preamble attached >>>
ADs updated daily at www.Tdata.com
2021-05-07 AIRBUS HELICOPTERS DEUTSCHLAND GMBH (TYPE CERTIFICATE PREVIOUSLY HELD BY EUROCOPTER DEUTSCHLAND GMBH): Amendment 39-21450; Docket No. FAA-2015-4497; Project Identifier 2016-SW-011-AD.
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective April 16, 2021.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD applies to  the following Airbus Helicopters  Deutschland GmbH
    (Type  Certificate  previously held  by  Eurocopter Deutschland  GmbH)
    helicopters, certificated in any category:

(1) Model BO-105A, BO-105C, and BO-105S helicopters with a voltage regula-
    tor part number  (P/N) 51565-000, 51565-000R, or 51509-002R installed;
    and

(2) Model MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-4,  MBB-BK 117 B-1,
    MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters.

(d) SUBJECT

    Joint Aircraft Service Component (JASC) Code: 2497,  Electrical Power
    System Wiring.

(e) UNSAFE CONDITION

    This AD was prompted  by a report  of a loss  of electrical ground be-
    tween  the  starter-generator  and  the  generator  voltage  regulator
    (regulator). The FAA is issuing this AD to address loss of  electrical
    ground between the starter-generator and the regulator. This condition
    could  result  in  an  overvoltage  of  electrical  power,  damage  to
    electronic  equipment,   and  subsequent   loss  of   control  of  the
    helicopter.

(f) COMPLIANCE

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

(g) REQUIRED ACTIONS

(1) Within 50 hours time-in-service (TIS):

(i) Visually inspect the wire terminal  of wire P55F16N/P56F16N  for Model
    BO-105A, BO-105C, and  BO-105S helicopters and  wire 1PA53B20/2PA53B20
    for Model MBB-BK 117 A-1,  MBB-BK 117 A-3, MBB-BK 117 A-4,  MBB-BK 117
    B-1,  MBB-BK 117 B-2,  and MBB-BK 117 C-1 helicopters on Terminal E of
    each  starter-generator  for  a  crack,  a  kink,  fraying, looseness,
    missing material, and corrosion. If there is a crack, a kink, fraying,
    looseness, missing material, or any corrosion, before further  flight,
    replace the wire terminal.

(ii) Measure the resistance between each starter-generator and its regula-
     tor  in accordance  with the  Accomplishment Instructions,  paragraph
     2.A.2.3.  of  Eurocopter  Alert  Service  Bulletin  ASB BO105-90-103,
     Revision 4, dated June 21, 2010, or paragraphs 2.A.2.3. and  2.A.2.5.
     of Eurocopter Alert Service Bulletin ASB-MBB-BK117-90-118, Revision 2
     dated May  4, 2009,  as applicable  to your  model helicopter. If the
     resistance is more than 500 milliohms, before further flight, replace
     the wire terminal.

(2) Within 150 hours TIS:

(i) Install  a  wire  harness  from  each  generator  voltage regulator as
    follows.

(A) For Model BO-105A, BO-105C, and BO-105S helicopters:  Wire harness P/N
    105-90081.

(B) For Model MBB-BK 117 A-1, MBB-BK 117 A-3,  MBB-BK 117 A-4,  MBB-BK 117
    B-1, and MBB-BK 117 B-2 helicopters: Wire harness P/N 117-901941.

(C) For Model MBB-BK 117 C-1 helicopters: Wire harness P/N 117-901961.

(ii) For Model MBB-BK 117 A-3, MBB-BK 117 A-4,  MBB-BK 117 B-1, MBB-BK 117
     B-2, and MBB-BK 117  C-1 helicopters, revise the  existing Rotorcraft
     Flight Manual (RFM) for your helicopter to include the information in
     Section  3  Emergency  and Malfunction  Procedures  of  the following
     temporary  revisions, as  applicable to  your helicopter:  Eurocopter
     Flight  Manual  BK117  A-3 Temporary  Revision  9,  Eurocopter Flight
     Manual BK117 A-4 Temporary Revision 5, Eurocopter Flight Manual BK117
     B-1  Temporary  Revision  6,  Eurocopter  Flight  Manual  BK  117 B-2
     Temporary  Revision  1,  or  Eurocopter  Flight  Manual  BK  117  C-1
     Temporary Revision 2, all dated September 22, 2006. Using a later RFM
     revision  with  information  identical  to  that  contained  in   the
     temporary revision  specified for  your helicopter  is acceptable for
     compliance with the requirement of this paragraph.

(iii) For Model MBB-BK 117 A-1 helicopters, revise Section 3 Emergency and
      Malfunction Procedures  of the existing RFM  for  your helicopter to
      include the information  in Figures 1 through 3  to paragraph (g)(2)
      (iii) of this AD.

                            FIGURE 1 TO PARAGRAPH (G)(2)(III)
    ______________________________________________________________________


                                CAUTION LIGHT INDICATIONS
                                    ______     _____
                                    GEN I  or   GEN
                                    ______     _____

    Conditions/Indications

    Affected generator has failed or is disconnected from the power distri
    -bution system.

    Procedure

    1. BUS-TIE switch position – Check

    If BUS–TIE in position OFF:

    2. Electrical short circuit procedure – Perform (refer to para 3.6.1)

    If voltage is out of normal range (> 30 V):

    2. Generator overvoltage procedure – Perform (refer to para 3.6.1.a)

    If BUS–TIE in position NORM:

    2. Affected GENERATOR switch – RESET, then ON

    GEN caution light remains on

    3. Relevant GENERATOR sw – OFF

    4. GEN TRIP switch (to trip generator) – Relevant position (I or II),
       then release

    5. AMM SEL switch – Select normal generator

    6. Ammeter and voltmeter – Monitor

    NOTE One generator alone will provide sufficient power for normal services.
    ______________________________________________________________________



                            FIGURE 2 TO PARAGRAPH (G)(2)(III)
    ______________________________________________________________________

                                CAUTION LIGHT INDICATIONS
                                    ______      _____
                                    GEN I  and   GEN
                                    ______      _____

    Conditions/Indications

    Both generators have failed or are disconnected from the power distri-
    bution system.

    Procedure

    1. GENERATOR 1 switch – RESET, then ON
    2. Ammeter and voltmeter – Check
    3. GENERATOR 1 switch – OFF
    4. GENERATOR 2 switch – RESET, then ON
    5. Ammeter and voltmeter – Check
    6. GENERATOR 2 switch – OFF

    If voltage is out of normal range (> 30 V):

    7. Generator overvoltage procedure – Perform (refer to para 3.6.1.a)

    If voltage is in normal range:

    8. Both GENERATOR switches – RESET, then ON

    If one GEN caution light remains on:

    9. Respective GENERATOR switch – OFF
    10. GEN TRIP switch – Respective position (I or II), then release

    If both GEN caution light remain on:

    11. GEN TRIP switch – Position I and II, then release
    12. PWR SELECT switch – OFF

    Battery supplies both flight essential busses.

    NOTE: If,  in addition,  both main busses are necessary,  both BUS-TIE
    switches can be set to NORM  and  PWR SELECT switch to BAT.  Then  the
    battery  supplies  both  flight  essential  busses  and also both main
    busses. In this case battery will be discharged at a high rate.

    13. AMM SEL switch – BAT
    14. Ammeter and voltmeter – Monitor
    15. LAND AS SOON AS PRACTICABLE

                ___________________________________________
                         Residual Battery Endurance
                ___________________________________________
                Continuous Load [A]   15  20  25  30  40

                Time [min]            60  45  35  30  22
                ___________________________________________
                NOTE Calculations are based on an assumed
                minimum battery capacity of 15 Ah. Times
                include 10 minutes landing light operation
                and 10 minutes radio transmission.
                ___________________________________________
                WARNING TOTAL ELECTRICAL FAILURE WILL LIMIT
                FUEL AVAILABLE TO QUANTITY CONTAINED IN
                SUPPLY TANKS AT TIME OF FAILURE AND THUS
                RESIDUAL FLIGHT TIME
    ______________________________________________________________________


                            FIGURE 3 TO PARAGRAPH (G)(2)(III)
    ______________________________________________________________________

    3.6. SYSTEM EMERGENCY/MALFUNCTION CONDITIONS
    3.6.1. Electrical Short Circuit - Generator System I Cutoff

    Conditions/Indications
    – Short circuit on main bus No. I  or on feeder line between generator
      No. I and main bus No. I or between main bus No. I and battery relay
    – Power supply is interrupted to main bus No. I and battery
    – Power supply is guaranteed to main bus No. II,  flight essential bus
      No. II and to non–essential bus  by generator No. II and to flight –
      essential bus No. I by battery.
    – GEN I caution light on
    – BAT DISCH warning light
    – BUS-TIE switch OFF
    – Failure of equipment powered by affected busses

    Procedure
    1. GENERATOR I switch – OFF
    2. GEN TRIP switch – Position I, then release
    3. AMM SEL switch – BAT
    4. Electrical consumption on No. I FLT ESS BUS – Reduce
    5. Ammeter and voltmeter – Monitor
    6. LAND AS SOON AS PRACTICABLE

    NOTE One generator alone will provide sufficient power for normal serv
    -ices.

    3.6.1.a Generator overvoltage
    Conditions/Indications
    – Voltmeter indication > 30 V
    – GEN I or GEN II caution light on

    Procedure
    1. Generator with high voltage – OFF (not to be used again)
    2. Other generator – RESET, then ON
    3. Ammeter and voltmeter – Monitor
    4. GEN TRIP switch – Position (I or II), then release
    5. AMM SEL switch – Select normal generator
    6. LAND AS SOON AS PRACTICABLE

    NOTE One generator alone will provide sufficient power for normal serv
    -ices.
    ______________________________________________________________________

(h) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager, Strategic Policy Rotorcraft Section, FAA, has the author-
    ity 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 certification  office, send it  to the attention  of the person
    identified in paragraph (i)(1) of this AD. Information may be  emailed
    to: 9-Denver-Aircraft-Cert@faa.gov or ronnea.l.derby.@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.

(i) RELATED INFORMATION

(1) For more information about this AD, contact Ronnea L. Derby, Aerospace
    Engineer,  Denver ACO Branch,  FAA,  26805 East 68th Ave.,  Room  214,
    Denver, CO 80249;  telephone 303-342-1093;  email ronnea.l.derby.@faa.
    gov.

(2) The subject of this AD is addressed in European Aviation Safety Agency
    (now European Union Aviation Safety Agency) (EASA) AD 2015-0098, dated
    June 2, 2015, and EASA AD 2015-0220, dated November 9, 2015.  You  may
    view the EASA ADs on the internet  at  https://www.regulations.gov  in
    Docket No. FAA-2015-4497.

(3) The following documents, which are not incorporated by reference, con-
    tain additional information about  the subject of this  AD: Eurocopter
    Alert Service Bulletin ASB-BO  105-80-118, Revision 1, dated  November
    29, 1995; Eurocopter Information  Notice 2370-I-24, Revision 0,  dated
    November 15, 2011; Eurocopter Service Bulletin SB-BO105-80-119,  dated
    November 7,  1994; and  Eurocopter Service  Bulletin SB  BO105-90-104,
    Revision 1, dated June 21, 2010.

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

(j) MATERIAL INCORPORATED BY REFERENCE

(1) The Director of the Federal Register  approved  the  incorporation  by
    reference (IBR) 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 this AD specifies otherwise.

(i) Eurocopter  Alert Service Bulletin  ASB-MBB-BK117-90-118,  Revision 2,
    dated May 4, 2009.

(ii) Eurocopter Alert Service Bulletin ASB BO105-90-103, Revision 4, dated
     June 21, 2010.

(iii) Eurocopter Flight Manual BK117 A-3 Temporary Revision 9,  dated Sep-
      tember 22, 2006.

(iv) Eurocopter Flight Manual BK117 A-4 Temporary Revision 5,  dated  Sep-
     tember 22, 2006.

(v) Eurocopter Flight Manual BK117 B-1 Temporary Revision 6, dated Septem-
    ber 22, 2006.

(vi) Eurocopter Flight Manual BK 117 B-2 Temporary Revision 1,  dated Sep-
     tember 22, 2006.

(vii) Eurocopter Flight Manual BK 117 C-1 Temporary Revision 2, dated Sep-
      tember 22, 2006.

(3) For Eurocopter service information identified in this AD, contact Air-
    bus Helicopters,  2701 N Forum Drive,  Grand Prairie, TX 75052;  tele-
    phone 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 fedreg
    .legal@nara.gov,  or go to: https://www.archives.gov/federal-register/
    cfr/ibr-locations.html.

Issued  on  February  19,  2021. Lance  T.  Gant,  Director,  Compliance &
Airworthiness Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Ronnea L. Derby, Aerospace Engineer, Den-
ver ACO Branch, FAA, 26805 East 68th Ave, Room 214, Denver, CO 80249; tel-
ephone 303-342-1093; email ronnea.l.derby.@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4497; Project Identifier 2016-SW-011-AD; Amendment
39-21450; AD 2021-05-07]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters Deutschland GmbH
(Type Certificate Previously Held by Eurocopter Deutschland GmbH)
Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model BO-105A,
BO-105C, BO-105S, MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-
BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters. This AD was
prompted by a report of a loss of electrical ground between the
starter-generator and the generator voltage regulator (regulator). This
AD requires inspecting the starter-generator electrical ground
connection, retrofitting the starter-generator wire harness, and
depending on model, revising the existing Rotorcraft Flight Manual
(RFM) for your helicopter. The FAA is issuing this AD to address the
unsafe condition on these products.

DATES: This AD is effective April 16, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 16,
2021.

ADDRESSES: For Eurocopter service information identified in this final
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 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.

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-2015-
4497; 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, 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: Ronnea L. Derby, Aerospace Engineer,
Denver ACO Branch, FAA, 26805 East 68th Ave., Room 214, Denver, CO
80249; telephone 303-342-1093; email ronnea.l.derby.@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

The European Aviation Safety Agency (now European Union Aviation
Safety Agency) (EASA), which is the Technical Agent for the Member
States of the European Union, has issued EASA AD 2015-0098, dated June
2, 2015 (EASA AD 2015-0098), and EASA AD 2015-0220, dated November 9,
2015 (EASA AD 2015-0220) (also referred to as the Mandatory Continuing
Airworthiness Information, or the MCAI), to correct an unsafe condition
for all Airbus Helicopters Model MBB-BK117 A-1, MBB-BK117 A-3, MBB-
BK117 A-4, MBB-BK117 B-1, MBB-BK117 B-2, and MBB-BK117 C-1 helicopters;
and Airbus Helicopters Model BO105 A, BO105 C, BO105 D and BO105 S
helicopters with certain part-numbered voltage regulators.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain Airbus
Helicopters Model BO-105A, BO-105C, and BO-105S helicopters; and all
Airbus Helicopters Model MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-
4, MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters. The
NPRM published in the Federal Register on July 16, 2020 (85 FR 43153).
The NPRM was prompted by a report of a loss of electrical ground
between the starter-generator and the regulator. The NPRM proposed to
require inspecting the starter-generator electrical ground connection,
retrofitting the starter-generator wire harness, and depending on
model, revising the existing RFM for your helicopter.
The FAA is issuing this AD to address the loss of electrical ground
between the starter-generator and the regulator. This condition could
result in an overvoltage of electrical power, damage to electronic
equipment, and subsequent loss of control of the helicopter.

Comments

The FAA gave the public the opportunity to participate in
developing this final rule. The FAA received no comments on the NPRM or
on the determination of the cost to the public.

Conclusion

The FAA reviewed the relevant data and determined that air safety
and the public interest require adopting this final rule as proposed,
except for minor editorial changes. The FAA has determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

Eurocopter (now Airbus Helicopters) issued Alert Service Bulletin
ASB-MBB-BK117-90-118, Revision 2, dated May 4, 2009, for certain Model
MBB-BK117 helicopters and Alert Service Bulletin ASB BO105-90-103,
Revision 4, dated June 21, 2010, for certain Model BO105 helicopters.
This service information specifies a visual inspection for damage,
corrosion, and cracks and measuring the resistance of the left-hand and
right-hand electrical ground connections between each starter-generator
and the regulator. If there is damage or suspected damage, or if the
resistance is out of tolerance, this service information specifies
replacing the wire terminal. This service information also specifies
performing the visual inspection and resistance measurement each time
the starter generator is removed or the wiring is disconnected until a
retrofit ground connection is installed. These documents are distinct
since they apply to different models.
Eurocopter also issued Eurocopter Flight Manual BK117 A-3 Temporary
Revision 9, Eurocopter Flight Manual BK117 A-4 Temporary Revision 5,
Eurocopter Flight Manual BK117 B-1 Temporary Revision 6, Eurocopter
Flight Manual BK 117 B-2 Temporary Revision 1, and Eurocopter Flight
Manual BK 117 C-1 Temporary Revision 2, all dated September 22, 2006,
to provide updated procedures in the event of a generator failure.
These documents are distinct since they apply to different 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

Eurocopter (now Airbus Helicopters) issued Service Bulletin SB
BO105-90-104, Revision 1, dated June 21, 2010, for certain Model BO105
helicopters. This service information specifies procedures for
installing a retrofit ground connection of the starter-generator.
Eurocopter issued Alert Service Bulletin ASB-BO 105-80-118,
Revision 1, dated November 29, 1995, and Service Bulletin SB-BO105-80-
119, dated November 7, 1994, both for certain Model BO105 helicopters.
This service information specifies retrofitting certain helicopters
with voltage regulators that incorporate overvoltage protection by
modifying the main relay box, modifying the overhead panel, and
performing a functional test.
Eurocopter issued Information Notice 2370-I-24, Revision 0, dated
November 15, 2011, for certain Model BO105 helicopters to provide
notice that a modified starter-generator may only be installed on
helicopters that have also been modified. This service information
states that combining modified with non-modified can cause overvoltage
in the electrical system during the first ground run following engine
replacement and subsequent damage to electronic equipment. This service
information also recommends retrofitting all helicopters approved to
only fly under visual flight rules.

Differences Between This AD and the EASA ADs

The EASA ADs require visually inspecting the wire terminals for
damage, corrosion, and cracks. This AD requires visually inspecting for
a crack, a kink, fraying, looseness, missing material, and corrosion.
The EASA ADs require repeating the visual inspection and resistance
measurement each time a starter-generator is removed or the wiring is
disconnected from a starter-generator. This AD does not because such a
compliance time would be difficult to enforce.
EASA AD 2015-0220 requires additional actions for Model BO-105
helicopters with a serial number up to 0160 than for helicopters with a
serial number 0161 and larger. This AD requires the same actions for
all Model BO-105 helicopters regardless of serial number.
EASA AD 2015-0220 allows credit for complying with Eurocopter Alert
Service Bulletin ASB BO105-90-103, Revision 2 or Revision 3, whereas
this AD does not.

Costs of Compliance

The FAA estimates that this AD affects 40 Model BO-105 helicopters
and 44 Model MBB-BK 117 helicopters of U.S. Registry. The FAA estimates
that operators may incur the following costs in order to comply with
this AD using an estimated labor cost of $85 per work-hour.
Performing a visual inspection and resistance measurement of the
electrical ground connection takes about 2 work-hours for an estimated
cost of $170 per helicopter and $14,280 for the U.S. fleet per
inspection and measurement.
Performing the retrofit of the wiring harness takes about 10 work-
hours. Required parts for a Model BO-105 helicopter cost $2,509 for an
estimated replacement cost of $3,359 per helicopter and $134,360 for
the U.S. fleet. Required parts for a Model MBB-BK 117 helicopter cost
$1,730 for an estimated replacement cost of $2,580 per helicopter and
$113,520 for the U.S. fleet. Revising the existing RFM for Model MBB-BK
117 helicopters takes about 0.5 work-hour, for an estimated cost of $43
per helicopter and $1,892 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

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 adding the following new airworthiness
directive: