
[Federal Register Volume 78, Number 137 (Wednesday, July 17, 2013)]
[Proposed Rules]
[Pages 42720-42722]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-17138]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0546; Directorate Identifier 2013-NM-050-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 
certain The Boeing Company Model 727 airplanes. This proposed AD is 
intended to complete certain mandated programs intended to support the 
airplane reaching its limit of validity (LOV) of the engineering data 
that support the established structural maintenance program. For 
certain airplanes, this proposed AD would require modification of the 
web of the horizontal stabilizer center section rear spar. For the 
other airplanes, this proposed AD would require an inspection for 
cracks in the web, and repair or modification as applicable. We are 
proposing this AD to prevent cracking at the upper fastener holes in 
the riveted web in the horizontal stabilizer center section rear spar, 
which could result in failure of the spar forging and lead to 
horizontal stabilizer separation and loss of control of the airplane.

DATES: We must receive comments on this proposed AD by September 3, 
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://

[[Page 42721]]

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: Chandraduth Ramdoss, Aerospace 
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft 
Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, 
California 90712-4137; phone: 562-627-5239; fax: 562-627-5210; email: 
chandraduth.ramdoss@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-2013-0546; 
Directorate Identifier 2013-NM-050-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

    As described in FAA Advisory Circular 120-104 (http://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs 
have been developed to support initiatives that will ensure the 
continued airworthiness of aging airplane structure. The last element 
of those initiatives is the requirement to establish a limit of 
validity (LOV) of the engineering data that support the structural 
maintenance program under 14 CFR 26.21. This proposed AD is the result 
of an assessment of the previously established programs by Boeing 
during the process of establishing the LOV for Model 727 airplanes. The 
actions specified in this proposed AD are necessary to complete certain 
programs to ensure the continued airworthiness of aging airplane 
structure and to support an airplane reaching its LOV.
    Fatigue tests on Model 727 airplanes indicated that cracking can 
occur at the upper fastener holes in the riveted web in the horizontal 
stabilizer center section rear spar, because under-gauge material was 
used for the web. Such cracking could result in damage to the rear spar 
forging and lead to horizontal stabilizer separation and loss of 
control of the airplane.

Relevant Service Information

    We reviewed Boeing Service Bulletin 55-46, dated April 8, 1970. For 
information on the procedures and compliance times, see this service 
information at http://www.regulations.gov by searching for Docket No. 
FAA-2013-0546.

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

Differences Between the Proposed AD and the Service Information

    The effectivity of Boeing Service Bulletin 55-46, dated April 8, 
1970, includes four groups of Model 727 airplanes. We have determined 
that only airplanes in Group III and Group IV are still in service. The 
applicability of this proposed AD therefore is limited to Group III and 
Group IV airplanes.
    Boeing Service Bulletin 55-46, dated April 8, 1970, specifies a 
compliance time for the modification at a ``major overhaul nearest to 
20,000 hours.'' But a Structures Task Group (STG) recommended a 
threshold of 60,000 total flight cycles for the modification. This 
proposed AD specifies that threshold, with a grace period of 24 months 
or 2,500 flight cycles. We have coordinated this compliance time with 
Boeing.
    Boeing Service Bulletin 55-46, dated April 8, 1970, specifies to 
contact the manufacturer for instructions on how to repair certain 
conditions, but 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 106 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
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                                                                                    Cost per       Cost on U.S.
              Action                        Labor cost            Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Modification......................  32 work-hours x $85 per            $7,154           $9,874       $1,036,770
                                     hour = $2,720.
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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

[[Page 42722]]

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-2013-0546; Directorate Identifier 
2013-NM-050-AD.

(a) Comments Due Date

    We must receive comments by September 3, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 727 airplanes, 
certificated in any category, identified as Group III and Group IV 
in Boeing Service Bulletin 55-46, dated April 8, 1970.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 55, Stabilizers.

(e) Unsafe Condition

    This AD is intended to complete certain mandated programs 
intended to support the airplane reaching its limit of validity 
(LOV) of the engineering data that support the established 
structural maintenance program. We are issuing this AD to prevent 
cracking at the upper fastener holes in the riveted web in the 
horizontal stabilizer center section rear spar, which could lead to 
horizontal stabilizer separation and loss of control of the 
airplane.

(f) Compliance

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

(g) Group III Airplanes: Inspection

    For airplanes identified as Group III in Boeing Service Bulletin 
55-46, dated April 8, 1970: At the later of the times specified in 
paragraphs (g)(1) and (g)(2) of this AD, do an eddy-current 
inspection for cracks in the web, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 55-46, dated 
April 8, 1970.
    (1) Before the accumulation of 60,000 total flight cycles.
    (2) Within 24 months or 2,500 flight cycles after the effective 
date of this AD, whichever occurs first.

(h) Group III Airplanes: Corrective Actions

    For airplanes identified as Group III in Boeing Service Bulletin 
55-46, dated April 8, 1970: After the inspection required by 
paragraph (g) of this AD, do the applicable actions specified in 
paragraph (h)(1) or (h)(2) of this AD.
    (1) If no crack is found, before further flight, modify the web 
of the horizontal stabilizer center section rear spar, in accordance 
with the Accomplishment Instructions of Boeing Service Bulletin 55-
46, dated April 8, 1970.
    (2) If any crack is found, repair before further flight using a 
method approved in accordance with the procedures specified in 
paragraph (j) of this AD.

(i) Group IV Airplanes: Modification

    For airplanes identified as Group IV in Boeing Service Bulletin 
55-46, dated April 8, 1970: At the later of the times specified in 
paragraphs (i)(1) and (i)(2) of this AD, modify the web of the 
horizontal stabilizer center section rear spar, in accordance with 
the Accomplishment Instructions of Boeing 727 Service Bulletin 55-
46, dated April 8, 1970.
    (1) Before the accumulation of 60,000 total flight cycles.
    (2) Within 24 months or 2,500 flight cycles after the effective 
date of this AD, whichever occurs first.

(j) 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: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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.

(k) Related Information

    (1) For more information about this AD, contact Chandraduth 
Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los 
Angeles Aircraft Certification Office (ACO), 3960 Paramount 
Boulevard, Lakewood, California 90712-4137; phone: 562-627-5239; 
fax: 562-627-5210; email: chandraduth.ramdoss@faa.gov.
    (2) For information about AMOCs, contact Berhane Alazar, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 
98057-3356; phone: 425-917-6577; fax: 425-917-6590; email: 
berhane.alazar@faa.gov.
    (3) 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 Avenue SW., Renton, Washington. For information on the 
availability of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on July 5, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-17138 Filed 7-16-13; 8:45 am]
BILLING CODE 4910-13-P


