Document ID: FAA-2022-1070-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Helicopters Deutschland GmbH (AHD) (Type Certificates previously held by Messerschmitt-Bolkow-Blohm [MBB], and Eurocopter Deutschland GmbH [ECD]) Helicopters
Posted Date: 2022-09-07T04:00Z

[Federal Register Volume 87, Number 172 (Wednesday, September 7, 2022)]
[Proposed Rules]
[Pages 54636-54641]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-19220]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-1070; Project Identifier MCAI-2021-00686-R]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
(AHD) (Type Certificates Previously Held by Messerschmitt-Bolkow-Blohm 
[MBB], and Eurocopter Deutschland GmbH [ECD]) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede airworthiness directive (AD) 77-
04-06, which applies to Messerschmitt-Bolkow-Blohm (MBB) (now Airbus 
Helicopters Deutschland GmbH (AHD)) Model BO-105A and BO-105 C 
helicopters; AD 2002-13-06, which applies to certain Eurocopter 
Deutschland GmbH (ECD) (now Airbus Helicopters Deutschland GmbH (AHD)) 
Model BO-105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 CB-4, BO-105 
CS-2, BO-105 CBS-2, BO-105S, and BO-105LS A-1 helicopters; AD 2016-25-
14, which applies to certain Airbus Helicopters Deutschland GmbH (AHD) 
Model BO-105LS A-3 helicopters; and AD 2021-10-14, which applies to 
certain Airbus Helicopters Deutschland GmbH (AHD) Model BO-105A, BO-

[[Page 54637]]

105C, BO-105S, and BO-105LS A-3 helicopters. AD 77-04-06 requires 
reducing the life limit on certain main rotor gearbox (MGB) supports. 
AD 2002-13-06 requires determining the calendar age, number of flights, 
and flight hours time-in-service (TIS) on certain tension-torsion (TT) 
straps; revising the Airworthiness Limitations Schedule (ALS) of the 
existing maintenance manual; removing and replacing each TT strap that 
has exceeded its life limit, or if the TT strap's total hours TIS or 
number of flights and age are not known; and modifying certain parts. 
AD 2016-25-14 requires establishing a life limit for certain TT straps 
and removing certain parts that have exceeded the new life limit. AD 
2021-10-14 requires replacement of certain TT straps with serviceable 
parts, and implementation of a new storage life limit for certain TT 
straps. Since the FAA issued those ADs, new and more restrictive 
airworthiness limitations have been issued. This proposed AD would 
require incorporating into existing maintenance records requirements 
(airworthiness limitations) as specified in a European Union Aviation 
Safety Agency (EASA) AD, which is proposed for incorporation by 
reference (IBR). This proposed AD would also prohibit the installation 
of certain part-numbered TT straps. The FAA is proposing this AD to 
address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by October 24, 
2022.

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 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 EASA material that is proposed for IBR in this NPRM, contact 
EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
8999 000; email [email protected]; internet www.easa.europa.eu. You 
may find the EASA material on the EASA website at https://ad.easa.europa.eu. For Airbus Helicopters service information 
identified in this NPRM, contact Airbus Helicopters, 2701 North Forum 
Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-
0323; fax (972) 641-3775; or at www.airbus.com/helicopters/services/technical-support.html. You may view this material 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. EASA material that is 
IBRed is also available at www.regulations.gov by searching for and 
locating Docket No. FAA-2022-1070.

Examining the AD Docket

    You may examine the AD docket at www.regulations.gov by searching 
for and locating Docket No. FAA-2022-1070; 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 NPRM, the EASA AD, any 
comments received, and other information. The street address for Docket 
Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Kristi Bradley, COS Program Manager, 
COS Program Management Section, Operational Safety Branch, Compliance & 
Airworthiness Division, FAA, 10101 Hillwood Parkway, Fort Worth, TX 
76177; telephone (817) 222-5110; email [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2022-1070; Project Identifier 
MCAI-2021-00686-R'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
this proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
www.regulations.gov, including any personal information you provide. 
The agency will also post a report summarizing each substantive verbal 
contact received about this NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to 
Kristi Bradley, COS Program Manager, COS Program Management Section, 
Operational Safety Branch, Compliance & Airworthiness Division, FAA, 
10101 Hillwood Parkway, Fort Worth, TX 76177; telephone (817) 222-5110; 
email [email protected] Any commentary that the FAA receives 
that is not specifically designated as CBI will be placed in the public 
docket for this rulemaking.

Background

    The FAA issued AD 77-04-06, Amendment 39-2835 (42 FR 9670, February 
17, 1977; amended 44 FR 46783, August 9, 1979) (AD 77-04-06) for 
Messerschmitt-Bolkow-Blohm (MBB) Model BO-105A and BO-105C helicopters. 
AD 77-04-06 was prompted by reports of internal corrosion of the MGB 
supports, which could significantly reduce the structural strength and 
service life. After AD 77-04-06 was issued, the FAA determined based on 
service experience and additional test investigations the total hours 
TIS for certain part-numbered MGB supports could be increased. 
Accordingly, the FAA amended AD 77-04-06 by issuing Amendment 39-3528 
(44 FR 46783, August 9, 1979), which increased the life limit for the 
MGB supports to 6,800 hours TIS.
    The FAA issued AD 2002-13-06, Amendment 39-12794 (67 FR 43526, June 
28, 2002) (AD 2002-13-06) for Eurocopter Deutschland GmbH (ECD) Model 
BO-105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 CB-4, BO-105S, BO-105 
CS-2, BO-105 CBS-2, BO-105 CBS-4, and BO-105LS A-1 helicopters, with 
main rotor (MR) head assembly, part number (P/N) 105-14101, and TT 
strap P/N 2602559 or 2606576, installed. AD 2002-13-06 was prompted by 
an accident in which an MR blade separated from a Eurocopter Model MBB-
BK 117 helicopter due to fatigue failure of a TT strap; the same part-
numbered TT strap is used on

[[Page 54638]]

Model BO-105 helicopters. AD 2002-13-06 was also prompted by the 
determination that an additional life limit for certain part-numbered 
TT straps needs to be established. AD 2002-13-06 requires creating a 
component log card or equivalent record and determining the calendar 
age, number of flights, and flight hours TIS on certain part-numbered 
TT straps; removing and replacing any TT strap that has exceeded its 
life limit, or the total hours TIS or number of flights and age are not 
known; and modifying certain MR heads before certain part-numbered TT 
straps are installed. AD 2002-13-06 also requires revising the ALS of 
the existing maintenance manual to reflect these new life limits.
    The FAA issued AD 2016-25-14, Amendment 39-18740 (81 FR 94944, 
December 27, 2016) (AD 2016-25-14) for Airbus Helicopters Deutschland 
GmbH Model BO-105LS A-3 helicopters with TT strap P/N 2604067 or P/N 
117-14110 installed. AD 2016-25-14 was prompted by the determination 
that life limits have been introduced for certain part-numbered TT 
straps installed on the helicopter lifting system, and during the 
revision of the ALS for the existing Model BO-105LS A-3 maintenance 
manual, the life limit for the TT strap was inadvertently deleted. AD 
2016-25-14 requires inspecting the helicopter records to determine if 
there is a life limit of 25,000 flights, or 10 years since the date of 
manufacturer, whichever occurs first, for the TT straps. Depending on 
the inspection results, AD 2016-25-14 requires establishing a life 
limit if none exists; revising the ALS of the existing maintenance 
manual, and creating a component history card or equivalent record to 
reflect this life limit; and replacing each TT strap that has reached 
or exceeded its life limit.
    The FAA issued AD 2021-10-14, Amendment 39-21547 (86 FR 27268, May 
20, 2021) (AD 2021-10-14) for Airbus Helicopters Deutschland GmbH Model 
BO-105A, BO-105C, BO-105S, and BO105LS A-3 helicopters equipped with a 
certain TT strap. AD 2021-10-14 was prompted by the FAA's determination 
that aging of the elastomeric material in a TT strap could affect the 
structural characteristics of the TT strap. AD 2021-10-14 requires 
replacement of certain TT straps with serviceable parts and 
implementation of a new storage life limit for TT straps.

Actions Since AD 77-04-06, AD 2002-13-06, AD 2016-25-14, and AD 2021-
10-14 Were Issued

    Since the FAA issued AD 77-04-06, AD 2002-13-06, AD 2016-25-14, and 
AD 2021-10-14, EASA, which is the Technical Agent for the Member States 
of the European Union, issued EASA AD 2021-0142, dated June 17, 2021 
(EASA AD 2021-0142), which superseded EASA AD 2019-0024, dated February 
4, 2019 (which prompted AD 2021-10-14); EASA AD 2015-0042, dated March 
9, 2015 (which prompted AD 2016-25-14); EASA AD 2013-0015, dated 
January 16, 2013; EASA AD 2010-0153, dated July 27, 2010; Luftfahrt-
Bundesamt (LBA) Germany AD 2001-281, dated October 18, 2001 (which 
prompted AD 2002-13-06); and LBA Germany AD 76-136/2, dated October 5, 
1978 (which prompted AD 77-04-06). EASA issued AD 2021-0142 to correct 
an unsafe condition for Airbus Helicopters Deutschland GmbH (AHD), 
formerly Eurocopter Deutschland GmbH, Eurocopter Hubschrauber 
Deutschland GmbH, Messerschmitt-B[ouml]lkow-Blohm GmbH; Eurocopter 
Canada Ltd, formerly Messerschmitt-B[ouml]lkow-Blohm Helicopter Canada 
Limited, Model BO105 A, BO105 C, BO105 D, BO105 S, BO105 LS A-1, and 
BO105 LS A-3 helicopters, all variants, all serial numbers, including 
BO105 LS A-3 helicopters modified in accordance with EASA Supplemental 
Type Certificate (STC) 10039633, or previously LBA Germany STC EMZ NR. 
0654/3058 (commercially known as ``Superlifter''). EASA advises the 
airworthiness limitations for AHD Model BO105 helicopters are defined 
and published in the AHD BO105 Aircraft Maintenance Manual (AMM) 
Chapter 101-15--ALS, Issue 2, Revision 31 (for BO105 A, BO105 C, BO105 
D, BO105 S, and BO105 LS A-1 helicopters); AHD BO105 LS A-3 AMM Chapter 
101-15--ALS, Issue 4, Revision 7 (for BO105 LS A-3 helicopters); and 
AHD BO105 LS A-3 AMM Appendix 010, Issue 1, Revision 4 (for BO105 LS A-
3 `Superlifter' helicopters); as applicable.
    EASA advises the instructions contained in ``the applicable ALS'' 
as defined in EASA AD 2021-0142 have been identified as mandatory 
actions for continued airworthiness, and failure to comply with those 
instructions could result in an unsafe condition. Accordingly, EASA AD 
2021-0142 requires accomplishment of the actions specified in ``the 
applicable ALS,'' as defined in EASA AD 2021-0142. The FAA is proposing 
this AD to address the failure of certain parts, which could result in 
the loss of control of the helicopter. See EASA AD 2021-0142 for 
additional background information.
    Additionally, the actions required to address the unsafe conditions 
in AD 77-04-06, AD 2002-13-06, AD 2016-25-14, and AD 2021-10-14 are 
included in ``the applicable ALS,'' as defined in EASA AD 2021-0142. 
Therefore, the FAA is proposing to supersede AD 77-04-06, AD 2002-13-
06, AD 2016-25-14, and AD 2021-10-14 in order to reduce the burden on 
operators by requiring compliance with a single FAA AD in lieu of 
multiple FAA ADs.
    AD 77-04-06 requires replacing MGB support P/N 105-10161 and 105-
10162 with serviceable supports within the next 10 hours TIS after the 
effective date of AD 77-04-06 or prior to the accumulation of 6,800 
hours TIS on the supports, whichever occurs later, and, thereafter, 
continue to replace the supports prior to the accumulation of 6,800 
hours TIS. EASA AD 2021-0142 requires incorporating ``the applicable 
ALS,'' as defined in EASA AD 2021-0142, which identifies the same life 
limit for these MGB supports as that required by AD 77-04-06. 
Therefore, the FAA is proposing to supersede AD 77-04-06 in order to 
reduce the burden on operators.
    AD 2002-13-06 requires creating a component log card or equivalent 
record and determining the calendar age, number of flights, and flight 
hours TIS on certain part-numbered TT straps; inspecting and replacing 
certain TT straps, as necessary; and modifying certain main rotor heads 
if alternate TT straps are installed. This action also establishes an 
additional life limit for certain part-numbered TT straps. EASA AD 
2021-0142 requires incorporating the limitations described in ``the 
applicable ALS,'' as defined in EASA AD 2021-0142, into the approved 
aircraft maintenance program and introduces a new storage life limit of 
5 years for certain TT straps.
    AD 2016-25-14 requires inspecting the ALS of the applicable 
maintenance manual for your helicopter or the Instructions for 
Continued Airworthiness (ICA) and the component history card or 
equivalent record for TT strap P/N 2604067 and P/N 117-14110 and 
determining whether those records specify a life limit of 25,000 
flights or 10 years since the date of manufacture, whichever occurs 
first. If the ALS, ICA, component history card, or equivalent record do 
not specify a life limit for the TT straps, or if they specify a life 
limit other than 25,000 flights or 10 years since the date of 
manufacture, whichever occurs first, AD 2016-25-14 requires revising 
the existing ALS or ICA by establishing a life limit for each TT strap 
P/N 2604067 and P/N 117-14110 of 25,000 flights or 10 years since the 
date of manufacture, whichever occurs first. AD 2016-25-14 also 
requires removing from service each TT

[[Page 54639]]

strap that has reached or exceeded its life limit. EASA AD 2021-0142 
requires incorporating ``the applicable ALS,'' as defined in EASA AD 
2021-0142, into the approved aircraft maintenance program and 
introduces a new storage life limit of 5 years for certain TT straps.
    AD 2021-10-14 requires replacement of certain TT straps with 
serviceable parts and implementation of a new storage life limit for TT 
straps. After AD 2021-10-14 was issued, EASA issued AD 2021-0142, which 
requires incorporating ``the applicable ALS,'' as defined in EASA AD 
2021-0142, into the approved aircraft maintenance program. The FAA 
determined that the life limits in AD 2021-10-14 for Bendix TT strap P/
Ns 2604067 and 117-14110 were incorrectly stated as 40,000 flight 
cycles for Model BO105LS A-3 helicopters. This proposed AD would 
correct the life limit to 25,000 flight cycles or 10 years, whichever 
occurs first, which is the life limit in ``the applicable ALS,'' as 
defined in EASA AD 2021-0142.
    Additionally, the FAA determined that AD 2021-10-14 incorrectly 
stated the life limits for Bendix TT strap P/Ns 2606576 and 2602559 as 
40,000 flight cycles for Model BO105A, BO105C, and BO105S helicopters. 
This proposed AD would correct the life limit to 15,600 flight cycles, 
2,400 hours TIS, or 10 years, whichever occurs first, which is the life 
limit in ``the applicable ALS,'' as defined in EASA AD 2021-0142.

FAA's Determination

    These helicopters have been approved by EASA and are approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Union, EASA has notified the FAA about the 
unsafe condition described in its AD. The FAA is proposing this AD 
after evaluating all known relevant information and determining that 
the unsafe condition described previously is likely to exist or develop 
on other helicopters of the same type design.

Related Service Information Under 1 CFR Part 51

    EASA AD 2021-0142 requires replacing certain components before 
exceeding their applicable life limit. EASA AD 2021-0142 also prohibits 
installing Bendix TT-strap P/N 2602559, P/N 2606576, P/N 2604067, or P/
N 117-14110, and requires revising the approved aircraft maintenance 
program (AMP) by incorporating the limitations described in ``the 
applicable ALS'' as defined in EASA AD 2021-0142.
    This material 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 reviewed Airbus Helicopters BO 105 Maintenance Manual (MM), 
Revision 31, dated December 15, 2020, for Model BO-105A, BO-105C, BO-
105 D, BO-105S, and BO-105LS A-1 helicopters; Airbus Helicopters BO 105 
LS A-3 MM, Revision 7, dated November 27, 2018, for Model BO-105 LS A-3 
helicopters; and Airbus Helicopters MM BO 105 LS A-3 ``Super Lifter'' 
Appendix 010, Revision 4, dated March 28, 2019, for BO 105 LS A-3 
``Superlifter'' helicopters.
    This service information specifies certain actions and associated 
thresholds and intervals, including life limits and maintenance tasks. 
These requirements (airworthiness limitations) include new life limits, 
including cure dates and storage life limits, for certain part-numbered 
TT straps.

Proposed AD Requirements in This NPRM

    This proposed AD would require incorporating into existing 
maintenance records requirements (airworthiness limitations), which are 
specified in EASA AD 2021-0142 described previously, except as 
discussed under ``Differences Between this Proposed AD and EASA AD 
2021-0142.'' This proposed AD would also prohibit the installation of 
Bendix TT-straps having certain P/Ns.

ADs Mandating Airworthiness Limitations

    The FAA has previously mandated airworthiness limitations by 
mandating each airworthiness limitation task (e.g., inspections and 
replacements (life limits)) as an AD requirement or issuing ADs that 
require revising the ALS of the existing maintenance manual or 
instructions for continued airworthiness to incorporate new or revised 
inspections and life limits. This proposed AD, however, would require 
operators to incorporate into maintenance records required by 14 CFR 
91.417(a)(2) or 135.439(a)(2), as applicable for your rotorcraft, the 
requirements (airworthiness limitations) specified in EASA AD 2021-
0142. The FAA does not intend this as a substantive change. For these 
ADs, the ALS requirements for operators are the same but are complied 
with differently. Requiring the incorporation of the new ALS 
requirements into the existing maintenance records, rather than 
requiring individual ALS tasks (e.g., repetitive inspections and 
replacements), requires operators to record AD compliance once after 
updating the maintenance records, rather than after every time the ALS 
task is completed.
    In addition, paragraph (h) of the proposed AD allows operators to 
incorporate later approved revisions of the applicable ALS as specified 
in the provisions of the ``Ref. Publications'' section of EASA AD 2021-
0142 without the need for an alternative method of compliance (AMOC).

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA developed a process to use some civil aviation 
authority (CAA) ADs as the primary source of information for compliance 
with requirements for corresponding FAA ADs. The FAA has been 
coordinating this process with manufacturers and CAAs. As a result, the 
FAA proposes to incorporate EASA AD 2021-0142 by reference in the FAA 
final rule. This proposed AD would, therefore, require compliance with 
EASA AD 2021-0142 through that incorporation, except for any 
differences identified as exceptions in the regulatory text of this 
proposed AD. Service information referenced in EASA AD 2021-0142 for 
compliance will be available at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2022-1070 after the FAA final 
rule is published.

Differences Between This Proposed AD and EASA AD 2021-0142

    This proposed AD does not require compliance with paragraphs (3), 
(4), and (5) of EASA AD 2021-0142.
    EASA AD 2021-0142 is applicable to Model BO-105D helicopters, 
whereas this proposed AD is not because Model BO-105D helicopters are 
not certificated by the FAA and are not included on the U.S. type 
certificate data sheet. EASA AD 2021-0142 is applicable to Model BO-105 
LS A-3 helicopters modified in accordance with EASA STC 10039633, or 
previously LBA Germany STC EMZ NR. 0654/3058 (commercially known as 
``Superlifter''), whereas this proposed AD would apply to Model BO-105 
LS A-3 helicopters modified in accordance with STC SR00043RD.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 67 helicopters of U.S. Registry. Labor rates are estimated at 
$85 per work-hour. Based on these numbers, the FAA

[[Page 54640]]

estimates the following costs to comply with this proposed AD.
    Incorporating requirements (airworthiness limitations) into 
existing maintenance records would take about 2 work-hours for an 
estimated cost of $170 per helicopter and $11,390 for the U.S. fleet.

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

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would 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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:
0
a. Removing Airworthiness Directive 77-04-06, Amendment 39-2835 (42 FR 
9670, February 17, 1977; amended 44 FR 46783, August 9, 1979); 
Airworthiness Directive 2002-13-06, Amendment 39-12794 (67 FR 43526, 
June 28, 2002); Airworthiness Directive 2016-25-14, Amendment 39-18740 
(81 FR 94944, December 27, 2016); and Airworthiness Directive 2021-10-
14, Amendment 39-21547 (86 FR 27268, May 20, 2021); and
0
b. Adding the following new airworthiness directive:

Airbus Helicopters Deutschland GmbH (AHD): Docket No. FAA-2022-1070; 
Project Identifier MCAI-2021-00686-R.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by October 24, 2022.

(b) Affected ADs

    This AD replaces the ADs specified in paragraphs (b)(1) through 
(4) of this AD.
    (1) AD 77-04-06, Amendment 39-2835 (42 FR 9670, February 17, 
1977; amended 44 FR 46783, August 9, 1979).
    (2) AD 2002-13-06, Amendment 39-12794 (67 FR 43526, June 28, 
2002).
    (3) AD 2016-25-14, Amendment 39-18740 (81 FR 94944, December 27, 
2016).
    (4) AD 2021-10-14, Amendment 39-21547 (86 FR 27268, May 20, 
2021).

    Note 1 to paragraph (b): The requirements of this AD capture the 
latest tasks and life limits required to prevent the unsafe 
conditions addressed by the ADs that are identified in paragraphs 
(b)(1) through (4) of this AD.

(c) Applicability

    This AD applies to all Airbus Helicopters Deutschland GmbH (AHD) 
Model BO-105A, BO-105C, BO-105S, BO-105LS A-1, and BO-105LS A-3 
helicopters, including BO-105LS A-3 helicopters modified in 
accordance with Supplemental Type Certificate SR00043RD, 
certificated in any category.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 6300, Main Rotor 
Drive System.

(e) Unsafe Condition

    This AD was prompted by new and more restrictive airworthiness 
limitations. The FAA is issuing this AD to address the failure of 
certain parts, which could result in the loss of control of the 
helicopter.

(f) Compliance

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

(g) Required Actions

    (1) Within 30 days after the effective date of this AD, 
incorporate into maintenance records required by 14 CFR 91.417(a)(2) 
or 135.439(a)(2), as applicable for your model and configuration 
helicopter, the requirements (airworthiness limitations) specified 
in paragraphs (1.1), (1.2), and (1.3), and the Definitions section, 
of European Union Aviation Safety Agency (EASA) AD 2021-0142, dated 
June 17, 2021 (EASA AD 2021-0142). Where paragraphs (1.2) and (1.3) 
of EASA AD 2021-0142 refer to its effective date, this AD requires 
using the effective date of this AD.
    (2) As of the effective date of this AD, comply with the parts 
installation prohibition specified in paragraph (2) of EASA AD 2021-
0142.

(h) Provisions for Alternative Requirements (Airworthiness Limitations)

    After the actions required by paragraph (g)(1) of this AD have 
been done, no alternative requirements (airworthiness limitations) 
are allowed unless they are approved as specified in the provisions 
of the ``Ref. Publications'' section of EASA AD 2021-0142.

(i) Special Flight Permit

    Special flight permits, as described in 14 CFR 21.197 and 
21.199, are prohibited.

(j) 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 (k)(2) 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.

(k) Related Information

    (1) For EASA AD 2021-0142, contact EASA, Konrad-Adenauer-Ufer 3, 
50668 Cologne, Germany; telephone +49 221 8999 000; email 
[email protected]; internet www.easa.europa.eu. You may find the 
EASA material on the EASA website at https://ad.easa.europa.eu. You 
may view this material 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. This material may be found in the AD 
docket at www.regulations.gov by searching for and locating Docket 
No. FAA-2022-1070.

[[Page 54641]]

    (2) For more information about this AD, contact Kristi Bradley, 
COS Program Manager, COS Program Management Section, Operational 
Safety Branch, Compliance & Airworthiness Division, FAA, 10101 
Hillwood Parkway, Fort Worth, TX 76177; telephone (817) 222-5110; 
email [email protected].

    Issued on August 31, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2022-19220 Filed 9-6-22; 8:45 am]
BILLING CODE 4910-13-P