03.
Prompted by these developments, EASA
issued AD 2006–0085R1 to increase the
inspection interval and to introduce the
installation of a reinforced MLG on the right
hand (RH) side and left hand (LH) side as an
optional terminating action for the repetitive
SDI required by this AD.
Since that AD was issued, it was found that
aeroplanes MSN 639 to 683 (inclusive) are
not affected by this AD. The applicability has
therefore been revised to remove those MSN.
The MCAI can be found in the AD
docket on the Internet at: https://
www.regulations.gov/
#!documentDetail;D=FAA-2015-20470002.
In addition, we have determined that
airplanes with MLG with forging body
that had not reached 1,750 landings as
of March 23, 2007 (the effective date of
AD 2007–04–13) were not affected by
the AD. This is not the intent and allows
airplanes to fly indefinitely with the
unsafe condition. This AD includes
those airplanes with MLG with forging
body either at or under 1,750 landings
as of March 23, 2007, and extends the
time between the repetitive inspections
until a reinforced landing gear is
installed, which terminates the
repetitive inspections.
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51457
Comments
Authority for This Rulemaking
We gave the public the opportunity to
participate in developing this AD. We
received one supportive comment to the
NPRM (80 FR 8821, February 19, 2015)
and no comments on the SNPRM (80 FR
33208, June 11, 2015) or on the
determination of the cost to the public.
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.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting the 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 (80 FR
33208, June 11, 2015) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM (80 FR 33208,
June 11, 2015).
Related Service Information Under 1
CFR Part 51
EADS SOCATA has issued TBM
Aircraft Mandatory Service Bulletin SB
70–130, ATA No. 32, dated January
2006, and SOCATA has issued DAHER–
SOCATA TBM Aircraft Mandatory
Service Bulletin SB 70–130, Revision 3,
dated December 2014. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI. The DAHER–
SOCATA TBM Aircraft Mandatory
Service Bulletin SB 70–130, Revision 3,
dated December 2014, incorporates
procedures for replacing cracked MLG
with a reinforced MLG as a terminating
action for the repetitive inspections.
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 will affect
431 products of U.S. registry. We also
estimate that it will take about 3 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate the
cost of this AD on U.S. operators to be
$109,905, or $255 per product.
In addition, we estimate that any
necessary follow-on actions will take
about 4 work-hours and require parts
costing $6,000, for a cost of $6,340 per
product. We have no way of
determining the number of products
that may need these actions.
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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 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 by searching for
and locating Docket No. FAA–2015–
2047; 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 the SNPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone (800) 647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
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51458
Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations
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
removing Amendment 39–14945 (72 FR
7576, February 16, 2007), and adding
the following new AD:
■
2015–17–10 SOCATA (type certificate
previously held by EADS SOCATA):
Amendment 39–18243; Docket No.
FAA–2015–2047; Directorate Identifier
2015–CE–013–AD.
(a) Effective Date
This AD becomes effective September 29,
2015.
(b) Affected ADs
This AD supersedes AD 2007–04–13,
Amendment 39–14945, (72 FR 7576,
February 16, 2007) (‘‘AD 2007–04–13’’).
(c) Applicability
This AD applies to SOCATA Model TBM
700 airplanes, serial numbers 1 through 638
and 687, that:
(1) are not equipped with a left-hand main
landing gear (MLG) body part number (P/N)
D68161 or D68161–1 and a right-hand MLG
body P/N D68162 or D68162–1; and
(2) are certificated in any category.
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(d) Subject
Air Transport Association of America
(ATA) Code 32: Landing gear.
(e) Reason
This AD was prompted from mandatory
continuing airworthiness information (MCAI)
originated by an aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as cracks
found on the main landing gear cylinders. In
addition, the FAA determined that airplanes
with MLG with forging body that had not
reached 1,750 landings as of March 23, 2007
(the effective date of AD 2007–04–13) were
not affected by AD 2007–04–13. This is not
the intent and allows airplanes to fly
indefinitely with the unsafe condition. This
AD increases the scope of the affected
airplanes by including those airplanes with
MLG with forging body either at or under
1,750 landings as of March 23, 2007,
increases the time between the repetitive
inspections, and incorporates a modification
to terminate the required repetitive
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inspections. We are issuing this AD to detect
and correct cracks in the shock strut cylinder
of the MLG, which could cause the MLG to
fail. Failure of the shock strut cylinder of the
MLG could result in a collapsed MLG during
takeoff or landing and possible reduced
structural integrity of the airplane.
(f) Actions and Compliance for Airplanes
Not Previously Affected by AD 2007–04–13
Unless already done, do the actions in
paragraphs (f)(1), (f)(2), and (h) of this AD:
(1) For MLG with forging body that were
either at or under 1,750 landings as of March
23, 2007 (the effective date of (AD 2007–04–
13): Upon or before accumulating 1,750
landings on the MLG with forging body since
new or within the next 100 landings after
September 29, 2015 (the effective date of this
AD), whichever occurs later, inspect the
forging body for cracks. Do the inspection
following the Accomplishment Instructions
of EADS SOCATA TBM Aircraft Mandatory
Service Bulletin SB 70–130, dated January
2006, or DAHER–SOCATA TBM Aircraft
Mandatory Service Bulletin SB 70–130,
Revision 3, dated December 2014.
(2) If no cracks are detected during the
inspection required in paragraph (f)(1) of this
AD, repetitively thereafter inspect at intervals
not to exceed 240 landings until a reinforced
landing gear specified in paragraph E.
Terminating Solution of the Accomplishment
Instructions in DAHER–SOCATA TBM
Aircraft Mandatory Service Bulletin SB 70–
130, Revision 3, dated December 2014, is
installed.
(g) Actions and Compliance for Airplanes
Previously Affected by AD 2007–04–13
Unless already done, do the actions in
paragraphs (g)(1), (g)(2), and (h) of this AD,
including all subparagraphs:
(1) As of March 23, 2007 (the effective date
retained from AD 2007–04–13), for MLG with
forging body totaling more than 1,750
landings but less than 3,501 landings since
new:
(i) Inspect the forging body for cracks
within 100 landings after March 23, 2007 (the
effective date retained from AD 2007–04–13),
following the Accomplishment Instructions
of EADS SOCATA TBM Aircraft Mandatory
Service Bulletin SB 70–130, dated January
2006, or DAHER–SOCATA TBM Aircraft
Mandatory Service Bulletin SB 70–130,
Revision 3, dated December 2014.
(ii) If no cracks are detected during the
inspection required in paragraph (g)(1)(i) of
this AD, repetitively thereafter inspect at
intervals not to exceed 240 landings until a
reinforced landing gear specified in
paragraph E. Terminating Solution of the
Accomplishment Instructions in DAHER–
SOCATA TBM Aircraft Mandatory Service
Bulletin SB 70–130, Revision 3, dated
December 2014, is installed.
(2) As of March 23, 2007 (the effective date
retained from AD 2007–04–13), for MLG with
forging body totaling more than 3,500
landings since new:
(i) Inspect the forging body for cracks
within 25 landings after March 23, 2007 (the
effective date retained from AD 2007–04–13),
following the Accomplishment Instructions
of EADS SOCATA TBM Aircraft Mandatory
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Service Bulletin SB 70–130, dated January
2006, or DAHER–SOCATA TBM Aircraft
Mandatory Service Bulletin SB 70–130,
Revision 3, dated December 2014.
(ii) If no cracks are detected during the
inspection required in paragraph (g)(2)(i) of
this AD, repetitively thereafter inspect at
intervals not to exceed 240 landings until a
reinforced landing gear specified in
paragraph E. Terminating Solution of the
Accomplishment Instructions in DAHER–
SOCATA TBM Aircraft Mandatory Service
Bulletin SB 70–130, Revision 3, dated
December 2014, is installed.
(h) Actions and Compliance for All Affected
Airplanes
If any cracks are detected during any
inspection required in paragraphs (f)(1)
through (g)(2) of this AD, including all
subparagraphs:
(1) Before further flight, remove the
affected landing gear leg and confirm the
presence of the crack with dye penetrant
inspection or fluorescent penetrant
inspection.
(2) If the crack is confirmed, before further
flight, contact SOCATA at the address in
paragraph (l)(5) of this AD to coordinate the
FAA-approved landing gear repair/
replacement and implement any FAAapproved repair/replacement instructions
obtained from SOCATA, or replace the
cracked landing gear with a reinforced
landing gear specified in paragraph E.
Terminating Solution of the Accomplishment
Instructions in DAHER–SOCATA TBM
Aircraft Mandatory Service Bulletin SB 70–
130, Revision 3, dated December 2014. This
replacement terminates the repetitive
inspections required by this AD.
(i) Calculating Unknown Number of
Landings for Compliance
The compliance times of this AD are
presented in landings instead of hours timein-service (TIS). If the number of landings is
unknown, hours TIS may be used by dividing
the number of hours TIS by 1.35.
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Albert J. Mercado, Aerospace
Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4119; fax: (816)
329–4090; email: albert.mercado@faa.gov.
Before using any approved AMOC on any
airplane to which the AMOC applies, notify
your appropriate principal inspector (PI) in
the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(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.
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Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations
(k) Related Information
DEPARTMENT OF TRANSPORTATION
Refer to MCAI European Aviation Safety
Agency (EASA) AD No. 2006–0085R2, dated
January 16, 2015, for related information.
You may examine the MCAI on the Internet
at https://www.regulations.gov/
#!documentDetail;D=FAA-2015-2047-0002.
(l) 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.
(3) The following service information was
approved for IBR on September 29, 2015.
(i) DAHER–SOCATA TBM Aircraft
Mandatory Service Bulletin SB 70–130,
Revision 3, dated December 2014.
(ii) Reserved.
(4) The following service information was
approved for IBR on March 23, 2007 (72 FR
7576, February 16, 2007).
(i) EADS SOCATA TBM Aircraft
Mandatory Service Bulletin SB 70–130, dated
January 2006.
(ii) Reserved.
(5) For SOCATA service information
identified in this AD, contact SOCATA,
Direction des Services, 65921 Tarbes Cedex
9, France; telephone: 33 (0)5 62.41.73.00; fax:
33 (0)5 62.41.76.54; or SOCATA North
America, North Perry Airport, 7501 S Airport
Rd., Pembroke Pines, Florida 33023,
telephone: (954) 893–1400; fax: (954) 964–
4141; Internet: https://www.socata.com.
(6) You may view this service information
at 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. In
addition, you can access this service
information on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2015–2047.
(7) 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.
Lhorne on DSK5TPTVN1PROD with RULES
Issued in Kansas City, Missouri, on August
14, 2015.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2015–20588 Filed 8–24–15; 8:45 am]
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–1050; Directorate
Identifier 2014–NM–123–AD; Amendment
39–18241; AD 2015–17–08]
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–8–400
series airplanes. This AD was prompted
by an in-service report of an
uncommanded and unannunciated nose
wheel steering during airplane
pushback from the gate. This AD
requires installing new cable assemblies
with a pull-down resistor. We are
issuing this AD to prevent an
uncommanded nose wheel steering
during takeoff or landing in the event of
an open circuit in the steering system,
and possible consequent runway
excursion.
SUMMARY:
This AD becomes effective
September 29, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 29, 2015.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-1050 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–
1050.
DATES:
PO 00000
Frm 00037
Fmt 4700
Sfmt 4700
51459
FOR FURTHER INFORMATION CONTACT:
Assata Dessaline, Aerospace Engineer,
Avionics and Services Branch, ANE–
172, FAA, New York Aircraft
Certification Office (ACO), 1600 Stewart
Avenue, Suite 410, Westbury, NY
11590; telephone (516) 228–7301; 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
January 23, 2015 (80 FR 3504).
The Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2013–38,
dated November 28, 2013 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Bombardier, Inc. Model
DHC–8–400, –401, and –402 series
airplanes. The MCAI states:
There has been one in-service report of an
un-commanded and un-annunciated nose
wheel steering during aeroplane push-back
from the gate. The investigation revealed that
a design deficiency exists within the steering
control unit (SCU) where an open circuit may
not be adequately detected and annunciated
to the flight crew. A sustained open circuit
could result in an un-commanded and unannunciated nose wheel steering input.
Un-commanded nose wheel steering
during takeoff or landing may lead to a
runway excursion.
This [Canadian] AD mandates the
installation of new cable assemblies, with a
pull-down resistor, to ensure that the nose
wheel steering system reverts to fail-safe free
castor mode in the event of an open circuit
in the steering system.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-10500002.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the NPRM (80 FR 3504,
January 23, 2015) and the FAA’s
response to each comment.
Request To Remove Certain Service
Information Procedures
Horizon Air requested that we amend
paragraph (g) of the proposed AD (80 FR
3504, January 23, 2015) to exclude Part
A, ‘‘Job Set-up,’’ and Part C ‘‘Close Out,’’
sections of the Accomplishment
Instructions in Bombardier Service
E:\FR\FM\25AUR1.SGM
25AUR1
]]>Agencies
[Federal Register Volume 80, Number 164 (Tuesday, August 25, 2015)]
[Rules and Regulations]
[Pages 51456-51459]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-20588]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-2047; Directorate Identifier 2015-CE-013-AD;
Amendment 39-18243; AD 2015-17-10]
RIN 2120-AA64
Airworthiness Directives; SOCATA Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2007-04-13 for
certain SOCATA Model TBM 700 airplaness (type certificate previously
held by EADS SOCATA). This AD results from mandatory continuing
airworthiness information (MCAI) issued by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as cracks
found on the main landing gear cylinders. We are issuing this AD to
require actions to address the unsafe condition on these products.
DATES: This AD is effective September 29, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September
29, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of March
23, 2007 (72 FR 7576, February 16, 2007).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2047; 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 20590.
For service information identified in this AD, contact SOCATA,
Direction des Services, 65921 Tarbes Cedex 9, France; telephone: 33
(0)5 62.41.73.00; fax: 33 (0)5 62.41.76.54; or SOCATA North America,
North Perry Airport, 7501 S Airport Rd., Pembroke Pines, Florida 33023,
telephone: (954) 893-1400; fax: (954) 964-4141; Internet: https://www.socata.com. You may view this 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. It is also available on the Internet at https://www.regulations.gov by searching for Docket No. FAA-2015-2047.
FOR FURTHER INFORMATION CONTACT: Albert J. Mercado, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090; email:
albert.mercado@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
make changes to an NPRM (80 FR 8821, February 19, 2015), which would
amend 14 CFR part 39 to add an AD that would apply to certain SOCATA
Model TBM 700 airplaness (type certificate previously held by EADS
SOCATA). That SNPRM was published in the Federal Register on June 11,
2015 (80 FR 33208), and proposed to supersede
[[Page 51457]]
AD 2007-04-13, Amendment 39-14945, (72 FR 7576, February 16, 2007)
(``AD 2007-04-13'').
Since we issued AD 2007-04-13, it has been determined that the time
between repetitive inspections should be extended and an optional
terminating action for the repetitive inspections is now available.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
No. 2006-0085R2, dated January 16, 2015 (referred to after this as
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
Cracks on several main landing gear (MLG) cylinders have been
reported in service.
This condition, if not to detected and corrected, could lead to
fatigue cracks in the shock strut cylinder of the MLG, which could
result in a collapsed MLG during take-off or landing runs, and
possibly reduce the structural integrity of the aeroplane.
To address this unsafe condition, EASA issued AD 2006-0085 to
require repetitive special detailed inspections (SDI) for cracks of
the MLG shock strut cylinder and, depending on findings, relevant
investigative and corrective actions.
After that AD was issued, SOCATA performed an analysis to
demonstrate that the inspection interval could be extended, and
developed a reinforced MLG less prone to fatigue, which is embodied
in production through SOCATA modification (MOD) 70-0190-32 and can
be introduced in service through SOCATA Service Bulletin (SB) 70-
130-32 at Revision 03.
Prompted by these developments, EASA issued AD 2006-0085R1 to
increase the inspection interval and to introduce the installation
of a reinforced MLG on the right hand (RH) side and left hand (LH)
side as an optional terminating action for the repetitive SDI
required by this AD.
Since that AD was issued, it was found that aeroplanes MSN 639
to 683 (inclusive) are not affected by this AD. The applicability
has therefore been revised to remove those MSN.
The MCAI can be found in the AD docket on the Internet at: https://www.regulations.gov/#!documentDetail;D=FAA-2015-2047-0002.
In addition, we have determined that airplanes with MLG with
forging body that had not reached 1,750 landings as of March 23, 2007
(the effective date of AD 2007-04-13) were not affected by the AD. This
is not the intent and allows airplanes to fly indefinitely with the
unsafe condition. This AD includes those airplanes with MLG with
forging body either at or under 1,750 landings as of March 23, 2007,
and extends the time between the repetitive inspections until a
reinforced landing gear is installed, which terminates the repetitive
inspections.
Comments
We gave the public the opportunity to participate in developing
this AD. We received one supportive comment to the NPRM (80 FR 8821,
February 19, 2015) and no comments on the SNPRM (80 FR 33208, June 11,
2015) 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 the 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 (80 FR 33208, June 11, 2015) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the SNPRM (80 FR 33208, June 11, 2015).
Related Service Information Under 1 CFR Part 51
EADS SOCATA has issued TBM Aircraft Mandatory Service Bulletin SB
70-130, ATA No. 32, dated January 2006, and SOCATA has issued DAHER-
SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3,
dated December 2014. The actions described in this service information
are intended to correct the unsafe condition identified in the MCAI.
The DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130,
Revision 3, dated December 2014, incorporates procedures for replacing
cracked MLG with a reinforced MLG as a terminating action for the
repetitive inspections. 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 will affect 431 products of U.S. registry.
We also estimate that it will take about 3 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD on U.S. operators to be $109,905, or $255 per product.
In addition, we estimate that any necessary follow-on actions will
take about 4 work-hours and require parts costing $6,000, for a cost of
$6,340 per product. We have no way of determining the number of
products that may need these actions.
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 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 by searching for and locating Docket No. FAA-2015-
2047; 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 the SNPRM, the regulatory evaluation, any comments received,
and other information. The street address for the Docket Office
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
[[Page 51458]]
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 removing Amendment 39-14945 (72 FR
7576, February 16, 2007), and adding the following new AD:
2015-17-10 SOCATA (type certificate previously held by EADS SOCATA):
Amendment 39-18243; Docket No. FAA-2015-2047; Directorate Identifier
2015-CE-013-AD.
(a) Effective Date
This AD becomes effective September 29, 2015.
(b) Affected ADs
This AD supersedes AD 2007-04-13, Amendment 39-14945, (72 FR
7576, February 16, 2007) (``AD 2007-04-13'').
(c) Applicability
This AD applies to SOCATA Model TBM 700 airplanes, serial
numbers 1 through 638 and 687, that:
(1) are not equipped with a left-hand main landing gear (MLG)
body part number (P/N) D68161 or D68161-1 and a right-hand MLG body
P/N D68162 or D68162-1; and
(2) are certificated in any category.
(d) Subject
Air Transport Association of America (ATA) Code 32: Landing
gear.
(e) Reason
This AD was prompted from mandatory continuing airworthiness
information (MCAI) originated by an aviation authority of another
country to identify and correct an unsafe condition on an aviation
product. The MCAI describes the unsafe condition as cracks found on
the main landing gear cylinders. In addition, the FAA determined
that airplanes with MLG with forging body that had not reached 1,750
landings as of March 23, 2007 (the effective date of AD 2007-04-13)
were not affected by AD 2007-04-13. This is not the intent and
allows airplanes to fly indefinitely with the unsafe condition. This
AD increases the scope of the affected airplanes by including those
airplanes with MLG with forging body either at or under 1,750
landings as of March 23, 2007, increases the time between the
repetitive inspections, and incorporates a modification to terminate
the required repetitive inspections. We are issuing this AD to
detect and correct cracks in the shock strut cylinder of the MLG,
which could cause the MLG to fail. Failure of the shock strut
cylinder of the MLG could result in a collapsed MLG during takeoff
or landing and possible reduced structural integrity of the
airplane.
(f) Actions and Compliance for Airplanes Not Previously Affected by AD
2007-04-13
Unless already done, do the actions in paragraphs (f)(1),
(f)(2), and (h) of this AD:
(1) For MLG with forging body that were either at or under 1,750
landings as of March 23, 2007 (the effective date of (AD 2007-04-
13): Upon or before accumulating 1,750 landings on the MLG with
forging body since new or within the next 100 landings after
September 29, 2015 (the effective date of this AD), whichever occurs
later, inspect the forging body for cracks. Do the inspection
following the Accomplishment Instructions of EADS SOCATA TBM
Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006,
or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130,
Revision 3, dated December 2014.
(2) If no cracks are detected during the inspection required in
paragraph (f)(1) of this AD, repetitively thereafter inspect at
intervals not to exceed 240 landings until a reinforced landing gear
specified in paragraph E. Terminating Solution of the Accomplishment
Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin
SB 70-130, Revision 3, dated December 2014, is installed.
(g) Actions and Compliance for Airplanes Previously Affected by AD
2007-04-13
Unless already done, do the actions in paragraphs (g)(1),
(g)(2), and (h) of this AD, including all subparagraphs:
(1) As of March 23, 2007 (the effective date retained from AD
2007-04-13), for MLG with forging body totaling more than 1,750
landings but less than 3,501 landings since new:
(i) Inspect the forging body for cracks within 100 landings
after March 23, 2007 (the effective date retained from AD 2007-04-
13), following the Accomplishment Instructions of EADS SOCATA TBM
Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006,
or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130,
Revision 3, dated December 2014.
(ii) If no cracks are detected during the inspection required in
paragraph (g)(1)(i) of this AD, repetitively thereafter inspect at
intervals not to exceed 240 landings until a reinforced landing gear
specified in paragraph E. Terminating Solution of the Accomplishment
Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin
SB 70-130, Revision 3, dated December 2014, is installed.
(2) As of March 23, 2007 (the effective date retained from AD
2007-04-13), for MLG with forging body totaling more than 3,500
landings since new:
(i) Inspect the forging body for cracks within 25 landings after
March 23, 2007 (the effective date retained from AD 2007-04-13),
following the Accomplishment Instructions of EADS SOCATA TBM
Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006,
or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130,
Revision 3, dated December 2014.
(ii) If no cracks are detected during the inspection required in
paragraph (g)(2)(i) of this AD, repetitively thereafter inspect at
intervals not to exceed 240 landings until a reinforced landing gear
specified in paragraph E. Terminating Solution of the Accomplishment
Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin
SB 70-130, Revision 3, dated December 2014, is installed.
(h) Actions and Compliance for All Affected Airplanes
If any cracks are detected during any inspection required in
paragraphs (f)(1) through (g)(2) of this AD, including all
subparagraphs:
(1) Before further flight, remove the affected landing gear leg
and confirm the presence of the crack with dye penetrant inspection
or fluorescent penetrant inspection.
(2) If the crack is confirmed, before further flight, contact
SOCATA at the address in paragraph (l)(5) of this AD to coordinate
the FAA-approved landing gear repair/replacement and implement any
FAA-approved repair/replacement instructions obtained from SOCATA,
or replace the cracked landing gear with a reinforced landing gear
specified in paragraph E. Terminating Solution of the Accomplishment
Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin
SB 70-130, Revision 3, dated December 2014. This replacement
terminates the repetitive inspections required by this AD.
(i) Calculating Unknown Number of Landings for Compliance
The compliance times of this AD are presented in landings
instead of hours time-in-service (TIS). If the number of landings is
unknown, hours TIS may be used by dividing the number of hours TIS
by 1.35.
(j) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Albert J. Mercado, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090;
email: albert.mercado@faa.gov. Before using any approved AMOC on any
airplane to which the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(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.
[[Page 51459]]
(k) Related Information
Refer to MCAI European Aviation Safety Agency (EASA) AD No.
2006-0085R2, dated January 16, 2015, for related information. You
may examine the MCAI on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2015-2047-0002.
(l) 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.
(3) The following service information was approved for IBR on
September 29, 2015.
(i) DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-
130, Revision 3, dated December 2014.
(ii) Reserved.
(4) The following service information was approved for IBR on
March 23, 2007 (72 FR 7576, February 16, 2007).
(i) EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-
130, dated January 2006.
(ii) Reserved.
(5) For SOCATA service information identified in this AD,
contact SOCATA, Direction des Services, 65921 Tarbes Cedex 9,
France; telephone: 33 (0)5 62.41.73.00; fax: 33 (0)5 62.41.76.54; or
SOCATA North America, North Perry Airport, 7501 S Airport Rd.,
Pembroke Pines, Florida 33023, telephone: (954) 893-1400; fax: (954)
964-4141; Internet: https://www.socata.com.
(6) You may view this service information at 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. In addition, you can access this service information
on the Internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2015-2047.
(7) 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 Kansas City, Missouri, on August 14, 2015.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015-20588 Filed 8-24-15; 8:45 am]
BILLING CODE 4910-13-P
