[Federal Register Volume 84, Number 76 (Friday, April 19, 2019)]
[Rules and Regulations]
[Pages 16394-16396]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-07562]
[[Page 16394]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9395; Product Identifier 2016-SW-027-AD; Amendment
39-19618; AD 2019-07-07]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters Deutschland GmbH
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for various
Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-
BK117 and Model BO-105 helicopters. This AD requires removing the
swashplate bellows (bellows) and repetitively inspecting the swashplate
assembly. This AD was prompted by reports of loose and missing clamps
installed on bellows. The actions of this AD are intended to detect and
prevent an unsafe condition on these products.
DATES: This AD is effective May 24, 2019.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of May 24, 2019.
ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775;
or at http://www.airbushelicopters.com/techpub.
You may review the referenced service information at the FAA,
Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy.,
Room 6N-321, Fort Worth, TX 76177. It is also available on the internet
at http://www.regulations.gov by searching for and locating Docket No.
FAA-2016-9395.
Examining the AD Docket
You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9395; 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 European Aviation Safety Agency (EASA) AD, any
incorporated-by-reference service information, the economic evaluation,
any comments received, and other information. The street address for
Docket Operations (phone: 800-647-5527) is U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110;
email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
On April 20, 2018, at 83 FR 17510, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 by adding an AD that would apply to Airbus Helicopters
Model BO-105A, BO-105C, BO-105S, BO105LS A-3, MBB-BK 117A-1, MBB-BK
117A-3, MBB-BK 117A-4, MBB-BK 117B-1, MBB-BK 117B-2, MBB-BK 117C-1,
MBB-BK 117C-2, and MBB-BK 117D-2 helicopters. The NPRM proposed to
require removing the bellows and repetitively inspecting the swashplate
assembly. The proposed requirements were intended to detect and prevent
a loose bellows clamp. This condition can cause loss of the bellows,
contact of the bellows with the main rotor blades, main rotor mast, and
tail rotor, and subsequent loss of helicopter control.
The NPRM was prompted by AD No. 2016-0142, dated July 19, 2016,
issued by EASA (EASA AD 2016-0142), which is the Technical Agent for
the Member States of the European Union, to correct an unsafe condition
for Airbus Helicopters Model MBB-BK 117A-1, MBB-BK 117A-3, MBB-BK 117A-
4, MBB-BK 117B-1, MBB-BK 117B-2, MBB-BK 117C-1, MBB-BK 117C-2, MBB-BK
117C-2e, BO-105A, BO-105C, BO-105D, BO105S, BO-105LS A-3 helicopters.
EASA advises of several reports of a lower clamp found missing from
the bellows and damaging the swashplate bearing ring before becoming
detached. EASA states an investigation showed that over-torqueing can
damage the clamp, which may have caused the clamp to become loose and
detach. According to EASA, this condition, if not detected and
corrected, could lead to loss of a swashplate clamp, resulting in loss
of helicopter control. A detached clamp could damage the swashplate and
pitch link or strike the tail rotor. EASA states that its AD is
considered interim action and a further AD to implement a terminating
action will follow.
Changes to the Final Rule
On April 12, 2018, EASA revised its AD and issued AD No. 2016-
0142R1 (``EASA AD 2016-0142R1''). EASA AD 2016-0142R1 removed the
repetitive 100-hour and 400-hour inspections contained in EASA AD 2016-
0142. EASA determined that the repetitive inspections were no longer
required to address the unsafe condition. EASA states the 400-hour
inspections will be included in the airworthiness limitations section
of the aircraft maintenance manual, and the 100-hour inspections will
be deleted.
We have made the same determination because of the lack of
corrosion found on the parts since the bellows were removed. The 100-
hour repetitive inspections contained in the NPRM have been removed in
this Final rule.
Comments
We gave the public the opportunity to participate in developing
this AD, but we received no comments on the NPRM.
FAA's Determination
These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to our bilateral agreement
with the European Union, EASA has notified us of the unsafe condition
described in the EASA AD. We are issuing this AD because we evaluated
all information provided by EASA and determined the unsafe condition
exists and is likely to exist or develop on other helicopters of these
same type designs and that air safety and the public interest require
adopting the AD requirements as proposed, except for the change
previously described. This change is consistent with the intent of the
proposals in the NPRM and will not increase the economic burden on any
operator nor increase the scope of this AD.
Interim Action
We consider this AD to be an interim action. The design approval
holder is currently developing a modification that will address the
unsafe condition identified in this AD. Once this modification is
developed, approved, and available, we might consider additional
rulemaking.
Differences Between This AD and the EASA AD
EASA AD 2016-0142R1 has a different compliance time for helicopters
with new bellows, while this AD does not. This AD applies to Model MBB-
BK 117D-2 helicopters while EASA AD 2016-0142R1 does not. EASA AD 2016-
0142R1 applies to
[[Page 16395]]
Model BO-105D helicopters, while this AD does not. This AD requires
repetitively inspecting the swashplate every 400 hours time-in-service,
while EASA AD 2016-0142R1 does not.
Related Service Information Under 1 CFR Part 51
We reviewed Airbus Helicopters Alert Service Bulletin (ASB) BO105-
40A-107 for Model BO105 C-series, D-series and S-series helicopters;
ASB BO105 LS-40A-12 for Model BO-105LS A-3 helicopters; ASB MBB-BK117-
40A-115 for Model MBB-BK 117A-1, MBB-BK 117A-3, MBB-BK 117A-4, MBB-BK
117B-1, MBB-BK 117B-2, and MBB-BK 117C-1 helicopters; and ASB MBB-BK117
C-2-62A-007 for Model MBB-BK 117C-2 and MBB-BK 117C-2e helicopters.
These ASBs are all Revision 4 and all dated May 23, 2016. We also
reviewed Airbus Helicopters ASB MBB-BK117 D-2-62A-003, Revision 2,
dated May 23, 2016, for Model MBB-BK117 D-2 and MBB-BK117 D-2m
helicopters. This service information specifies removing the bellows
and repetitively inspecting the swashplate.
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.
Costs of Compliance
We estimate that this AD affects 286 helicopters of U.S. Registry
and that labor costs average $85 per work hour. Based on these
estimates, we expect the following costs:
Removing and inspecting the swashplate assembly requires 3
work-hours. No parts are needed for a cost of $255 per helicopter and
$72,930 for the U.S. fleet per inspection cycle.
Repairing a scratched support tube requires 3 work-hours.
No parts are needed for a cost of $255 per helicopter.
Replacing a corroded or damaged clamp requires 2 work-
hours. Parts cost $8 for a cost of $178 per helicopter.
Replacing corroded ball bearings requires 4 work-hours.
Parts cost $3,000 for a cost of $3,340 per helicopter.
Removing foreign objects from the outer deflection ring
requires 2 work-hours. No parts are needed for a cost of $170 per
helicopter.
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 helicopters identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction; and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.
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):
2019-07-07 Airbus Helicopters Deutschland GmbH: Amendment 39-19618;
Docket No. FAA-2016-9395; Product Identifier 2016-SW-027-AD.
(a) Applicability
This AD applies to Airbus Helicopters Deutschland GmbH Model BO-
105A, BO-105C, BO-105S, BO105LS A-3, MBB-BK 117A-1, MBB-BK 117A-3,
MBB-BK 117A-4, MBB-BK 117B-1, MBB-BK 117B-2, MBB-BK 117C-1, MBB-BK
117C-2, and MBB-BK 117D-2 helicopters, certificated in any category.
Note 1 to paragraph (a) of this AD: Helicopters with an MBB-BK
117C-2e designation are Model MBB-BK 117C-2 helicopters.
(b) Unsafe Condition
This AD defines the unsafe condition as a loose bellows clamp.
This condition can cause loss of the bellows, contact of the bellows
with the main rotor blades, main rotor mast, and tail rotor, and
subsequent loss of helicopter control.
(c) Effective Date
This AD becomes effective May 24, 2019.
(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) Within 50 hours time-in-service (TIS):
(i) Remove the swashplate bellows (bellows) part number (P/N)
105-10113.05, P/N 4638305043, P/N 4619305044, or B623M20X2240 from
the swashplate.
(ii) Inspect the swashplate by following the Accomplishment
Instructions, paragraph 3.B.1.(h) through 3.B.1.(k) of Airbus
Helicopters Alert Service Bulletin (ASB) BO105-40A-107, Revision 4,
dated May 23, 2016 (ASB BO105-40A-107); ASB BO105 LS-40A-12,
Revision 4, dated May 23, 2016 (ASB BO105 LS-40A-12); ASB MBB-BK117-
40A-115, Revision 4, dated May 23, 2016 (ASB MBB-BK117-40A-115); or
ASB MBB-BK117 C-2-62A-007, Revision 4, dated May 23, 2016 (ASB MBB-
BK117 C-2-62A-007); or paragraph 3.B.1.5 through 3.B.1.8 of Airbus
Helicopters ASB MBB-BK117 D-2-62A-003, Revision 2, dated May 23,
2016 (ASB MBB-BK117 D-2-62A-003); whichever is applicable to your
helicopter. If there is corrosion on a ball bearing, you are not
required to contact Airbus Helicopters customer support; instead,
before further flight, replace the ball bearing.
(2) Within 400 hours TIS after complying with the actions in
paragraph (1) of this AD, and thereafter at intervals not to exceed
400 hours TIS, inspect the swashplate by following the
Accomplishment Instructions, paragraph 3.B.3 of ASB BO105-40A-107,
ASB BO105 LS-40A-12, ASB MBB-BK117-40A-115, ASB MBB-BK117 C-2-62A-
007, or ASB MBB-BK117 D-2-62A-003.
(3) Do not install a bellows P/N 105-10113.05, P/N 4619305044,
or P/N 4638305043 or a gearbox with a bellows P/N 105-10113.05, P/N
4619305044, or P/N 4638305043 on any helicopter.
[[Page 16396]]
(f) 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:
Matt Fuller, Senior Aviation Safety Engineer, Safety Management
Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office, before operating any aircraft
complying with this AD through an AMOC.
(g) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency (EASA) AD No. 2016-0142, dated July 19, 2016, and EASA AD No.
2016-0142R1, dated April 12, 2018. You may view the EASA ADs on the
internet at http://www.regulations.gov in Docket No. FAA-2016-9395.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor
System.
(i) 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 BO105-40A-107,
Revision 4, dated May 23, 2016.
(ii) Airbus Helicopters Alert Service Bulletin BO105 LS-40A-12,
Revision 4, dated May 23, 2016.
(iii) Airbus Helicopters Alert Service Bulletin MBB-BK117-40A-
115, Revision 4, dated May 23, 2016.
(iv) Airbus Helicopters Alert Service Bulletin MBB-BK117 C-2-
62A-007, Revision 4, dated May 23, 2016.
(v) Airbus Helicopters Alert Service Bulletin MBB-BK117 D-2-62A-
003, Revision 2, dated May 23, 2016.
(3) For Airbus Helicopters service information identified in
this AD, contact Airbus Helicopters, 2701 N. Forum Drive, Grand
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax
(972) 641-3775; or at http://www.airbushelicopters.com/techpub.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on March 21, 2019.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2019-07562 Filed 4-18-19; 8:45 am]
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