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2020-23-03 AIRBUS HELICOPTERS: Amendment 39-21319; Docket No. FAA-2018-0893; Product Identifier 2018-SW-032-AD.
(a) APPLICABILITY

    This airworthiness directive (AD) applies to Airbus Helicopters  Model
    AS332C,  AS332C1, AS332L,  AS332L1, AS332L2,  and EC225LP  helicopters
    with emergency flotation gear installed, certificated in any category,
    except  those helicopters  that have  Airbus Helicopters  Modification
    (MOD) 0728456 already installed.

(b) UNSAFE CONDITION

    This AD defines the unsafe condition as failure of a rear upper  screw
    fitting  on  the  emergency flotation  gear.  This  condition, if  not
    detected  and  corrected, could  result  in failure  of  the emergency
    flotation system and subsequent capsizing of the helicopter.

(c) AFFECTED ADS

    This AD replaces AD 2017-09-05,  Amendment 39-18867 (82 FR 21913,  May
    11, 2017).

(d) EFFECTIVE DATE

    This AD becomes effective January 4, 2021.

(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

(1) Within 15 hours time-in-service (TIS),  and  before  each  flight over
    water thereafter,  visually check  each emergency  flotation gear left
    hand (LH) and right hand (RH) rear upper fitting to determine  whether
    the  heads of  the lower  screws are  present. Figure  1 to  paragraph
    (f)(1) of this AD depicts where the lower three screws (noted as B and
    E) are located. Check each screw for looseness by determining  whether
    it can  be rotated  by hand.  These actions  may be  performed by  the
    owner/operator (pilot)  holding at  least a  private pilot certificate
    and must be entered into the aircraft records showing compliance  with
    this AD  in  accordance with 14 CFR 43.9(a)(1) through (4)  and 14 CFR
    91.417(a)(2)(v). The record must be  maintained as required by 14  CFR
    91.417, 121.380, or 135.439.

                            ILLUSTRATION (Figure 1)

(2) If a screw head is missing,  or  if a screw is loose,  before  further
    flight over water,  install MOD 0728456 by completing paragraph (f)(3)
    of this AD.

(3) Within 300 hours TIS, unless required before further flight over water
    by paragraph (f)(2)  of  this  AD,  install  MOD 0728456  by doing the
    following:

Note 1 to paragraph (f)(3):  The installation of MOD 0728456 on the LH and
RH sides is identical.

(i) Remove external fitting (a)  and  remove  from service screws (c), (d)
    and (e), washers (f), and nuts (g)  as shown in Figure 1, Detail A  of
    Airbus Helicopters  Alert Service  Bulletin (ASB)  No. AS332-25.03.43,
    Revision 0, dated April 4, 2018 (ASB AS332-25.03-43 Rev 0), or ASB No.
    EC225-25A207, Revision 0,  dated April 4,  2018 (ASB EC225-25A207  Rev
    0), as applicable to your model helicopter. As an option, you may  use
    Airbus Helicopters  ASB No.  AS332-25.03.43 or  ASB No.  EC225-25A207,
    each Revision 2 and dated March 21, 2019 (ASB AS332-25.03-43 Rev 2  or
    ASB  EC225-25A207  Rev 2),  as  applicable to  your  model helicopter,
    instead of ASB AS332-25.03-43 Rev 0 or ASB EC225-25A207 Rev 0.

(ii) Install base washers (1)  (structural side),  spherical  washers  (2)
     (screw  side),  and  screws (3)  and coat  with sealing  compound (or
     similar) on the smooth surface of  the nuts (5) as shown in  Figure 2
     of ASB AS332-25.03-43 Rev 0 or ASB EC225-25A207 Rev 0, as  applicable
     to your model helicopter. As  an option, you may use  ASB AS332-25.03
     -43 Rev  2 or  ASB EC225-25A207  Rev 2,  as applicable  to your model
     helicopter, instead of ASB  AS332-25.03-43 Rev 0 or  ASB EC225-25A207
     Rev 0.

(iii) Inspect each washer  on the external fitting (a)  for contact with a
      weld as shown in Figure 2,  Detail A of ASB AS332-25.03-43 Rev  0 or
      ASB EC225-25A207  Rev 0,  and inspect  each washer  on the  internal
      fitting for contact with the  fitting radius. As an option,  you may
      use  or ASB  AS332-25.03-43 Rev  2  or  ASB EC225-25A207  Rev 2,  as
      applicable to your model  helicopter, instead of ASB  AS332-25.03-43
      Rev 0 or ASB EC225-25A207 Rev 0.

(A) If a washer on the external fitting makes contact with a weld, perform
    a spotfacing to the diameter of 17mm (+ 0.1/- 0.1)  with a cutter root
    radius of 0.5mm.

(B) If a washer on the internal fitting falls in the radius of the bracket
    perform a spotfacing to the diameter of 17mm (+ 0.1/- 0.1) with a cut-
    ter root radius of 0.5mm.

(iv) Torque each nut to 169-203 lbf.in (1.9-2.3 daN.m),  and apply sealing
     compound to outer edge of the LH rear upper fitting.

(4) Completion of the requirements in paragraph  in (f)(3) of this AD con-
    stitutes  terminating  action  for  the  repetitive checks required in
    paragraph (f)(1) of this AD.

(g) SPECIAL FLIGHT PERMITS

    Special flight permits are prohibited for flights over water.

(h) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager, Rotorcraft Standards Branch,  FAA,  may approve AMOCs for
    this AD.  Send your proposal to:  Matthew Fuller,  AD Program Manager,
    Operational Safety Branch,  Airworthiness  Products  Section,  General
    Aviation & Rotorcraft Unit,  FAA, 10101 Hillwood Pkwy., Fort 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 Emergency Alert Service Bulletin  (EASB) No. 05.01.
    06, and EASB No. 05A047,  each Revision 0 and dated December 18, 2015,
    and each Revision 1 and dated April 4, 2018, which are not incorporat-
    ed 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)  (EASA)  AD No. 2018-0090,
    dated April 20, 2018.  You may view the EASA AD  on  the  Internet  at
    https://www.regulations.gov in Docket No. FAA-2018-0893.

(j) SUBJECT

    Joint Aircraft Service Component (JASC) Code: 3212 Emergency Flotation
    Section.

(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. AS332-25.03.43,
    Revision 0, dated April 4, 2018.

(ii) Airbus Helicopters ASB No. AS332-25.03.43 Revision 2, dated March 21,
     2019.

(iii) Airbus Helicopters ASB No. EC225-25A207, Revision 0,  dated April 4,
      2018.

(iv) Airbus Helicopters ASB No. EC225-25A207, Revision 2,  dated March 21,
     2019.

(3) For service information identified in this AD, contact Airbus Helicop-
    ters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone 800-232-
    0323 or 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 fedreg
    .legal@nara.gov,  or go to: https://www.archives.gov/federal-register/
    cfr/ibr-locations.html.

Issued on October 27, 2020. Lance T Gant, Director, Compliance & Airworth-
iness Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Matt Fuller,  AD Program Manager,  Opera-
tional Safety Branch,  Airworthiness Products Section,  General Aviation &
Rotorcraft Unit, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone
817-222-5110; email matthew.fuller@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0893; Product Identifier 2018-SW-032-AD; Amendment
39-21319; AD 2020-23-03]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2017-09-05
for Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2,
and EC225LP helicopters. AD 2017-09-05 required repetitively checking
screws in the emergency flotation gear. This new AD retains the
requirements of AD 2017-09-05 but also requires installing a
modification (MOD), which is a terminating action for the repetitive
checks. This AD was prompted by the development of the MOD by Airbus
Helicopters that addresses the unsafe condition. The actions of this AD
are intended to address an unsafe condition on these products.

DATES: This AD is effective January 4, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 4,
2021.

ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX
75052; telephone 800-232-0323 or 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-2018-0893.

Examining the AD Docket

You may examine the AD docket on the internet at https://www.regulations.gov
in Docket No. FAA-2018-0893; 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,
Operational Safety Branch, Airworthiness Products Section, General
Aviation & 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 notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to remove AD 2017-09-05, Amendment 39-18867 (82 FR 21913,
May 11, 2017) (``AD 2017-09-05''), and add a new AD. AD 2017-09-05
applied to Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1,
AS332L2, and EC225LP helicopters with emergency flotation gear
installed. The NPRM published in the Federal Register on August 7, 2020
(85 FR 47921). The NPRM proposed to require, within 15 hours time-in-
service (TIS) and thereafter, before each flight over water, visually
checking each emergency flotation gear left-hand (LH) and right-hand
(RH) rear upper fitting for the presence of screw heads and looseness.
An owner/operator (pilot) may perform the required visual check but
must enter compliance with the applicable paragraph of this AD in the
helicopter maintenance records in accordance with 14 CFR 43.9(a)(1)
through (4) and 91.417(a)(2)(v). A pilot may perform this check because
it involves visually checking the rear upper fittings of the LH and RH
emergency flotation gears for the presence of screw heads and twisting
the screws by hand. This action can be performed equally well by a
pilot or a mechanic. This check is an exception to the FAA's standard
maintenance regulations. If any screws are loose or any screw heads are
missing, the NPRM proposed to require removing from service the screws
on each LH and RH side on the flotation gear rear fitting and
installing MOD 0728456, base washers and spherical washers. The NPRM
also proposed to require, within 300 hours TIS, installing MOD 0728456
as a terminating action for the repetitive checks.
AD 2017-09-05 was prompted by EASA AD 2015-0239-E, dated December
18, 2015 (EASA AD 2015-0239-E), issued by EASA, which is the Technical
Agent for the Member States of the European Union, to correct an unsafe
condition for Airbus Helicopters Model AS332C, AS332C1, AS332L,
AS332L1, AS332L2, and EC225LP helicopters. EASA advised that a screw
ruptured on the rear upper fitting on the LH emergency flotation gear
of an AS332 helicopter. EASA stated that this condition, if not
detected and corrected, could result in the failure of an emergency
flotation system when ditching and unstable floating of the helicopter,
possibly resulting in injuries to the occupants. The EASA AD
consequently required repetitive inspections of the lower attachment
screws of rear upper fitting on the rear LH and RH emergency flotation
gears. EASA stated that the root cause of the failure had not yet been
identified.

After the FAA issued AD 2017-09-05, Airbus Helicopters identified
the root cause of the screw rupture as a tapering gap under the fitting
attachment screw heads creating excessive stress loads. Consequently,
EASA issued AD No. 2018-0090, dated April 20, 2018 (EASA AD 2018-0090),
to supersede EASA AD 2015-0239-E. EASA AD 2018-0090 retains the
repetitive inspection requirements in EASA AD 2015-0239-E and also
requires the installation of Airbus Helicopters MOD 0728456 as a
terminating action for the repetitive inspections. MOD 0728456 involves
the installation of spherical washers and longer screws on the rear
upper fittings of the flotation gear to remove the stress applied to
the screw heads.

Actions Since the NPRM Was Issued

Since the FAA issued the NPRM, it was identified that the NPRM
specified installing MOD 0728456 by using Airbus Helicopters Alert
Service Bulletin (ASB) No. AS332-25.03.43 or ASB No. EC225-25A207, each
Revision 0 and dated April 4, 2018, in paragraphs (f)(3)(i) through
(iii) of this AD. However, the FAA intended to update this service
information to Airbus Helicopters ASB No. AS332-25.03.43 or ASB No.
EC225-25A207, each Revision 2 and dated March 21, 2019. Since the
updated service information does not affect compliance, this final rule
allows the use of either Revision 0 or Revision 2 of this service
information to install MOD 0728456.

Comments

The FAA gave the public the opportunity to participate in
developing this final rule, but the FAA did not receive any comments on
the NPRM or on the determination of the cost to the public.

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 of the
unsafe condition described in its AD. The FAA is issuing this AD after
evaluating all of the information provided by EASA and determining the
unsafe condition exists and is likely to exist or develop on other
helicopters of these same type design and that air safety and the
public interest require adopting the AD requirements as proposed except
for minor editorial changes. The two instances of 17mm (+ 0.1/+ 0.1) as
published in the Required Actions of the NPRM have been corrected to
17mm (+ 0.1/- 0.1). These minor editorial changes are consistent with
the intent of the proposals in the NPRM and will not increase the
economic burden on any operator nor increase the scope of this AD.

Differences Between This AD and the EASA AD

The EASA AD allows using tools for the inspection, while this AD
requires checking by hand. The EASA AD requires contacting Airbus
Helicopters if a screw is missing or loose, while this AD does not. The
EASA AD requires that repetitive inspections occur at intervals not to
exceed 15 hours TIS, while this AD requires the repetitive checks
before each flight over water.

Related Service Information Under 1 CFR Part 51


Airbus Helicopters has issued ASB No. AS332-25.03.43, Revision 0,
dated April 4, 2018, for Model AS332C, AS332C1, AS332L, AS332L1, and
AS332L2 helicopters and for military Model AS332B, AS332B1, AS332F1,
AS332M, and AS332M1 helicopters. The FAA also reviewed ASB No. EC225-
25A207, Revision 0, dated April 4, 2018, for Model EC 225 LP
helicopters. This service information specifies, within 12 months,
installing MOD 0728456 by installing spherical leveling washers and
longer screws to attach the rear upper fittings of the LH and RH
emergency flotation gear. Airbus
Helicopters specifies that helicopters that have undergone MOD 0728456
are exempt from these service information requirements. Airbus
Helicopters revised each of these ASBs, now at Revision 2 and dated
March 21, 2019, to specify an alternative to the protection of the
spotfacing(s) and add an instruction to apply primer after the
protection and before painting the parts.
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

Airbus Helicopters has issued Emergency Alert Service Bulletin
(EASB) No. 05.01.06, Revision 0, dated December 18, 2015, for Model
AS332C, AS332C1, AS332L, AS332L1, and AS332L2 helicopters and for
military Model AS332B, AS332B1, AS332F1, AS332M, and AS332M1
helicopters, and EASB No. 05A047, Revision 0, dated December 18, 2015,
for Model EC225LP helicopters. This service information specifies
repetitively inspecting the lower screws of the rear upper fitting on
the rear LH and RH emergency floating gears for the presence of the
heads and stressing the screw heads using a tool to make sure that the
screw head does not move. If all screw heads are present, the service
information requires no further action. If at least one screw head is
missing or is loose, the service information specifies replacing the
two lower screws and the upper screw and informing Airbus Helicopters.
Airbus Helicopters revised each of these EASBs to Revision 1, dated
April 4, 2018, to exclude helicopters with MOD 0728456 installed from
the effectivity.

Costs of Compliance

The FAA estimates that this AD affects 29 helicopters of U.S.
Registry. The FAA estimates that operators may incur the following
costs in order to comply with this AD. Labor costs are estimated at $85
per work-hour.
Checking the screws for looseness and a missing head takes about 5
minutes, for an estimated cost of about $7 per helicopter and $203 for
the U.S. fleet.
Performing the MOD takes about 16 work-hours, and parts cost about
$3,030 for total estimated cost of $4,390 per helicopter and $127,310
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 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


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 (AD) 2017-09-05, Amendment 39-18867
(82 FR 21913, May 11, 2017); and

b. Adding the following new AD: