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2019-20-09 DE HAVILLAND AIRCRAFT OF CANADA LIMITED (TYPE CERTIFICATE PREVIOUSLY HELD BY BOMBARDIER, INC.):
Amendment 39-19762; Docket No. FAA-2019-0493; Product Identifier 2019-NM-043-AD.

(a) EFFECTIVE DATE

    This AD is effective November 27, 2019.

(b) AFFECTED ADS

    This  AD  replaces  AD  2011-18-15,  Amendment 39-16797  (76 FR 54093,
    August 31, 2011) ("AD 2011-18-15").

(c) APPLICABILITY

    This  AD  applies  to  De Havilland Aircraft of Canada  Limited  Model
    DHC-8-400, -401, and -402 airplanes,  certificated  in  any  category,
    serial numbers 4001 through 4437 inclusive.

(d) SUBJECT

    Air Transport Association (ATA) of America Code 57, Wings.

(e) REASON

    This AD  was prompted  by in-service  reports of  cracked barrel  nuts
    found at the front  spar locations of the  wing-to-fuselage attachment
    joints, and  a loose  washer in  the barrel  nut assembly.  The FAA is
    issuing this AD to address cracked  barrel nuts and a loose washer  in
    the barrel nut assembly, which  could result in failure of  the barrel
    nuts, compromising  the structural  integrity of  the wing-to-fuselage
    attachments, and  possible separation  of the  wing from  the airplane
    during flight.

(f) COMPLIANCE

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

(g) RETAINED INITIAL AND REPETITIVE CHECKS AND INSPECTIONS,  WITH  REVISED
    SERVICE INFORMATION

    This paragraph restates the requirements of paragraph (g) of  AD 2011-
    18-15,  with  revised  service  information.  At  the  applicable time
    specified in paragraph (g)(1) or (2) of this AD: Do a torque check  to
    determine  if the  bolt preload  is correct,  and  if  the preload  is
    correct,  before  further flight,  do  a detailed  inspection  of each
    barrel  nut  and  cradle  for  cracking,  pitting  or  corrosion,   in
    accordance  with  paragraph  3.B.,  part  A,  of  the   Accomplishment
    Instructions  of Bombardier  Alert Service  Bulletin A84-57-25,  dated
    July 20, 2011; or  Bombardier Service Bulletin A84-57-25,  Revision A,
    dated  July 16, 2018.  After  the effective  date  of  this  AD,  only
    Bombardier  Service Bulletin A84-57-25,  Revision  A,  dated  July 16,
    2018, may  be used.  Repeat the  torque check  and, as applicable, the
    inspection thereafter at intervals not to exceed 2,000 flight hours or
    12 months, whichever occurs first.

(1) For airplanes that have accumulated 1,900  or  more total flight hours
    as of September 15, 2011 (the effective date of AD 2011-18-15), or for
    which it has been 12 months or more since the date of issuance of  the
    original Canadian airworthiness certificate or the date of issuance of
    the  original  Canadian  export  certificate  of  airworthiness  as of
    September 15, 2011: Within 100 flight hours or 10 days after September
    15, 2011, whichever occurs first.

(2) For airplanes that have accumulated less than 1,900 total flight hours
    as of September  15, 2011 (the  effective date of  AD 2011-18-15), and
    for which it has been less  than 12 months since the date  of issuance
    of  the original  Canadian airworthiness  certificate or  the date  of
    issuance of the original Canadian export certificate of  airworthiness
    as of  September 15,  2011: Prior  to the  accumulation of 2,000 total
    flight hours or  within 12 months  since the date  of issuance of  the
    original Canadian  standard airworthiness  certificate or  the date of
    issuance of the original Canadian export certificate of airworthiness,
    whichever occurs first.

(h) RETAINED CORRECTIVE ACTIONS FOR INCORRECT BOLT PRELOAD,  WITH  REVISED
    SERVICE INFORMATION

    This paragraph restates the requirements of paragraph (h) of  AD 2011-
    18-15, with revised service information. If any bolt preload is  found
    to be incorrect (i.e., the ring can be rotated during any torque check
    required by paragraph (g) of this AD), before further flight,  replace
    all hardware at that location (except the saddle washer and  retainer)
    in  accordance  with paragraph  3.B.,  part B,  of  the Accomplishment
    Instructions  of Bombardier  Alert Service  Bulletin A84-57-25,  dated
    July 20, 2011; or paragraph 3.B. of the Accomplishment Instructions of
    Bombardier Service Bulletin 84-57-26, Revision C, dated July 16, 2018.
    After the effective date of this AD,  only Bombardier Service Bulletin
    84-57-26, Revision C, dated July 16, 2018, may be used.

(i) RETAINED CORRECTIVE ACTIONS FOR BARREL NUT/CRADLE DISCREPANCIES,  WITH
    REVISED SERVICE INFORMATION

    This paragraph restates the requirements of paragraph (i) of  AD 2011-
    18-15, with  revised service  information. If  any crack,  pitting, or
    corrosion of the barrel nut  or cradle is found during  any inspection
    required by paragraph (g) of  this AD, before further flight,  replace
    all hardware at that location (except the saddle washer and  retainer)
    in  accordance  with paragraph  3.B.,  part B,  of  the Accomplishment
    Instructions  of Bombardier  Alert Service  Bulletin A84-57-25,  dated
    July 20, 2011; or paragraph 3.B. of the Accomplishment Instructions of
    Bombardier Service Bulletin 84-57-26, Revision C, dated July 16, 2018.
    After the effective date of this AD, only Bombardier Service  Bulletin
    84-57-26, Revision C, dated July 16, 2018, may be used.

(j) NEW REQUIREMENT OF THIS AD: REPLACEMENT AND VISUAL INSPECTION

    Within 12,000 flight  hours or 72  months after the  effective date of
    this AD, whichever occurs first: Do a visual inspection of the  saddle
    washer and retainer for any damage (cracks) or corrosion; and  replace
    the  wing  front  spar  barrel  nuts,  bolts,  and  preload indicating
    washers;  in  accordance  with paragraph  3.B.  of  the Accomplishment
    Instructions  of  Bombardier Service  Bulletin  84-57-26,  Revision C,
    dated July 16, 2018.

(k) NEW CORRECTIVE ACTIONS FOR DAMAGE (CRACKS) OR CORROSION

    If any damage (cracks) or corrosion is found during any inspection re-
    quired by paragraph (j) of this AD: Before further flight,  accomplish
    corrective  actions  in  accordance with  the procedures  specified in
    paragraph (p)(2) of this AD.

(l) NEW PROVISION OF THIS AD:  TERMINATING ACTIONS  FOR  REPETITIVE TORQUE
    CHECKS AND DETAILED INSPECTIONS

    Accomplishment of  the applicable  actions required  by paragraphs (j)
    and (k) of this AD, at  all four barrel nut locations, terminates  the
    repetitive torque checks and detailed inspections of paragraph (g)  of
    this AD.

(m) PARTS INSTALLATION PROHIBITION

    As of the effective date of this AD no person may install, on any air-
    plane, a barrel nut having part number DSC228-16.

(n) RETAINED  SPECIAL FLIGHT PERMIT PROVISIONS,  WITH  REVISED  COMPLIANCE
    LANGUAGE

    This paragraph restates the requirements of paragraph (k) of  AD 2011-
    18-15, with  revised compliance  language. Special  flight permits, as
    described in 14 CFR  21.197 and 21.199, may  be issued to operate  the
    airplane  to  a  location where  the requirements  of this  AD can  be
    accomplished, but  concurrence by  the Manager,  New York  ACO Branch,
    FAA, is required before issuance of the special flight permit.  Before
    using  any  approved  special flight  permits,  notify  your principal
    maintenance inspector (PMI) or principal avionics inspector (PAI),  as
    appropriate,  or  lacking  a principal  inspector,  your  local Flight
    Standards  District Office  (FSDO).  Operators  must request  a repair
    drawing  from Bombardier,  Inc., or  De Havilland  Aircraft of  Canada
    Limited, which provides recommendations for a one-time special  flight
    permit.  After  the  effective  date of  this  AD,  only  De Havilland
    Aircraft of Canada Limited may provide the repair drawing. The  repair
    drawing will be  applicable to the  operatorís aircraft serial  number
    only.  Special  flight  permits may  be  permitted  provided that  the
    conditions specified in paragraphs (n)(1)  through (5) of this AD  are
    met.

(1) Only one barrel nut out of four is cracked,  one cradle is cracked, or
    one washer is loose;  all other strut (wing front spar) bolt locations
    must be free of damage.

(2) The airplane must operate with reduced airspeed not to exceed 180 KIAS
    (knots indicated air speed). No passengers and no cargo are onboard.

(3) The airplane must not operate in known  or forecast turbulence,  other
    than light turbulence.

(4) The airplane descent rate on landing flare-out is not to exceed 5 feet
    per second.

(5) Heavy braking  or  hard turning of the airplane  upon landing is to be
    avoided if possible.

(o) CREDIT FOR PREVIOUS ACTIONS

(1) This paragraph  restates the provisions of paragraph (j)  of  AD 2011-
    18-15, with revised formatting  and updated service information.  This
    paragraph provides credit for torque checks, initial inspections,  and
    replacements required by paragraphs (g)  and (h) of this AD,  if those
    actions were performed before the effective date of this AD using  the
    service information specified in  paragraphs (o)(1)(i) through (v)  of
    this  AD,  which  is not  incorporated by  reference in  this AD.  The
    repetitive torque checks, and as applicable, the inspections  required
    by paragraph (g) of this AD must be continued at the time specified.

(i) Bombardier Alert Service Bulletin A84-57-19, dated February 1, 2008.

(ii) Bombardier  Alert  Service  Bulletin  A84-57-19,  Revision  A,  dated
     February 6, 2008.

(iii) Bombardier Alert Service Bulletin A84-57-19, Revision B, dated March
      6, 2008.

(iv) Bombardier Alert Service Bulletin A84-57-19, Revision C, dated August
     20, 2008.

(v) Bombardier Alert Service Bulletin A84-57-19, Revision D,  dated August
    12, 2011.

(2) This paragraph  provides credit for the actions required by paragraphs
    (h) through (k) of this AD, if those actions were performed before the
    effective date of this AD  using the service information specified  in
    paragraphs  (o)(2)(i)   through  (iii)   of  this   AD.  This  service
    information is not incorporated by reference in this AD.

(i) Bombardier Service Bulletin 84-57-26, dated March 21, 2013.

(ii) Bombardier Service Bulletin 84-57-26 Revision A, dated July 18, 2014.

(iii) Bombardier Service Bulletin 84-57-26, Revision B, dated February 26,
      2015.

(3) This paragraph provides credit for the actions required  by paragraphs
    (h) and (i) of this AD,  if  those  actions were performed  before the
    effective date of this AD  using the service information  specified in
    paragraphs (o)(3)(i) and (ii) of this AD.

(i) Bombardier Alert Service Bulletin A84-57-25 dated July 20, 2011, which
    was incorporated by reference in AD 2011-18-15.

(ii) Bombardier  Service Bulletin A84-57-25,  Revision A,  dated  July 16,
     2018, which is incorporated by reference in this AD.

(p) OTHER FAA AD PROVISIONS

(1) Alternative Methods of Compliance (AMOCs):  The Manager,  New York ACO
    Branch,  FAA,  has the authority to approve AMOCs for this AD,  if re-
    quested 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 ATTN: Program  Manager, Continuing Operational Safety,  FAA, New
    York ACO Branch, 1600 Stewart  Avenue, Suite 410, Westbury, NY  11590;
    phone:  516-228-7300;  fax: 516-794-5531.  Before  using any  approved
    AMOC,  notify  your  appropriate  principal  inspector,  or  lacking a
    principal  inspector,  the  manager  of  the  local  flight  standards
    district office/certificate holding district office.

(2) Contacting the Manufacturer:  For any requirement in this AD to obtain
    corrective  actions   from  a   manufacturer,  the   action  must   be
    accomplished using  a method  approved by  the Manager,  New York  ACO
    Branch,  FAA;  or  Transport  Canada  Civil  Aviation  (TCCA);  or  De
    Havilland   Aircraft  of   Canada  Limitedís   TCCA  Design   Approval
    Organization (DAO). If approved by the DAO, the approval must  include
    the DAOauthorized signature.

(3) AMOCs approved previously  for AD 2011-18-15 are approved as AMOCs for
    the corresponding provisions of this AD.

(q) RELATED INFORMATION

(1) Refer   to   Mandatory  Continuing  Airworthiness  Information  (MCAI)
    Canadian AD CF-2011-24R1, dated January 21, 2019, for related informa-
    tion. This MCAI may be found in the AD docket on the Internet at http:
    //www.regulations.gov by searching  for  and  locating Docket No. FAA-
    2019-0493.

(2) For more information about this AD,  contact Andrea Jimenez, Aerospace
    Engineer, Airframe and Propulsion Section,  FAA,  New York ACO Branch,
    1600 Stewart Ave., Suite 410, Westbury, NY 11590; phone: 516-228-7330;
    fax: 516-794-5531; email: 9-avs-nyaco-cos@faa.gov.

(3) Service information  identified in this AD that is not incorporated by
    reference is available at the addresses specified in paragraphs (r)(4)
    and (5) of this AD.

(r) 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.

(3) The following service information was approved for IBR on November 27,
    2019.

(i) Bombardier Service Bulletin A84-57-25, Revision A, dated July 16, 2018

(ii) Bombardier Service Bulletin 84-57-26, Revision C, dated July 16, 2018

(4) For service information identified  in this AD,  contact  De Havilland
    Aircraft of Canada Ltd.,  Q-Series  Technical  Help  Desk, 123 Garratt
    Boulevard, Toronto, Ontario M3K 1Y5, Canada; phone: 416-375-4000; fax:
    416-375-4539; email thd@dehavilland.com; Internet https://dehavilland.
    com.

(5) You may view this service information at the FAA,  Transport Standards
    Branch,  2200 South 216th St., Des Moines, WA.  For information on the
    availability of this material at the FAA, call 206-231-3195.

(6) You  may  view  this  service  information  that  is  incorporated  by
    reference 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:  http://www.archives.gov/federal-
    register/cfr/ibr-locations.html.

Issued  in  Des Moines, Washington, on October 7, 2019.  Michael Kaszycki,
Acting Manager, System Oversight Division,  Aircraft Certification Service

FOR FURTHER INFORMATION CONTACT: Andrea Jimenez,  Aerospace Engineer, Air-
frame and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart Ave.,
Suite 410, Westbury, NY 11590;  phone: 516-228-7330; fax: 516-794-5531; e-
mail: 9-avs-nyaco-cos@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0493; Product Identifier 2019-NM-043-AD; Amendment
39-19762; AD 2019-20-09]
RIN 2120-AA64

Airworthiness Directives; De Havilland Aircraft of Canada Limited
(Type Certificate Previously Held by Bombardier, Inc.) Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2011-18-
15, which applied to certain De Havilland Aircraft of Canada Limited
Model DHC-8-400 series airplanes. AD 2011-18-15 required initial and
repetitive torque checks of the bolt preload; detailed inspection of
the barrel nuts and cradle for cracking, pitting, and corrosion if the
bolt preload is correct; and replacement of certain hardware if
necessary. This AD continues to require those actions. This AD also
requires new inspections and replacement of certain hardware, which
would terminate the repetitive torque checks and inspections; and
removes airplanes from the applicability. This AD was prompted by in-
service reports of cracked barrel nuts found at the front spar
locations of the wing-to-fuselage attachment joints, and a loose washer
in the barrel nut assembly. The FAA is issuing this AD to address the
unsafe condition on these products.

DATES: This AD is effective November 27, 2019.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 27,
2019.

ADDRESSES: For service information identified in this final rule,
contact De Havilland Aircraft of Canada Ltd., Q-Series Technical Help
Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; phone:
416-375-4000; fax: 416-375-4539; email: thd@dehavilland.com; internet:
https://dehavilland.com. You may view this referenced service
information at the FAA, Transport Standards Branch, 2200 South 216th
St., Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195. It is also available on the
internet at http://www.regulations.gov by searching for and locating
Docket No. FAA-2019-0493.

Examining the AD Docket

You may examine the AD docket on the internet at http://www.regulations.
gov by searching for and locating Docket No. FAA-2019-
0493; 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 regulatory evaluation, any comments received, and
other information. The address for Docket Operations is U.S. Department
of Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer,
Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590; phone: 516-228-7330; fax: 516-
794-5531; email: 9-avs-nyaco-cos@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD CF-2011-24R1, dated
January 21, 2019 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for certain De Havilland Aircraft of Canada Limited Model
DHC-8-400 series airplanes. You may examine the MCAI in the AD docket
on the internet at http://www.regulations.gov by searching for and
locating Docket No. FAA-2019-0493.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2011-18-15, Amendment 39-16797 (76 FR
54093, August 31, 2011) (``AD 2011-18-15''). AD 2011-18-15 applied to
certain De Havilland Aircraft of Canada Limited Model DHC-8-400 series
airplanes. The NPRM published in the Federal Register on July 9, 2019
(84 FR 32664). The NPRM was prompted by in-service reports of cracked
barrel nuts found at the front spar locations of the wing-to-fuselage
attachment joints, and a loose washer in the barrel nut assembly. The
NPRM proposed to continue to require initial and repetitive torque
checks of the bolt preload; detailed inspection of the barrel nuts and
cradle for cracking, pitting, and corrosion if the bolt preload is
correct; and replacement of hardware if necessary. The NPRM also
proposed to require new inspections and replacement of certain
hardware, which would terminate the repetitive torque checks and
inspections; and remove airplanes from the applicability. We are
issuing this AD to address cracked barrel nuts and a loose washer in
the barrel nut assembly, which could result in failure of the barrel
nuts, compromising the structural integrity of the wing-to-fuselage
attachments, and possible separation of the wing from the airplane
during flight. See the MCAI for additional background information.

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.

Explanation of Changes Made to This Final Rule

The FAA has revised this final rule to identify the legal name of
the manufacturer as published in the most recent type certificate data
sheet (TCDS) for the affected airplane models.
The FAA has revised paragraph (n) of this AD to refer to De
Havilland Aircraft of Canada Limited (the current TCDS holder) as the
appropriate contact for the referenced repair drawing.

Conclusion

The FAA reviewed the relevant data and determined that air safety
and the public interest require adopting this final rule as proposed,
with the changes described previously and 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.
The FAA also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.

Related Service Information Under 1 CFR Part 51

Bombardier has issued the following service information.
Service Bulletin A84-57-25, Revision A, dated July 16,
2018. This service information describes procedures for initial and
repetitive torque checks of the bolt preload, detailed inspection of
the barrel nuts and cradle for cracking, pitting, and corrosion if the
bolt preload is correct, and replacement of hardware if necessary.
Service Bulletin 84-57-26, Revision C, dated July 16,
2018. This service information describes procedures for a visual
inspection of the saddle washer and retainer for any damage (cracks)
and corrosion, and replacement of the existing wing front spar barrel
nuts, bolts, and preload indicating washers.
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.

Costs of Compliance

The FAA estimates that this AD affects 54 airplanes of U.S.
registry.
The FAA estimates the following costs to comply with this AD:

Estimated Costs for Required Actions

Action
Labor cost
Parts cost Cost per product Cost on U.S. operators
Retained actions from AD 2011-18-15 15 work-hours x $85 per hour = $1,275
$10,492
$11,767
$635,418
New actions 15 work-hours x $85 per hour = $1,275
10,492
11,767
635,418

The FAA has received no definitive data that would enable us to
provide cost estimates for the on-condition repairs specified in this
AD.

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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes and
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

The FAA 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 removing Airworthiness Directive (AD)
2011-18-15, Amendment 39-16797 (76 FR 54093, August 31, 2011), and
adding the following new AD: