Airworthiness Directives; Diamond Aircraft Industries GmbH Airplanes, 35630-35634 [2017-15669]
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35630
Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations
as identified in Boeing Alert Service Bulletin
737–53A1365, dated January 23, 2017.
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/EBD1CEC7B301293
E86257CB30045557A?OpenDocument&
Highlight=st01219se) does not affect the
ability to accomplish the actions required by
this AD. Therefore, for airplanes on which
STC ST01219SE is installed, a ‘‘change in
product’’ alternative method of compliance
(AMOC) approval request is not necessary to
comply with the requirements of 14 CFR
39.17.
(d) Subject
Air Transport Association (ATA) of
America Code 53; Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by
the design approval holder indicating that
the lower skin at the skin lap splice lower
fastener row is subject to widespread fatigue
damage. We are issuing this AD to detect and
correct cracks in the lower skin, which, if not
detected, could link up, resulting in reduced
structural integrity of the airplane and
consequent uncontrolled decompression of
the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections
Except as provided by paragraph (i) of this
AD, at the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1365, dated
January 23, 2017: Do external eddy current
inspections at stringer S–14 on the left and
right sides of the airplane (S–14L and S–14R)
for any crack in the skin lap splice at the
lower fastener row, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1365, dated January
23, 2017. Repeat the inspections thereafter at
the applicable times specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1365, dated January 23,
2017.
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(h) Repair
If any crack is found during any inspection
required by paragraph (g) of this AD, repair
before further flight using a method approved
in accordance with the procedures specified
in paragraph (j) of this AD. Although Boeing
Alert Service Bulletin 737–53A1365, dated
January 23, 2017, specifies to contact Boeing
for appropriate action and specifies that
action as ‘‘RC’’ (Required for Compliance),
this AD requires repair as specified in this
paragraph.
(i) Exceptions to Service Information
Specifications
(1) Where Boeing Alert Service Bulletin
737–53A1365, dated January 23, 2017,
specifies a compliance time ‘‘after the
original issue date of this service bulletin,’’
this AD requires compliance within the
specified compliance time after the effective
date of this AD.
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(2) The Condition column of Table 1 and
Table 2 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1365,
dated January 23, 2017, refers to total flight
cycles ‘‘at the original issue date of this
service bulletin.’’ This AD, however, applies
to the airplanes with the specified total flight
cycles as of the effective date of this AD.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), 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 the
attention of the person identified in
paragraph (k) of this AD. Information may be
emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov.
(2) 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (h) of
this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (j)(4)(i) and (j)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(k) Related Information
For more information about this AD,
contact James Guo, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5357; fax: 562–627–5210; email: james.guo@
faa.gov.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
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(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) Boeing Alert Service Bulletin 737–
53A1365, dated January 23, 2017.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet https://
www.myboeingfleet.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on July 14,
2017.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–15477 Filed 7–31–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0640; Directorate
Identifier 2017–CE–020–AD; Amendment
39–18969; AD 2017–15–09]
RIN 2120–AA64
Airworthiness Directives; Diamond
Aircraft Industries GmbH Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Diamond Aircraft Industries GmbH
Model DA 42 airplanes. This AD
requires installing engine exhaust pipe
clamps with spring washers, repetitively
inspecting the engine exhaust pipe
clamps for cracks, and replacing the
clamps if found cracked. This AD was
prompted by cracks in the affected
engine exhaust pipes, which could
cause failure of the propeller regulating
valve because of hot exhaust gases
coming from the fractured pipes. We are
issuing this AD to correct the unsafe
condition on these products.
SUMMARY:
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Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations
This AD is effective August 1,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 1, 2017.
We must receive comments on this
AD by September 15, 2017.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Diamond Aircraft
Industries GmbH, N.A. Otto-Stra+e 5,
A–2700 Wiener Neustadt, Austria,
telephone: +43 2622 26700; fax: +43
2622 26780; email: office@diamondair.at; Internet: https://
www.diamondaircraft.com. You may
review 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
locating Docket No. FAA–2017–0640.
DATES:
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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–2017–
0640; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (phone: 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Mike Kiesov, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4144; fax: (816)
329–4090; email: mike.kiesov@faa.gov.
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SUPPLEMENTARY INFORMATION:
FAA’s Determination
Discussion
AD 2017–01–12, Amendment 39–
18779 (82 FR 5359, January 18, 2017)
(‘‘AD 2017–01–12’’) requires either
replacing the engine exhaust pipes with
new design pipes or installing clamps
on the old design pipes on Diamond
Model DA 42 airplanes. AD 2017–01–12
is based on European Aviation Safety
Agency (EASA) AD No. 2016–0156R1,
dated November 23, 2016. EASA is the
Technical Agent for the Member States
of the European Community.
After issuance of AD 2017–01–12, we
received reports of cracks on the new
design engine exhaust pipes. To address
this cracking issue, we issued AD 2017–
11–08, Amendment 39–18907 (82 FR
24843, May 31, 2017) (‘‘AD 2017–11–
08’’). AD 2017–11–08 requires
repetitively inspecting the new design
engine exhaust pipes installed on
Diamond Model DA 42 airplanes and
replacing any cracked pipes. AD 2017–
11–08 is based on EASA AD No. 2017–
0090, dated May 17, 2017.
Since issuance of AD 2017–11–08, we
received reports of cracks found on the
engine exhaust pipe clamps that were
installed on the old design engine
exhaust pipes as a requirement in AD
2017–01–12. The FAA and EASA are
working concurrently on AD action for
the United States and Europe. EASA
recently issued AD No.: 2017–0120,
dated July 13, 2017, to address actions
similar to that of this FAA AD.
This condition, if not corrected, could
result in hot exhaust gases coming from
the fractured pipes and leading to an
uncommanded engine in-flight
shutdown or overheat damage, which
could result in a forced landing,
consequent damage, and occupant
injury.
We are issuing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Related Service Information Under 1
CFR Part 51
Diamond Aircraft Industries GmbH
has issued Mandatory Service Bulletin
MSB 42–120/2, dated June 7, 2017, and
Work Instruction WI–MSB 42–120,
Revision 3, dated July 6, 2017. In
combination, the service information
describes procedures for installing
engine exhaust pipe clamps with spring
washers and inspecting the engine
exhaust pipe clamps for cracks, with
replacement if cracks are found. 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
the final rule.
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AD Requirements
This AD requires accomplishing the
actions specified in the service
information described previously.
FAA’s Justification and Determination
of the Effective Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because affected engine exhaust
pipes could crack and cause hot gases
to leak from fractured exhaust pipes and
lead to an uncommanded engine inflight shutdown. Therefore, we find that
notice and opportunity for prior public
comment are impracticable and that
good cause exists for making this
amendment effective in less than 30
days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include the docket number
FAA–2017–0640 and Directorate
Identifier 2017–CE–020–AD at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
Costs of Compliance
We estimate that this AD affects 130
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
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Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations
ESTIMATED COSTS
Action
Labor cost
Parts cost
Install engine exhaust pipe clamps with
spring washers.
Inspect engine exhaust pipe clamps ..............
4 work-hours × $85 per hour = $340 (for
both clamps).
2 work-hours × $85 per hour = $170 .............
Cost per
product
Cost on U.S.
operators
* $100
$440
$57,200
N/A
170
22,100
* (for both clamps)
We estimate the following costs to do
any necessary replacements that will be
required based on the results of the
inspections. We have no way of
determining the number of airplanes
that may need these replacements:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Replace cracked clamps .................
4 work-hours × $85 per hour = $340 (for both clamps) ...........................
Cost per
product
* $100
$440
* (for both clamps)
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is mandatory. Comments
concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to the FAA at 800
Independence Ave. SW., Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
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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
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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
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
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–15–09 Diamond Aircraft Industries
GmbH: Amendment 39–18969; Docket
No. FAA–2017–0640; Directorate
Identifier 2017–CE–020–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective August 1, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Diamond Aircraft
Industries (DAI) GmbH Model DA 42
airplanes, serial numbers 42.004 through
42.427 and 42.AC001 through 42.AC151,
certificated in any category, that have:
(1) Either a Technify Motors GmbH TAE
125–02–99 or TAE 125–02–114 engine
installed; and
(2) DAI part numbers (P/N) D60–7806–00–
01 and P/N D60–7806–00–02 engine exhaust
clamps installed.
(d) Subject
Air Transport Association of America
(ATA) Code 78: Engine Exhaust.
(e) Reason
This AD was prompted by cracks in the
affected engine exhaust pipes, which could
cause failure of the propeller regulating valve
because of hot exhaust gases coming from the
fractured pipes. We are issuing this AD to
prevent an uncommanded engine in-flight
shutdown or overheat damage, which could
result in a forced landing, consequent
damage, and occupant injury.
(f) Actions and Compliance
Unless already done, do the actions in
paragraphs (f)(1) through (6) of this AD.
(1) Before or upon accumulating 40 hours
time-in-service (TIS) on the affected engine
exhaust pipes or within the next 10 hours
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35633
as specified in DAI Mandatory Service
Bulletin MSB 42–120/2, dated June 7, 2017.
(ii) Reinstall any uncracked clamp or
replace with a new clamp and incorporate
spring washers following III.2 Action 2—
installation of additional exhaust clamp in
the INSTRUCTIONS section of DAI Work
Instruction WI–MSB 42–120, Revision 3,
dated July 6, 2017, as specified in DAI
Mandatory Service Bulletin MSB 42–120/2,
dated June 7, 2017. See figure 1 to paragraph
(f)(1)(ii) of this AD for additional information
on the sequence of installation actions as
identified in DAI Work Instruction WI–MSB
42–120, Revision 3, dated July 6, 2017. Credit
is not given for installation of an engine
exhaust clamp installed following DAI Work
Instruction WI–MSB 42–120, Revision 1,
dated December 14, 2016, (installation of
exhaust clamp without spring washers), or
DAI Work Instruction MSB–42–120, Revision
2, dated June 7, 2017.
(2) Within 25 hours TIS after the
installation required by paragraph (f)(1)(ii) of
this AD and repetitively thereafter at
intervals not to exceed 25 hours TIS, inspect
each engine exhaust clamp for cracks
following III.3 Action 3—Inspection of
exhaust clamp for cracks of the
INSTRUCTIONS section DAI Work
Instruction WI–MSB 42–120, Revision 3,
dated July 6, 2017, as specified in DAI
Mandatory Service Bulletin MSB 42–120/2,
dated June 7, 2017.
(3) If any crack(s) is found on any engine
exhaust clamp during any inspection
required by this AD, before further flight,
replace or modify the affected engine exhaust
clamp(s) following III.2 Action 2—
installation of additional exhaust clamp in
the INSTRUCTIONS section of DAI Work
Instruction WI–MSB 42–120, Revision 3,
dated July 6, 2017, as specified in DAI
Mandatory Service Bulletin MSB 42–120/2,
dated June 7, 2017.
(4) If during any replacement or
modification required by this AD the exhaust
clamp assembly cannot be installed without
side force using step 10 of III.2 Action 2—
installation of additional exhaust clamp in
the INSTRUCTIONS section of DAI Work
Instruction WI–MSB 42–120, Revision 3,
dated July 6, 2017, before further flight
contact the FAA at the address specified in
paragraph (i) of this AD to obtain and
incorporate an FAA-approved repair/
modification approved specifically for this
AD. The FAA will coordinate with the
European Aviation Safety Agency (EASA)
and DAI for the development of a repair/
modification to address the specific problem.
(5) The replacement required by
paragraphs (f)(1)(ii) or (f)(3) of this AD does
not terminate the repetitive inspections
required by paragraph (f)(2) of this AD when
DAI part numbers (P/N) D60–7806–00–01
and P/N D60–7806–00–02 engine exhaust
clamps are installed.
(6) Within 10 days after any inspection
where a cracked clamp is found or within 10
days after August 1, 2017 (the effective date
of this AD), whichever occurs later, report
the results to the FAA at the address
specified in paragraph (i)(1) of this AD and
to DAI at the address specified in paragraph
(j)(3) of this AD. Report all the information
included in the Appendix to this AD.
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(g) Paperwork Reduction Act Burden
Statement
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 5 minutes per
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave. SW., Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
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ER01AU17.000
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TIS after August 1, 2017 (the effective date
of this AD), whichever occurs later, do the
actions in paragraphs (f)(1)(i) and (ii) of this
AD.
(i) Inspect each engine exhaust clamp for
cracks following III.3 Action 3—Inspection of
exhaust clamp for cracks of the
INSTRUCTIONS section of Diamond Aircraft
Industries GmbH (DAI) Work Instruction WI–
MSB 42–120, Revision 3, dated July 6, 2017,
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Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations
(h) Alternative Methods of Compliance
(AMOCs)
(1) 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. 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 the attention of the person identified in
paragraph (i) of this AD.
(2) 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.
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(i) Related Information
(1) For more information about this AD,
contact Mike Kiesov, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4144; fax: (816) 329–
4090; email: mike.kiesov@faa.gov.
(2) Refer to MCAI EASA AD No.: 2017–
0120, dated July 13, 2017, for related
information. You may examine the MCAI on
the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2017–0640.
(j) 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) Diamond Aircraft Industries GmbH
Mandatory Service Bulletin MSB 42–120/2,
dated June 7, 2017.
(ii) Diamond Aircraft Industries GmbH
Work Instruction WI–MSB 42–120, Revision
3, dated July 6, 2017.
(3) For Diamond Aircraft Industries GmbH
service information identified in this AD,
contact Diamond Aircraft Industries GmbH,
N.A. Otto-Stra+e 5, A–2700 Wiener Neustadt,
Austria, telephone: +43 2622 26700; fax: +43
2622 26780; email: office@diamond-air.at;
Internet: https://www.diamondaircraft.com.
(4) You may view this 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
locating Docket No. FAA–2017–0640.
(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.
ll Left-hand Engine Only
ll Right-hand Engine Only
ll Both Engines
Number of Inspections Since Found
Cracked: llllllllllllllll
Clamp installed per: lll Section 8, lll
Section 9, or lllSection 10 of subsection
III.2 of Diamond Aircraft Industries GmbH
Work Instruction WI–MSB 42–120, Revision
3, dated July 6, 2017.
Clamp installed per the following Revision
level of Diamond Aircraft Industries GmbH
Work Instruction WI–MSB 42–120:
ll Original Issue
ll Revision 1
ll Revision 2
Issued in Kansas City, Missouri, on July 19,
2017.
Melvin Johnson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2017–15669 Filed 7–31–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0331; Directorate
Identifier 2016–NM–213–AD; Amendment
39–18971; AD 2017–15–11]
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, –106, –201, –202, –301, –311, and
–315 airplanes. This AD was prompted
by reports of undamped main landing
gear (MLG) extension in-service. This
AD requires replacement of the MLG
retraction actuator rod-ends on both
MLG assemblies. We are issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective September 5,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 5, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Bombardier, Inc., Q-Series Technical
Appendix to AD 2017–15–09
Help Desk, 123 Garratt Boulevard,
Airplane Serial Number: lllllllll Toronto, Ontario M3K 1Y5, Canada;
Total Hours TIS of the Airplane: lllll telephone 416–375–4000; fax 416–375–
Total Hours TIS Since Clamp was Installed:
4539; email thd.qseries@
Clamp was installed on:
aero.bombardier.com; Internet https://
VerDate Sep<11>2014
17:30 Jul 31, 2017
Jkt 241001
SUMMARY:
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
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–2017–
0331.
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–2017–
0331; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is Docket Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Fabio Buttitta, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office (ACO), 1600
Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone 516–228–7303; 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–8–102, –103, –106, –201, –202,
–301, –311, and –315 airplanes. The
NPRM published in the Federal
Register on May 2, 2017 (82 FR 20453)
(‘‘the NPRM’’). The NPRM was
prompted by reports of undamped MLG
extension in-service. The NPRM
proposed to require replacement of the
MLG retraction actuator rod-ends on
both MLG assemblies. We are issuing
this AD to prevent MLG undamped
extensions, which could result in MLG
structural failure, resulting in an unsafe
asymmetric landing gear configuration.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2016–36,
dated November 22, 2016 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
E:\FR\FM\01AUR1.SGM
01AUR1
Agencies
[Federal Register Volume 82, Number 146 (Tuesday, August 1, 2017)]
[Rules and Regulations]
[Pages 35630-35634]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-15669]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0640; Directorate Identifier 2017-CE-020-AD;
Amendment 39-18969; AD 2017-15-09]
RIN 2120-AA64
Airworthiness Directives; Diamond Aircraft Industries GmbH
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Diamond Aircraft Industries GmbH Model DA 42 airplanes. This AD
requires installing engine exhaust pipe clamps with spring washers,
repetitively inspecting the engine exhaust pipe clamps for cracks, and
replacing the clamps if found cracked. This AD was prompted by cracks
in the affected engine exhaust pipes, which could cause failure of the
propeller regulating valve because of hot exhaust gases coming from the
fractured pipes. We are issuing this AD to correct the unsafe condition
on these products.
[[Page 35631]]
DATES: This AD is effective August 1, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 1,
2017.
We must receive comments on this AD by September 15, 2017.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Diamond
Aircraft Industries GmbH, N.A. Otto-Stra[szlig]e 5, A-2700 Wiener
Neustadt, Austria, telephone: +43 2622 26700; fax: +43 2622 26780;
email: office@diamond-air.at; Internet: https://www.diamondaircraft.com.
You may review 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 locating Docket No. FAA-2017-0640.
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-2017-
0640; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (phone:
800-647-5527) is in the ADDRESSES section. Comments will be available
in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Mike Kiesov, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4144; fax: (816) 329-4090; email:
mike.kiesov@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
AD 2017-01-12, Amendment 39-18779 (82 FR 5359, January 18, 2017)
(``AD 2017-01-12'') requires either replacing the engine exhaust pipes
with new design pipes or installing clamps on the old design pipes on
Diamond Model DA 42 airplanes. AD 2017-01-12 is based on European
Aviation Safety Agency (EASA) AD No. 2016-0156R1, dated November 23,
2016. EASA is the Technical Agent for the Member States of the European
Community.
After issuance of AD 2017-01-12, we received reports of cracks on
the new design engine exhaust pipes. To address this cracking issue, we
issued AD 2017-11-08, Amendment 39-18907 (82 FR 24843, May 31, 2017)
(``AD 2017-11-08''). AD 2017-11-08 requires repetitively inspecting the
new design engine exhaust pipes installed on Diamond Model DA 42
airplanes and replacing any cracked pipes. AD 2017-11-08 is based on
EASA AD No. 2017-0090, dated May 17, 2017.
Since issuance of AD 2017-11-08, we received reports of cracks
found on the engine exhaust pipe clamps that were installed on the old
design engine exhaust pipes as a requirement in AD 2017-01-12. The FAA
and EASA are working concurrently on AD action for the United States
and Europe. EASA recently issued AD No.: 2017-0120, dated July 13,
2017, to address actions similar to that of this FAA AD.
This condition, if not corrected, could result in hot exhaust gases
coming from the fractured pipes and leading to an uncommanded engine
in-flight shutdown or overheat damage, which could result in a forced
landing, consequent damage, and occupant injury.
Related Service Information Under 1 CFR Part 51
Diamond Aircraft Industries GmbH has issued Mandatory Service
Bulletin MSB 42-120/2, dated June 7, 2017, and Work Instruction WI-MSB
42-120, Revision 3, dated July 6, 2017. In combination, the service
information describes procedures for installing engine exhaust pipe
clamps with spring washers and inspecting the engine exhaust pipe
clamps for cracks, with replacement if cracks are found. 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 the final rule.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
AD Requirements
This AD requires accomplishing the actions specified in the service
information described previously.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
affected engine exhaust pipes could crack and cause hot gases to leak
from fractured exhaust pipes and lead to an uncommanded engine in-
flight shutdown. Therefore, we find that notice and opportunity for
prior public comment are impracticable and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send any written data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include the docket number FAA-2017-0640 and
Directorate Identifier 2017-CE-020-AD at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this AD. We will
consider all comments received by the closing date and may amend this
AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Costs of Compliance
We estimate that this AD affects 130 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
[[Page 35632]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Install engine exhaust pipe clamps 4 work-hours x $85 per * $100 $440 $57,200
with spring washers. hour = $340 (for both
clamps).
Inspect engine exhaust pipe clamps.... 2 work-hours x $85 per N/A 170 22,100
hour = $170.
----------------------------------------------------------------------------------------------------------------
* (for both clamps)
We estimate the following costs to do any necessary replacements
that will be required based on the results of the inspections. We have
no way of determining the number of airplanes that may need these
replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replace cracked clamps..................... 4 work-hours x $85 per hour = $340 * $100 $440
(for both clamps).
----------------------------------------------------------------------------------------------------------------
* (for both clamps)
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
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
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 DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2017-15-09 Diamond Aircraft Industries GmbH: Amendment 39-18969;
Docket No. FAA-2017-0640; Directorate Identifier 2017-CE-020-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective August 1,
2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Diamond Aircraft Industries (DAI) GmbH Model
DA 42 airplanes, serial numbers 42.004 through 42.427 and 42.AC001
through 42.AC151, certificated in any category, that have:
(1) Either a Technify Motors GmbH TAE 125-02-99 or TAE 125-02-
114 engine installed; and
(2) DAI part numbers (P/N) D60-7806-00-01 and P/N D60-7806-00-02
engine exhaust clamps installed.
(d) Subject
Air Transport Association of America (ATA) Code 78: Engine
Exhaust.
(e) Reason
This AD was prompted by cracks in the affected engine exhaust
pipes, which could cause failure of the propeller regulating valve
because of hot exhaust gases coming from the fractured pipes. We are
issuing this AD to prevent an uncommanded engine in-flight shutdown
or overheat damage, which could result in a forced landing,
consequent damage, and occupant injury.
(f) Actions and Compliance
Unless already done, do the actions in paragraphs (f)(1) through
(6) of this AD.
(1) Before or upon accumulating 40 hours time-in-service (TIS)
on the affected engine exhaust pipes or within the next 10 hours
[[Page 35633]]
TIS after August 1, 2017 (the effective date of this AD), whichever
occurs later, do the actions in paragraphs (f)(1)(i) and (ii) of
this AD.
(i) Inspect each engine exhaust clamp for cracks following III.3
Action 3--Inspection of exhaust clamp for cracks of the INSTRUCTIONS
section of Diamond Aircraft Industries GmbH (DAI) Work Instruction
WI-MSB 42-120, Revision 3, dated July 6, 2017, as specified in DAI
Mandatory Service Bulletin MSB 42-120/2, dated June 7, 2017.
(ii) Reinstall any uncracked clamp or replace with a new clamp
and incorporate spring washers following III.2 Action 2--
installation of additional exhaust clamp in the INSTRUCTIONS section
of DAI Work Instruction WI-MSB 42-120, Revision 3, dated July 6,
2017, as specified in DAI Mandatory Service Bulletin MSB 42-120/2,
dated June 7, 2017. See figure 1 to paragraph (f)(1)(ii) of this AD
for additional information on the sequence of installation actions
as identified in DAI Work Instruction WI-MSB 42-120, Revision 3,
dated July 6, 2017. Credit is not given for installation of an
engine exhaust clamp installed following DAI Work Instruction WI-MSB
42-120, Revision 1, dated December 14, 2016, (installation of
exhaust clamp without spring washers), or DAI Work Instruction MSB-
42-120, Revision 2, dated June 7, 2017.
[GRAPHIC] [TIFF OMITTED] TR01AU17.000
(2) Within 25 hours TIS after the installation required by
paragraph (f)(1)(ii) of this AD and repetitively thereafter at
intervals not to exceed 25 hours TIS, inspect each engine exhaust
clamp for cracks following III.3 Action 3--Inspection of exhaust
clamp for cracks of the INSTRUCTIONS section DAI Work Instruction
WI-MSB 42-120, Revision 3, dated July 6, 2017, as specified in DAI
Mandatory Service Bulletin MSB 42-120/2, dated June 7, 2017.
(3) If any crack(s) is found on any engine exhaust clamp during
any inspection required by this AD, before further flight, replace
or modify the affected engine exhaust clamp(s) following III.2
Action 2--installation of additional exhaust clamp in the
INSTRUCTIONS section of DAI Work Instruction WI-MSB 42-120, Revision
3, dated July 6, 2017, as specified in DAI Mandatory Service
Bulletin MSB 42-120/2, dated June 7, 2017.
(4) If during any replacement or modification required by this
AD the exhaust clamp assembly cannot be installed without side force
using step 10 of III.2 Action 2--installation of additional exhaust
clamp in the INSTRUCTIONS section of DAI Work Instruction WI-MSB 42-
120, Revision 3, dated July 6, 2017, before further flight contact
the FAA at the address specified in paragraph (i) of this AD to
obtain and incorporate an FAA-approved repair/modification approved
specifically for this AD. The FAA will coordinate with the European
Aviation Safety Agency (EASA) and DAI for the development of a
repair/modification to address the specific problem.
(5) The replacement required by paragraphs (f)(1)(ii) or (f)(3)
of this AD does not terminate the repetitive inspections required by
paragraph (f)(2) of this AD when DAI part numbers (P/N) D60-7806-00-
01 and P/N D60-7806-00-02 engine exhaust clamps are installed.
(6) Within 10 days after any inspection where a cracked clamp is
found or within 10 days after August 1, 2017 (the effective date of
this AD), whichever occurs later, report the results to the FAA at
the address specified in paragraph (i)(1) of this AD and to DAI at
the address specified in paragraph (j)(3) of this AD. Report all the
information included in the Appendix to this AD.
(g) Paperwork Reduction Act Burden Statement
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty
for failure to comply with a collection of information subject to
the requirements of the Paperwork Reduction Act unless that
collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
[[Page 35634]]
(h) Alternative Methods of Compliance (AMOCs)
(1) 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. 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 the attention of the person
identified in paragraph (i) of this AD.
(2) 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.
(i) Related Information
(1) For more information about this AD, contact Mike Kiesov,
Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4144;
fax: (816) 329-4090; email: mike.kiesov@faa.gov.
(2) Refer to MCAI EASA AD No.: 2017-0120, dated July 13, 2017,
for related information. You may examine the MCAI on the Internet at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2017-0640.
(j) 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) Diamond Aircraft Industries GmbH Mandatory Service Bulletin
MSB 42-120/2, dated June 7, 2017.
(ii) Diamond Aircraft Industries GmbH Work Instruction WI-MSB
42-120, Revision 3, dated July 6, 2017.
(3) For Diamond Aircraft Industries GmbH service information
identified in this AD, contact Diamond Aircraft Industries GmbH,
N.A. Otto-Stra[szlig]e 5, A-2700 Wiener Neustadt, Austria,
telephone: +43 2622 26700; fax: +43 2622 26780; email:
office@diamond-air.at; Internet: https://www.diamondaircraft.com.
(4) You may view this 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 locating Docket No. FAA-2017-
0640.
(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.
Appendix to AD 2017-15-09
Airplane Serial Number:------------------------------------------------
Total Hours TIS of the Airplane:---------------------------------------
Total Hours TIS Since Clamp was Installed:-----------------------------
Clamp was installed on:
__ Left-hand Engine Only
__ Right-hand Engine Only
__ Both Engines
Number of Inspections Since Found Cracked:-----------------------------
Clamp installed per: ___ Section 8, ___ Section 9, or ___Section 10
of subsection III.2 of Diamond Aircraft Industries GmbH Work
Instruction WI-MSB 42-120, Revision 3, dated July 6, 2017.
Clamp installed per the following Revision level of Diamond Aircraft
Industries GmbH Work Instruction WI-MSB 42-120:
__ Original Issue
__ Revision 1
__ Revision 2
Issued in Kansas City, Missouri, on July 19, 2017.
Melvin Johnson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-15669 Filed 7-31-17; 8:45 am]
BILLING CODE 4910-13-P