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2021-07-05 LEONARDO S.P.A. (TYPE CERTIFICATE PREVIOUSLY HELD BY AGUSTA S.P.A.) (LEONARDO): Amendment 39-21482; Docket No. FAA-2021-0194; Project Identifier MCAI-2020-01434-R.
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective April 8, 2021.

(b) AFFECTED ADS

    This AD replaces AD 2007-26-52,  Amendment 39-15519  (73 FR 26316, May
    9, 2008).

(c) APPLICABILITY

    This AD applies to Leonardo Model A109C, A109E and A109K2 helicopters,
    certificated  in any  category,  with  a main  rotor blade  (MRB) part
    number (P/N) 709-0103-01-all dash numbers installed.

(d) SUBJECT

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

(e) UNSAFE CONDITION

    This AD was prompted by reports of the in-flight loss of tip caps. The
    FAA is issuing this AD to prevent  loss of a tip cap from an  MRB. The
    unsafe condition, if not addressed, could result in an increase in MRB
    vibration and subsequent loss of control of the helicopter.

(f) COMPLIANCE

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

(g) REQUIRED ACTIONS

(1) For an MRB  with a serial number  that has a prefix of either "EM-" or
    "A5-",  except an MRB  with a tip cap  P/N 709-0103-29-109  installed,
    within 10 hours time-in-service (TIS) after the effective date of this
    AD, unless accomplished previously, and thereafter at intervals not to
    exceed 25 hours TIS:

(i) Tap inspect the upper and lower sides of each tip cap for bonding sep-
    aration between the metal shells and the honeycomb core using a  steel
    hammer P/N 109-3101-58-1 or a coin (quarter) in the area indicated  as
    honeycomb core on Figure 1 of Agusta Alert Bollettino Tecnico (BT) No.
    109-106, BT No. 109K-22, or BT  No. 109EP-1, each Revision B and  each
    dated December 19,  2000 (BT No.  109-106, BT No.  109K-22, or BT  No.
    109EP-1), as applicable  to your helicopter  model. Also, tap  inspect
    for bonding separation in the tip  cap to blade bond area (no  bonding
    voids are permitted in this area).

(ii) Visually inspect the upper and lower sides  of each blade tip cap for
     swelling or deformation.

(iii) Dye-penetrant inspect  the  tip cap leading edge  along  the  welded
      joint line of the upper and lower tip cap skin shells for a crack in
      accordance with the Compliance Instructions, steps 3. through 3.2.6.
      of BT No. 109-106, BT No. 109K-22, or BT No. 109EP-1,  as applicable
      to your helicopter model.

(iv) If there is any swelling, deformation or crack; or bonding separation
     that exceeds  allowable limits,  remove the blade from service before
     further flight.

(v) If there is no swelling, deformation or crack;  or  if bonding separa-
    tion does not exceed allowable limits, continue to perform the inspec-
    tions required by this AD.

(2) For an MRB  with a tip cap P/N 709-0103-29-109 installed,  perform the
    following at the specified intervals:

(i) For  each  tip cap  with less than 600 hours TIS,  before reaching 600
    hours TIS, and thereafter, at intervals not to exceed 50 hours TIS or

(ii) For each tip cap with 600 or more hours TIS,  within the next 5 hours
     TIS or 30 days after the effective date of this AD,  whichever occurs
     first, and thereafter at intervals not to exceed 50 hours TIS.

(A) Dye-penetrant inspect  the welded bead  on  the  tip cap  leading edge
    (joint line between  the two metal  shells) for a  crack in accordance
    with  the  Accomplishment  Instructions,  steps  3.1  through  3.6, of
    Leonardo Helicopters Alert Service Bulletin (ASB) No. 109-125, ASB No.
    109EP-085,  or  ASB No. 109K-048,  each  at  Revision A and each dated
    October 19, 2020, as applicable your helicopter model.

(B) If there is a crack,  remove the tip cap  from service  before further
    flight.

(3) As of the effective date of this AD,  do not install  any MRB with tip
    cap P/N 709-0103-29-109 on any helicopter unless it has been inspected
    in accordance with the inspection requirements of this AD.

(h) 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 require-
    ments of this AD can be accomplished provided that:

(1) No passengers are onboard;

(2) The time to fly to the location does not exceed 10 hours TIS; and

(3) The airspeed does not exceed 70 knots indicated air speed (KIAS).

(i) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager, International Validation Branch,  FAA,  has the authority
    to approve AMOCs for this AD, if requested using the procedures  found
    in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to
    your principal inspector or local Flight Standards District Office, as
    appropriate. If  sending information  directly to  the manager  of the
    International  Validation  Branch, send  it  to the  attention  of the
    person identified in paragraph (j)(1) of this AD.  Information may  be
    emailed to: 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.

(j) RELATED INFORMATION

(1) For more information  about this AD,  contact  Fred Guerin,  Aerospace
    Engineer, General Aviation & Rotorcraft Section, International Valida-
    tion Branch, FAA, 2200 South 216th St, Des Moines, WA 98198; telephone
    (206) 231-3500; email fred.guerin@faa.gov.

(2) The subject of this AD  is addressed in European Union Aviation Safety
    Agency (EASA) AD 2020-0230,  dated October 22, 2020.  You may view the
    EASA AD on the internet  at https://www.regulations.gov  in Docket No.
    FAA-2021-0194.

(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.

(3) The following service information  was  approved  for  IBR on April 8,
    2021.

(i) Leonardo Helicopters  Alert Service Bulletin No. 109-125,  Revision A,
    dated October 19, 2020.

(ii) Leonardo Helicopters Alert Service Bulletin No. 109EP-085, Revision A
     dated October 19, 2020.

(iii) Leonardo Helicopters Alert Service Bulletin No. 109K-048, Revision A
      dated October 19, 2020.

(4) The following service information was approved  for IBR  on January 7,
    2002 (66 FR 60144, December 3, 2001).

(i) Agusta Alert Bollettino Tecnico No. 109-106, Revision B dated December
    19, 2000.

(ii) Agusta Alert Bollettino Tecnico No. 109EP-1, Revision B, dated Decem-
     ber 19, 2000.

(iii) Agusta  Alert  Bollettino  Tecnico  No. 109K-22,  Revision B,  dated
      December 9, 2000.

(5) For Leonardo Helicopters and Agusta  service information identified in
    this AD, contact Leonardo S.p.a. Helicopters, Emanuele Bufano, Head of
    Airworthiness,  Viale G. Agusta 520,  21017 C. Costa di Samarate  (Va)
    Italy; telephone +39-0331-225074;  fax +39-0331-229046; or at https://
    www.leonardocompany.com/en/home.

(6) 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.

(7) 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 March 19, 2021. Lance T. Gant, Director, Compliance & Airworthi-
ness Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Fred Guerin, Aerospace Engineer,  General
Aviation & Rotorcraft Section,  International Validation Branch, FAA, 2200
South 216th St.,  Des Moines, WA 98198;  telephone  (206) 231-3500;  email
fred.guerin@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0194; Project Identifier MCAI-2020-01434-R;
Amendment 39-21482; AD 2021-07-05]
RIN 2120-AA64

Airworthiness Directives; Leonardo S.p.a. (Type Certificate
Previously Held by Agusta S.p.A.) (Leonardo) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2007-26-52
which applied to certain Agusta S.p.A. (now Leonardo) Model A109C,
A109E, and A109K2 helicopters. AD 2007-26-52 required inspecting for
swelling, deformation, bonding separation, and for a crack on each main
rotor blade (MRB) with a certain part-numbered tip cap installed, and
removing the MRB from service before further flight if any of these
conditions exist and exceed the prescribed limits. This AD retains all
inspections for certain serial-numbered MRBs, but for MRBs with a
certain tip cap installed, this AD requires dye-penetrant inspections
rather than visual inspections. This AD was prompted by additional
reports of in-flight loss of part of a tip cap. The FAA is issuing this
AD to address the unsafe condition on these products.

DATES: This AD becomes effective April 8, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of April 8, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain other documents listed in this AD as of January 7,
2002 (66 FR 60144, December 3, 2001).
The FAA must receive comments on this AD by May 10, 2021.

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 https://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 Agusta and Leonardo Helicopters service information identified
in this final rule, contact Leonardo S.p.a. Helicopters, Emanuele
Bufano, Head of Airworthiness, Viale G.Agusta 520, 21017 C.Costa di
Samarate (Va) Italy; telephone +39-0331-225074; fax +39-0331-229046; or
at https://www.leonardocompany.com/en/home. 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. It is also available at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0194.

Examining the AD Docket

You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0194; 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 street address for Docket Operations is
listed above.

FOR FURTHER INFORMATION CONTACT: Fred Guerin, Aerospace Engineer,
General Aviation & Rotorcraft Section, International Validation Branch,
FAA, 2200 South 216th St., Des Moines, WA 98198; telephone (206) 231-
3500; email fred.guerin@faa.gov.

SUPPLEMENTARY INFORMATION:

Background

The FAA issued Emergency AD 2007-26-52 on December 20, 2007 and
published it as a Final rule; request for comments on May 9, 2008, as
Amendment 39-15519 (73 FR 26316). AD 2007-26-52 applied to Agusta
S.p.A. (now Leonardo) Model A109C, A109E, and A109K2 helicopters with
an MRB part number (P/N) 709-0103-01-all dash numbers installed. AD
2007-26-52 required, for any MRB with a serial number (S/N) with a
prefix of either ``EM-'' or ``A5-'', except a MRB with a tip cap P/N
709-0103-29-109, within 10 hours time-in-service (TIS) and thereafter
at intervals not to exceed 25 hours TIS:
A tap inspection of the upper and lower sides of each tip
cap and in the tip cap to blade bond area for bonding separation;
A visual inspection of the upper and lower side of each
blade tip cap for swelling or deformation; and
A dye-penetrant inspection of the tip cap leading edge
along the welded joint line of the upper and lower tip cap skin shells
for a crack.
For any MRB with a tip cap P/N 709-0103-29-109 installed, the AD
required visually inspecting for a crack on the leading edge at the
welded bead (joint line of shells) using a 10x or higher power
magnifying glass, and if there is damage other than a crack, inspecting
the area using a dye-penetrant inspection method, within the following
compliance times:
For a tip cap P/N 709-0103-29-109 with 600 or more hours
TIS, inspect within the next 5 hours TIS or 30 days, whichever occurs
first, and thereafter at intervals not to exceed 50 hours TIS; or
For a tip cap P/N 709-0103-29-109 with less than 600 hours
TIS, inspect before reaching 600 hours TIS, and thereafter, at
intervals not to exceed 50 hours TIS.
AD 2007-26-52 also required replacing the MRB if swelling,
deformation, a crack, or bonding separation that exceeds the prescribed
limits is found in an MRB with an affected prefix, except an MRB with a
tip cap P/N 709-0103-29-109. The MRB must be replaced with an airworthy
MRB before further flight. If a crack is found in a MRB with tip cap P/
N 709-0103-29-109, then AD 2007-26-52 required replacing the MRB before
further flight. The actions were required to be accomplished in
accordance with the manufacturer's service information.
AD 2007-26-52 was prompted by EASA AD 2007-0306-E, dated December
14, 2007 (EASA AD 2007-0306-E). EASA, which is the Technical Agent for
the Member States of the European Union, notified the FAA that an
unsafe condition may exist on Agusta Model A109C, A109E, and A109K2
helicopters. EASA advises that an incident occurred in which a Model
A109E helicopter lost part of the tip of the MRB due to fracture of the
welded bead (joint line of shells). The manufacturer advised that the
investigation relating to this tip cap failure was still ongoing.

Actions Since AD 2007-26-52 Was Issued

Since the FAA issued AD 2007-26-52, EASA issued AD 2020-0230, dated
October 22, 2020 (EASA AD 2020-0230), which supersedes EASA AD 2007-
0306-E, to correct an unsafe condition for Leonardo S.p.a. Helicopters,
formerly Finmeccanica S.p.A., AgustaWestland S.p.A., Agusta
S.p.A., Model A109E, A109K2, and A109C helicopters, all serial numbers.
EASA advises that recent occurrences of affected parts detachment have
been reported. EASA advises that the visual inspection for MRBs with
tip cap P/N 709-0103-29-109 installed is no longer acceptable to detect
part cracking and that this condition, if not detected and corrected,
could lead to further affected parts detachments, possibly resulting in
reduced control of the helicopter.
Accordingly, EASA AD 2020-0230 replaces the requirements of EASA AD
2007-0306-E for MRBs with a tip cap P/N 709-0103-29-109 installed, by
changing the visual inspections of affected parts to dye-penetrant
inspections and requires, depending on findings, replacement.

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 issuing 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 designs.

Related Service Information Under 1 CFR Part 51

The FAA previously reviewed the following Agusta Alert Bollettino
Tecnicos (BT), each Revision B and each dated December 19, 2000:
No. 109-106 which applies to Model A109C helicopters;
No. 109EP-1 which applies to Model A109E helicopters; and
No. 109K-22 which applies to Model A109K2 helicopters.
These BTs specify procedures for inspecting the MRB tip cap for
bonding separation and a crack; a tap inspection of the tip cap for
bonding separation in the blade bond; and a dye-penetrant inspection of
the tip cap leading edge along the welded joint line of the upper and
lower tip cap skin shells for a crack.
The FAA reviewed the following Leonardo Helicopters Alert Service
Bulletins (ASBs), each Revision A and each dated October 19, 2020:
No. 109-125 which applies to Model A109C helicopters;
No. 109EP-085 which applies to Model A109E helicopters;
and
No. 109K-048 which applies to Model A109K2 helicopters.
These ASBs specify dye-penetrant inspecting the tip cap P/N 709-
0103-29-109 for cracks on the tip cap leading edge at the welded bead
(joint line of shells) and removes the magnifying glass inspection that
was specified in the original ASBs.
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.

AD Requirements

This AD continues to require, for an MRB with a S/N that has a
prefix of either ``EM-'' or ``A5-'', except an MRB with a tip cap P/N
709-0103-29-109 installed, within 10 hours TIS after the effective date
of this AD and thereafter at intervals not to exceed 25 hours TIS, tap
inspecting each tip cap for bonding separation in specified areas; tap
inspecting for bonding separation in the tip cap to blade bond area;
visually inspecting the upper and lower sides of each blade tip cap for
swelling or deformation; and dye-penetrant inspecting the tip cap
leading edge along the welded joint line of the upper and lower tip cap
skin shells for a crack. If there is any swelling, deformation, or
crack, or bonding separation that exceeds allowable limits, removing
the blade from service is required before further flight; if there is
no swelling, deformation or crack, or if bonding separation does not
exceed allowable limits, continuing the inspections is required.
For an MRB with a tip cap P/N 709-0103-29-109 installed, this AD
now requires, for each tip cap with less than 600 hours TIS, before
reaching 600 hours TIS, and thereafter, at intervals not to exceed 50
hours TIS, or for each tip cap with 600 or more hours TIS, within the
next 5 hours TIS or 30 days after the effective date of this AD,
whichever occurs first, and thereafter at intervals not to exceed 50
hours TIS, dye-penetrant inspecting the welded bead on the tip cap
leading edge (joint line between the two metal shells) for a crack and
removing the tip cap from service if there is a crack.
This AD also prohibits installing an MRB with tip cap P/N 709-0103-
29-109 on any helicopter unless it has been inspected in accordance
with the inspection requirements of this AD.

Justification for Immediate Adoption and Determination of the Effective
Date


Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and
comment procedures for rules when the agency, for ``good cause,'' finds
that those procedures are ``impracticable, unnecessary, or contrary to
the public interest.'' Under this section, an agency, upon finding good
cause, may issue a final rule without providing notice and seeking
comment prior to issuance. Further, section 553(d) of the APA
authorizes agencies to make rules effective in less than thirty days,
upon a finding of good cause.
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies foregoing notice and comment prior to adoption of this rule
because inspections for certain MRBs must be accomplished within 5 or
10 hours TIS after the effective date of this AD, depending on the MRB,
and corrective action is required before further flight. Accordingly,
notice and opportunity for prior public comment are impracticable and
contrary to the public interest pursuant to 5 U.S.C. 553(b)(3)(B). In
addition, the FAA finds that good cause exists pursuant to 5 U.S.C.
553(d) for making this amendment effective in less than 30 days, for
the same reasons the FAA found good cause to forego notice and comment.

Comments Invited

The FAA invites you to send any written data, views, or arguments
about this final rule. Send your comments to an address listed under
ADDRESSES. Include ``Docket No. FAA-2021-0194; Project Identifier MCAI-
2020-01434-R'' at the beginning of your comments. The most helpful
comments reference a specific portion of the final rule, 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 final rule 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
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this final rule.

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 AD 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 AD, 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 AD. Submissions
containing CBI should be sent to Fred Guerin, Aerospace Engineer,
General Aviation & Rotorcraft Section, International Validation Branch,
FAA, 2200 South 216th St., Des Moines, WA 98198; telephone (206) 231-
3500; email fred.guerin@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.

Regulatory Flexibility Act

The requirements of the Regulatory Flexibility Act (RFA) do not
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt
a rule without prior notice and comment. Because the FAA has determined
that it has good cause to adopt this rule without prior notice and
comment, RFA analysis is not required.

Costs of Compliance

The FAA estimates that this AD affects 72 helicopters of U.S.
Registry. Labor rates are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates the following costs to comply with
this AD.
Each tap inspection will take about 3 work-hours and there are no
parts costs for an estimated cost of about $255 per helicopter per
inspection cycle.
Each visual inspection will take about 1 work-hour and there are no
parts cost for an estimated cost of about $85 per helicopter per
inspection cycle.
Each dye-penetrant inspection will take about 3 work-hours and
parts will cost about $100 for an estimated cost of about $355 per
helicopter per inspection cycle.
Replacing a blade, if required, will take about 2 work-hours and
parts will cost about $98,435 per blade, for an estimated cost of about
$98,605 per replacement.
Replacing a tip cap, if required, will take about 30 work-hours and
parts will cost about $3,034 per tip cap, for an estimated cost of
about $5,584 per replacement.
The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected operators.

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, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866, and
(2) Will not affect intrastate aviation in Alaska.

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) 2007-26-52, Amendment 39-15519
(73 FR 26316, May 9, 2008); and

b. Adding the following new AD: