Document ID: FAA-2014-0308-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: M7 Aerospace LLC Airplanes
Posted Date: 2014-05-14T04:00Z

[Federal Register Volume 79, Number 93 (Wednesday, May 14, 2014)]
[Proposed Rules]
[Pages 27505-27508]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-11072]

 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 79, No. 93 / Wednesday, May 14, 2014 / 
Proposed Rules  

[[Page 27505]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0308; Directorate Identifier 2014-CE-012-AD]
RIN 2120-AA64

Airworthiness Directives; M7 Aerospace LLC Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt 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 proposed 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. This proposed AD would require 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 proposing this AD to correct the unsafe condition 
on these products.

DATES: We must receive comments on this proposed AD by June 30, 2014.

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 http://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 service information identified in this proposed 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 review 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2014-0308; 
Directorate Identifier 2014-CE-012-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We received reports of fatigue cracking of the main cabin door 
surround structure on several M7 Aerospace LLC Models SA227-AT, SA227-
AC, SA227-BC, SA227-CC, and SA227-DC airplanes that have a bayonet 
shear pin type of latching mechanism for the main cabin door.
    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.
    This condition, if not corrected, could result in probable 
decompression failure with possible loss of structural integrity of the 
cabin structure.

Relevant Service Information

    We reviewed M7 Aerospace LLC SA227 Series Commuter Category Service 
Bulletin CC7-53-005 and SA227 Series Service Bulletin 227-53-009, both 
dated November 15, 2013. The service information describes procedures 
for repetitively inspecting the internal and external skin doublers, 
fuselage skin, and the fuselage door frame corner member for cracks. 
The service information also describes procedures for repairing the 
cracks. In addition, if no cracks are found, the service information 
also includes procedures for installing a repair kit as preventative 
measure to extend the inspection intervals.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously. This proposed AD also 
requires sending inspection results to M7 Aerospace LLC.

Costs of Compliance

    We estimate that this proposed AD affects 250 airplanes of U.S. 
registry.

[[Page 27506]]

    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
              Action                     Labor  cost           Parts  cost          product         operators
----------------------------------------------------------------------------------------------------------------
Threshold high frequency eddy       2.5 work-hours x $85  Not Applicable......         $212.50          $53,125
 current (HFEC)/low frequency eddy   per hour = $212.50.
 current (LFEC)/detailed visual
 inspection.
----------------------------------------------------------------------------------------------------------------

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

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

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 proposed 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

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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].

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

M7 Aerospace LLC: Docket No. FAA-2014-0308; Directorate Identifier 
2014-CE-012-AD.

(a) Comments Due Date

    We must receive comments by June 30, 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,

[[Page 27507]]

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 an initial detailed visual inspection 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 inspection 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 the effective date of this AD.
    (ii) For aircraft with 20,001-35,000 TAC, inspect within the 
next 600 flight cycles after the effective date of this AD.
    (iii) For aircraft with 12,000-20,000 TAC, inspect within the 
next 1,000 flight cycles after 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 the 
effective date of this AD, whichever occurs later.
    (2) If no cracks are found during the inspection required by 
paragraph (g)(1) of this AD, repetitively thereafter at intervals 
not to exceed 2,000 flight cycles do a detailed visual inspection 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 installing repair kit part number (P/N) 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 replacing the fuselage skin by installing kit 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 no damage, defects, or cracks are found, you may install 
repair kit P/N 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 P/N 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 the effective date of this AD, owner/operators who had the 
initial 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

    (1) 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.
    (2) 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.m7aerospace.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.

[[Page 27508]]

    Issued in Kansas City, Missouri on May 7, 2014.
Timothy Smyth,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-11072 Filed 5-13-14; 8:45 am]
BILLING CODE 4910-13-P