preamble attached >>>
ADs updated daily at www.Tdata.com
2021-26-14 AIRBUS HELICOPTERS: Amendment 39-21873; Docket No. FAA-2021-0873; Project Identifier MCAI-2021-00336-R.
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective February 9, 2022.

(b) AFFECTED ADS

    This AD replaces AD 2018-11-01,  Amendment 39-19289 (83 FR 23778,  May
    23, 2018) (AD 2018-11-01).

(c) APPLICABILITY

    This AD applies to Airbus Helicopters  Model AS332L2 and Model EC225LP
    helicopters, certificated in any category, as specified in  paragraphs
    (c)(1) and (2) of this AD.

(1) Model AS332L2 helicopters  equipped  with extended aluminum splices on
    frame 5295 installed in accordance with Airbus Helicopters  (AH) Modi-
    fication (MOD) 0726517,  Eurocopter  (EC)  AS332 Service Bulletin (SB)
    53.01.52,  or AH repair design 332-53-507-06, 332-53-21-07, or 332-53-
    82-06; except helicopters embodying AH MOD 0728463, AH SB AS 332-53.01
    .97, or repair design 332-53-409-12, 332-53-1284-13, 332-53-1079-16 or
    332-53-1358-16.

Note 1 to paragraph (c)(1):  As referenced in paragraphs (c)(1) and (2) of
this AD, helicopters with AH MOD 0728463 installed have replaced the alum-
inum splices with steel splices.

(2) Model EC225LP helicopters  equipped  with extended aluminum splices on
    frame 5295 installed in accordance with AH MOD 0726517, or EC EC225 SB
    53-003 (pre AH MOD 0726493 and post AH MOD 0726517),  except  helicop-
    ters embodying AH MOD 0728463, or SB EC225-53-061.

Note 2 to paragraph (c)(2): Helicopters with AH MOD 0726493 have installed
steel splice kit part number 332A08-2649-3072.

(d) SUBJECT

    Joint Aircraft Service Component (JASC) Code: 5300, Fuselage Structure

(e) UNSAFE CONDITION

    This AD was prompted  by reports of cracks on frame 5295 and on alumi-
    num splices installed to prevent those cracks. The FAA is issuing this
    AD to  address cracking  on frame  5295 and  on the  inner skins.  The
    unsafe condition, if not addressed, could result in loss of structural
    integrity of the  helicopter frame and  subsequent loss of  control of
    the helicopter.

(f) COMPLIANCE

    Comply with this AD within the compliance times specified,  unless al-
    ready done.

(g) RETAINED INSTALLATION AND INSPECTIONS WITH NEW SERVICE INFORMATION AND
    CORRECTIVE ACTIONS (MODIFICATION)

    This paragraph retains the requirements of paragraph (e) of AD 2018-11
    -01, with new service information  and  corrective actions  (modifica-
    tion).

(1) Before a splice reaches 1,700 hours time-in-service  (TIS),  within 50
    hours TIS or before the helicopter reaches 11,950 hours TIS, whichever
    occurs latest, do the following.

(i) Install the rail support cut-out  and  identify the left-hand (LH) and
    right-hand (RH) junction profile,  in accordance  with the Accomplish-
    ment Instructions, paragraph 3.B.2., of Airbus Helicopters Alert Serv-
    ice Bulletin (ASB) No. EC225-05A038 Revision 1, dated February 9, 2021
    (Airbus Helicopters ASB No. EC225-05A038, Revision 1); or Airbus Heli-
    copters ASB No. AS332-05.00.97,  Revision  1,  dated  February 9, 2021
    (Airbus Helicopters ASB No. AS332-05.00.97, Revision 1);  whichever is
    applicable to your helicopter.

(ii) Inspect each splice  for  a  crack  in the area depicted as Area Y in
     Figure 3 of Airbus Helicopters ASB No. EC225-05A038,  Revision 1;  or
     Airbus Helicopters ASB No. AS332-05.00.97,  Revision 1;  whichever is
     applicable to your helicopter.  If a crack exists,  do the applicable
     action required by paragraph (g)(1)(ii)(A) or (B) of this AD.

(A) For any cracking found before the effective date of this AD: Repair or
    replace the splice before further flight.

(B) For any cracking found  on  or  after  the  effective date of this AD:
    Before further flight,  modify the helicopter in accordance with para-
    graph 3.B.2.  of the Accomplishment Instructions of Airbus Helicopters
    Service Bulletin (SB) No. AS332-53.01.97, Revision 0,  dated  February
    9, 2021  (Airbus Helicopters  SB No. AS332-53.01.97,  Revision 0);  or
    Service Bulletin No. EC225-53-061, Revision 0,  dated February 9, 2021
    (Airbus Helicopters SB No. EC225-53-061, Revision 0); as applicable to
    your helicopter; except as specified in paragraph (h) of this AD.

(2) Thereafter at intervals  not  to  exceed 110 hours TIS,  inspect  each
    splice for a crack in the area depicted as Area Y  in Figure 3 of Air-
    bus Helicopters ASB No. EC225-05A038, Revision 1;  or  Airbus Helicop-
    ters ASB No. AS332-05.00.97,  Revision  1;  whichever is applicable to
    your helicopter. If a crack exists, do the applicable actions required
    by paragraph (g)(2)(i) or (ii) of this AD. Accomplishing the modifica-
    tion specified in paragraph (g)(1)(ii)(B)  and  (g)(2)(ii)  of this AD
    terminates the inspections required by this paragraph.

(i) For any cracking found before the effective date of this AD: Repair or
    replace the splice before further flight.

(ii) For any cracking found on or after the effective date of this AD: Be-
     fore further flight,  modify the helicopter  in accordance with para-
     graph 3.B.2. of the Accomplishment Instructions of Airbus Helicopters
     SB No. AS332-53.01.97,  Revision 0;  or  Airbus Helicopters SB No. EC
     225-53-061, Revision 0;  as applicable to your helicopter;  except as
     specified in paragraph (h) of this AD.

(h) SERVICE INFORMATION EXCEPTIONS

(1) Where Airbus Helicopters ASB No. EC225-05A038, Revision 1; Airbus Hel-
    icopters ASB No. AS332-05.00.97, Revision 1; Airbus Helicopters SB No.
    AS332-53.01.97,  Revision 0;  and Airbus Helicopters SB No. EC 225-53-
    061, Revision 0;  specify to perform dye-penetrant inspections  "if in
    doubt" or "if any doubt,"  this AD requires performing a dye-penetrant
    inspection during inspections done on  or  after the effective date of
    this AD.

(2) Where Airbus Helicopters SB No. AS332-53.01.97, Revision 0; and Airbus
    Helicopters SB No. EC 225-53-061 Revision 0; specify discarding parts,
    this AD requires removing those parts from service.

(3) Where Airbus Helicopters SB No. AS332-53.01.97, Revision 0; and Airbus
    Helicopters  SB  No.  EC 225-53-061,  Revision  0,  specify contacting
    Airbus Helicopter for corrective action or further procedures, this AD
    requires  repair done  in accordance  with a  method approved  by  the
    Manager,  General   Aviation  &   Rotorcraft  Section,   International
    Validation Branch, FAA;  or EASA; or  Airbus Helicopters' EASA  Design
    Organization Approval (DOA). If approved by the DOA, the approval must
    include the DOA-authorized signature.

(4) Airbus Helicopters SB No. AS332-53.01.97, Revision 0; and Airbus Heli-
    copters SB No. EC 225-53-061,  Revision 0, specify a visual  check and
    dye penetrant inspection for cracks on the inside and outside of frame
    5295. For this AD, if any cracking is found during any visual check or
    dye penetrant  inspection on  the inside  and outside  of frame  5295,
    before further flight, repair in accordance with a method approved  by
    the  Manager,  General Aviation  &  Rotorcraft Section,  International
    Validation Branch, FAA; or EASA;  or Airbus Helicopters' EASA DOA.  If
    approved  by the  DOA, the  approval must  include the  DOA-authorized
    signature.

(i) REPORTING NOT REQUIRED

    Although Airbus Helicopters  SB No. AS332-53.01.97,  Revision  0;  and
    Airbus Helicopters SB No. EC 225-53-061, Revision 0; specify to submit
    certain information to the manufacturer, this AD does not include that
    requirement.

(j) CREDIT FOR PREVIOUS ACTIONS

(1) This paragraph provides  credit  for  the  installation  of  the  rail
    support cut-out required by paragraph (g)(1)(i)  of this AD,  if  that
    action was performed  before June 27, 2018  (the effective date  of AD
    2018-11-01) using Airbus Helicopters MOD 0728090 or Airbus Helicopters
    SB No. 05-019, Revision 4, dated September 22, 2014.

(2) This paragraph provides credit for the actions required  by paragraphs
    (g)(1) and (2) of this AD,  if the actions were performed  before  the
    effective date of  this  AD  using  Airbus Helicopters  ASB No. EC225-
    05A038, Revision 0, dated April 15, 2014 or Airbus Helicopters ASB No.
    AS332-05.00.97, Revision 0, dated April 15, 2014.

(k) SPECIAL FLIGHT PERMITS

    Special flight permits  may be issued in accordance with 14 CFR 21.197
    and 21.199 to operate the helicopter  to a location  where the actions
    can be performed, provided no passengers are onboard.

(l) 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 (m)(1)  of this AD. Information may  be
    emailed to: 9-AVS-AIR-730-AMOC@faa.gov.

(2) Before using any approved AMOC,  notify your appropriate principal in-
    spector,  or  lacking a principal inspector,  the manager of the local
    flight standards district office/certificate holding district office.

(m) RELATED INFORMATION

(1) For more information about this AD,  contact Andrea Jimenez, Aerospace
    Engineer,  COS Program Management Section,  Operational Safety Branch,
    Compliance & Airworthiness Division, FAA, 1600 Stewart Ave, Suite 410,
    Westbury, NY 11590; telephone (516) 228-7330; email andrea.jimenez@faa
    .gov.

(2) Service information identified in this AD  that is not incorporated by
    reference is available at the addresses specified in paragraphs (n)(3)
    and (4) of this AD.

(3) The subject of this AD is addressed  in European Union Aviation Safety
    Agency (EASA)  AD 2021-0075,  dated  March 16, 2021.  You may view the
    EASA AD at https://www.regulations.gov in Docket No. FAA-2021-0873.

(n) 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 No. AS332-05.00.97, Revision
    1, dated February 9, 2021.

(ii) Airbus Helicopters Alert Service Bulletin No. EC225-05A038,  Revision
     1, dated February 9, 2021.

(iii) Airbus Helicopters Service Bulletin No. AS332-53.01.97,  Revision 0,
      dated February 9, 2021.

(iv) Airbus Helicopters  Service Bulletin  No. EC225-53-061,  Revision  0,
     dated February 9, 2021.

(3) For service information identified in this AD, contact Airbus Helicop-
    ters, 2701 North 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  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 refer-
    ence at the National Archives and Records Administration  (NARA).  For
    information on the availability of this material  at NARA,  email: fr.
    inspection@nara.gov,   or   go  to:  https://www.archives.gov/federal-
    register/cfr/ibr-locations.html.

Issued on December 10, 2021. Lance T Gant, Director, Compliance & Airworth
-iness Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Andrea Jimenez,  Aerospace Engineer,  COS
Program Management Section,  Operational Safety Branch,  Compliance & Air-
worthiness Division, FAA, 1600 Stewart Ave, Suite 410, Westbury, NY 11590;
telephone (516) 228-7330; email andrea.jimenez@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0873; Project Identifier MCAI-2021-00336-R;
Amendment 39-21873; AD 2021-26-14]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2018-11-
01, which applied to certain Airbus Helicopters Model AS332L2 and
EC225LP helicopters. AD 2018-11-01 required installing a cut-out for
the left-hand (LH) and right-hand (RH) rail support junction profiles
and repetitively inspecting splices, frame 5295, and related equipment
for a crack. Since the FAA issued AD 2018-11-01, the manufacturer has
developed a modification for in-service helicopters for replacing
aluminum splices with steel splices on frame 5295. This AD retains the
requirements of AD 2018-11-01 and requires a modification for replacing
aluminum splices with steel splices on frame 5295 if cracking is found.
This AD also provides terminating action for the repetitive
inspections. The FAA is issuing this AD to address the unsafe condition
on these products.

DATES: This AD is effective February 9, 2022.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 9,
2022.

ADDRESSES: For service information identified in this final rule,
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 https://www.airbus.com/helicopters/services/technical-support.html.
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. Service information that
is incorporated by reference is also available at https://www.regulations.gov
by searching for and locating Docket No. FAA-2021-0873.

Examining the AD Docket

You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0873; 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
European Union Aviation Safety Agency (EASA) AD, any comments received,
and other information. The 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: Andrea Jimenez, Aerospace Engineer,
COS Program Management Section, Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY
11590; telephone (516) 228-7330; email andrea.jimenez@faa.gov.

SUPPLEMENTARY INFORMATION:

Background

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2018-11-01, Amendment 39-19289 (83 FR
23778, May 23, 2018), (AD 2018-11-01). AD 2018-11-01 applied to Airbus
Helicopters Model AS332L2 and EC225LP helicopters with an extended
aluminum splice installed on frame 5295, except helicopters with steel
splice kit part number 332A08-2649-3072 installed. AD 2018-11-01
required installing a cut-out for the LH and RH rail support junction
profiles and repetitively inspecting splices, frame 5295, and related
equipment for a crack. AD 2018-11-01 was prompted by reports of cracks
on frame 5295 and on splices installed to prevent those cracks. The FAA
issued AD 2018-11-01 to address a crack in frame 5295, which if not
detected and corrected, could lead to loss of structural integrity of
the helicopter frame and subsequent loss of control of the helicopter.
The NPRM published in the Federal Register on October 22, 2021 (86
FR 58600). In the NPRM, the FAA proposed to retain the requirements of
AD 2018-11-01 and require a modification for replacing aluminum splices
with steel splices on frame 5295 if cracking is found. The NPRM was
prompted by EASA AD 2021-0075, dated March 16, 2021 (EASA AD 2021-
0075), which supersedes EASA Emergency AD 2014-0098-E, dated April 25,
2014 (EASA Emergency AD 2014-0098-E), issued by EASA, which is the
Technical Agent for the Member States of the European Union.
EASA advises that since EASA Emergency AD 2014-0098-E was issued,
Airbus Helicopters developed MOD 0728463, available for helicopters in
service through the applicable modification service bulletin, providing
instructions to replace aluminum splices with steel splices on frame
5295. Airbus Helicopters also issued the applicable inspection alert
service bulletins, as defined in EASA AD 2021-0075. Accordingly, EASA
AD 2021-0075 retains the requirements of EASA Emergency AD 2014-0098-E,
which is superseded, and requires a modification, replacing aluminum
splices with steel splices on helicopters on which any cracked aluminum
splice has been detected. EASA AD 2021-0075 also advises that the
modification is terminating action for the repetitive inspections.

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 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 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 the following Airbus Helicopters service
information.
Alert Service Bulletins Nos. AS332-05.00.97, Revision 1;
and EC225-05A038, Revision 1; both dated February 9, 2021; which
specify procedures for, among other actions, installing a cut-out for
the LH and RH rail support junction profiles and inspecting splices,
frame 5295, and related equipment for a crack. These documents are
distinct since they apply to different helicopter models.
Service Bulletins Nos. AS332-53.01.97, Revision 0; and
EC225-53-061, Revision 0; both dated February 9, 2021; which specify
procedures for modifying the helicopter by replacing the aluminum LH
and RH splices with steel splices under the plates and the brackets of the main
gear box (MGB) bars. The modification includes taking reference readings of the
brackets of the MGB bars, removing the MGB brackets and plates,
removing the aluminum splices and inspecting the joggling areas for
scratches or other damage, inspecting frame 5295 for cracking
(including a dye penetrant inspection if the inspection results are not
conclusive), identifying the current measurements (values) of the rivet
and attachment plate holes for installation of the steel splice
(including determining the values of the rivet holes and attachment
plate holes on frame 5295 with a calibrated pad and determining the
elongations of the holes and the lengths of the straps), modifying the
door hinge rail brackets on the LH and RH sides, and installing the
steel splices. These documents are distinct since they apply to
different helicopter models.
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 reviewed Eurocopter Helicopters (now Airbus Helicopters)
Service Bulletin No. 53-003, Revision 4, for Model EC225LP helicopters
and Service Bulletin No. 53.01.52, Revision 5, for Model AS332L2
helicopters, both dated July 23, 2010. The service bulletins specify
procedures to reinforce frame 5295 by installing a new titanium plate
underneath the fitting and a new widened aluminum splice below the
upper corner of the door.
The FAA also reviewed Airbus Helicopters Service Bulletin No. 05-
019, Revision 4, dated September 22, 2014, for Model EC225 LP
helicopters. This service information specifies procedures for cutting
out the junction profiles.
The FAA also reviewed Airbus Helicopters Alert Service Bulletins
Nos. AS332-05.00.97, Revision 0; and EC225-05A038, Revision 0; both
dated April 15, 2014; which specify procedures for, among other
actions, installing a cut-out for the LH and RH rail support junction
profiles and inspecting splices, frame 5295, and related equipment for
a crack.

Redesignation of AD 2018-11-01 Paragraph Identifier


Since AD 2018-11-01 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have been redesignated in this AD, as listed in
the following table:

Revised Paragraph Identifier

Requirement in AD 2018-11-01 Corresponding requirement in this AD
paragraph (e)
paragraph (g)
paragraph (f)
paragraph (j)(1)

Differences Between This AD and the EASA AD 2021-0075

EASA AD 2021-0075 requires contacting Airbus Helicopters for
approved repair instructions if any crack is found during an
inspection. This AD would not require that action.

Costs of Compliance

The FAA estimates that this AD would affect 38 helicopters of U.S.
registry. The FAA estimates the following costs to comply with this AD:

Estimated Costs for Required Actions

Action Labor cost Parts cost Cost per product Cost on U.S. operators
Retained installation of cut-outs on frame 5295 from AD 2018-11-01 40 work-hours x $85 per hour = $3,400 $5,000 $8,400 $319,200
Retained inspection of frame 5295 from AD 2018-11-01 2 work-hours x $85 per hour = $170, per inspection cycle 0 170, per inspection cycle 6,460, per inspection cycle

The FAA estimates the following costs to do any necessary repairs
that would be required based on the results of the inspection. The
agency has no way of determining the number of aircraft that might need
these repairs:

Estimated Costs of On-Condition Actions

Action Labor cost Parts cost Cost per product
Repair 40 work-hours x $85 per hour = $3,400 $5,000 $8,400
New modification (replacement of aluminum splices with steel splices) 830 work-hours x $85 per hour = $70,550 35,000 105,550

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,
(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

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]


2. The FAA amends Sec. 39.13 by:

a. Removing Airworthiness Directive 2018-11-01, Amendment 39-19289 (83
FR 23778, May 23, 2018); and

b. Adding the following new airworthiness directive: