Airworthiness Directives; Diamond Aircraft Industries GmbH Airplanes, 23780-23788 [2018-10580]
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23780
Federal Register / Vol. 83, No. 100 / Wednesday, May 23, 2018 / Rules and Regulations
(a) Applicability
This AD applies to Model AS332L2 and
Model EC225LP helicopters, certificated in
any category, with an extended aluminum
splice installed on frame 5295, except
helicopters with steel splice kit part number
332A08–2649–3072 installed.
Note 1 to paragraph (a) of this AD:
Helicopters with Modification (MOD)
0726517 have an extended aluminum splice
installed.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack on helicopter frame 5295. This
condition could result in structural failure of
the frame and subsequent loss of control of
the helicopter.
(c) Effective Date
This AD becomes effective June 27, 2018.
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
(1) Before a splice reaches 1,700 hours
time-in-service (TIS), within 50 hours TIS, or
before the helicopter reaches 11,950 hours
TIS, whichever occurs later, do the following:
(i) Install the rail support cut-out and
identify the right-hand and left-hand junction
profile in accordance with the
Accomplishment Instructions, paragraph
3.B.2, of Airbus Helicopters Alert Service
Bulletin (ASB) No. EC225–05A038, Revision
0, dated April 15, 2014 (ASB EC225–
05A038), or ASB No. AS332–05.00.97,
Revision 0, dated April 15, 2014 (ASB
AS332–05.00.97), whichever is applicable to
your helicopter.
(ii) Inspect each splice for a crack in the
area depicted as Area Y in Figure 3 of ASB
EC225–05A038 or ASB AS332–05.00.97,
whichever is applicable to your helicopter. If
a crack exists, repair or replace the splice
before further flight.
(2) Thereafter at intervals not to exceed 110
hours TIS, inspect each splice for a crack in
the area depicted as Area Y in Figure 3 of
ASB EC225–05A038 or ASB AS332–05.00.97.
If a crack exists, repair or replace the splice
before further flight.
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(f) Credit for Actions Previously Completed
Installing rail support cut-outs in
accordance with MOD 0728090 or Airbus
Helicopters Service Bulletin No. 05–019,
Revision 4, dated September 22, 2014, before
the effective date of this AD is considered
acceptable for compliance with the
corresponding actions specified in paragraph
(e)(1)(i) of this AD.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Section, Rotorcraft Standards Branch, FAA,
may approve AMOCs for this AD. Send your
proposal to: Gary Roach, Aviation Safety
Engineer, Regulations & Policy Section,
Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
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telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@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
(1) Airbus Helicopters Service Bulletin
(SB) No. 05–019, Revision 4, dated
September 22, 2014, and Eurocopter
Helicopters (now Airbus Helicopters) SB No.
53–003, Revision 4, and SB No. 53.01.52,
Revision 5, both dated July 23, 2010, which
are not incorporated by reference, contain
additional information about the subject of
this AD. For 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. You
may view the referenced service information
at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2014–0098–E, dated April 25, 2014. You
may view the EASA AD on the internet at
https://www.regulations.gov in Docket No.
FAA–2015–3883.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 5310, Fuselage Main, Structure.
(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 No. EC225–05A038, Revision 0,
dated April 15, 2014.
(ii) Airbus Helicopters Alert Service
Bulletin No. AS332–05.00.97, Revision 0,
dated April 15, 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 the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 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://
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www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on May 16,
2018.
Scott A. Horn,
Deputy Director for Regulatory Operations,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2018–10921 Filed 5–22–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0188; Product
Identifier 2018–CE–002–AD; Amendment
39–19285; AD 2018–10–10]
RIN 2120–AA64
Airworthiness Directives; Diamond
Aircraft Industries GmbH Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for comments
AGENCY:
We are superseding
Airworthiness Directive (AD) 2017–01–
12, AD 2017–11–08, and AD 2017–15–
09 for certain Diamond Aircraft
Industries GmbH Model DA 42
airplanes. This AD results from
mandatory continuing airworthiness
information (MCAI) issued by the
aviation authority of another country to
identify and address an unsafe
condition on an aviation product. The
MCAI describes the unsafe condition as
uncommanded engine shutdown during
flight due to failure of the propellerregulating valve caused by hot exhaust
gases coming from fractured engine
exhaust pipes. We are issuing this AD
to require actions to address the unsafe
condition on these products.
DATES: This AD is effective June 12,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 12, 2018.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of May 31, 2017 (82 FR
24843, May 31, 2017) and August 1,
2017 (82 FR 35630, August 1, 2017).
We must receive comments on this
AD by July 9, 2018.
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.
SUMMARY:
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Federal Register / Vol. 83, No. 100 / Wednesday, May 23, 2018 / Rules and Regulations
• 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-Strabe 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 copies of the referenced service
information at the FAA, Small Airplane
Standards Branch, 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–2018–0188.
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–2018–
0188; or in person at Docket Operations
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 Docket Operations
(telephone (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 Standards Branch, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4144; fax: (816) 329–4090; email:
mike.kiesov@faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued AD 2017–01–12,
Amendment 39–18779 (82 FR 5359,
January 18, 2017) (‘‘AD 2017–01–12’’);
AD 2017–11–08, Amendment 39–18907
(82 FR 24843, May 31, 2017) (‘‘AD
2017–11–08’’), and AD 2017–15–09,
Amendment 39–18969 (82 FR 35630,
August 1, 2017) (‘‘AD 2017–15–09’’).
Those ADs required actions intended to
address an unsafe condition on certain
Diamond Aircraft Industries GmbH
Model DA 42 airplanes and was based
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16:18 May 22, 2018
Jkt 244001
on mandatory continuing airworthiness
information (MCAI) originated by an
aviation authority of another country.
Since we issued AD 2017–01–12, AD
2017–11–08, and AD 2017–15–09, the
European Aviation Safety Agency
(EASA) has issued a new AD.
The EASA, which is the Technical
Agent for the Member States of the
European Community, has issued AD
No. 2017–0254, dated December 21,
2017 (referred to after this as ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
Two cases were reported of uncommanded
engine in-flight shutdown (IFSD) on DA 42
aeroplanes. Subsequent investigation
identified that these occurrences were due to
failure of the propeller regulating valve,
caused by hot exhaust gases coming from
fractured engine exhaust pipes. The initiating
cracks on the exhaust pipes were not
detected during previous inspections, since
those exhaust pipes are equipped with nonremovable heat shields that do not allow
inspection for certain sections of the exhaust
pipe.
This condition, if not corrected, could lead
to further cases of IFSD or overheat damage,
possibly resulting in a forced landing, with
consequent damage to the aeroplane and
injury to occupants.
To address this potential unsafe condition,
Diamond Aircraft Industries (DAI) developed
an exhaust pipe without a directly attached
integral heat shield that allows visual
inspection over the entire exhaust pipe
length. DAI issued Mandatory Service
Bulletin (MSB) 42–120 and relevant Working
Instruction (WI) WI–MSB 42–120, providing
instructions to install the modified exhaust
pipes. As an interim measure, an additional
bracket was designed to hold the exhaust
pipe in place in case of a pipe fracture. EASA
issued AD 2016–0156 (later revised),
requiring replacement of the exhaust pipes
with pipes having the new design, or
installation of the additional brackets.
After EASA AD 2016–0156R1 was issued,
cracks were found during inspection on
modified exhaust pipes. Further investigation
determined that, with the modified exhaust
pipe design, vibration leads to cracking.
Consequently, DAI published MSB 42–129,
providing instructions for inspection of
modified exhaust pipes, and EASA issued
AD 2017–0090, retaining the requirements of
EASA AD 2016–0156R1, which was
superseded, and additionally requiring
repetitive inspections of modified exhaust
pipes and, depending on findings, repair or
replacement.
After EASA AD 2017–0090 was issued,
cracks were found on additional brackets, as
previously installed per DAI WI–MSB 42–
120. Prompted by these findings, DAI revised
MSB 42–120 and the relevant part of WI–
MSB 42–120 (now at Revision 4), providing
improved instructions for the installation of
brackets, and additional instructions to
inspect those brackets. Consequently, EASA
issued AD 2017–0120, retaining the
requirements of EASA AD 2017–0090, which
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23781
was superseded, and additionally requiring
those actions for the additional brackets. That
[EASA] AD also required reinstallation of the
additional brackets in accordance with
improved instructions.
Since EASA AD 2017–0120 was issued, it
has been determined that installation of
additional exhaust pipe brackets, combined
with additional inspections, is the most
adequate solution to address the original
unsafe condition, while it was also
established that the modified exhaust pipes
without directly attached heat shield are not
adequate as replacement parts. Durability
analysis of the design is still under
investigation and further improvements in
the exhaust design are expected.
For the reasons described above, this
[EASA] AD partially retains the requirements
of EASA AD 2017–0120, which is
superseded, removing the option to install a
modified exhaust pipe without direct heat
shield, and adding inspection requirements
for aeroplanes modified in accordance with
Section III.2 of DAI WI–MSB 42–120
Revision 3 or later (installation of additional
brackets), and for aeroplanes on which an
exhaust pipe with directly attached heat
shield was re-installed in accordance with
DAI OSB 42–131.
You may examine the MCAI on the
internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2018–0188.
Relative Service Information Under 1
CFR Part 51
Diamond Aircraft Industries GmbH
(DAI) has issued Work Instruction WI–
MSB 42–120, Revision 3, dated July 6,
2017, Work Instruction WI–MSB 42–
120, Revision 4, dated December 20,
2018, Mandatory Service Bulletin MSB–
42–129, dated May 17, 2017, and Work
Instruction WI–OSB 42–131, dated
December 20, 2017. DAI Work
Instruction WI–MSB 42–120, Revision
3, dated July 6, 2017, and Work
Instruction WI–MSB 42–120, Revision
4, dated December 20, 2018, have
identical procedures for installing
additional engine exhaust pipe clamps
with spring washers on original engine
exhaust pipes. DAI Work Instruction
WI–MSB 42–120, Revision 4, dated
December 20, 2018, also includes
procedures for inspecting the original
engine exhaust pipe for cracks. DAI
Mandatory Service Bulletin MSB–42–
129, dated May 17, 2017, describes
procedures for inspecting the modified
engine exhaust pipe for cracks. DAI
Work Instruction WI–OSB 42–131,
dated December 20, 2017, describes
procedures for replacing either the
original or the modified engine exhaust
pipe 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 this AD.
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Federal Register / Vol. 83, No. 100 / Wednesday, May 23, 2018 / Rules and Regulations
FAA’s Determination and Requirements
of This AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with this State of
Design Authority, they have notified us
of the unsafe condition described in the
MCAI and service information
referenced above. We are issuing this
AD because we evaluated all
information provided by the State of
Design Authority and determined the
unsafe condition exists and is likely to
exist or develop on other products of the
same type design.
FAA’s 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
good cause that notice and opportunity
for prior public comment are
impracticable. In addition, for the
reason stated above, we find 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
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2018–0188;
Directorate Identifier 2018–CE–002–
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 will affect
130 products of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Cost per
product
Action
Labor cost
Parts cost
Inspect engine exhaust pipe .......................
Install additional engine exhaust pipe
clamps with spring washers.
Inspect engine exhaust pipe clamps ..........
2 work-hours × $85 = $170 ......................
4 work-hours × $85 per hour = $340 (for
both clamps).
2 work-hours × $85 per hour = $170 .......
N/A ..........................
$100 (for both
clamps).
N/A ..........................
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
Cost on U.S.
operators
$170
440
$22,100
57,300
170
22,100
determining the number of airplanes
that may need these replacements:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per
product
Replace cracked engine exhaust pipe ..................
Replace cracked engine exhaust pipe clamps .....
4 work-hours × $85 per hour = $340 ...................
4 work-hours × $85 per hour = $340 (for both
clamps).
$1,900 ...........................
$100 (for both clamps) ..
........................
$440
We estimate that 20 of the affected
airplanes have the ‘‘modified exhaust
pipes,’’ Diamond Aircraft Industries P/
N D60–9078–06–01_01 or Technify P/N
52–7810–H0014 01, installed that may
be subject to replacement by this AD
and 110 of the affected airplanes are
subject to the initial installation of
additional engine exhaust pipe clamps
and spring washers, inspections, and
the conditional replacement
requirement of this AD.
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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
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16:18 May 22, 2018
Jkt 244001
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.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
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In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to small airplanes, gliders,
balloons, airships, domestic business jet
transport airplanes, and associated
appliances to the Director of the Policy
and Innovation Division.
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
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Federal Register / Vol. 83, No. 100 / Wednesday, May 23, 2018 / Rules and Regulations
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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 39–18779 (82 FR
5359, January 18, 2017), Amendment
39–18907 (82 FR 24843, May 31, 2017),
and Amendment 39–18969 (82 FR
35630, August 1, 2017) and adding the
following new AD:
■
2018–10–10 Diamond Aircraft Industries
GmbH: Amendment 39–19285; Docket
No. FAA–2018–0188; Directorate
Identifier 2018–CE–002–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective June 12, 2018.
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(b) Affected ADs
This AD replaces 2017–01–12, Amendment
39–18779 (82 FR 5359, January 18, 2017)
(‘‘AD 2017–01–12’’); AD 2017–11–08,
Amendment 39–18907 (82 FR 24843, May 31,
2017) (‘‘AD 2017–11–08’’), and AD 2017–15–
09, Amendment 39–18969 (82 FR 35630,
August 1, 2017) (‘‘AD 2017–15–09’’).
(c) Applicability
This AD applies to Diamond Aircraft
Industries GmbH Model DA 42 airplanes,
serial numbers 42.004 through 42.427 and
42.AC001 through 42.AC151, certificated in
any category, that have either a TAE 125–02–
99 or TAE 125–02–114 engine installed, and:
(1) are equipped with an original engine
exhaust pipe, Diamond Aircraft Industries
(DAI) part number (P/N) D60–9078–06–01 or
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16:18 May 22, 2018
Jkt 244001
Technify P/Ns 52–7810–H0001 02, 52–7810–
H0001 03, 52–7810–H0001 04; or
(2) are equipped with a modified engine
exhaust pipe DAI P/N D60–9078–06–01_01
or Technify 52–7810–H0014 01.
(d) Subject
Air Transport Association of America
(ATA) Code 78: Engine Exhaust.
(e) Reason
This AD was prompted by mandatory
continuing airworthiness information (MCAI)
issued by the aviation authority of another
country to identify and address an unsafe
condition on an aviation product. It has been
determined that installation of additional
exhaust pipe brackets, combined with
additional inspections, is the most adequate
solution to address the original unsafe
condition, while it was also established that
the modified exhaust pipes without directly
attached heat shield are not adequate as
replacement parts. Durability analysis of the
design is still under investigation and further
improvements in the exhaust design are
expected. For these reasons, this AD removes
the option to install a modified exhaust pipe
without direct heat shield, adds inspection
requirements for airplanes modified in
accordance with Section III.2 of Diamond
Aircraft Industries (DAI) WI–MSB 42–120
Revision 3, dated July 6, 2017 (installation of
additional brackets), and for airplanes on
which an exhaust pipe with directly attached
heat shield was re-installed in accordance
with DAI Work Instruction WI–OSB 42–131,
dated December 20, 2017. The MCAI
describes the unsafe condition as
uncommanded engine shutdown during
flight due to failure of the propeller
regulating valve caused by hot exhaust gases
coming from fractured engine exhaust pipes.
We are issuing this AD to prevent failure of
the propeller regulating valve, which could
result in forced landing, consequent damage
and occupant injury.
(f) Compliance
Unless already done, do the following
actions.
(1) An airplane is only required to have the
actions of either (g) or (h) of this AD
accomplished depending on the
configuration.
(2) For the purpose of this AD, if the flight
hours accumulated since first installation of
an affected exhaust pipe or additional
exhaust pipe clamp is not known, use the
total hours time-in-service (TIS) accumulated
on the airplane.
(g) Actions for Airplanes With Installed
Original Engine Exhaust Pipes as of June 12,
2018 (the Effective Date of This AD)
See Appendix 1 to AD 2018–10–10 for a
chart of required actions. An original engine
exhaust pipe is defined in paragraph (c),
Applicability, of this AD.
(1) At the applicable compliance time in
paragraphs (g)(1)(i) and (ii) of this AD, and
repetitively thereafter at intervals not to
exceed 500 hours time-in-service (TIS),
inspect the installed engine exhaust pipe. Do
this inspection following section III.4—
Inspection of exhaust pipe in the
INSTRUCTIONS section of DAI Work
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23783
Instruction WI–MSB 42–120, Revision 4,
dated December 20, 2017.
(i) If the engine exhaust pipe has 1,300
hours TIS or less since first installed on an
airplane as of June 12, 2018 (the effective
date of this AD): Before or upon
accumulating 1,500 hours TIS since the
engine exhaust pipe was first installed on an
airplane, and repetitively thereafter at
intervals not to exceed 500 hours TIS.
(ii) If the engine exhaust pipe has more
than 1,300 hours TIS since first installed on
an airplane as of June 12, 2018 (the effective
date of this AD): Within the next 200 hours
TIS after June 12, 2018 (the effective date of
this AD), and repetitively thereafter at
intervals not to exceed 500 hours time-inservice (TIS).
(2) During any inspection required in
paragraph (g)(1) of this AD, if the engine
exhaust pipe does not pass the inspection
criteria, before further flight replace the
engine exhaust pipe following section III.1—
Re-installation of Exhaust Pipes with Directly
Attached Heat Shield in the INSTRUCTIONS
section of DAI Work Instruction WI–OSB 42–
131, dated December 20, 2017 (which
includes installing additional engine exhaust
pipe clamps, an exhaust sheet, and
incorporates spring washers). After
replacement continue with the 500-hour TIS
repetitive inspections.
(i) If only the engine exhaust pipe heat
shield is loose, a one-time single weld is
allowed following section III.3—Repair of
Heat Shields of DAI P/N D60–9078–06–01/
Technify P/Ns 52–7810–H0001 03 and 52–
7810–H0001 04 in the INSTRUCTIONS
section of DAI Work Instruction WI–OSB 42–
131, dated December 20, 2017. After a repair
of the heat shield, if a single weld point is
subsequently found cracked, the heat shield
is considered to be loose and the exhaust
pipe must be replaced. After replacement or
repair, continue with the 500-hour TIS
repetitive inspections.
(ii) Engine exhaust pipes re-qualified
following section III.2—Re-Qualification of
Exhaust Pipes DAI P/N D60–9078–06–01/
Technify P/Ns 52–7810–H0001 02, 52–7810–
H0001 03, or 52–7810–H0001 04 in the
INSTRUCTIONS section of DAI Work
Instruction WI–OSB 42–131, dated December
20, 2017, are considered to have accumulated
1,500 hours TIS.
(3) Before further flight after the initial
inspection required in paragraph (g)(1) of this
AD and if no cracks were found or a repair
to the exhaust pipe heat shield was done as
required in paragraph (g)(2)(i) of this AD,
then install additional engine exhaust pipe
clamps, DAI P/Ns D60–7806–00–01 and
D60–7806–00–02, and exhaust sheet, P/N
D60–7806–00–03, and incorporate spring
washers. Do the installations 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, or Revision 4, dated
December 20, 2017. See figure 1 to paragraph
(g)(3) 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 and
Revision 4, dated December 20, 2017.
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(4) During any engine exhaust pipe clamp
and exhaust sheet with spring washer
installation/replacement required in
paragraphs (g)(2), (3), (6), and (7) of this AD,
if 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, or
Revision 4, dated December 20, 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) At the applicable compliance time in
paragraphs (g)(5)(i) and (ii) of this AD and
repetitively thereafter at intervals not to
exceed 25 hours TIS, remove and inspect
each engine exhaust clamp for cracks. Do this
inspection following III.3 Action 3—
Inspection of exhaust clamp for cracks of the
INSTRUCTIONS section of DAI Work
Instruction WI–MSB 42–120, Revision 3,
VerDate Sep<11>2014
16:18 May 22, 2018
Jkt 244001
dated July 6, 2017, or Revision 4, dated
December 20, 2017.
(i) If the engine exhaust pipe clamp has
less than 40 hours TIS since first installed on
an airplane as of June 12, 2018 (the effective
date of this AD): Before or upon
accumulating 50 hours TIS since the engine
exhaust pipe clamp was first installed on an
airplane.
(ii) If the engine exhaust pipe clamp has
40 hours TIS or more since first installed on
an airplane as of June 12, 2018 (the effective
date of this AD): Within the next 10 hours
TIS after June 12, 2018 (the effective date of
this AD).
(6) Before further flight after any inspection
required in paragraph (g)(5) of this AD and
no crack is found, reinstall the engine
exhaust pipe 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, or Revision 4, dated
December 20, 2017. See figure 1 to paragraph
(g)(3) of this AD for additional information
on the sequence of installation actions as
identified in DAI Work Instruction WI–MSB
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
42–120, Revision 3, dated July 6, 2017, and
or Revision 4, dated December 20, 2017.
Continue with the 25-hour TIS repetitive
inspection as long as no cracks are found.
(7) Before further flight after any inspection
required in paragraph (g)(5) of this AD and
a cracked engine exhaust pipe clamp is
found, replace the cracked engine exhaust
pipe clamp with a new engine exhaust pipe
clamp and incorporate spring washers
following the service instructions specified
in paragraph (g)(6) of this AD. All newly
installed engine exhaust pipe clamps are
subject to an initial 50-hour TIS and
repetitive 25-hour TIS inspections for cracks
following the service instructions specified
in paragraph (g)(5) of this AD.
(h) Actions for Airplanes With Installed
Modified Engine Exhaust Pipes as of June 12,
2018 (the Effective Date of This AD)
See Appendix 2 to AD 2018–10–10 for a
chart of required actions. A modified engine
exhaust pipe is defined in paragraph (c),
Applicability, of this AD.
(1) At the applicable compliance time in
paragraphs (h)(1)(i) and (ii) of this AD and
repetitively thereafter at intervals not to
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exceed 50 hours TIS, inspect each engine
exhaust pipe for cracks. Do this inspection
following I.9 Accomplishment/Instructions
in DAI Mandatory Service Bulletin MSB–42–
129, dated May 17, 2017.
(i) If the engine exhaust pipe has less than
40 hours TIS since first installed on an
airplane as of June 12, 2018 (the effective
date of this AD): Before or upon
accumulating 50 hours TIS since the affected
engine exhaust pipe was first installed on an
airplane, repetitively thereafter inspect at
intervals not to exceed 50 hours TIS.
(ii) If the engine exhaust pipe has 40 hours
TIS or more since first installed on an
airplane as of June 12, 2018 (the effective
date of this AD): Within the next 10 hours
TIS after June 12, 2018 (the effective date of
this AD), repetitively thereafter inspect at
intervals not to exceed 50 hours TIS.
(2) If a crack is found during any
inspection required by paragraph (h)(1) of
this AD, before further flight replace the
engine exhaust pipe with an engine exhaust
pipe, DAI P/N D60–9078–06–01 or Technify
P/Ns 52–7810–H0001 02, 52–7810–H0001 03,
or 52–7810–H0001 04. Do the replacement
following section III.1—Re-installation of
Exhaust Pipes with Directly Attached Heat
Shield in the INSTRUCTIONS section of DAI
Work Instruction WI–OSB 42–131, dated
December 20, 2017, which includes installing
additional engine exhaust pipe clamps, an
exhaust sheet, and incorporates spring
washers.
(3) After installing an engine exhaust pipe,
DAI P/N D60–9078–06–01 or Technify P/Ns
52–7810–H0001 02, 52–7810–H0001 03, or
52–7810–H0001 04 (which includes
installing additional engine exhaust pipe
clamps, an exhaust sheet, and incorporates
spring washers), repetitively thereafter
inspect at intervals not to exceed 500 hours
TIS. Do this inspection following section
III.4—Inspection of exhaust pipe in the
INSTRUCTIONS section of DAI Work
Instruction WI–MSB 42–120, Revision 4,
dated December 20, 2017.
VerDate Sep<11>2014
16:18 May 22, 2018
Jkt 244001
(4) During any inspection required in
paragraph (h)(3) of this AD, if the engine
exhaust pipe does not pass the inspection
criteria, before further flight replace the
engine exhaust pipe following section III.1—
Re-installation of Exhaust Pipes with Directly
Attached Heat Shield in the INSTRUCTIONS
section of DAI Work Instruction WI–OSB 42–
131, dated December 20, 2017 (which
includes installing additional engine exhaust
pipe clamps, an exhaust sheet, and
incorporates spring washers). After
replacement, continue with the 500-hour TIS
repetitive inspections.
(i) If only the engine exhaust pipe heat
shield is loose, a one-time single weld is
allowed following section III.3—Repair of
Heat Shields of DAI P/N D60–9078–06–01/
Technify P/Ns 52–7810–H0001 03 and 52–
7810–H0001 04 in the INSTRUCTIONS
section of DAI Work Instruction WI–OSB 42–
131, dated December 20, 2017. After a repair
of the heat shield, if a single weld point is
subsequently found cracked, the heat shield
is considered to be loose and the exhaust
pipe must be replaced. After replacement or
repair, continue with the 500-hour TIS
repetitive inspections.
(ii) Engine exhaust pipes re-qualified
following section III.2—Re-Qualification of
Exhaust Pipes DAI P/N D60–9078–06–01/
Technify P/Ns 52–7810–H0001 02, 52–7810–
H0001 03, or 52–7810–H0001 04 in the
INSTRUCTIONS section of DAI Work
Instruction WI–OSB 42–131, dated December
20, 2017, are considered to have accumulated
1,500 hours TIS.
(5) During any engine exhaust pipe clamp,
exhaust sheet with spring washer
installation/replacement required in
paragraphs (h)(2), (4), (7), and (8) of this AD,
if 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, or
Revision 4, dated December 20, 2017, before
further flight contact the FAA at the address
PO 00000
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23785
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.
(6) At the applicable compliance time in
paragraphs (h)(6)(i) and (ii) of this AD and
repetitively thereafter at intervals not to
exceed 25 hours TIS, remove and inspect
each engine exhaust clamp for cracks. Do this
inspection following III.3 Action 3—
Inspection of exhaust clamp for cracks of the
INSTRUCTIONS section of DAI Work
Instruction WI–MSB 42–120, Revision 3,
dated July 6, 2017, or Revision 4, dated
December 20, 2017.
(i) If the engine exhaust pipe clamp has
less than 40 hours TIS since first installed on
an airplane as of June 12, 2018 (the effective
date of this AD): Before or upon
accumulating 50 hours TIS since the engine
exhaust pipe clamp was first installed on an
airplane.
(ii) If the engine exhaust pipe clamp has
40 hours TIS or more since first installed on
an airplane as of June 12, 2018
(the effective date of this AD): Within the
next 10 hours TIS after June 12, 2018 (the
effective date of this AD).
(7) Before further flight after any inspection
required in paragraph (h)(6) of this AD and
no crack is found, reinstall the engine
exhaust pipe 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, or Revision 4, dated
December 20, 2017. See figure 2 to paragraph
(g)(7) 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, and
or Revision 4, dated December 20, 2017.
Continue with the 25-hour TIS repetitive
inspection as long as no cracks are found.
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(8) Before further flight after any inspection
required in paragraph (h)(6) of this AD and
a cracked engine exhaust pipe clamp is
found, replace the cracked engine exhaust
pipe clamp with a new engine exhaust pipe
clamp and incorporate spring washers
following the service instructions specified
in paragraph (h)(7) of this AD. All newly
installed engine exhaust pipe clamps are
subject to an initial 50-hour TIS and
repetitive 25-hour TIS inspections for cracks
following the service instructions specified
in paragraph (h)() of this AD.
(i) 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: Mike Kiesov, Aerospace Engineer,
FAA, Small Airplane Standards Branch, 901
VerDate Sep<11>2014
16:18 May 22, 2018
Jkt 244001
Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4144; fax: (816)
329–4090; email: mike.kiesov@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.
(j) Related Information
Refer to MCAI EASA AD No. 2017–0254,
dated December 21, 2017, for related
information. You may examine the MCAI on
the internet at https://www.regulations.gov by
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
searching for and locating Docket No. FAA–
2018–0188.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on June 12, 2018.
(i) Diamond Aircraft Industries GmbH
Work Instruction WI–MSB 42–120, Revision
4, dated December 20, 2017.
(ii) Diamond Aircraft Industries GmbH
Work Instruction WI–OSB 42–131, dated
December 20, 2017.
(4) The following service information was
approved for IBR on May 31, 2017 (82 FR
24843, May 31, 2017).
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VerDate Sep<11>2014
16:18 May 22, 2018
Jkt 244001
contact Diamond Aircraft Industries GmbH,
N.A. Otto-Strasse 5, A–2700 Wiener
Neustadt, Austria, telephone: +43 2622
26700; fax: +43 2622 26780; email: office@
diamond-air.at; internet: https://
www.diamondaircraft.com.
(7) You may view this service information
at FAA, Small Airplane Branch, 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
PO 00000
Frm 00013
Fmt 4700
Sfmt 4725
by searching for locating Docket No. FAA–
2018–0188.
(8) You may view the 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.
BILLING CODE 4910–13–P
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(i) Diamond Aircraft Industries GmbH
Mandatory Service Bulletin MSB–42–129,
dated May 17, 2017.
(ii) Reserved.
(5) The following service information was
approved for IBR on August 1, 2017 (82 FR
35630, August 1, 2017).
(i) Diamond Aircraft Industries GmbH
Work Instruction WI–MSB 42–120, Revision
3, dated July 6, 2017.
(ii) Reserved.
(6) For Diamond Aircraft Industries GmbH
service information identified in this AD,
23787
Federal Register / Vol. 83, No. 100 / Wednesday, May 23, 2018 / Rules and Regulations
Issued in Kansas City, Missouri, on May
11, 2018.
Melvin J. Johnson,
Aircraft Certification Service, Deputy
Director, Policy and Innovation Division,
AIR–601.
DEPARTMENT OF TRANSPORTATION
[FR Doc. 2018–10580 Filed 5–22–18; 8:45 am]
[Docket No. FAA–2018–0447; Product
Identifier 2018–NM–080–AD; Amendment
39–19290; AD 2018–11–02]
daltland on DSKBBV9HB2PROD with RULES
BILLING CODE 4910–13–C
Federal Aviation Administration
Airworthiness Directives; Lockheed
Martin Corporation/Lockheed Martin
Aeronautics Company
Federal Aviation
Administration (FAA), DOT.
AGENCY:
16:18 May 22, 2018
Jkt 244001
We are adopting a new
airworthiness directive (AD) for all
Lockheed Martin Corporation/Lockheed
Martin Aeronautics Company Model
188A and 188C airplanes; and Model
P3A, P–3A, and P3B airplanes type
certificated under various other type
certificate holders. Certain variants of
Model 188A and 188C airplanes are
known as ‘‘P–3’’ series airplanes. P–3
series airplanes include but are not
limited to Model CP–140, NP–3A, P3A,
P–3A, P3B, P–3B, P–3C, P–3P, and WP–
3D airplanes. This AD requires a
borescope inspection of the aileron
SUMMARY:
14 CFR Part 39
RIN 2120–AA64
VerDate Sep<11>2014
Final rule; request for
comments.
ACTION:
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23788
]]>Agencies
[Federal Register Volume 83, Number 100 (Wednesday, May 23, 2018)]
[Rules and Regulations]
[Pages 23780-23788]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-10580]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0188; Product Identifier 2018-CE-002-AD; Amendment
39-19285; AD 2018-10-10]
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 superseding Airworthiness Directive (AD) 2017-01-12, AD
2017-11-08, and AD 2017-15-09 for certain Diamond Aircraft Industries
GmbH Model DA 42 airplanes. This AD results from mandatory continuing
airworthiness information (MCAI) issued by the aviation authority of
another country to identify and address an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as
uncommanded engine shutdown during flight due to failure of the
propeller-regulating valve caused by hot exhaust gases coming from
fractured engine exhaust pipes. We are issuing this AD to require
actions to address the unsafe condition on these products.
DATES: This AD is effective June 12, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 12,
2018.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of May 31,
2017 (82 FR 24843, May 31, 2017) and August 1, 2017 (82 FR 35630,
August 1, 2017).
We must receive comments on this AD by July 9, 2018.
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.
[[Page 23781]]
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[beta]e 5, A-2700 Wiener
Neustadt, Austria, telephone: +43 2622 26700; fax: +43 2622 26780;
email: [email protected]; internet: https://www.diamondaircraft.com.
You may review copies of the referenced service information at the FAA,
Small Airplane Standards Branch, 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-2018-0188.
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-2018-
0188; or in person at Docket Operations 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 Docket Operations (telephone (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 Standards Branch, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4144; fax: (816) 329-4090; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued AD 2017-01-12, Amendment 39-18779 (82 FR 5359, January
18, 2017) (``AD 2017-01-12''); AD 2017-11-08, Amendment 39-18907 (82 FR
24843, May 31, 2017) (``AD 2017-11-08''), and AD 2017-15-09, Amendment
39-18969 (82 FR 35630, August 1, 2017) (``AD 2017-15-09''). Those ADs
required actions intended to address an unsafe condition on certain
Diamond Aircraft Industries GmbH Model DA 42 airplanes and was based on
mandatory continuing airworthiness information (MCAI) originated by an
aviation authority of another country.
Since we issued AD 2017-01-12, AD 2017-11-08, and AD 2017-15-09,
the European Aviation Safety Agency (EASA) has issued a new AD.
The EASA, which is the Technical Agent for the Member States of the
European Community, has issued AD No. 2017-0254, dated December 21,
2017 (referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:
Two cases were reported of uncommanded engine in-flight shutdown
(IFSD) on DA 42 aeroplanes. Subsequent investigation identified that
these occurrences were due to failure of the propeller regulating
valve, caused by hot exhaust gases coming from fractured engine
exhaust pipes. The initiating cracks on the exhaust pipes were not
detected during previous inspections, since those exhaust pipes are
equipped with non-removable heat shields that do not allow
inspection for certain sections of the exhaust pipe.
This condition, if not corrected, could lead to further cases of
IFSD or overheat damage, possibly resulting in a forced landing,
with consequent damage to the aeroplane and injury to occupants.
To address this potential unsafe condition, Diamond Aircraft
Industries (DAI) developed an exhaust pipe without a directly
attached integral heat shield that allows visual inspection over the
entire exhaust pipe length. DAI issued Mandatory Service Bulletin
(MSB) 42-120 and relevant Working Instruction (WI) WI-MSB 42-120,
providing instructions to install the modified exhaust pipes. As an
interim measure, an additional bracket was designed to hold the
exhaust pipe in place in case of a pipe fracture. EASA issued AD
2016-0156 (later revised), requiring replacement of the exhaust
pipes with pipes having the new design, or installation of the
additional brackets.
After EASA AD 2016-0156R1 was issued, cracks were found during
inspection on modified exhaust pipes. Further investigation
determined that, with the modified exhaust pipe design, vibration
leads to cracking. Consequently, DAI published MSB 42-129, providing
instructions for inspection of modified exhaust pipes, and EASA
issued AD 2017-0090, retaining the requirements of EASA AD 2016-
0156R1, which was superseded, and additionally requiring repetitive
inspections of modified exhaust pipes and, depending on findings,
repair or replacement.
After EASA AD 2017-0090 was issued, cracks were found on
additional brackets, as previously installed per DAI WI-MSB 42-120.
Prompted by these findings, DAI revised MSB 42-120 and the relevant
part of WI-MSB 42-120 (now at Revision 4), providing improved
instructions for the installation of brackets, and additional
instructions to inspect those brackets. Consequently, EASA issued AD
2017-0120, retaining the requirements of EASA AD 2017-0090, which
was superseded, and additionally requiring those actions for the
additional brackets. That [EASA] AD also required reinstallation of
the additional brackets in accordance with improved instructions.
Since EASA AD 2017-0120 was issued, it has been determined that
installation of additional exhaust pipe brackets, combined with
additional inspections, is the most adequate solution to address the
original unsafe condition, while it was also established that the
modified exhaust pipes without directly attached heat shield are not
adequate as replacement parts. Durability analysis of the design is
still under investigation and further improvements in the exhaust
design are expected.
For the reasons described above, this [EASA] AD partially
retains the requirements of EASA AD 2017-0120, which is superseded,
removing the option to install a modified exhaust pipe without
direct heat shield, and adding inspection requirements for
aeroplanes modified in accordance with Section III.2 of DAI WI-MSB
42-120 Revision 3 or later (installation of additional brackets),
and for aeroplanes on which an exhaust pipe with directly attached
heat shield was re-installed in accordance with DAI OSB 42-131.
You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0188.
Relative Service Information Under 1 CFR Part 51
Diamond Aircraft Industries GmbH (DAI) has issued Work Instruction
WI-MSB 42-120, Revision 3, dated July 6, 2017, Work Instruction WI-MSB
42-120, Revision 4, dated December 20, 2018, Mandatory Service Bulletin
MSB-42-129, dated May 17, 2017, and Work Instruction WI-OSB 42-131,
dated December 20, 2017. DAI Work Instruction WI-MSB 42-120, Revision
3, dated July 6, 2017, and Work Instruction WI-MSB 42-120, Revision 4,
dated December 20, 2018, have identical procedures for installing
additional engine exhaust pipe clamps with spring washers on original
engine exhaust pipes. DAI Work Instruction WI-MSB 42-120, Revision 4,
dated December 20, 2018, also includes procedures for inspecting the
original engine exhaust pipe for cracks. DAI Mandatory Service Bulletin
MSB-42-129, dated May 17, 2017, describes procedures for inspecting the
modified engine exhaust pipe for cracks. DAI Work Instruction WI-OSB
42-131, dated December 20, 2017, describes procedures for replacing
either the original or the modified engine exhaust pipe 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 this
AD.
[[Page 23782]]
FAA's Determination and Requirements of This AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with this State of Design Authority, they
have notified us of the unsafe condition described in the MCAI and
service information referenced above. We are issuing this AD because we
evaluated all information provided by the State of Design Authority and
determined the unsafe condition exists and is likely to exist or
develop on other products of the same type design.
FAA's 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 good cause that notice and
opportunity for prior public comment are impracticable. In addition,
for the reason stated above, we find 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 we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2018-0188; Directorate
Identifier 2018-CE-002-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 will affect 130 products of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspect engine exhaust pipe...... 2 work-hours x $85 = N/A................ $170 $22,100
$170.
Install additional engine exhaust 4 work-hours x $85 per $100 (for both 440 57,300
pipe clamps with spring washers. hour = $340 (for both clamps).
clamps).
Inspect engine exhaust pipe 2 work-hours x $85 per N/A................ 170 22,100
clamps. hour = $170.
----------------------------------------------------------------------------------------------------------------
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 engine exhaust pipe... 4 work-hours x $85 per hour = $1,900.................. ..............
$340.
Replace cracked engine exhaust pipe 4 work-hours x $85 per hour = $100 (for both clamps).. $440
clamps. $340 (for both clamps).
----------------------------------------------------------------------------------------------------------------
We estimate that 20 of the affected airplanes have the ``modified
exhaust pipes,'' Diamond Aircraft Industries P/N D60-9078-06-01_01 or
Technify P/N 52-7810-H0014 01, installed that may be subject to
replacement by this AD and 110 of the affected airplanes are subject to
the initial installation of additional engine exhaust pipe clamps and
spring washers, inspections, and the conditional replacement
requirement of this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to small airplanes, gliders,
balloons, airships, domestic business jet transport airplanes, and
associated appliances to the Director of the Policy and Innovation
Division.
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
[[Page 23783]]
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-18779 (82 FR
5359, January 18, 2017), Amendment 39-18907 (82 FR 24843, May 31,
2017), and Amendment 39-18969 (82 FR 35630, August 1, 2017) and adding
the following new AD:
2018-10-10 Diamond Aircraft Industries GmbH: Amendment 39-19285;
Docket No. FAA-2018-0188; Directorate Identifier 2018-CE-002-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective June 12,
2018.
(b) Affected ADs
This AD replaces 2017-01-12, Amendment 39-18779 (82 FR 5359,
January 18, 2017) (``AD 2017-01-12''); AD 2017-11-08, Amendment 39-
18907 (82 FR 24843, May 31, 2017) (``AD 2017-11-08''), and AD 2017-
15-09, Amendment 39-18969 (82 FR 35630, August 1, 2017) (``AD 2017-
15-09'').
(c) Applicability
This AD applies to Diamond Aircraft Industries GmbH Model DA 42
airplanes, serial numbers 42.004 through 42.427 and 42.AC001 through
42.AC151, certificated in any category, that have either a TAE 125-
02-99 or TAE 125-02-114 engine installed, and:
(1) are equipped with an original engine exhaust pipe, Diamond
Aircraft Industries (DAI) part number (P/N) D60-9078-06-01 or
Technify P/Ns 52-7810-H0001 02, 52-7810-H0001 03, 52-7810-H0001 04;
or
(2) are equipped with a modified engine exhaust pipe DAI P/N
D60-9078-06-01_01 or Technify 52-7810-H0014 01.
(d) Subject
Air Transport Association of America (ATA) Code 78: Engine
Exhaust.
(e) Reason
This AD was prompted by mandatory continuing airworthiness
information (MCAI) issued by the aviation authority of another
country to identify and address an unsafe condition on an aviation
product. It has been determined that installation of additional
exhaust pipe brackets, combined with additional inspections, is the
most adequate solution to address the original unsafe condition,
while it was also established that the modified exhaust pipes
without directly attached heat shield are not adequate as
replacement parts. Durability analysis of the design is still under
investigation and further improvements in the exhaust design are
expected. For these reasons, this AD removes the option to install a
modified exhaust pipe without direct heat shield, adds inspection
requirements for airplanes modified in accordance with Section III.2
of Diamond Aircraft Industries (DAI) WI-MSB 42-120 Revision 3, dated
July 6, 2017 (installation of additional brackets), and for
airplanes on which an exhaust pipe with directly attached heat
shield was re-installed in accordance with DAI Work Instruction WI-
OSB 42-131, dated December 20, 2017. The MCAI describes the unsafe
condition as uncommanded engine shutdown during flight due to
failure of the propeller regulating valve caused by hot exhaust
gases coming from fractured engine exhaust pipes. We are issuing
this AD to prevent failure of the propeller regulating valve, which
could result in forced landing, consequent damage and occupant
injury.
(f) Compliance
Unless already done, do the following actions.
(1) An airplane is only required to have the actions of either
(g) or (h) of this AD accomplished depending on the configuration.
(2) For the purpose of this AD, if the flight hours accumulated
since first installation of an affected exhaust pipe or additional
exhaust pipe clamp is not known, use the total hours time-in-service
(TIS) accumulated on the airplane.
(g) Actions for Airplanes With Installed Original Engine Exhaust Pipes
as of June 12, 2018 (the Effective Date of This AD)
See Appendix 1 to AD 2018-10-10 for a chart of required actions.
An original engine exhaust pipe is defined in paragraph (c),
Applicability, of this AD.
(1) At the applicable compliance time in paragraphs (g)(1)(i)
and (ii) of this AD, and repetitively thereafter at intervals not to
exceed 500 hours time-in-service (TIS), inspect the installed engine
exhaust pipe. Do this inspection following section III.4--Inspection
of exhaust pipe in the INSTRUCTIONS section of DAI Work Instruction
WI-MSB 42-120, Revision 4, dated December 20, 2017.
(i) If the engine exhaust pipe has 1,300 hours TIS or less since
first installed on an airplane as of June 12, 2018 (the effective
date of this AD): Before or upon accumulating 1,500 hours TIS since
the engine exhaust pipe was first installed on an airplane, and
repetitively thereafter at intervals not to exceed 500 hours TIS.
(ii) If the engine exhaust pipe has more than 1,300 hours TIS
since first installed on an airplane as of June 12, 2018 (the
effective date of this AD): Within the next 200 hours TIS after June
12, 2018 (the effective date of this AD), and repetitively
thereafter at intervals not to exceed 500 hours time-in-service
(TIS).
(2) During any inspection required in paragraph (g)(1) of this
AD, if the engine exhaust pipe does not pass the inspection
criteria, before further flight replace the engine exhaust pipe
following section III.1--Re-installation of Exhaust Pipes with
Directly Attached Heat Shield in the INSTRUCTIONS section of DAI
Work Instruction WI-OSB 42-131, dated December 20, 2017 (which
includes installing additional engine exhaust pipe clamps, an
exhaust sheet, and incorporates spring washers). After replacement
continue with the 500-hour TIS repetitive inspections.
(i) If only the engine exhaust pipe heat shield is loose, a one-
time single weld is allowed following section III.3--Repair of Heat
Shields of DAI P/N D60-9078-06-01/Technify P/Ns 52-7810-H0001 03 and
52-7810-H0001 04 in the INSTRUCTIONS section of DAI Work Instruction
WI-OSB 42-131, dated December 20, 2017. After a repair of the heat
shield, if a single weld point is subsequently found cracked, the
heat shield is considered to be loose and the exhaust pipe must be
replaced. After replacement or repair, continue with the 500-hour
TIS repetitive inspections.
(ii) Engine exhaust pipes re-qualified following section III.2--
Re-Qualification of Exhaust Pipes DAI P/N D60-9078-06-01/Technify P/
Ns 52-7810-H0001 02, 52-7810-H0001 03, or 52-7810-H0001 04 in the
INSTRUCTIONS section of DAI Work Instruction WI-OSB 42-131, dated
December 20, 2017, are considered to have accumulated 1,500 hours
TIS.
(3) Before further flight after the initial inspection required
in paragraph (g)(1) of this AD and if no cracks were found or a
repair to the exhaust pipe heat shield was done as required in
paragraph (g)(2)(i) of this AD, then install additional engine
exhaust pipe clamps, DAI P/Ns D60-7806-00-01 and D60-7806-00-02, and
exhaust sheet, P/N D60-7806-00-03, and incorporate spring washers.
Do the installations 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, or
Revision 4, dated December 20, 2017. See figure 1 to paragraph
(g)(3) 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 and Revision 4, dated
December 20, 2017.
[[Page 23784]]
[GRAPHIC] [TIFF OMITTED] TR23MY18.000
(4) During any engine exhaust pipe clamp and exhaust sheet with
spring washer installation/replacement required in paragraphs
(g)(2), (3), (6), and (7) of this AD, if 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, or Revision 4, dated December 20, 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) At the applicable compliance time in paragraphs (g)(5)(i)
and (ii) of this AD and repetitively thereafter at intervals not to
exceed 25 hours TIS, remove and inspect each engine exhaust clamp
for cracks. Do this inspection following III.3 Action 3--Inspection
of exhaust clamp for cracks of the INSTRUCTIONS section of DAI Work
Instruction WI-MSB 42-120, Revision 3, dated July 6, 2017, or
Revision 4, dated December 20, 2017.
(i) If the engine exhaust pipe clamp has less than 40 hours TIS
since first installed on an airplane as of June 12, 2018 (the
effective date of this AD): Before or upon accumulating 50 hours TIS
since the engine exhaust pipe clamp was first installed on an
airplane.
(ii) If the engine exhaust pipe clamp has 40 hours TIS or more
since first installed on an airplane as of June 12, 2018 (the
effective date of this AD): Within the next 10 hours TIS after June
12, 2018 (the effective date of this AD).
(6) Before further flight after any inspection required in
paragraph (g)(5) of this AD and no crack is found, reinstall the
engine exhaust pipe 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, or Revision 4, dated December 20, 2017. See
figure 1 to paragraph (g)(3) 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, and or
Revision 4, dated December 20, 2017. Continue with the 25-hour TIS
repetitive inspection as long as no cracks are found.
(7) Before further flight after any inspection required in
paragraph (g)(5) of this AD and a cracked engine exhaust pipe clamp
is found, replace the cracked engine exhaust pipe clamp with a new
engine exhaust pipe clamp and incorporate spring washers following
the service instructions specified in paragraph (g)(6) of this AD.
All newly installed engine exhaust pipe clamps are subject to an
initial 50-hour TIS and repetitive 25-hour TIS inspections for
cracks following the service instructions specified in paragraph
(g)(5) of this AD.
(h) Actions for Airplanes With Installed Modified Engine Exhaust Pipes
as of June 12, 2018 (the Effective Date of This AD)
See Appendix 2 to AD 2018-10-10 for a chart of required actions.
A modified engine exhaust pipe is defined in paragraph (c),
Applicability, of this AD.
(1) At the applicable compliance time in paragraphs (h)(1)(i)
and (ii) of this AD and repetitively thereafter at intervals not to
[[Page 23785]]
exceed 50 hours TIS, inspect each engine exhaust pipe for cracks. Do
this inspection following I.9 Accomplishment/Instructions in DAI
Mandatory Service Bulletin MSB-42-129, dated May 17, 2017.
(i) If the engine exhaust pipe has less than 40 hours TIS since
first installed on an airplane as of June 12, 2018 (the effective
date of this AD): Before or upon accumulating 50 hours TIS since the
affected engine exhaust pipe was first installed on an airplane,
repetitively thereafter inspect at intervals not to exceed 50 hours
TIS.
(ii) If the engine exhaust pipe has 40 hours TIS or more since
first installed on an airplane as of June 12, 2018 (the effective
date of this AD): Within the next 10 hours TIS after June 12, 2018
(the effective date of this AD), repetitively thereafter inspect at
intervals not to exceed 50 hours TIS.
(2) If a crack is found during any inspection required by
paragraph (h)(1) of this AD, before further flight replace the
engine exhaust pipe with an engine exhaust pipe, DAI P/N D60-9078-
06-01 or Technify P/Ns 52-7810-H0001 02, 52-7810-H0001 03, or 52-
7810-H0001 04. Do the replacement following section III.1--Re-
installation of Exhaust Pipes with Directly Attached Heat Shield in
the INSTRUCTIONS section of DAI Work Instruction WI-OSB 42-131,
dated December 20, 2017, which includes installing additional engine
exhaust pipe clamps, an exhaust sheet, and incorporates spring
washers.
(3) After installing an engine exhaust pipe, DAI P/N D60-9078-
06-01 or Technify P/Ns 52-7810-H0001 02, 52-7810-H0001 03, or 52-
7810-H0001 04 (which includes installing additional engine exhaust
pipe clamps, an exhaust sheet, and incorporates spring washers),
repetitively thereafter inspect at intervals not to exceed 500 hours
TIS. Do this inspection following section III.4--Inspection of
exhaust pipe in the INSTRUCTIONS section of DAI Work Instruction WI-
MSB 42-120, Revision 4, dated December 20, 2017.
(4) During any inspection required in paragraph (h)(3) of this
AD, if the engine exhaust pipe does not pass the inspection
criteria, before further flight replace the engine exhaust pipe
following section III.1--Re-installation of Exhaust Pipes with
Directly Attached Heat Shield in the INSTRUCTIONS section of DAI
Work Instruction WI-OSB 42-131, dated December 20, 2017 (which
includes installing additional engine exhaust pipe clamps, an
exhaust sheet, and incorporates spring washers). After replacement,
continue with the 500-hour TIS repetitive inspections.
(i) If only the engine exhaust pipe heat shield is loose, a one-
time single weld is allowed following section III.3--Repair of Heat
Shields of DAI P/N D60-9078-06-01/Technify P/Ns 52-7810-H0001 03 and
52-7810-H0001 04 in the INSTRUCTIONS section of DAI Work Instruction
WI-OSB 42-131, dated December 20, 2017. After a repair of the heat
shield, if a single weld point is subsequently found cracked, the
heat shield is considered to be loose and the exhaust pipe must be
replaced. After replacement or repair, continue with the 500-hour
TIS repetitive inspections.
(ii) Engine exhaust pipes re-qualified following section III.2--
Re-Qualification of Exhaust Pipes DAI P/N D60-9078-06-01/Technify P/
Ns 52-7810-H0001 02, 52-7810-H0001 03, or 52-7810-H0001 04 in the
INSTRUCTIONS section of DAI Work Instruction WI-OSB 42-131, dated
December 20, 2017, are considered to have accumulated 1,500 hours
TIS.
(5) During any engine exhaust pipe clamp, exhaust sheet with
spring washer installation/replacement required in paragraphs
(h)(2), (4), (7), and (8) of this AD, if 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, or Revision 4, dated December 20, 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.
(6) At the applicable compliance time in paragraphs (h)(6)(i)
and (ii) of this AD and repetitively thereafter at intervals not to
exceed 25 hours TIS, remove and inspect each engine exhaust clamp
for cracks. Do this inspection following III.3 Action 3--Inspection
of exhaust clamp for cracks of the INSTRUCTIONS section of DAI Work
Instruction WI-MSB 42-120, Revision 3, dated July 6, 2017, or
Revision 4, dated December 20, 2017.
(i) If the engine exhaust pipe clamp has less than 40 hours TIS
since first installed on an airplane as of June 12, 2018 (the
effective date of this AD): Before or upon accumulating 50 hours TIS
since the engine exhaust pipe clamp was first installed on an
airplane.
(ii) If the engine exhaust pipe clamp has 40 hours TIS or more
since first installed on an airplane as of June 12, 2018
(the effective date of this AD): Within the next 10 hours TIS
after June 12, 2018 (the effective date of this AD).
(7) Before further flight after any inspection required in
paragraph (h)(6) of this AD and no crack is found, reinstall the
engine exhaust pipe 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, or Revision 4, dated December 20, 2017. See
figure 2 to paragraph (g)(7) 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, and or
Revision 4, dated December 20, 2017. Continue with the 25-hour TIS
repetitive inspection as long as no cracks are found.
[[Page 23786]]
[GRAPHIC] [TIFF OMITTED] TR23MY18.001
(8) Before further flight after any inspection required in
paragraph (h)(6) of this AD and a cracked engine exhaust pipe clamp
is found, replace the cracked engine exhaust pipe clamp with a new
engine exhaust pipe clamp and incorporate spring washers following
the service instructions specified in paragraph (h)(7) of this AD.
All newly installed engine exhaust pipe clamps are subject to an
initial 50-hour TIS and repetitive 25-hour TIS inspections for
cracks following the service instructions specified in paragraph
(h)() of this AD.
(i) 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: Mike Kiesov, Aerospace Engineer, FAA, Small
Airplane Standards Branch, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4144; fax: (816) 329-4090;
email: [email protected]. 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.
(j) Related Information
Refer to MCAI EASA AD No. 2017-0254, dated December 21, 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-2018-0188.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
June 12, 2018.
(i) Diamond Aircraft Industries GmbH Work Instruction WI-MSB 42-
120, Revision 4, dated December 20, 2017.
(ii) Diamond Aircraft Industries GmbH Work Instruction WI-OSB
42-131, dated December 20, 2017.
(4) The following service information was approved for IBR on
May 31, 2017 (82 FR 24843, May 31, 2017).
[[Page 23787]]
(i) Diamond Aircraft Industries GmbH Mandatory Service Bulletin
MSB-42-129, dated May 17, 2017.
(ii) Reserved.
(5) The following service information was approved for IBR on
August 1, 2017 (82 FR 35630, August 1, 2017).
(i) Diamond Aircraft Industries GmbH Work Instruction WI-MSB 42-
120, Revision 3, dated July 6, 2017.
(ii) Reserved.
(6) For Diamond Aircraft Industries GmbH service information
identified in this AD, contact Diamond Aircraft Industries GmbH,
N.A. Otto-Strasse 5, A-2700 Wiener Neustadt, Austria, telephone: +43
2622 26700; fax: +43 2622 26780; email: [email protected];
internet: https://www.diamondaircraft.com.
(7) You may view this service information at FAA, Small Airplane
Branch, 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-2018-0188.
(8) You may view the 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.
BILLING CODE 4910-13-P
[GRAPHIC] [TIFF OMITTED] TR23MY18.002
[[Page 23788]]
[GRAPHIC] [TIFF OMITTED] TR23MY18.003
Issued in Kansas City, Missouri, on May 11, 2018.
Melvin J. Johnson,
Aircraft Certification Service, Deputy Director, Policy and Innovation
Division, AIR-601.
[FR Doc. 2018-10580 Filed 5-22-18; 8:45 am]
BILLING CODE 4910-13-C
