[Federal Register Volume 80, Number 115 (Tuesday, June 16, 2015)]
[Proposed Rules]
[Pages 34326-34330]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-14698]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2207; Directorate Identifier 2015-CE-003-AD]
RIN 2120-AA64


Airworthiness Directives; M7 Aerospace LLC Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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[[Page 34327]]

SUMMARY: We propose to supersede Airworthiness Directive (AD) 97-02-02, 
which applies to certain Models SA26-AT, SA26-T, SA226-AT, SA226-T, 
SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), 
SA227-CC, SA227-DC (C-26B), and SA227-TT airplanes. AD 97-02-02 
currently requires applying torque to the control column pitch bearing 
attaching nuts, inspecting the bearing assembly, inspecting the 
elevator control rod end bearing retainer/dust seals, and replacing or 
installing new parts as necessary. Since we issued AD 97-02-02, an 
operator experienced a complete loss of elevator control because of 
failure of the bolt attaching the elevator control rod to the elevator 
walking beam under the cockpit floor. This proposed AD would prevent 
loss of pitch control, which if not corrected, could result in loss of 
airplane control. We are proposing this AD to correct the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by July 31, 2015.

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: [email protected]. 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-2015-
2207; 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-143 (c/o San Antonio MIDO), 10100 Reunion Place, Suite 650, 
San Antonio, Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370; 
email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-2207; 
Directorate Identifier 2015-CE-003-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

    On January 6, 1997, we issued AD 97-02-02, Amendment 39-9886 (62 FR 
2552, January 17, 1997), (``AD 97-02-02''), for certain M7 Aerospace 
LLC Models SA26-AT, SA26-T, SA226-AT, SA226-T, SA226-T(B), SA226-TC, 
SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC (C-
26B), and SA227-TT airplanes. AD 97-02-02 requires applying torque to 
check the security of the control column pitch bearing attaching nuts, 
inspecting for any looseness or movement of the bearing assembly, and 
inspecting the elevator control rod end bearing retainer/dust seals for 
creasing. If any of these problems are evident, replace these parts, as 
well as install a new bolt and washer to the elevator control rod end 
bearing assembly at the walking beam connection. AD 97-02-02 resulted 
from reports of Fairchild SA227 series airplanes losing pitch control 
in-flight. We issued AD 97-02-02 to prevent loss of pitch control, 
which if not corrected, could result in loss of airplane control.

Actions Since AD 97-02-02 Was Issued

    Since we issued AD 97-02-02, an operator experienced complete loss 
of elevator control due to failure of the bolt attaching the elevator 
control rod to the elevator walking beam under the cockpit floor. A 
follow-on inspection of the operator's fleet revealed a variety of 
hardware installed. Some hardware matched the illustrated parts catalog 
(IPC), some matched the AD 97-02-02 configuration, and some matched 
neither of those configurations.
    When AD 97-02-02 was issued, the IPC was never revised to match the 
hardware configuration called out in AD 97-02-02 or in the service 
information associated with that AD. Because of the conflict between 
the AD and the IPC configurations, an airplane that was in compliance 
with the requirements of AD 97-02-02 could have had an incorrect 
hardware configuration installed during routine maintenance after 
complying with the AD. The IPC has been updated and corrected by M7 
Aerospace, LLC.
    Also, since we issued AD 97-02-02, the manufacturer developed an 
improved design for the control column pivot bearing and support 
structure that terminates the repetitive torque check and replacement 
of control column pivot bearings.
    The manufacturer also issued new service information that adds the 
10,000-hour time in service (TIS) repetitive replacement of the control 
column pivot bearing that is in the airworthiness limitations section 
(ALS) of the airplane maintenance manual (AMM) and (if this revision is 
mandated) requires the replacement of the pivot bearing with the 
improved design within 35,000 hours TIS that is in the supplemental 
inspections document (SID). Issue of the new service information, the 
revised IPC, and this proposed AD will eliminate the conflicts between 
AD 97-02-02, the service information, the IPC, the ALS, and the SID.

Relevant Service Information Under 1 CFR 51

    We reviewed M7 Aerospace SA26 Series Service Bulletin No. 26-27-30-
046 R2, dated December 5, 2014; Fairchild Aircraft SA26 Series Service 
Bulletin No. 26-27-30-047, dated June 16, 1997; M7 Aerospace SA226 
Series Service Bulletin No. 226-27-060 R2, dated December 5, 2014; 
Fairchild Aerospace SA226 Series Service Bulletin No. 226-27-061, dated 
June 16, 1997; M7 Aerospace SA227 Series Service Bulletin, No. 227-27-
041 R2, dated December 5, 2014; Fairchild

[[Page 34328]]

Aircraft SA227 Series Service Bulletin No. 227-27-042, dated June 16, 
1997; M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin 
No. CC7-27-010 R2, dated December 5, 2014; and Fairchild Aircraft SA227 
Series Commuter Category Service Bulletin No. CC7-27-011, dated June 
16, 1997. The service information describes procedures for inspecting 
for movement and correct torque of the elevator control pivot bearing, 
inspecting the elevator control rod for damage, and replacing parts as 
necessary. The service information also adds a repetitive replacement 
of the control column pivot bearings at 10,000 hours TIS and requires 
replacement of the control column pivot bearing with the improved 
design within 35,000 hours TIS. This 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 of the NPRM.

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 retain none of the requirements of AD 97-02-
02. This proposed AD would require inspecting for movement and correct 
torque of the elevator control pivot bearing, inspecting the elevator 
control rod for damage, and replacing parts as necessary. This proposed 
AD would also require a 10,000-hour TIS repetitive replacement of the 
control column pivot bearing and require replacement of the control 
column pivot bearing with the improved design within 35,000 hours TIS. 
Replacing the original control column pivot bearing with the improved 
design terminates the requirement to repetitively replace the original 
control column pivot bearing every 10,000 hours.

Costs of Compliance

    We estimate that this proposed AD affects 360 airplanes of U.S. 
registry.
    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
----------------------------------------------------------------------------------------------------------------
Inspection of torque on the      2 work-hours x $85  Not applicable.............            $170         $61,200
 control column pivot bearing.    per hour = $170.
Control column pivot bearing     8 work-hours x $85  300........................             980         352,800
 replacement.                     per hour = $680.
New designed control column      20 work-hours x     2,450......................           4,150       1,494,000
 pivot bearing replacement.       $85 per hour =
                                  $1,700.
Elevator rod end bolt            4 work-hours x $85  10.........................             350         126,000
 replacement.                     per hour = $340.
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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

    We have 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 that the 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 removing Airworthiness Directive (AD) 
97-02-02, Amendment 39-9886 (62 FR 2552, January 17, 1997), and adding 
the following new AD:

M7 Aerospace: Docket No. FAA-2015-2207; Directorate Identifier 2015-
CE-003-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by July 31, 
2015.

(b) Affected ADs

    This AD supersedes AD 97-02-02, Amendment 39-9886 (62 FR 2552, 
January 17, 1997).

(c) Applicability

    This AD applies to M7 Aerospace LLC Models SA26-AT, SA26-T, 
SA226-AT, SA226-T, SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, 
SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), SA227-TT, all serial 
numbers, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 27, Flight Controls.

(e) Unsafe Condition

    AD 97-02-02 (62 FR 2552, January 17, 1997) (``AD 97-02-02'') 
resulted from reports of Fairchild SA227 series airplanes losing 
pitch control in-flight. This supersedure was prompted by an 
operator experiencing

[[Page 34329]]

complete loss of elevator control because of failure of the bolt 
attaching the elevator control rod to the elevator walking beam 
under the cockpit floor. We are issuing this AD to prevent loss of 
pitch control, which if not corrected, could result in loss of 
airplane control.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done. Models SA227-CC and SA227-DC, serial numbers 
892, 893, and 895 and up, have the revised (modified) configuration. 
Since those airplanes are already in compliance, they do not have to 
do the actions in paragraphs (h) or (i) of this AD, including all 
subparagraphs. Those airplanes must still do the actions required in 
paragraph (j) of this AD, including all subparagraphs.

(g) Credit for Actions Accomplished in Accordance With Previous Service 
Information

    This AD allows credit for the control column pivot bearing 
torque check and initial replacement required in paragraph (i)(2) of 
this AD and the elevator rod bolt inspection and initial replacement 
required in paragraphs (j)(1) and (j)(3)(i) of this AD, if done 
before the effective date of this AD, following the procedures 
specified in the Accomplishment Instructions of the applicable 
service information listed in paragraphs (g)(1) through (g)(4) of 
this AD:
    (1) M7 Aerospace SA227 Commuter Category Service Bulletin No. 
CC7-27-010, original issue or revision 1.
    (2) M7 Aerospace SA227 Series Service Bulletin No. 227-27-041, 
original issue or revision 1.
    (3) M7 Aerospace SA226 Series Service Bulletin No. 226-27-060, 
original issue or revision 1.
    (4) M7 Aerospace SA26 Series Service Bulletin No. 26-27-30-046, 
original issue or revision 1.

(h) Control Column Pivot Bearing Revised (Modified) Configuration

    (1) On or before the airplane accumulates a total of 35,000 
hours time-in-service (TIS) or within the next 1,000 hours TIS after 
the effective date of this AD, whichever occurs later, you must 
revise (modify) the control column pivot bearing configuration with 
the improved design. Use the applicable service information listed 
in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Revising 
(modifying) the configuration of the control column pivot bearing 
with the improved design terminates the actions for paragraph (i) of 
this AD, including all subparagraphs, but you must still complete 
the required actions in paragraph (j) of this AD, including all 
subparagraphs.
    (i) Fairchild Aircraft SA26 Series Service Bulletin No. 26-27-
30-047, dated June 16, 1997;
    (ii) Fairchild Aircraft SA226 Series Service Bulletin No. 226-
27-061, dated June 16, 1997;
    (iii) Fairchild Aircraft SA227 Series Service Bulletin No. 227-
27-042, dated June 16, 1997; or
    (iv) Fairchild Aircraft SA227 Series Commuter Category No. CC7-
27-011, dated June 16, 1997.
    (2) You may at any time before 35,000 hours TIS revise (modify) 
the control column pivot bearing configuration with the improved 
design to terminate the repetitive replacement of the original 
control column pivot bearing using the applicable service 
information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of 
this AD. This action terminates the requirements of paragraph (i) of 
this AD, including all subparagraphs, but you must still complete 
the required actions in pargraph (j) of this AD, including all 
subparagraphs.

(i) Torque Check or Replacement of the Control Column Pivot Bearing

    (1) Use the service information, as applicable, listed in 
paragraphs (i)(1)(i) through (i)(1)(iv) of this AD to do a control 
column pivot bearing torque check or replacement at the applicable 
compliance times in paragraph (i)(2) or (i)(3) of this AD, including 
all subparagraphs:
    (i) M7 Aerospace LLC SA26 Series Service Bulletin No. 26-27-30-
046 R2, dated December 5, 2014;
    (ii) M7 Aerospace LLC SA226 Series Service Bulletin No. 226-27-
060 R2, dated December 5, 2014;
    (iii) M7 Aerospace LLC SA227 Series Service Bulletin No. 227-27-
041 R2, dated December 5, 2014; or
    (iv) M7 Aerospace LLC SA227 Series Commuter Category Service 
Bulletin No. CC7-27-010 R2, December 5, 2014.
    (2) For airplanes where the control column pivot bearing has 
been torque checked or replaced within the last 10,000 hours TIS 
before the effective date of this AD using the applicable service 
information listed in paragraph (g)(1) through (g)(4) or (i)(1)(i) 
through (i)(1)(iv) of this AD, do one of the following actions:
    (i) Within the next 10,000 hours TIS after the last control 
column pivot bearing replacement or within the next 1,000 hours TIS 
after the effective date of this AD, whichever occurs later, and 
repetitively thereafter every 10,000 hours TIS, replace the control 
column pivot bearing following paragraph 2.B. of the Accomplishment 
Instructions of the applicable service information listed in 
paragraphs (i)(1)(i) through (i)(1)(iv) of this AD; or
    (ii) Within the next 10,000 hours TIS after the last control 
column pivot bearing replacement or within the next 1,000 hours TIS 
after the effective date of this AD, whichever occurs later, revise 
(modify) the control column pivot bearing configuration with the 
improved design using the applicable service information listed in 
paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Revising 
(modifying) the configuration of the control column pivot bearing 
with the improved design terminates the repetitive replacement of 
the original control column pivot bearing. No other actions are 
required for paragraph (i) of this AD, including all subparagraphs, 
but you must still complete the actions in paragraph (j) of this AD, 
including all subparagraphs.
    (3) For airplanes where the control column pivot bearing has not 
been torque checked or replaced within the last 10,000 hours TIS 
before the effective date of this AD using the applicable service 
information listed in paragraphs (g)(1) through (g)(4) or (i)(1)(i) 
through (i)(1)(iv) of this AD, within the next 200 hours TIS after 
the effective date of this AD, torque check the control column pivot 
bearing following paragraph 2.A. of the service information listed 
in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD.
    (4) If nut movement occurs during the torque check required in 
paragraph (i)(3) of this AD, do one of the following actions:
    (i) Before further flight and repetitively thereafter at 
intervals not to exceed every 10,000 hours TIS, replace the control 
column pivot bearing following paragraph 2.B. of the Accomplishment 
Instructions of the applicable service information listed in 
paragraphs (i)(1)(i) through (i)(1)(iv) of this AD; or
    (ii) Before further flight, revise (modify) the control column 
pivot bearing configuration with the improved design using the 
applicable service information listed in paragraphs (h)(1)(i) 
through (h)(1)(iv) of this AD. Revising (modifying) the 
configuration of the control column pivot bearing with the improved 
design terminates the repetitive replacement of the original control 
column pivot bearing. No other actions are required for paragraph 
(i) of this AD, including all subparagraphs, but you must still 
complete the actions in paragraph (j) of this AD, including all 
subparagraphs.
    (5) If no nut movement occurs during the torque check required 
in paragraph (i)(3) of this AD, do one of the following actions:
    (i) Within the next 1,000 hours TIS after the effective date of 
this AD, replace the control column pivot bearing following 
paragraph 2.B. of the Accomplishment Instructions of the applicable 
service information listed in paragraphs (i)(1)(i) through 
(i)(1)(iv) of this AD; or
    (ii) Within the next 1,000 hours TIS after the effective date of 
this AD, revise (modify) the control column pivot bearing 
configuration with the improved design using the applicable service 
information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of 
this AD. Revising (modifying) the configuration of the control 
column pivot bearing with the improved design terminates the 
repetitive replacement of the original control column pivot bearing.

(j) Inspect the Elevator Control Rod Ends and Hardware

    (1) Within the next 200 hours TIS after the effective date of 
this AD, inspect the elevator control rod ends and hardware for 
wear, creasing, or other damage and verify the elevator rod bolt and 
attachment hardware for correct configuration following paragraph 
2.D. of the Accomplishment Instructions of the applicable service 
information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of 
this AD.
    (2) If any damage is found during the inspection required in 
paragraph (j)(1) of this AD or the elevator rod bolt and attachment 
hardware does not match the correct configuration, before further 
flight, replace the elevator rod bolt, rod ends, and associated 
hardware following paragraph 2.D.

[[Page 34330]]

of the Accomplishment Instructions of the applicable service 
information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of 
this AD.
    (3) Replace the elevator rod end bolt and associated hardware 
following paragraph 2.D. of the Accomplishment Instructions of the 
applicable service information listed in paragraphs (i)(1)(i) 
through (i)(1)(iv) of this AD at whichever of the following 
compliance times applies and repetitively thereafter at intervals 
not to exceed 10,000 hours TIS:
    (i) For airplanes where the elevator rod bolt has been replaced: 
Within the next 10,000 hours TIS after the last elevator rod bolt 
replacement or within the next 1,000 hours TIS after the effective 
date of this AD, whichever occurs later; or
    (ii) For airplanes where the elevator rod bolt has never been 
replaced: Within the next 200 hours TIS after the effective date of 
this AD.

 (k) 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 paragraph (l)(1) 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.

(l) Related Information

    (1) For more information about this AD, contact Andrew McAnaul, 
Aerospace Engineer, FAA, ASW-143 (c/o San Antonio MIDO), 10100 
Reunion Place, Suite 650, San Antonio, Texas 78216; phone: (210) 
308-3365; fax: (210) 308-3370; email: [email protected].
    (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.elbitsystems-us.com; email: [email protected]. 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.

    Issued in Kansas City, Missouri, on June 9, 2015.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015-14698 Filed 6-15-15; 8:45 am]
 BILLING CODE 4910-13-P