[Federal Register Volume 78, Number 70 (Thursday, April 11, 2013)]
[Proposed Rules]
[Pages 21569-21571]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-08454]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0299; Directorate Identifier 2012-NM-072-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
The Boeing Company Model 727 airplanes. This proposed AD was prompted 
by reports of cracks on the elevator rear spar stiffener assembly. This 
proposed AD would require repetitive detailed inspections for cracking 
of the elevator rear spar stiffener assembly, and corrective actions if 
necessary. We are proposing this AD to detect and correct cracking of 
the elevator rear spar stiffener assembly, which could adversely affect 
elevator structural stiffness, that could lead to elevator vibration 
and possible interference with the tab control rod and which could 
result in flutter and consequent loss of control of the airplane.

DATES: We must receive comments on this proposed AD by May 28, 2013.

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 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind Ave. 
SW., Renton, WA. For information on the availability of this material 
at the FAA, call 425-227-1221.

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 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: Berhane Alazar, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6577; fax: 
425-917-6590; email: [email protected].

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-2013-0299; 
Directorate Identifier 2012-NM-072-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://

[[Page 21570]]

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 cracks on the elevator rear spar stiffener 
assembly. An operator reported finding a crack on the rear spar 
stiffener assembly while accomplishing Boeing Service Bulletin 727-55-
0089 to address cracking of the elevator rear spar web at the elevator 
tab hinge fittings. A cracked elevator rear spar stiffener assembly, if 
not detected and corrected, could adversely affect elevator structural 
stiffness, which could result in elevator vibration and possible 
interference with the tab control rod and could lead to flutter and 
consequent loss of control of the airplane.

Relevant Service Information

    We reviewed Boeing Special Attention Service Bulletin 727-55-0094, 
dated March 21, 2012. For information on the procedures and compliance 
times, see this service information at http://www.regulations.gov by 
searching for Docket No. FAA-2013-0299.

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.
    The phrase ``related investigative actions'' might be used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that: (1) Are related to the primary actions, and (2) are actions that 
further investigate the nature of any condition found. Related 
investigative actions in an AD could include, for example, inspections.
    In addition, the phrase ``corrective actions'' might be used in 
this proposed AD. ``Corrective actions'' are actions that correct or 
address any condition found. Corrective actions in an AD could include, 
for example, repairs.

Costs of Compliance

    We estimate that this proposed AD affects 98 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
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                                                                                                 Cost on U.S.
        Action                 Labor cost              Parts cost         Cost per product        operators
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Inspection...........  5 work-hours x $85 per     None................  $425 per inspection  $41,650 per
                        hour = $425 per                                  cycle.               inspection cycle
                        inspection cycle..
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
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 
this replacement:

                                               On-Condition Costs
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                                                                                                       Cost per
                 Action                             Labor cost                    Parts cost           product
----------------------------------------------------------------------------------------------------------------
Replacement............................  7 work-hours x $85 per hour =    Unknown..................         $595
                                          $595.
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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 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):

The Boeing Company: Docket No. FAA-2013-0299; Directorate Identifier 
2012-NM-072-AD.

[[Page 21571]]

(a) Comments Due Date

    We must receive comments by May 28, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 727, 727C, 727-
100, 727-100C, 727-200, and 727-200F series airplanes, certificated 
in any category.

(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 cracks on the elevator rear 
spar stiffener assembly. We are issuing this AD to detect and 
correct cracking of the elevator rear spar stiffener assembly, which 
could adversely affect elevator structural stiffness, that could 
lead to elevator vibration and possible interference with the tab 
control rod and which could result in elevator flutter and 
consequent loss of control of the airplane.

(f) Compliance

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

(g) Repetitive Inspections and Corrective Actions

    Except as provided by paragraph (h) of this AD, at the 
applicable time specified in table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Special Attention Service Bulletin 727-55-
0094, dated March 21, 2012, do a detailed inspection for any 
cracking of the elevator rear spar stiffener assembly, and all 
applicable corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 727-55-
0094, dated March 21, 2012. Do all applicable corrective actions 
before further flight. Repeat the inspection thereafter at the 
applicable time specified in table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Special Attention Service Bulletin 727-55-
0094, dated March 21, 2012, except as provided by paragraph (j) of 
this AD.

(h) Exception

    Where Boeing Special Attention Service Bulletin 727-55-0094, 
dated March 21, 2012, specifies a compliance time ``from the 
original issue date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.

(i) Optional Replacement

    Replacing the elevator rear spar stiffener assembly with a new 
assembly in accordance with Part 4 or 5, as applicable, of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 727-55-0094, dated March 21, 2012, terminates the 
inspections required by paragraph (g) of this AD for that assembly, 
except as required by paragraph (j) of this AD.

(j) Post-Replacement Inspection Compliance Time

    For any elevator rear spar stiffener assembly replaced as 
required by paragraph (g) of the AD or as specified in paragraph (i) 
of this AD: Do the next inspection required by paragraph (g) of this 
AD for that assembly within 96 months after accomplishing the 
replacement and repeat thereafter at the times specified in 
paragraph (g) of this AD.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (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 the Related Information 
section of this AD. Information may be emailed to: [email protected].
    (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.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO, to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.

(l) Related Information

    (1) For more information about this AD, contact Berhane Alazar, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6577; fax: 425-917-6590; email: 
[email protected].
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced 
service information at the FAA, Transport Airplane Directorate, 1601 
Lind Ave. SW., Renton, WA. For information on the availability of 
this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on March 28, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-08454 Filed 4-10-13; 8:45 am]
BILLING CODE 4910-13-P