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2013-24-03	BEECHCRAFT CORPORATION (TYPE CERTIFICATE PREVIOUSLY HELD BY HAWKER BEECHCRAFT CORPORATION): Amendment 39-17677; Docket No. FAA-2013-0753; Directorate Identifier 2013-CE-025-AD.

(a) EFFECTIVE DATE

    This AD is effective January 13, 2014.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD applies to  the following Beechcraft Corporation  airplanes in
    table 1 of this AD, certificated in any category:

             TABLE 1 TO PARAGRAPH (C) OF THIS AD - APPLICABILITY          
    ______________________________________________________________________
          MODEL                            SERIAL NUMBERS
    ______________________________________________________________________
          1900                    UA-3.

          1900C                   UB-1 through UB-74, UC-1 through UC-174.

          1900C (C-12J)           UD-1 through UD-6.

          1900D                   UE-1 through UE-439.
    ______________________________________________________________________

(d) SUBJECT

    Joint Aircraft System Component (JASC)/Air Transport Association (ATA)
    of America Code 55, Stabilizers.

(e) UNSAFE CONDITION

    This AD  was prompted  by reports  of cracking  in the  front spar cap
    angles and hat  section of the  vertical stabilizer structure.  We are
    issuing  this  AD  to  detect and  correct  cracking  in  the vertical
    stabilizer structure, which  could lead to  structural failure of  the
    vertical stabilizer and result in loss of control.

(f) COMPLIANCE

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

(g) VISUAL INSPECTIONS

(1) For  all  airplanes:  Within  the next 600 hours time-in-service (TIS)
    after January 13, 2014 (the  effective date of this AD),  inspect part
    number (P/N) 101-640011-3/-4 spar angles and P/N 114-640000-25/-26 hat
    section  for  cracks  following  the  Accomplishment  Instructions  in
    paragraph 3.A. of Hawker  Beechcraft Mandatory Service Bulletin  SB 55
    -4114, dated August 2012.

(2) For Models 1900 and 1900C airplanes:  Within 1,200 hours TIS after the
    initial inspection required in paragraph (g)(1) of this AD or within 2
    years after  the initial  inspection required  in paragraph  (g)(1) of
    this  AD,  whichever  occurs  first,  and  repetitively  thereafter at
    intervals not to exceed 1,200  hours TIS or 2 years,  whichever occurs
    first, inspect P/N 101-640011-3  and P/N 101-640011-4 spar  cap angles
    for cracks. Follow  Procedure 8 under  Vertical Stabilizer in  the "I"
    Check  Procedures of  Hawker Beechcraft  Corporation Model  1900/1900C
    Airliner Structural Inspection  Manual, Part Number  98-30937G2, dated
    May 1, 2013.

(3) For Models 1900 and 1900C airplanes:  Within 1,200 hours TIS after the
    initial inspection required in paragraph (g)(1) of this AD or within 2
    years after  the initial  inspection required  in paragraph  (g)(1) of
    this  AD,  whichever  occurs  first,  and  repetitively  thereafter at
    intervals not to exceed 1,200  hours TIS or 2 years,  whichever occurs
    first, inspect P/N 114-640000-25 and P/N 114-640000-26 hat section for
    cracks. Follow Procedure 9 under Vertical Stabilizer in the "I"  Check
    Procedures of Hawker Beechcraft Corporation Model 1900/1900C  Airliner
    Structural Inspection  Manual,  Part  Number 98-30937G2,  dated May 1,
    2013.

(4) For Model 1900D airplanes: Within 1,200 hours TIS  after  the  initial
    inspection required in paragraph (g)(1)  of this AD or within  2 years
    after the initial inspection required in paragraph (g)(1) of this  AD,
    whichever occurs first, and  repetitively thereafter at intervals  not
    to exceed 1,200 hours TIS or 2 years, whichever occurs first,  inspect
    P/N  101-640011-3 and  P/N 101-640011-4  spar cap  angles for  cracks.
    Follow  Procedure  6.b. under  Vertical  Stabilizer Canted  Stabilizer
    Station (CSS 69.184 through VSS 91.10) in the "I" Check Procedures  of
    Beechcraft  Corporation  Model  1900D  Airliner  Structural Inspection
    Manual, Part Number 129-590000-65E5, dated May 1, 2013.

(5) For Model 1900D airplanes: Within 1,200 hours TIS  after  the  initial
    inspection required in paragraph (g)(1)  of this AD or within  2 years
    after the initial inspection required in paragraph (g)(1) of this  AD,
    whichever occurs first, and  repetitively thereafter at intervals  not
    to exceed 1,200 hours TIS or 2 years, whichever occurs first,  inspect
    P/N 114-640000-25 and P/N 114-640000-26 hat section for cracks. Follow
    Procedure  6.c. under  Vertical Stabilizer  Canted Stabilizer  Station
    (CSS  69.184  through  VSS  91.10)  in  the  "I"  Check  Procedures of
    Beechcraft  Corporation  Model  1900D  Airliner  Structural Inspection
    Manual, Part Number 129-590000-65E5, dated May 1, 2013.

(h) REPAIR

    If any  cracks are  found during  any of  the inspections  required in
    paragraph (g) of this AD, to include all subparagraphs, before further
    flight,  you  must  contact Beechcraft  Corporation  to  obtain repair
    instructions  approved by  the Wichita  Aircraft Certification  Office
    (ACO) specifically for compliance  with this AD and  incorporate those
    instructions.  You  can   find  contact  information   for  Beechcraft
    Corporation in paragraph (l)(3) of this AD.

(i) SPECIAL FLIGHT PERMIT

    If  cracks  are  found  during  any  of  the  inspections  required in
    paragraph (g) of  this AD, to  include all subparagraphs,  the FAA may
    allow a one-time special flight permit to a repair facility  depending
    on the  cracking found.  You must  contact Beechcraft  Corporation and
    provide  them  with crack  detail  information for  them  to determine
    residual strength  of the  airplane before  applying to  the FAA for a
    special flight permit. You can find contact information for Beechcraft
    Corporation in paragraph (l)(3) of this AD.

(j) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager, Wichita ACO, 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 ACO, send it  to
    the attention of the person identified in paragraph (k) of this AD.

(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.

(k) RELATED INFORMATION

    For more information about this AD,  contact  Paul Chapman,  Aerospace
    Engineer,  Wichita Aircraft  Certification Office,  FAA, 1801  Airport
    Road, Room  100, Wichita,  Kansas 67209;  phone: (316)  946-4152; fax:
    (316) 946-4107; email: paul.chapman@faa.gov.

(l) 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) Hawker Beechcraft Mandatory Service Bulletin SB 55-4114,  dated August
    2012.

(ii) Hawker  Beechcraft  Corporation  Model 1900/1900C Airliner Structural
     Inspection Manual, Part Number 98-30937G2, dated May 1, 2013.

(iii) Beechcraft  Corporation  Model  1900D Airliner Structural Inspection
      Manual, Part Number 129-590000-65E5, dated May 1, 2013.

(3) For  Beechraft Corporation  service information identified in this AD,
    contact Beechcraft Corporation at address:  10511 E. Central, Wichita,
    Kansas 67206; phone: (800) 429-5372 or (316) 676-3140; Internet: http:
    //www.beechcraft.com/customer_support/contact_us/.

(4) You  may  view  this  service  information  at the FAA, Small Airplane
    Directorate, 901 Locust, Kansas City, Missouri 64106. For  information
    on the availability of this material at the FAA, call (816) 329-4148.

(5) 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, call
    202-741-6030,  or go to: http://www.archives.gov/federal-register/cfr/
    ibr-locations.html.

Issued  in  Kanas  City, Missouri,  on  November 15, 2013.  Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Paul Chapman, Aerospace Engineer, Wichita
Aircraft Certification Office, FAA, 1801 Airport Road, Room 100,  Wichita,
Kansas 67209;  phone: (316) 946-4152;  fax: (316) 946-4107;  email:  paul.
chapman@faa.gov.

PREAMBLE

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Beechcraft Corporation (type certificate previously held by Hawker
Beechcraft Corporation) Models 1900, 1900C, and 1900D airplanes. This
AD was prompted by reports of cracking in the front spar cap angles and
hat section structure of the vertical stabilizer. This AD requires
inspections of the vertical stabilizer spar angles and hat section for
cracks with corrective actions as necessary. We are issuing this AD to
correct the unsafe condition on these products.

DATES: This AD is effective January 13, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 13,
2014.

ADDRESSES: For service information identified in this AD, contact
Beechcraft Corporation at address: 10511 E. Central, Wichita, Kansas
67206; phone: (800) 429-5372 or (316) 676-3140; Internet: http://www.beechcraft.com/customer_support/contact_us/. You may view this
referenced service information at the FAA, Small Airplane Directorate,
901 Locust, Kansas City, Missouri 64106. For information on the
availability of this material at the FAA, call (816) 329-4148.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.
gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (phone: 800-647-5527) is Document Management Facility,
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: Paul Chapman, Aerospace Engineer,
Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room
100, Wichita, Kansas 67209; phone: (316) 946-4152; fax: (316) 946-4107;
email: paul.chapman@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to the specified products. The
NPRM published in the Federal Register on August 27, 2013 (78 FR
52870). The NPRM proposed to require doing visual inspections of the
vertical stabilizer spar angles and hat section for cracks and taking
corrective actions as necessary.

Comments

We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
and the FAA's response to each comment.

Further Support for the AD

Scott Lewis suggested that the number of cracks reported may not be
accurate. The commenter stated that his fleet had 53 cracks, which is a
much higher percentage of airplanes cracked than the 56 cracks reported
in the 140 airplanes that Beechcraft reported to the FAA. The commenter
proposed no changes to the AD.
We agree that the percentage of cracks reported may be low. This
further justifies the need for the AD action and therefore, no changes
to the final rule are necessary.

Costs of Compliance Too Low

Scott Lewis stated the costs supplied by Beechcraft are too low and
that the actual costs are running $5,983 per side for the spar cap
angles plus $9,212 for engineer support for a total of $15,195. This is
compared to the $3,150 cited in the NPRM. This does not include the
cost of the hat section if it requires repair.

We agree with the commenter. After re-verifying the cost estimate
with Beechcraft, they have corrected the costs as follows:
$6,000 per side for the spar repair kit;
Around $15,000 for engineering support since these are not
standard repairs.
We have changed the AD accordingly.

Continued Flight Before Repair Provided Cracks Do Not Propagate

Scott Lewis stated that he had been issued up to an additional
2,700 flight hours after a crack was found as long as the crack did not
propagate. Although no request to change the NPRM was made, the FAA
infers that the commenter wants to add the provision of flight with
known cracks provided any known crack does not propagate.
The FAA does not agree. The FAA's Small Airplane Directorate does
not allow further flight with known cracks in critical structure
without additional substantiating data. Advisory Circular (AC) 23-13A,
Chapter 6, dated September 29, 2005, describes what additional data is
required to allow flight with known cracks (found on the Internet at
http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgAdvisoryCircular.nsf).
We are making no changes to the AD based on this comment.

Conclusion

We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD as proposed except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (78 FR 52870, August 27, 2013) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 52870, August 27, 2013).

Costs of Compliance

We estimate that this AD affects 400 airplanes.
We estimate the following costs to comply with this AD:

Estimated Costs

Action	Labor cost	Parts cost	Cost per product	Cost on U.S. operators
Visual inspection of the vertical stabilizer spar angles and hat section.	1.5 work-hours x $85 per hour = $127.50	Not applicable	$127.50	$51,000

We estimate the following costs to do any necessary repairs that
are required based on the results of the inspection. We have no way of
determining the number of airplanes that might need these repairs:

On-Condition Costs

Action	Labor cost	Parts cost	Cost per product
Repair of the spar cap (right hand or left hand).	30 work-hours x $85 per hour = $2,550.	$6,000 per side plus $15,000 per engineering support.	As much as $29,550 if both sides needed repair.

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.
We are 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) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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 (AD):