Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters

[Federal Register Volume 86, Number 132 (Wednesday, July 14, 2021)]
[Rules and Regulations]
[Pages 37017-37019]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-14925]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0335; Project Identifier MCAI-2020-01665-R; 
Amendment 39-21632; AD 2021-14-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Airbus Helicopters Deutschland GmbH Model MBB-BK 117 A-1, MBB-BK 117 A-
3, MBB-BK 117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 
helicopters. This AD was prompted by a report of sudden severe 
vibrations and a cracked open blade trailing edge caused by a loosened 
lead inner weight. This AD requires inspections to determine if any 
bolted main rotor blades are installed, and replacement of the affected 
main rotor blades. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective August 18, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of August 18, 
2021.

ADDRESSES: For service information identified in this final rule, 
contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 
75052; phone: 972-641-0000 or 800-232-0323; fax: 972-641-3775; or at 
https://www.airbus.com/helicopters/services/-support.html. 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. Service information that is incorporated by reference 
is also available at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2021-0335.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0335; 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 
Luftfahrt-Bundesamt AD, 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: Kathleen Arrigotti, Aerospace 
Engineer, Large Aircraft Section, International Validation Branch, FAA, 
2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-231-
3218; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to all Airbus Helicopters 
Deutschland GmbH Model MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-4, 
MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters. The 
NPRM published in the Federal Register on April 26, 2021 (86 FR 21965). 
In the NPRM, the FAA proposed to require inspections to determine if 
any bolted main rotor blades are installed, and replacement of the 
affected main rotor blades. The NPRM was prompted by a report of sudden 
severe vibrations and a cracked open blade trailing edge caused by a 
loosened lead inner weight.
    German AD D-2005-115, effective March 15, 2005 (German AD D-2005-
115), issued by Luftfahrt-Bundesamt, which is the aviation authority 
for Germany, was issued to correct an unsafe condition for Eurocopter 
Deutschland (now Airbus Helicopters Deutschland GmbH) Model MBB-BK 117 
A-1, MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, 
and MBB-BK 117 C-1 helicopters. Luftfahrt-Bundesamt advises that during 
the flight of a BK117 severe vibrations suddenly occurred, stemming 
from a cracked open blade trailing edge, which was traced to a loosened 
lead inner weight bolt. Additional inspection revealed extreme cavities 
of the lead weight resulting from the bolting process, which was 
performed as a repair for main rotor blades with bulging in the area of 
the lead inner weights. This condition, if not addressed, could result 
in loss of control of the helicopter.
    Accordingly, German AD D-2005-115 requires an inspection and log 
card review to determine if any bolted main rotor blades are installed, 
and replacement of the affected main rotor blades.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or on the determination of 
the costs.

Conclusion

    These helicopters have been approved by the aviation authority of 
Germany and are approved for operation in the United States. Pursuant 
to the FAA's bilateral agreement with Germany (now a member of the 
European Union), Luftfahrt-Bundesamt, its technical representative, has 
notified the FAA of the unsafe condition described in its AD. The FAA 
reviewed the relevant data and determined that air safety requires 
adopting this AD as proposed. Accordingly, the FAA is issuing this AD 
to address the unsafe condition on these helicopters. Except for minor 
editorial changes, this AD is adopted as proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Eurocopter Alert Service Bulletin No. ASB-MBB-
BK117-10-125, dated February 14, 2005. This service information 
specifies procedures for an inspection (for cracking of the paint) and 
log card review (for a certain entry or equivalent) to determine if any 
bolted main rotor blades (i.e., main rotor blades with bolted lead 
inner weights) are installed, and replacement of the affected main 
rotor blades.
    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

    The FAA estimates that this AD affects 44 helicopters of U.S. 
Registry. Labor rates are estimated at $85 per work-hour. Based on 
these numbers, the FAA estimates the following costs to comply with 
this AD.

[[Page 37018]]



                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
3 work-hours x $85 per hour = $255...........................              $0             $255          $11,220
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary on-
condition replacements that would be required based on the results of 
any required actions. The FAA has no way of determining the number of 
helicopters that might need these on-condition replacements:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
           Labor cost                 Parts cost       Cost per product
------------------------------------------------------------------------
Up to 20 work-hours x $85 per     Up to $23,100 per   Up to $24,800 per
 hour = $1,700 per blade (up to    blade (up to 4      blade (up to 4
 4 blades).                        blades).            blades).
------------------------------------------------------------------------

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 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) 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.

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:

2021-14-05 Airbus Helicopters Deutschland GmbH: Amendment 39-21632; 
Docket No. FAA-2021-0335; Project Identifier MCAI-2020-01665-R.

(a) Effective Date

    This airworthiness directive (AD) is effective August 18, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Helicopters Deutschland GmbH Model 
MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK 117 B-1, MBB-
BK 117 B-2, and MBB-BK 117 C-1 helicopters, certificated in any 
category.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor 
Blades.

(e) Unsafe Condition

    This AD was prompted by a report of sudden severe vibrations and 
a cracked open blade trailing edge caused by a loosened lead inner 
weight. The FAA is issuing this AD to address bolted lead inner 
weights of the main rotor blade, which could loosen and cause 
cracking of the open blade trailing edge. The unsafe condition, if 
not addressed, could result in loss of control of the helicopter.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    Within 30 days after the effective date of this AD, review the 
log card (or equivalent record) and visually inspect each main rotor 
blade to determine if any bolted main rotor blades (i.e., main rotor 
blade with bolted lead inner weight) are installed in accordance 
with paragraphs 2.A.1., 2.B.1., 2.B.2., and 2.B.3. of the 
Accomplishment Instructions of Eurocopter Alert Service Bulletin No. 
ASB-MBB-BK117-10-125, dated February 14, 2005. If during the review, 
the total hours time-in-service (TIS) cannot be positively 
determined, this AD requires treating that part as having 
accumulated more than 3,000 total hours TIS. If any bolted main 
rotor blade (i.e., main rotor blade with bolted lead inner weight) 
is installed, replace the main rotor blade in accordance with 
paragraph 2.B.4. of the Accomplishment Instructions of Eurocopter 
Alert Service Bulletin ASB-MBB-BK117-10-125, dated February 14, 
2005, as follows:
    (1) For a bolted main rotor blade that has accumulated less than 
2,300 total hours TIS on the blade since bolting of the lead inner 
weight as of the effective date of this AD: Before accumulating 
2,500 total hours TIS on the blade since bolting of the lead inner 
weights.
    (2) For a bolted main rotor blade that has accumulated 2,300 
total hours TIS up to 3,000 total hours TIS inclusive, on the blade 
since bolting of the lead inner weight as of the effective date of 
this AD: Within 200 hours TIS after the effective date of this AD.
    (3) For a bolted main rotor blade that has accumulated more than 
3,000 total hours TIS on the blade since bolting of the lead inner 
weight as of the effective date of this AD: Within 50 hours TIS 
after the effective date of this AD.

[[Page 37019]]

(h) Contacting the Manufacturer To Determine TIS

    Where Eurocopter Alert Service Bulletin ASB-MBB-BK117-10-125, 
dated February 14, 2005, specifies to send a form to the 
manufacturer to determine TIS since bolting, this AD does not 
include that requirement.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, International Validation 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 International Validation Branch, send 
it to the attention of the person identified in paragraph (j)(1) of 
this AD. Information may be emailed to: [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

    (1) For more information about this AD, contact Kathleen 
Arrigotti, Aerospace Engineer, Large Aircraft Section, International 
Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; 
phone and fax: 206-231-3218; email: [email protected].
    (2) The subject of this AD is addressed in Luftfahrt-Bundesamt 
German AD D-2005-115, effective March 15, 2005. You may view the 
Luftfahrt-Bundesamt German AD at https://www.regulations.gov in 
Docket No. FAA-2021-0335.

(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) Eurocopter Alert Service Bulletin No. ASB-MBB-BK117-10-125, 
dated February 14, 2005.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; 
phone: 972-641-0000 or 800-232-0323; fax: 972-641-3775; or at 
https://www.airbus.com/helicopters/services/-support.html.
    (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, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on July 8, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-14925 Filed 7-13-21; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T01:49:53.892249+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

93ffa1e70011b5a2e198c93aa5e5bee5ad9571a6365c6ce06d3d8d4721f888e1

Text SHA-256

c6bc27e74a1149fcf9b772ea46f52cbb16115451982d8b2abca93e5922336f51