[Federal Register Volume 85, Number 144 (Monday, July 27, 2020)]
[Rules and Regulations]
[Pages 45066-45069]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-16166]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1123; Product Identifier 2017-SW-013-AD; Amendment 
39-21176; AD 2020-15-13]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2017-02-07 
for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-
BK 117 C-2 and Model MBB-BK 117 D-2 helicopters. AD 2017-02-07 required 
a repetitive inspection and a one-time torque of each hydraulic module 
plate assembly attachment point (attachment point). This new AD retains 
the initial inspection and torque requirements of AD 2017-02-07 and 
requires replacing the attachment point hardware. This AD was prompted 
by a terminating action has been developed to address the unsafe 
condition. The actions of this AD are intended to address an unsafe 
condition on these products.

DATES: This AD is effective August 31, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 31, 
2020.

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 
https://www.airbus.com/helicopters/services/technical-support.html. You 
may view this 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1123.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov in Docket No. FAA-2017-1123; 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 (now European Union Aviation Safety Agency) (EASA) AD, 
any service information that is incorporated by reference, any comments 
received, and other information. The street address for Docket 
Operations 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, AD Program Manager, 
Continued Operational Safety Branch, Airworthiness Products Section, 
General Aviation and Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort 
Worth, TX 76177; telephone 817-222-5110; email matthew.fuller@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a supplemental notice of proposed rulemaking (SNPRM) 
to amend 14 CFR part 39 to supersede AD 2017-02-07, Amendment 39-18786 
(82 FR 10267, February 10, 2017) (``AD 2017-02-07''). AD 2017-02-07 
applied to Airbus Helicopters Model MBB-BK 117 C-2 helicopters, serial 
numbers up to and including 9750, and Model MBB-BK 117 D-2 helicopters, 
serial numbers up to and including 20110, with a hydraulic module plate 
assembly part number B291M0003103 with a single locking attachment 
point installed. The SNPRM published in the Federal Register on 
February 27, 2020 (85 FR 11315). The FAA preceded the SNPRM with a 
notice of proposed rulemaking (NPRM) that published in the Federal 
Register on December 5, 2017 (82 FR 57390). The NPRM proposed to retain 
the initial inspection and torque requirements of AD 2017-

[[Page 45067]]

02-07 and require replacing each single locking attachment point 
mechanism with a double locking attachment point mechanism. The SNPRM 
proposed to add a requirement to reposition the aft grounding straps 
and inspect the clamping effect of the aft attachment points when the 
double locking attachment hardware is installed, and for helicopters 
that have previously installed the double locking attachment hardware, 
the SNPRM proposed to add an alternative clamp effect inspection 
requirement. The SNPRM also corrected the torque application 
requirement proposed in the NPRM to just each forward (not aft) 
attachment point.
    The NPRM was prompted by EASA AD No. 2017-0047, dated March 13, 
2017, issued by EASA, which is the Technical Agent for the Member 
States of the European Union, to correct an unsafe condition on Airbus 
Helicopters Deutschland GmbH (formerly Eurocopter Deutschland GmbH) 
Model MBB-BK117 C-2, MBB-BK117 C-2e, MBB-BK117 D-2 and MBB-BK117 D-2m 
helicopters. EASA advises that the hydraulic plate assembly on certain 
MBB-BK117 models has four attachment points on the fuselage secured by 
a single locking mechanism. According to EASA, a design reassessment 
revealed stiffness of the hydraulic plate may be insufficient to 
withstand the in-service loads in the event one of the four single 
locking attachment points fails. The EASA AD requires a repetitive 
inspection and one-time torque tightening of the attachment points 
until replacement of the single locking attachment hardware with double 
locking attachment hardware.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The FAA has considered the comment 
received. One commenter commented in support of the SNPRM.

FAA's Determination

    The FAA has reviewed the relevant information and determined that 
an 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.

Differences Between this AD and the EASA AD

    The EASA AD specifies performing the visual inspection of each 
attachment point at intervals not exceeding 400 flight hours. This AD 
does not require a repetitive inspection. This AD requires the 
replacement of each single locking attachment point mechanism with a 
double locking attachment point mechanism within 300 hours TIS instead, 
which makes subsequent inspections unnecessary. Since EASA has not 
revised or superseded its AD to incorporate Revision 3 of the service 
information, the EASA AD does not require inspecting the clamping 
effect of the aft joints, torque tightening the bolts, and corrective 
action if necessary for helicopters with a hydraulic module plate 
assembly with double locking attachment hardware installed in 
accordance with Airbus Helicopters Alert Service Bulletin (ASB) No. ASB 
MBB-BK117 C-2-29A-003 or ASB No. ASB MBB-BK117 D-2-29A-001, both 
Revision 2 and dated February 1, 2017.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-
003 for Model MBB-BK 117 C-2 helicopters and ASB No. ASB MBB-BK117 D-2-
29A-001 for Model MBB-BK 117 D-2 helicopters, both Revision 3 and dated 
December 19, 2017. Until the attachment points are modified with double 
locking attachment mechanisms, this service information specifies a 
repetitive visual inspection for condition and correct installation of 
the attachment points and replacing the affected parts if there is a 
crack. This service information also specifies a tightening torque 
check of the forward attachment points after the initial inspection and 
replacing the affected parts if torque cannot be applied. This service 
information specifies procedures to replace the single locking 
attachment hardware with double locking attachment hardware.
    For certain helicopters with a hydraulic module plate assembly with 
the double locking attachment hardware installed, this revision of the 
service information contains procedures to inspect the clamping effect 
of the aft attachment points and torque tightening the screw joints 
(bolts). If a bolt can be turned while applying this torque, the 
service information specifies instructions to replace the split pin, 
washer, and self-locking castellated nut, check the bolt for wear and 
replace it if necessary, change the position of the aft grounding 
strap, check the electrical bonding, and apply PU-Lacquer to the 
grounding connection.
    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.

Other Related Service Information

    The FAA also reviewed Airbus Helicopters ASB No. ASB MBB-BK117 C-2-
29A-003 for Model MBB-BK 117 C-2 helicopters and ASB No. ASB MBB-BK117 
D-2-29A-001 for Model MBB-BK 117 D-2 helicopters, both Revision 1 and 
dated October 14, 2016, and both Revision 2 and dated February 1, 2017. 
Revisions 1 and 2 of this service information contain the same visual 
inspection and torque tightening check procedures as Revision 3. 
Revision 2 of this service information adds the procedures to replace 
the single locking attachment hardware with double locking attachment 
hardware and contains the same forward locking attachment hardware 
replacement procedures as Revision 3.

Costs of Compliance

    The FAA estimates that this AD affects 167 helicopters of U.S. 
Registry. The FAA estimates that operators may incur the following 
costs in order to comply with this AD. The FAA estimates the cost of 
labor at $85 per work-hour.
    Visually inspecting the four attachment points takes about 0.75 
work-hour for an estimated cost of $64 per helicopter and $10,688 for 
the U.S. fleet. Inspecting the torque of the attachment points takes 
about 0.25 work-hour for an estimated cost of $21 per helicopter and 
$3,507 for the U.S. fleet. Replacing any of the attachment point parts 
takes a minimal amount of time and parts cost about $48 per attachment 
point. Installing four double locking attachment point mechanisms takes 
a minimal amount of time and parts cost about $400 per helicopter and 
$66,800 for the U.S. fleet.
    For certain double locking attachment hardware aft joints, 
inspecting the clamping effect and applying torque takes about 1 work-
hour for an estimated cost of $85 per helicopter. If required, 
inspecting and replacing parts, repositioning the aft grounding strap, 
inspecting the electrical bonding, and applying lacquer to the 
grounding connection takes about 0.5 work-hour and parts cost about $15 
for an estimated cost of $58 per helicopter.
    According to Airbus Helicopters' service information, some of the 
costs of this AD may be covered under warranty, thereby reducing the 
cost impact on affected individuals. The FAA does not control warranty 
coverage by Airbus Helicopters. Accordingly, the FAA has included all 
costs in this cost estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue

[[Page 45068]]

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

    The FAA has determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866,
    2. Will not affect intrastate aviation in Alaska, and
    3. 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 Airworthiness Directive (AD) 
2017-02-07, Amendment 39-18786 (82 FR 10267, February 10, 2017), and 
adding the following new AD:

2020-15-13 Airbus Helicopters Deutschland GmbH: Amendment 39-21176; 
Docket No. FAA-2017-1123; Product Identifier 2017-SW-013-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Deutschland GmbH Model 
MBB-BK 117 C-2 helicopters, serial numbers up to and including 9750, 
and Airbus Helicopters Deutschland GmbH Model MBB-BK 117 D-2 
helicopters, serial numbers up to and including 20110, certificated 
in any category, with a hydraulic module plate assembly part number 
B291M0003103 with a single locking attachment point installed or 
with a double locking attachment point installed before the 
effective date of this AD in accordance with Airbus Helicopters 
Alert Service Bulletin (ASB) No. ASB MBB-BK117 C-2-29A-003 (ASB MBB-
BK117 C-2-29A-003 Rev 2) or ASB No. ASB MBB-BK117 D-2-29A-001 (ASB 
MBB-BK117 D-2-29A-001 Rev 2), both Revision 2 and dated February 1, 
2017, as applicable to your model helicopter.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of a hydraulic 
module plate assembly attachment point (attachment point). This 
condition could result in loss of the hydraulic module plate and 
subsequent loss of control of the helicopter.

(c) Affected ADs

    This AD replaces AD 2017-02-07, Amendment 39-18786 (82 FR 10267, 
February 10, 2017).

(d) Effective Date

    This AD becomes effective August 31, 2020.

(e) 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.

(f) Required Actions

    Comply with either paragraphs (f)(1) and (2) of this AD, or 
paragraph (f)(3) of this AD, as applicable to your helicopter.
    (1) For helicopters with a hydraulic module plate assembly with 
a single locking attachment hardware installed, within 100 hours 
time-in-service (TIS):
    (i) Visually inspect the split pins, castellated nuts, plugs, 
nuts, and hexagon bolts of each attachment point for a crack and for 
proper installation by following the Accomplishment Instructions, 
paragraphs 3.B.1.3.a. through 3.B.1.3.d., of Airbus Helicopters ASB 
No. ASB MBB-BK117 C-2-29A-003 (ASB MBB-BK117 C-2-29A-003 Rev 3) or 
Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001 (ASB MBB-BK117 
D-2-29A-001 Rev 3), both Revision 3 and dated December 19, 2017, as 
applicable to your model helicopter. Replace any part that has a 
crack before further flight. If the split pins, castellated nuts, or 
hexagon bolts are not as depicted in Figures 1 and 2 of ASB MBB-
BK117 C-2-29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, before 
further flight, properly install them.
    (ii) Apply a torque of 9 to 10 Nm to the left-hand (LH) and 
right-hand (RH) nuts of each forward attachment point. If a torque 
of 9 to 10 Nm cannot be applied, replace the affected nut before 
further flight.
    (2) For helicopters with a hydraulic module plate assembly with 
a single locking attachment hardware installed, within 300 hours 
TIS:
    (i) Replace each forward single locking attachment hardware with 
double locking attachment hardware by following the Accomplishment 
Instructions, paragraphs 3.B.3.3. through 3.B.3.6. on page 11 of ASB 
MBB-BK117 C-2-29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, as 
applicable to your model helicopter, except you are not required to 
discard old parts.
    (ii) Replace each aft single locking attachment hardware with 
double locking attachment hardware and reposition the LH and RH aft 
grounding straps by following the Accomplishment Instructions, 
paragraphs 3.B.3.1. through 3.B.3.7. on page 13 of ASB MBB-BK117 C-
2-29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, as applicable to 
your model helicopter, except you are not required to discard old 
parts.
    (3) If you have replaced the attachment hardware with double 
locking attachment hardware before the effective date of this AD in 
accordance with ASB MBB-BK117 C-2-29A-003 Rev 2 or ASB MBB-BK117 D-
2-29A-001 Rev 2, as applicable to your model helicopter: Within 300 
hours TIS, inspect the clamping effect of the LH and RH aft screw 
joints (bolts) of the hydraulic module plate by following the 
Accomplishment Instructions, paragraph 3.B.5., of ASB MBB-BK117 C-2-
29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, as applicable to 
your model helicopter, except you are not required to discard old 
parts.

    Note 1 to paragraph (f)(3) of this AD:  Airbus Helicopters 
refers to bolts as ``screw joints.''

(g) Credit for Previous Actions

    Actions accomplished before the effective date of this AD in 
accordance with the procedures specified in the following are 
considered acceptable for compliance with the corresponding actions 
in paragraph (f)(1) of this AD:
    (1) AD 2017-02-07, Amendment 39-18786 (82 FR 10267, February 10, 
2017).
    (2) Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003, 
Revision 1, dated October 14, 2016.
    (3) Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003, 
Revision 2, dated February 1, 2017.
    (4) Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001, 
Revision 1, dated October 14, 2016.
    (5) Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001, 
Revision 2, dated February 1, 2017.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Rotorcraft Standards Branch, FAA, may approve 
AMOCs for this AD. Send your proposal to: Matt Fuller, AD Program 
Manager, Continued Operational Safety Branch, Airworthiness Products 
Section, General Aviation and Rotorcraft Unit, FAA, 10101 Hillwood 
Pkwy., Fort

[[Page 45069]]

Worth, TX 76177; telephone 817-222-5110; email 9-ASW-FTW-AMOC-Requests@faa.gov.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, the FAA suggests 
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.

(i) Additional Information

    (1) Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003 and ASB 
No. ASB MBB-BK117 D-2-29A-001, both Revision 1 and dated October 14, 
2016, and both Revision 2 and dated February 1, 2017, 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, 2701 N Forum Drive, Grand Prairie, TX 
75052; telephone 972-641-0000 or 800-232-0323; fax 972-641-3775; or 
at https://www.airbus.com/helicopters/services/technical-support.html. You may view a copy of the 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 (now European Union Aviation Safety Agency) AD No. 
2017-0047, dated March 13, 2017. You may view the EASA AD on the 
internet at https://www.regulations.gov in Docket No. FAA-2017-1123.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 2900, Hydraulic 
Power System.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information listed in this 
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Airbus Helicopters Alert Service Bulletin (ASB) No. ASB MBB-
BK117 C-2-29A-003, Revision 3, dated December 19, 2017.
    (ii) Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001, 
Revision 3, dated December 19, 2017.
    (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 https://www.airbus.com/helicopters/services/technical-support.html.
    (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, email fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on July 15, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-16166 Filed 7-24-20; 8:45 am]
BILLING CODE 4910-13-P


