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2014-15-01 M7 AEROSPACE LLC: Amendment 39-17903; Docket No. FAA-2014-0308; Directorate Identifier 2014-CE-012-AD.
(a) EFFECTIVE DATE

    This AD is effective August 27, 2014.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD applies to the M7 Aerospace LLC airplanes listed in paragraphs
    (c)(1) through  (c)(5) of  this AD  that are  equipped with  a bayonet
    shear pin main cabin door  latching mechanism and are certificated  in
    any category. Airplanes equipped with a "click-clack" main cabin  door
    latching  mechanism  are not  affected  by this  AD.  Figure 3  of  M7
    Aerospace LLC SA227 Series  Commuter Category Service Bulletin  CC7-53
    -005, and M7 Aerospace  LLC SA227 Series Service  Bulletin 227-53-009,
    both dated  November 15, 2013,  is  a picture  showing both  styles of
    latching mechanisms.

(1) Model SA227-AT airplanes,  serial numbers (S/Ns)  AT570 through AT631,
    and AT695.

(2) Model SA227-AC airplanes, S/Ns AC570 through AC788.

(3) Model SA227-BC airplanes,  S/Ns BC762, BC764, BC766, and BC770 through
    BC789.

(4) Model SA227-CC airplanes, S/N CC827, CC829, and CC840 through CC844.

(5) Model SA227-DC airplanes,  S/Ns DC784,  DC790  through  DC826,  DC828,
    DC830 through DC839, and DC845 through DC904.

(d) SUBJECT

    Joint Aircraft System Component (JASC)/Air Transport Association (ATA)
    of America - Code 5310, Fuselage Main, Structure.

(e) UNSAFE CONDITION

    This AD  was prompted  by fatigue  cracks found  in the  internal door
    surround doubler, the external skin fuselage skin, and the door corner
    fittings at the fuselage upper  forward corner of the main  cabin door
    cutout. We are  issuing the AD  to prevent decompression  failure with
    possible loss of structural integrity of the cabin structure.

(f) COMPLIANCE

    Comply with this AD within the compliance times specified in paragraph
    (g) through  paragraph (k)  of this  AD, including  all subparagraphs,
    unless already done.

(g) INSPECTIONS

(1) Do the initial inspections  of  the  fuselage upper forward corner and
    other 3  corners of  the main  cabin door  cutout for cracks following
    Table 1  in Step  2. ACCOMPLISHMENT  INSTRUCTIONS of  M7 Aerospace LLC
    SA227  Series  Commuter  Category Service  Bulletin  CC7-53-005  or M7
    Aerospace LLC  SA227 Series  Service Bulletin  227-53-009, both  dated
    November 15, 2013, as applicable. Do the inspections at the compliance
    times specified in paragraphs (g)(1)(i) through (g)(1)(iv) of this AD.
    For the purposes  of this AD,  owner/operators who do  not track total
    aircraft flight cycles (TAC), use  a .5 to 1 conversion,  e.g., 35,000
    TAC  is  equivalent  to   17,500  hours  time-in-service  (TIS).   For
    owner/operators  who  do  not  track  flight  cycles,  use  a  1  to 1
    conversion, e.g., 300 flight cycles are equivalent to 300 hours TIS.

(i) For aircraft with more than 35,000 TAC,  inspect  within  the next 300
    flight cycles after August 27, 2014 (the effective date of this AD).

(ii) For aircraft with 20,001 - 35,000 TAC,  inspect  within  the next 600
     flight cycles after August 27, 2014 (the effective date of this AD).

(iii) For aircraft with 12,000 - 20,000 TAC, inspect within the next 1,000
      flight cycles after August 27, 2014 (the effective date of this AD).

(iv) For  aircraft  with  less  than 12,000 TAC,  inspect at 12,000 flight
     cycles or within the next  1,000 flight cycles after August  27, 2014
     (the effective date of this AD), whichever occurs later.

(2) If no  cracks  are  found during the inspections required by paragraph
    (g)(1) of this AD, repetitively thereafter at intervals not to  exceed
    2,000 flight cycles do the  inspections of the fuselage upper  forward
    corner and other 3  corners of the main  cabin door cutout for  cracks
    following  Table  1  in  Step  2.  ACCOMPLISHMENT  INSTRUCTIONS  of M7
    Aerospace LLC  SA227 Series  Commuter Category Service Bulletin CC7-53
    -005  or  M7 Aerospace  LLC SA227  Series Service Bulletin 227-53-009,
    both dated November 15, 2013, as applicable.

(h) REPAIR CRACKS AND REPETITIVELY INSPECT

(1) If any  cracks  are  found during any inspection required in paragraph
    (g) through paragraph (i) of this AD, before further flight after  the
    inspection in which  a crack is  found, repair or  replace the cracked
    structure following Step  3. REPAIR OF  CRACKED INNER DOUBLE,  Step 4.
    REPAIR OF  CRACKED FUSELAGE  SKIN, and/or  Step 5.  REPAIR OF  CRACKED
    CORNER  FITTING of  M7 Aerospace  LLC SA227  Series Commuter  Category
    Service Bulletin CC7-53-005, or M7 Aerospace LLC SA227 Series  Service
    Bulletin 227-53-009, both dated November 15, 2013, as applicable.

(2) If you made the repairs required in paragraph (h)(1) of this AD by in-
    stalling repair kit drawing 27K24191-001, do the threshold and  repeat
    inspections following Table 2  in Step 2. ACCOMPLISHMENT  INSTRUCTIONS
    of M7 Aerospace  LLC SA227 Series  Commuter Category Service  Bulletin
    CC7-53-005, dated November 15, 2013; or M7 Aerospace LLC SA227  Series
    Service Bulletin 227-53-009, dated November 15, 2013, as applicable.

(3) If you made the repairs required in paragraph (h)(1) of this AD by re-
    placing the fuselage  skin by installing  repair kit drawing  27K24191
    -003, or if the  corner fitting was replaced  and no other cracks  are
    present, repetitively thereafter inspect following Table 1 in Step  2.
    ACCOMPLISHMENT INSTRUCTIONS of M7 Aerospace LLC SA227 Series  Commuter
    Category Service Bulletin CC7-53-005, or M7 Aerospace LLC SA227 Series
    Service  Bulletin  227-53-009,  both  dated  November  15,  2013,   as
    applicable.

(i) EXTEND REPETITIVE INSPECTION INTERVALS

    After any inspection required in  paragraph (g)(1) and (g)(2) of  this
    AD and if  no damage, defects,  or cracks are  found, you may  install
    repair  kit drawing  27K24191-001 following  Step 6.  ADDITION OF  KIT
    DRAWING  REPAIR MEMBERS  AS PREVENTATIVE  ACTION of  M7 Aerospace  LLC
    SA227  Series Commuter  Category Service  Bulletin CC7-53-005,  or  M7
    Aerospace LLC  SA227 Series  Service Bulletin  227-53-009, both  dated
    November 15, 2013, as applicable, to extend the inspection  intervals.
    After installing repair kit drawing 27K24191-001, do the threshold and
    repeat  inspections  following  Table  3  of  Step  2.  ACCOMPLISHMENT
    INSTRUCTIONS  of  M7  Aerospace  LLC  SA227  Series  Commuter Category
    Service Bulletin CC7-53-005, or M7 Aerospace LLC SA227 Series  Service
    Bulletin 227-53-009, both dated November 15, 2013, as applicable.

(j) REPORTING REQUIREMENT

    Within 30 days after any inspection required by paragraph (g)  through
    paragraph (i) of this AD where  a crack or any other damage  is found,
    report the results  of that inspection  to M7 Aerospace  LLC following
    the  instructions  specified  in  Step  2.I.  of  the   ACCOMPLISHMENT
    INSTRUCTIONS  of  M7  Aerospace  LLC  SA227  Series  Commuter Category
    Service Bulletin CC7-53-005, dated November 15, 2013; or Step 2.J.  of
    the  ACCOMPLISHMENT  INSTRUCTIONS  of M7  Aerospace  LLC  SA227 Series
    Service Bulletin 227-53-009, dated November 15, 2013, as applicable.

(k) CREDIT FOR PREVIOUS REPAIRS

    As of August 27, 2014 (the effective date of this AD), owner/operators
    who had the  an inspection and  any resulting repairs  done before the
    effective  date  of  this AD  using  procedures  different from  those
    specified in M7 Aerospace  LLC SA227 Series Commuter  Category Service
    Bulletin CC7-53-005,  dated November  15, 2013;  and M7  Aerospace LLC
    SA227 Series Service Bulletin 227-53-009, dated November 15, 2013, may
    apply for  an alternative  method of  compliance (AMOC)  following the
    instructions in paragraph (m) of this AD.

(l) PAPERWORK REDUCTION ACT BURDEN STATEMENT

    A federal  agency may  not conduct  or sponsor,  and a  person is  not
    required to respond to, nor shall a person be subject to a penalty for
    failure to  comply with  a collection  of information  subject to  the
    requirements of the Paperwork Reduction Act unless that collection  of
    information  displays  a current  valid  OMB Control  Number.  The OMB
    Control Number  for this  information collection  is 2120-0056. Public
    reporting  for  this  collection of  information  is  estimated to  be
    approximately 5 minutes per response, including the time for reviewing
    instructions, completing and reviewing the collection of  information.
    All  responses  to  this  collection  of  information  are  mandatory.
    Comments concerning the  accuracy of this  burden and suggestions  for
    reducing the burden should be directed to the FAA at: 800 Independence
    Ave. SW, Washington, DC 20591, Attn: Information Collection  Clearance
    Officer, AES-200.

(m) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager,  Fort Worth Airplane Certification Office,  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 the Related Information section of this AD.

(2) 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.

(n) RELATED INFORMATION

    For more information about this AD,  contact Andrew McAnaul, Aerospace
    Engineer,  FAA,  ASW-150 (c/o San Antonio MIDO),  10100 Reunion Place,
    Suite 650, San Antonio, Texas 78216; phone: (210) 308-3365; fax: (210)
    308-3370; email: andrew.mcanaul@faa.gov.

(o) 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 the AD specifies otherwise.

(i) M7 Aerospace LLC  SA227  Series  Commuter  Category  Service  Bulletin
    CC7-53-005, dated November 15, 2013.

(ii) M7 Aerospace LLC  SA227  Series  Service  Bulletin 227-53-009,  dated
     November 15, 2013.

(3) For  M7 Aerospace LLC  service  information  identified  in  this  AD,
    contact  M7 Aerospace LLC,  10823 NE Entrance Road, San Antonio, Texas
    78216; phone: (210) 824-9421;  fax: (210) 804-7766;  Internet: http://
    www.m7aerospace.com; email: MetroTech@M7Aerospace.com.

(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 Kansas  City,  Missouri  on  July 14, 2014.  Kelly A. Broadway,
Acting  Manager,  Small   Airplane  Directorate,  Aircraft   Certification
Service.

FOR FURTHER INFORMATION CONTACT: Andrew McAnaul, Aerospace Engineer,  FAA,
ASW-150  (c/o  San Antonio  MIDO),  10100 Reunion  Place,  Suite 650,  San
Antonio, Texas 78216;  phone: (210) 308-3365;  fax: (210) 308-3370; email:
andrew.mcanaul@faa.gov.
PREAMBLE 

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: We are adopting a new airworthiness directive (AD) for M7
Aerospace LLC Models SA227-AT, SA227-AC, SA227-BC, SA227-CC, and
SA227- DC airplanes equipped with a bayonet shear pin main cabin door
latching mechanism. This AD was prompted by fatigue cracks found in the
internal door surround doubler, the fuselage external skin, and the door
corner fittings at the fuselage upper forward corner of the main cabin door
cutout. This AD requires repetitively inspecting the four corners of
the main cabin door cutout for cracks, making necessary repairs, and
reporting inspection results to M7 Aerospace LLC. We are issuing this
AD to correct the unsafe condition on these products.

DATES: This AD is effective August 27, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 27,
2014.

ADDRESSES: For service information identified in this AD, contact M7
Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas 78216;
phone: (210) 824-9421; fax: (210) 804-7766; Internet: http://www.
elbitsystems-us.com; email: MetroTech@M7Aerospace.com. 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 by searching for and locating Docket No. FAA-2014-
0308; 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: Andrew McAnaul, Aerospace
Engineer, FAA, ASW-150 (c/o San Antonio MIDO), 10100 Reunion Place,
Suite 650, San Antonio, Texas 78216; phone: (210) 308-3365; fax: (210)
308-3370; email: andrew.mcanaul@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 M7 Aerospace LLC Models
SA227-AT, SA227-AC, SA227-BC, SA227-CC, and SA227-DC airplanes
equipped with a bayonet shear pin main cabin door latching mechanism.
The NPRM published in the Federal Register on May 14, 2014 (79 FR 27505).
The NPRM was prompted by reports of fatigue cracking of the main
cabin door surround structure. Investigation revealed that the fatigue
cracks are related to a change in loading due to design changes in the
door surround structure and the door latching system. We are issuing
this AD to correct the unsafe condition on these products.

Comments

We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (79 FR 27505, May 14,
2014) or on the determination of the cost to the public.

Conclusion

We reviewed the relevant data and determined that air safety and
the public interest require adopting this AD as proposed except for
minor editorial. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 27505, May 14, 2014) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 27505, May 14, 2014).

Costs of Compliance

We estimate that this AD affects 250 airplanes of U.S. registry.
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
Threshold high frequency eddy current (HFEC)/low frequency eddy current (LFEC)/detailed visual inspection. 2.5 work-hours x $85 per hour = $212.50 Not Applicable
$212.50
$53,125

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

On-Condition Costs

Action
Labor cost
Parts cost
Cost per product
Repair Installation 48 work-hours x $85 per hour = $4,080.
$6,670
$10,750

Paperwork Reduction Act

A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW., Washington, DC 20591. ATTN: Information
Collection Clearance Officer, AES-200.

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):