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PROPOSED AD AIRBUS HELICOPTERS: Docket No. FAA-2018-0893; Product Identifier 2018-SW-032-AD.
(a) APPLICABILITY

    This 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 39-188767 (82 FR 21913, May
    11, 2017).

(d) COMMENTS DUE DATE

    The FAA must receive comments by September 21, 2020.

(e) COMPLIANCE

    You are  responsible for  performing each  action required  by this AD
    within  the  specified  compliance time  unless  it  has already  been
    accomplished prior to that time.

(f) REQUIRED ACTIONS

(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  Title 14  Code  of Federal  Regulations
    (14CFR) Sec. Sec.  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) of this AD:  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), or ASB No. EC225
    -25A207, Revision 0,  dated April 4, 2018 (ASB EC225-25A207),  as app-
    licable to your model helicopter.

(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  or ASB EC225-25A207,  as  applicable  to  your
     model helicopter.

(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  or ASB
      EC225-25A207, and inspect  each washer on  the internal fitting  for
      contact with the fitting radius.

(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-
    stitute terminating action for the repetitive checks required in para-
    graph (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: Matt Fuller, Safety Management Program
    Manager,  Airworthiness Products Section,  Operational  Safety Branch,
    General Aviation and 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,  both Revision 0, and both dated December 18,
    2015, which are not incorporated by reference,  contain additional in-
    formation about the subject of this AD. For service information ident-
    ified 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.airbushelicopters.com/techpub. You may
    review this referenced 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 the AD Docket.

(j) SUBJECT

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

Issued on August 3, 2020.  Ross Landes,  Deputy  Director  for  Regulatory
Operations,  Compliance & Airworthiness Division,  Aircraft  Certification
Service.

DATES: The FAA must receive comments on this proposed AD  by September 21,
2020.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0893; Product Identifier 2018-SW-032-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2017-09-05 for Airbus Helicopters Model AS332C, AS332C1, AS332L,
AS332L1, AS332L2, and EC225LP helicopters. AD 2017-09-05 requires
repetitively checking screws in the emergency flotation gear. Since the
FAA issued AD 2017-09-05, Airbus Helicopters developed a modification
that addresses the unsafe condition. This proposed AD would retain the
requirements of AD 2017-09-05 but would require installing the
modification, which would be a terminating action for the repetitive
checks required by AD 2017-09-05. The actions of this proposed AD are
intended to address an unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by September
21, 2020.

ADDRESSES: You may send comments by any of the following methods:

Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the
online instructions for sending your comments electronically.

Fax: 202-493-2251.

Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.

Hand Delivery: Deliver to the "Mail" address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

You may examine the AD docket on the internet at https://www.regulations.
gov by searching for and locating 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 proposed AD, the European Aviation Safety Agency (now European
Union Aviation Safety Agency) (EASA) AD, any comments received and
other information. The street address for Docket Operations is listed
above. Comments will be available in the AD docket shortly after
receipt.

For service information identified in this proposed rule, contact
Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052;
telephone 972-641-0000 or 800-232-0323; fax 972-641-3775; or at https://
www.airbus.com/helicopters/services/technical-support.html. You may
view this referenced service information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321,
Fort Worth, TX 76177.

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

SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA invites you to participate in this rulemaking by submitting
written comments, data, or views. The most helpful comments reference a
specific portion of the proposal, explain the reason for any
recommended change, and include supporting data. To ensure the docket
does not contain duplicate comments, commenters should send only one
copy of written comments, or if comments are filed electronically,
commenters should submit only one time.

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 file in the docket all comments received, as well
as a report summarizing each substantive public contact with FAA
personnel concerning this proposed rulemaking. Before acting on this
proposal, the FAA will consider all comments the FAA receives on or
before the closing date for comments. The FAA will consider comments
filed after the comment period has closed if it is possible to do so
without incurring expense or delay. The FAA may change this proposal in
light of the comments received.

Confidential Business Information


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 Matt Fuller, Safety Management Program Manager,
Airworthiness Products Section, Operational Safety Branch, General
Aviation and Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone 817-222-5110; email matthew.fuller@faa.gov. Any
commentary that the FAA receives which is not specifically designated
as CBI will be placed in the public docket for this rulemaking.

Discussion

The FAA issued AD 2017-09-05, Amendment 39-18867 (82 FR 21913, May
11, 2017) ("AD 2017-09-05"), for Airbus Helicopters Model AS332C,
AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters with
emergency flotation gear installed. AD 2017-09-05 requires repetitive
visual checks of the emergency flotation gear screws. Those actions are
intended to prevent the 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.

AD 2017-09-05 was prompted by EASA Emergency AD No. 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. EASA
advised that a screw ruptured on the rear upper fitting on the left-
hand (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 injury to the
occupants. The EASA AD consequently required repetitive inspections of
the lower attachment screws of rear upper fitting on the rear LH and
right-hand (RH) emergency flotation gears. EASA stated that the root
cause of the failure had not yet been identified.

Actions Since AD 2017-09-05 Was Issued

Since 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
requirements in EASA AD 2015-0239-E and also requires the installation
of Airbus Helicopters modification (MOD) 0728456 as a terminating
action for the repetitive inspections required in EASA AD 2015-0239-E.
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.

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 an
unsafe condition is likely to exist or develop on other helicopters of
the same type design.

Differences Between This Proposed AD and the EASA AD

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

Related Service Information Under 1 CFR Part 51


The FAA reviewed Airbus Helicopters Alert Service Bulletin (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. Both ASBs specify, 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 the ASB's requirements.

This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.

Other Related Service Information

The FAA also reviewed Airbus Helicopters 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.

Proposed AD Requirements

This proposed AD would require, within 15 hours TIS and thereafter
before each flight over water, visually checking each emergency
flotation gear LH and 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
the AD into 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 inspection 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, which can be performed
equally well by a pilot or a mechanic. This check is an exception to
our standard maintenance regulations. If any screws are loose or any
screw heads are missing, this proposed AD would 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.
This proposed AD would also require, within 300 hours TIS installing
MOD 0728456, as a terminating action for the repetitive checks.

Costs of Compliance

The FAA estimates that this proposed AD would affect 29 helicopters
of U.S. Registry. The FAA estimates that operators may incur the
following costs in order to comply with this proposed AD. Labor costs
are estimated at $85 per work-hour.

Checking the screws for looseness and a missing head would take
about 5 minutes, for an estimated cost of about $7 per helicopter and
$203 for the U.S. fleet.

Performing the modification would take about 16 work-hours, and
parts would 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 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, I certify this proposed regulation:

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 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


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: