Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters, 46429-46432 [2019-18708]
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Federal Register / Vol. 84, No. 171 / Wednesday, September 4, 2019 / Rules and Regulations
paragraph (h) of AD 2018–10–12 for that
airplane only. All other requirements of
paragraph (h) of AD 2018–10–12 remain in
effect.
(j) Exceptions to Service Information
Specifications
(1) For purposes of determining
compliance with the requirements of this AD:
Where Boeing Alert Service Bulletin 737–
57A1269, Revision 2, dated October 11, 2018,
uses the phrase ‘‘the Revision 2 date of this
service bulletin,’’ this AD requires using ‘‘the
effective date of this AD.’’
(2) Where Boeing Alert Service Bulletin
737–57A1269, Revision 2, dated October 11,
2018, specifies contacting Boeing for repair
instructions: This AD requires doing the
repair before further flight using a method
approved in accordance with the procedures
specified in paragraph (k) of this AD.
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(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles ACO Branch,
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
certification office, send it to the attention of
the person identified in paragraph (l) of this
AD. Information may be emailed to: 9-ANMLAACO-AMOC-Requests@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 Company
Organization Designation Authorization
(ODA) that has been authorized by the
Manager, Los Angeles ACO Branch, FAA, 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.
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 Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(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 Des Moines, Washington, on
August 15, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–19012 Filed 9–3–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0643; Product
Identifier 2019–SW–013–AD; Amendment
39–19719; AD 2019–10–51]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters Deutschland GmbH
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
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which contained the requirements of
this amendment.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication identified in this
AD as of September 19, 2019.
The FAA must receive comments on
this AD by October 21, 2019.
You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this final rule, contact Air Methods
Corporation, 5500 South Quebec Street,
Suite 300, Greenwood Village, CO
80111; telephone 303–792–7557 or at
https://www.unitedrotorcraft.com/. 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. It is also available
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0643.
ADDRESSES:
Examining the AD Docket
The FAA is publishing a new
airworthiness directive (AD) for all
Airbus Helicopters Deutschland GmbH
(l) Related Information
Helicopters (Airbus) Model MBB–BK
For more information about this AD,
117 C–2 helicopters. Emergency AD
contact Peter Jarzomb, Aerospace Engineer,
2019–10–51 was sent previously to all
Airframe Section, FAA, Los Angeles ACO
known U.S. owners and operators of
Branch, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627– these helicopters. This AD requires, for
certain helicopters, inspecting the
5234; fax: 562–627–5210; email:
Peter.Jarzomb@faa.gov.
fuselage frame and providing certain
information to the FAA. This AD also
(m) Material Incorporated by Reference
prohibits installing certain components
(1) The Director of the Federal Register
as part of Supplemental Type Certificate
approved the incorporation by reference
(STC) SR00592DE on any helicopter.
(IBR) of the service information listed in this
This AD was prompted by reports of
paragraph under 5 U.S.C. 552(a) and 1 CFR
fatigue cracks in the fuselage frame. The
part 51.
(2) You must use this service information
FAA is issuing this AD to address the
as applicable to do the actions required by
unsafe condition on these products.
this AD, unless the AD specifies otherwise.
DATES: This AD is effective September
(i) Boeing Alert Service Bulletin 737–
57A1269, Revision 2, dated October 11, 2018. 19, 2019 to all persons except those
persons to whom it was made
(ii) [Reserved]
immediately effective by Emergency AD
(3) For service information identified in
this AD, contact Boeing Commercial
2019–10–51, issued on May 16, 2019,
SUMMARY:
46429
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0643; 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 final rule,
the regulatory evaluation, any
comments received, and other
information. The street address for
Docket Operations is listed above.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Cynthia Bradley, Aviation Safety
Engineer, Denver ACO Branch,
Compliance & Airworthiness Division,
FAA, 26805 East 68th Ave., Room 214,
Denver, CO 80249; telephone (303) 342–
1082; email cynthia.bradley@faa.gov.
SUPPLEMENTARY INFORMATION:
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Federal Register / Vol. 84, No. 171 / Wednesday, September 4, 2019 / Rules and Regulations
Discussion
On May 16, 2019, the FAA issued
Emergency AD 2019–10–51, which
requires for certain serial-numbered
helicopters, inspecting the fuselage
frame before further flight and providing
certain information to the FAA within
10 hours time-in-service (TIS) after the
required inspections. This AD also
prohibits installing certain components
as part of STC SR00592DE on any
helicopter. Emergency AD 2019–10–51
was sent previously to all known U.S.
owners and operators of these
helicopters. This action was prompted
by reports of fatigue cracks in the
fuselage frame, through the left-hand
door frame webs and frame cap at
station 4135. These cracks occurred on
certain serial numbered helicopters with
STC SR00592DE installed. The cracks
initiated under the doubler that
reinforces the door frame where
recessed medical wall fittings are
attached. In one case, the crack under
the doubler propagated through the
inboard frame cap and onto the inboard
web. This condition, if not corrected,
could result in excessive vibration, an
in-flight breakup, and subsequent loss of
control of the helicopter. Although the
exact cause of this unsafe condition is
still being investigated, the FAA has
determined that the cracks are a result
of the recessed medical wall rack
installation.
for cracks and loose rivets, and making
repairs if necessary or reinstalling the
inboard web of the box beam and the
cabin interior panels with the medical
wall rack to remain removed and
• Within 10 hours TIS after the
required inspections, providing the
inspection results, photographs of
inspected areas, total helicopter hours
TIS since installation of STC
SR00592DE, and the helicopter serial
number to the FAA.
This AD also prohibits installing on
any helicopter recessed medical wall
assembly part number (P/N) 778–1400–
001, wall mount fittings P/N 900–9959–
001, aft medical wall doubler P/N 900–
9989, and medical wall long doubler P/
N 900–6021 at stations 4135 and
4963.19 as part of STC SR00592DE.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Air Methods Alert
Service Bulletin ASB19–03, Revision IR,
dated May 6, 2019 (ASB). The ASB
requires removing the recessed medical
wall rack and describes procedures for
inspecting the door frame at the forward
medical wall rack doubler for cracks. If
cracks are discovered, the ASB specifies
that the aircraft is grounded until
repairs are made. 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.
The FAA considers this AD interim
action. The inspection reports that are
required by this AD will enable the FAA
to obtain better insight into the cause of
the cracking and eventually to develop
final action to address the unsafe
condition. Once final action has been
identified, the FAA might consider
further rulemaking. Also, the FAA is
currently considering requiring
repetitive inspections of the frame.
However, the planned compliance time
for those inspections would allow
enough time to provide notice and
opportunity for prior public comment
on the merits of the repetitive
inspections.
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FAA’s Determination
The FAA is issuing this AD after
evaluating all the relevant information
and determining the unsafe condition
described previously is likely to exist or
develop in other products of this same
type design.
AD Requirements
This AD requires the following for
certain serial-numbered helicopters:
• Before further flight, removing the
recessed medical wall rack, inspecting
the fuselage frame box beam structure
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Differences Between This AD and the
Service Information
This AD requires the inspections
before further flight, whereas the ASB
specifies within 10 flight hours. This
AD requires a single inspection before
further flight, whereas the ASB specifies
repetitive inspections every 200 hours
TIS following the initial inspection.
This AD does not require contacting Air
Methods for disposition on the
discovery of cracks, whereas the ASB
does.
Interim Action
FAA’s Justification and Determination
of the Effective Date
Section 553(b)(3)(B) of the
Administrative Procedure Act (APA) (5
U.S.C.) authorizes agencies to dispense
with notice and comment procedures
for rules when the agency, for ‘‘good
cause,’’ finds that those procedures are
‘‘impracticable, unnecessary, or contrary
to the public interest.’’ Under this
section, an agency, upon finding good
cause, may issue a final rule without
seeking comment prior to the
rulemaking.
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An unsafe condition exists that
required the immediate adoption of
Emergency AD 2019–10–51, issued on
May 16, 2019, to all known U.S. owners
and operators of these helicopters. The
FAA found that the risk to the flying
public justified waiving notice and
comment prior to adoption of this rule
because an unsafe condition existed
which required corrective actions before
further flight. These conditions still
exist and the AD is hereby published in
the Federal Register as an amendment
to section 39.13 of the Federal Aviation
Regulations (14 CFR 39.13) to make it
effective to all persons. Accordingly,
notice and opportunity for prior public
comment are impracticable and contrary
to public interest pursuant to 5 U.S.C.
553(b)(3)(B). In addition, for the reason
stated above, the FAA finds that good
cause exists pursuant to 5 U.S.C. 553(d)
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, the FAA invites you to send
any written data, views, or arguments
about this final rule. Send your
comments to an address listed under the
ADDRESSES section. Include the docket
number FAA–2019–0643 and Product
Identifier 2019–SW–013–AD at the
beginning of your comments. The FAA
specifically invites comments on the
overall regulatory, economic,
environmental, and energy aspects of
this final rule. The FAA will consider
all comments received by the closing
date and may amend this final rule
because of those comments.
The FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
FAA will also post a report
summarizing each substantive verbal
contact received about this final rule.
Costs of Compliance
The FAA estimates that this AD
affects 10 helicopters of U.S. registry
and estimates the following costs to
comply with this AD. Labor costs are
estimated at $85 per work-hour.
Removing the recessed medical wall
rack takes about 0.25 work-hour,
inspecting for cracks and loose rivets
takes about 8 work-hours, and reporting
the required information takes about 1
work-hour for an estimated cost of $786
per helicopter and $7,860 for the
affected U.S. fleet. Thirty-three blind
rivets at about $1.50 each are required
to reinstall the inboard web if there are
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Federal Register / Vol. 84, No. 171 / Wednesday, September 4, 2019 / Rules and Regulations
no cracks for a total cost of $50. Loose
fitting/doubler rivets cost about $1.50
each. The FAA has no way of estimating
the cost to repair any cracked structure.
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 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 currently 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 1 hour per response,
including the time for reviewing
instructions, searching existing data
sources, gathering and maintaining the
data needed, completing and reviewing
the collection of information. All
responses to this collection of
information are mandatory. Send
comments regarding this burden
estimate or any other aspect of this
collection of information, including
suggestions for reducing this burden to:
Information Collection Clearance
Officer, Federal Aviation
Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177–1524.
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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.
The FAA is 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
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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,
and
(2) Will not affect intrastate aviation
in Alaska.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2019–10–51 Airbus Helicopters
Deutschland GmbH: Amendment 39–
19719; Docket No. FAA–2019–0643;
Product Identifier 2019–SW–013–AD.
(a) Effective Date
This AD is effective September 19, 2019 to
all persons except those persons to whom it
was made immediately effective by
Emergency AD 2019–10–51, issued on May
16, 2019, which contained the requirements
of this amendment.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Helicopters
Deutschland GmbH Model MBB–BK 117 C–
2 helicopters, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC) of
America Code: 5311, Fuselage main frame.
(e) Unsafe Condition
This AD was prompted by reports of
fatigue cracks in a fuselage frame. The FAA
is issuing this AD to correct the unsafe
condition on these helicopters.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) For helicopters with serial numbers
9069, 9185, 9255, 9377, 9389, 9403, 9411,
9457, 9529, or 9637, before further flight:
(i) Remove the recessed medical wall rack
in accordance with Part 1, paragraphs 4.1.
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46431
through 4.3., of Air Methods Alert Service
Bulletin ASB19–03, Revision IR, dated May
6, 2019 (ASB).
(ii) Inspect the fuselage frame box beam
structure for cracks and loose rivets at station
4135 in accordance with Part 2, paragraphs
5.1 through 5.4., of the ASB, except you are
not required to contact Air Methods for
disposition if cracks are found. Instead, if
there is a crack, repair using a method
approved by the Manager, Denver ACO
Branch, Compliance & Airworthiness
Division, FAA, 26805 East 68th Ave., Room
214, Denver, CO 80249; telephone (303) 342–
1081; email: 9 Denver-Aircraft-Cert@faa.gov.
Replace any loose rivets.
(iii) If there are no cracks, reinstall the
inboard web of the box beam and the cabin
interior panels in accordance with Part 2,
paragraphs 5.5. and 5.6. of the ASB. Do not
reinstall the recessed medical wall rack.
(2) For helicopters with serial numbers
9069, 9185, 9255, 9377, 9389, 9403, 9411,
9457, 9529, or 9637, within 10 hours timein-service (TIS) after the required
inspections, provide the inspection results,
photographs of inspected areas, total
helicopter hours TIS since installation of
Supplemental Type Certificate (STC)
SR00592DE, and helicopter serial number to
the attention of the person identified in
paragraph (j) of this AD. This information is
required even if there are no cracks.
(3) For all helicopters, after the effective
date of this AD, do not install on any
helicopter recessed medical wall assembly
part number (P/N) 778–1400–001, wall
mount fittings P/N 900–9959–001, aft
medical wall doubler P/N 900–9989, and
medical wall long doubler P/N 900–6021 at
stations 4135 and 4963.19 as part of STC
SR00592DE.
(h) 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 currently 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 1 hour per
response, including the time for reviewing
instructions, searching existing data sources,
gathering and maintaining the data needed,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Send
comments regarding this burden estimate or
any other aspect of this collection of
information, including suggestions for
reducing this burden to: Information
Collection Clearance Officer, Federal
Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177–1524.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Denver ACO Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
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Federal Register / Vol. 84, No. 171 / Wednesday, September 4, 2019 / Rules and Regulations
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
certification office, send it to the attention of
the person identified in paragraph (j) of this
AD and notify the Denver ACO Branch of the
request by email at: 9-Denver-Aircraft-Cert@
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.
(j) Related Information
For more information about this AD,
contact Cynthia Bradley, Aviation Safety
Engineer, Denver ACO Branch, Compliance &
Airworthiness Division, FAA, 26805 East
68th Ave., Room 214, Denver, CO 80249;
telephone (303) 342–1082; email
cynthia.bradley@faa.gov.
(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 the AD specifies otherwise.
(i) Air Methods Alert Service Bulletin
ASB19–03, Revision IR, dated May 6, 2019.
(ii) [Reserved]
(3) For Air Methods service information
identified in this AD, contact Air Methods
Corporation, 5500 South Quebec Street, Suite
300, Greenwood Village, CO 80111;
telephone 303–792–7557 or at https://
www.unitedrotorcraft.com/.
(4) You may view this service information
at 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://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on August 19,
2019.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
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[FR Doc. 2019–18708 Filed 9–3–19; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0608; Product
Identifier 2019–NM–084–AD; Amendment
39–19713; AD 2019–16–10]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is adopting an
airworthiness directive (AD) for certain
The Boeing Company Model 787–8
airplanes. This AD requires a one-time
inspection of the horizontal stabilizer
pivot pin assemblies for misalignment
and incorrect gapping, and applicable
on-condition actions. This AD was
prompted by a report of possible
misalignment of the horizontal stabilizer
pivot pin lock ring, outer pivot pin, and
outboard spacer at final assembly. The
FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective September
19, 2019.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 19, 2019.
The FAA must receive comments on
this AD by October 21, 2019.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
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. You may view
this referenced service information at
the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA.
SUMMARY:
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For information on the availability of
this material at the FAA, call 206–231–
3195. It is also available on the internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2019–0608.
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–2019–
0608; 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 final rule, the regulatory
evaluation, any comments received, and
other information. The street address for
Docket Operations is listed above.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Greg
Rutar, Aerospace Engineer, Airframe
Section, FAA, Seattle ACO Branch, 2200
South 216th St., Des Moines, WA 98198;
phone and fax: 206–231–3529; email:
Greg.Rutar@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA has received a report
indicating possible misalignment of the
horizontal stabilizer pivot pin lock ring,
outer pivot pin, and outboard spacer at
final assembly. One operator reported a
left side pivot pin assembly that did not
have a visible gap between the outboard
nut and trap fitting. The pivot pin
outboard spacer was not set correctly
flush against the horizontal stabilizer
pivot bearing and outboard washer due
to a misaligned pivot pin lock ring. It
was determined that only certain
airplanes were possibly delivered with
this condition. This condition, if not
addressed, could result in decreased
lateral load capacity, the loss of pivot
pin retention parts, and consequent loss
of the horizontal stabilizer and loss of
control of the airplane.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing Alert
Requirements Bulletin B787–81205–
SB550009–00 RB, Issue 001, dated April
2, 2019. This service information
describes procedures for a one-time
detailed inspection of the horizontal
stabilizer pivot pin assemblies for
misalignment and incorrect gapping,
and applicable on-condition actions.
On-condition actions include replacing
any incorrectly installed horizontal
stabilizer pivot pin assembly. This
service information is reasonably
available because the interested parties
have access to it through their normal
E:\FR\FM\04SER1.SGM
04SER1
]]>Agencies
[Federal Register Volume 84, Number 171 (Wednesday, September 4, 2019)]
[Rules and Regulations]
[Pages 46429-46432]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-18708]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0643; Product Identifier 2019-SW-013-AD; Amendment
39-19719; AD 2019-10-51]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters Deutschland GmbH
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is publishing a new airworthiness directive (AD) for
all Airbus Helicopters Deutschland GmbH Helicopters (Airbus) Model MBB-
BK 117 C-2 helicopters. Emergency AD 2019-10-51 was sent previously to
all known U.S. owners and operators of these helicopters. This AD
requires, for certain helicopters, inspecting the fuselage frame and
providing certain information to the FAA. This AD also prohibits
installing certain components as part of Supplemental Type Certificate
(STC) SR00592DE on any helicopter. This AD was prompted by reports of
fatigue cracks in the fuselage frame. The FAA is issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective September 19, 2019 to all persons except
those persons to whom it was made immediately effective by Emergency AD
2019-10-51, issued on May 16, 2019, which contained the requirements of
this amendment.
The Director of the Federal Register approved the incorporation by
reference of a certain publication identified in this AD as of
September 19, 2019.
The FAA must receive comments on this AD by October 21, 2019.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this final rule, contact Air
Methods Corporation, 5500 South Quebec Street, Suite 300, Greenwood
Village, CO 80111; telephone 303-792-7557 or at https://www.unitedrotorcraft.com/. 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. It is also
available on the internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2019-0643.
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-2019-
0643; 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 final rule, the regulatory evaluation, any comments received, and
other information. The street address for Docket Operations is listed
above. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Cynthia Bradley, Aviation Safety
Engineer, Denver ACO Branch, Compliance & Airworthiness Division, FAA,
26805 East 68th Ave., Room 214, Denver, CO 80249; telephone (303) 342-
1082; email [email protected].
SUPPLEMENTARY INFORMATION:
[[Page 46430]]
Discussion
On May 16, 2019, the FAA issued Emergency AD 2019-10-51, which
requires for certain serial-numbered helicopters, inspecting the
fuselage frame before further flight and providing certain information
to the FAA within 10 hours time-in-service (TIS) after the required
inspections. This AD also prohibits installing certain components as
part of STC SR00592DE on any helicopter. Emergency AD 2019-10-51 was
sent previously to all known U.S. owners and operators of these
helicopters. This action was prompted by reports of fatigue cracks in
the fuselage frame, through the left-hand door frame webs and frame cap
at station 4135. These cracks occurred on certain serial numbered
helicopters with STC SR00592DE installed. The cracks initiated under
the doubler that reinforces the door frame where recessed medical wall
fittings are attached. In one case, the crack under the doubler
propagated through the inboard frame cap and onto the inboard web. This
condition, if not corrected, could result in excessive vibration, an
in-flight breakup, and subsequent loss of control of the helicopter.
Although the exact cause of this unsafe condition is still being
investigated, the FAA has determined that the cracks are a result of
the recessed medical wall rack installation.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Air Methods Alert Service Bulletin ASB19-03,
Revision IR, dated May 6, 2019 (ASB). The ASB requires removing the
recessed medical wall rack and describes procedures for inspecting the
door frame at the forward medical wall rack doubler for cracks. If
cracks are discovered, the ASB specifies that the aircraft is grounded
until repairs are made. 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.
FAA's Determination
The FAA is issuing this AD after evaluating all the relevant
information and determining the unsafe condition described previously
is likely to exist or develop in other products of this same type
design.
AD Requirements
This AD requires the following for certain serial-numbered
helicopters:
Before further flight, removing the recessed medical wall
rack, inspecting the fuselage frame box beam structure for cracks and
loose rivets, and making repairs if necessary or reinstalling the
inboard web of the box beam and the cabin interior panels with the
medical wall rack to remain removed and
Within 10 hours TIS after the required inspections,
providing the inspection results, photographs of inspected areas, total
helicopter hours TIS since installation of STC SR00592DE, and the
helicopter serial number to the FAA.
This AD also prohibits installing on any helicopter recessed
medical wall assembly part number (P/N) 778-1400-001, wall mount
fittings P/N 900-9959-001, aft medical wall doubler P/N 900-9989, and
medical wall long doubler P/N 900-6021 at stations 4135 and 4963.19 as
part of STC SR00592DE.
Differences Between This AD and the Service Information
This AD requires the inspections before further flight, whereas the
ASB specifies within 10 flight hours. This AD requires a single
inspection before further flight, whereas the ASB specifies repetitive
inspections every 200 hours TIS following the initial inspection. This
AD does not require contacting Air Methods for disposition on the
discovery of cracks, whereas the ASB does.
Interim Action
The FAA considers this AD interim action. The inspection reports
that are required by this AD will enable the FAA to obtain better
insight into the cause of the cracking and eventually to develop final
action to address the unsafe condition. Once final action has been
identified, the FAA might consider further rulemaking. Also, the FAA is
currently considering requiring repetitive inspections of the frame.
However, the planned compliance time for those inspections would allow
enough time to provide notice and opportunity for prior public comment
on the merits of the repetitive inspections.
FAA's Justification and Determination of the Effective Date
Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5
U.S.C.) authorizes agencies to dispense with notice and comment
procedures for rules when the agency, for ``good cause,'' finds that
those procedures are ``impracticable, unnecessary, or contrary to the
public interest.'' Under this section, an agency, upon finding good
cause, may issue a final rule without seeking comment prior to the
rulemaking.
An unsafe condition exists that required the immediate adoption of
Emergency AD 2019-10-51, issued on May 16, 2019, to all known U.S.
owners and operators of these helicopters. The FAA found that the risk
to the flying public justified waiving notice and comment prior to
adoption of this rule because an unsafe condition existed which
required corrective actions before further flight. These conditions
still exist and the AD is hereby published in the Federal Register as
an amendment to section 39.13 of the Federal Aviation Regulations (14
CFR 39.13) to make it effective to all persons. Accordingly, notice and
opportunity for prior public comment are impracticable and contrary to
public interest pursuant to 5 U.S.C. 553(b)(3)(B). In addition, for the
reason stated above, the FAA finds that good cause exists pursuant to 5
U.S.C. 553(d) 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, the FAA invites you to send any written data, views,
or arguments about this final rule. Send your comments to an address
listed under the ADDRESSES section. Include the docket number FAA-2019-
0643 and Product Identifier 2019-SW-013-AD at the beginning of your
comments. The FAA specifically invites comments on the overall
regulatory, economic, environmental, and energy aspects of this final
rule. The FAA will consider all comments received by the closing date
and may amend this final rule because of those comments.
The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact received about this final rule.
Costs of Compliance
The FAA estimates that this AD affects 10 helicopters of U.S.
registry and estimates the following costs to comply with this AD.
Labor costs are estimated at $85 per work-hour. Removing the recessed
medical wall rack takes about 0.25 work-hour, inspecting for cracks and
loose rivets takes about 8 work-hours, and reporting the required
information takes about 1 work-hour for an estimated cost of $786 per
helicopter and $7,860 for the affected U.S. fleet. Thirty-three blind
rivets at about $1.50 each are required to reinstall the inboard web if
there are
[[Page 46431]]
no cracks for a total cost of $50. Loose fitting/doubler rivets cost
about $1.50 each. The FAA has no way of estimating the cost to repair
any cracked structure.
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 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 currently 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 1 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, completing and reviewing the collection of
information. All responses to this collection of information are
mandatory. Send comments regarding this burden estimate or any other
aspect of this collection of information, including suggestions for
reducing this burden to: Information Collection Clearance Officer,
Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX
76177-1524.
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.
The FAA is 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, and
(2) Will not affect intrastate aviation in Alaska.
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):
2019-10-51 Airbus Helicopters Deutschland GmbH: Amendment 39-19719;
Docket No. FAA-2019-0643; Product Identifier 2019-SW-013-AD.
(a) Effective Date
This AD is effective September 19, 2019 to all persons except
those persons to whom it was made immediately effective by Emergency
AD 2019-10-51, issued on May 16, 2019, which contained the
requirements of this amendment.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Helicopters Deutschland GmbH Model
MBB-BK 117 C-2 helicopters, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC) of America Code: 5311,
Fuselage main frame.
(e) Unsafe Condition
This AD was prompted by reports of fatigue cracks in a fuselage
frame. The FAA is issuing this AD to correct the unsafe condition on
these helicopters.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) For helicopters with serial numbers 9069, 9185, 9255, 9377,
9389, 9403, 9411, 9457, 9529, or 9637, before further flight:
(i) Remove the recessed medical wall rack in accordance with
Part 1, paragraphs 4.1. through 4.3., of Air Methods Alert Service
Bulletin ASB19-03, Revision IR, dated May 6, 2019 (ASB).
(ii) Inspect the fuselage frame box beam structure for cracks
and loose rivets at station 4135 in accordance with Part 2,
paragraphs 5.1 through 5.4., of the ASB, except you are not required
to contact Air Methods for disposition if cracks are found. Instead,
if there is a crack, repair using a method approved by the Manager,
Denver ACO Branch, Compliance & Airworthiness Division, FAA, 26805
East 68th Ave., Room 214, Denver, CO 80249; telephone (303) 342-
1081; email: 9 [email protected]. Replace any loose
rivets.
(iii) If there are no cracks, reinstall the inboard web of the
box beam and the cabin interior panels in accordance with Part 2,
paragraphs 5.5. and 5.6. of the ASB. Do not reinstall the recessed
medical wall rack.
(2) For helicopters with serial numbers 9069, 9185, 9255, 9377,
9389, 9403, 9411, 9457, 9529, or 9637, within 10 hours time-in-
service (TIS) after the required inspections, provide the inspection
results, photographs of inspected areas, total helicopter hours TIS
since installation of Supplemental Type Certificate (STC) SR00592DE,
and helicopter serial number to the attention of the person
identified in paragraph (j) of this AD. This information is required
even if there are no cracks.
(3) For all helicopters, after the effective date of this AD, do
not install on any helicopter recessed medical wall assembly part
number (P/N) 778-1400-001, wall mount fittings P/N 900-9959-001, aft
medical wall doubler P/N 900-9989, and medical wall long doubler P/N
900-6021 at stations 4135 and 4963.19 as part of STC SR00592DE.
(h) 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 currently 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 1 hour per response, including the
time for reviewing instructions, searching existing data sources,
gathering and maintaining the data needed, completing and reviewing
the collection of information. All responses to this collection of
information are mandatory. Send comments regarding this burden
estimate or any other aspect of this collection of information,
including suggestions for reducing this burden to: Information
Collection Clearance Officer, Federal Aviation Administration, 10101
Hillwood Parkway, Fort Worth, TX 76177-1524.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Denver ACO Branch, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures
[[Page 46432]]
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 certification office, send it to the attention of
the person identified in paragraph (j) of this AD and notify the
Denver ACO Branch of the request by email at: [email protected]">9-[email protected].
(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.
(j) Related Information
For more information about this AD, contact Cynthia Bradley,
Aviation Safety Engineer, Denver ACO Branch, Compliance &
Airworthiness Division, FAA, 26805 East 68th Ave., Room 214, Denver,
CO 80249; telephone (303) 342-1082; email [email protected].
(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 the AD specifies otherwise.
(i) Air Methods Alert Service Bulletin ASB19-03, Revision IR,
dated May 6, 2019.
(ii) [Reserved]
(3) For Air Methods service information identified in this AD,
contact Air Methods Corporation, 5500 South Quebec Street, Suite
300, Greenwood Village, CO 80111; telephone 303-792-7557 or at
https://www.unitedrotorcraft.com/.
(4) You may view this service information at 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://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on August 19, 2019.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2019-18708 Filed 9-3-19; 8:45 am]
BILLING CODE 4910-13-P
