[Federal Register Volume 78, Number 85 (Thursday, May 2, 2013)]
[Proposed Rules]
[Pages 25662-25664]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-10367]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0361; Directorate Identifier 2013-NM-026-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 series airplanes. This proposed AD was 
prompted by a report of cracking in the left-side chord of the fin 
closure rib on the vertical stabilizer. This proposed AD would require 
repetitive inspections of the left and right side chords of the fin 
closure rib for cracking and corrosion, and related investigative and 
corrective actions if necessary. We are proposing this AD to detect and 
correct cracking and corrosion in the left and right side chords of the 
fin closure rib, which could lead to widespread cracking in the chords 
that might weaken the fin closure rib structure and result in loss of 
airplane control due to lack of horizontal stabilizer support.

DATES: We must receive comments on this proposed AD by June 17, 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 Boeing 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 
Avenue SW., Renton, Washington. 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, Washington 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-2013-0361; 
Directorate Identifier 2013-NM-026-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

    During a routine maintenance inspection an operator reported 
finding a crack on the left-side chord of the fin closure rib. The 
crack measured 2.4 inches long and ran along the length of the chord. 
Cracking on the left-side chord of the fin closure rib is the result of 
intergranual stress corrosion caused by the material properties of 
2024-T351 extrusion from which the closure rib chord is made. This 
material becomes vulnerable after the surface finishes begin to break 
down as a result of normal in-service aging. We are

[[Page 25663]]

proposing this AD to detect and correct cracking and corrosion in the 
left and right side chords of the fin closure rib, which could lead to 
widespread cracking in the chords that might weaken the fin closure rib 
structure, and result in loss of airplane control due to lack of 
horizontal stabilizer support.

Relevant Service Information

    We reviewed Boeing Special Attention Service Bulletin 727-55-0095, 
dated September 24, 2012. For information on the procedures and 
compliance times, see this service information at http://www.regulations.gov by searching for Docket No. FAA-2013-0361.

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, except as discussed 
under ``Differences Between the Proposed AD and the Service 
Information.''

Differences Between the Proposed AD and the Service Information

    Where Boeing Special Attention Service Bulletin 727-55-0095, dated 
September 24, 2012, specifies to contact the manufacturer for 
instructions on how to repair certain conditions, this proposed AD 
would require repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

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
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per  product         operators
----------------------------------------------------------------------------------------------------------------
Inspections......................  17 work-hours x $85            $0  $1,445 per            $141,610 per
                                    per hour = $1,445                  inspection cycle.     inspection cycle.
                                    per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

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-2013-0361; Directorate Identifier 
2013-NM-026-AD.

(a) Comments Due Date

    We must receive comments by June 17, 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 a report of cracking in the left-side 
chord of the fin closure rib on the vertical stabilizer. We are 
issuing this AD to detect and correct cracking and corrosion in the 
left and right side chords of the fin closure rib, which could lead 
to widespread cracking in the chords that might weaken the fin 
closure rib structure, and result in loss of airplane control due to 
lack of horizontal stabilizer support.

[[Page 25664]]

(f) Compliance

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

(g) Detailed and High Frequency Eddy Current (HFEC) Inspections

    Within 24 months after the effective date of this AD: Do a 
detailed inspection for cracking and corrosion of the left and right 
side chords of the fin closure rib, and do a HFEC inspection of the 
left- and right-side chords for cracking, in accordance with the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 727-55-0095, dated September 24, 2012. If any cracking or 
corrosion is found, before further flight, repair or replace the 
affected right or left-side chord using a method approved in 
accordance with the procedures specified in paragraph (h) of this 
AD. Repeat the detailed inspection and HFEC inspection thereafter at 
intervals not to exceed 26 months.

(h) 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.

(i) 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, Washington 
98057-3356; phone: 425-917-6577; fax: 425-917-6590; email: 
[email protected].
    (2) For Boeing 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 also review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, Washington. For 
information on the availability of this material at the FAA, call 
425-227-1221.

    Issued in Renton, Washington, on April 23, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-10367 Filed 5-1-13; 8:45 am]
BILLING CODE 4910-13-P