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[Federal Register Volume 79, Number 48 (Wednesday, March 12, 2014)]
[Proposed Rules]
[Pages 13931-13934]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-05428]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0141; Directorate Identifier 2013-NM-024-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 727-100 series 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 
repetitive inspections for cracking in stringers or frames until 
modification, and repair if necessary. We are proposing this AD to 
detect and correct cracking in stringers or frames originating at or 
near stringer-to-frame attachment fastener holes, which could result in 
reduced structural integrity of the airplane, and decompression of the 
cabin.

DATES: We must receive comments on this proposed AD by April 28, 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 
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 view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue 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 by searching for and locating Docket No. FAA-2014-
0141; 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: Chandra Ramdoss, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 
(562) 627-5239; fax: (562) 627-5210; email: 
chandraduth.ramdoss@faa.gov.

SUPPLEMENTARY INFORMATION:

[[Page 13932]]

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-2014-0141; 
Directorate Identifier 2013-NM-024-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 The Boeing Company 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 conducted by the manufacturer show that repeated 
pressurization cycles result in fatigue cracks at some of the stringer-
to-frame connections along the crown of the fuselage. Undetected 
cracking at the stringer-to-frame connections along the crown of the 
fuselage, and the lack of stringer-to-body frame tie clips in the crown 
area of the fuselage, could result in damage to wire bundles and 
control cables for the flight control system, reduced structural 
integrity of the airplane, and decompression of the cabin.

Related Rulemaking

    On January 16, 1990, we issued AD 90-06-09, Amendment 39-6488 (55 
FR 8370, March 7, 1990), which applied to certain Boeing Model 727 
series airplanes. AD 90-06-09 required structural modifications 
specified in Section 3 of Boeing Document D6-54860, ``Aging Airplane 
Service Bulletin Structural Modification and Inspection Program--Model 
727,'' Revision C, dated December 11, 1989. AD 90-06-09 was prompted by 
a report by the Model 727 Structures Working Group. The actions 
required by AD 90-06-09 were intended to prevent structural failure of 
the airplane. One of the requirements of AD 90-06-09 was to do the 
modification in accordance with Boeing Service Bulletin 727-53-0041, 
Revision 4 dated July 27, 1973, prior to the accumulation of 60,000 
flights or 4 years whichever occurs later.
    On March 23, 1994, we issued AD 94-07-08, Amendment 39-8866 (59 FR 
14545, March 29, 1994), which applied to certain Boeing Model 727 
series airplanes. AD 94-07-08 required structural inspections specified 
in section 4 and appendices A.4 and B.4 of Boeing Document Number D6-
54860, ``Aging Airplane Service Bulletin Structural Modification and 
Inspection Program--Model 727,'' Revision G, dated March 5, 1993, and 
corrective actions if necessary. The corrective actions included doing 
small repairs and modifications. AD 94-07-08 was prompted by reports of 
incidents involving fatigue cracking and corrosion. The actions 
required by AD 94-07-08 included only post-modification visual 
inspections per Boeing Service Bulletin 727-53-0041, Revision 5, dated 
January 25, 1990.
    This proposed rule requires repetitive inspections on those 
airplanes that have not yet accomplished the modification that is 
required by AD 90-06-09.

Relevant Service Information

    We reviewed Boeing Service Bulletin 727-53-0041, Revision 6, dated 
September 5, 1991. For information on the procedures and compliance 
times, see this service information at http://www.regulations.gov by 
searching for Docket No. FAA-2014-0141.

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.

Costs of Compliance

    We estimate that this proposed AD affects 2 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
----------------------------------------------------------------------------------------------------------------
Inspection and repetitive          60 work-hours x $85              $0  $5,100 per           $10,200 per
 inspections.                       per hour = $5,100                    inspection.          inspection.
                                    per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary modifications 
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 modifications:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
               Action                         Labor cost                Parts cost           Cost per product
----------------------------------------------------------------------------------------------------------------
Modification.......................  600 work-hours x $85 per     Up to $11,481.........  Up to $62,481 per
                                      hour = $51,000 per                                   modification.
                                      inspection cycle.
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[[Page 13933]]

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-2014-0141; Directorate Identifier 
2013-NM-024-AD.

(a) Comments Due Date

    We must receive comments by April 28, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 727-100 series 
airplanes, certificated in any category, as identified in Boeing 
Service Bulletin 727-53-0041, Revision 6, dated September 5, 1991, 
unless previously modified in accordance with the service 
information specified in paragraphs (c)(1), (c)(2) or (c)(3) of this 
AD.
    (1) Boeing Service Bulletin 727-53-0041, Revision 4, dated July 
27, 1973.
    (2) Boeing Service Bulletin 727-53-0041, Revision 5, dated 
January 25, 1990.
    (3) Boeing Service Bulletin 727-53-0041, Revision 6, dated 
September 5, 1991.

    Note 1 to paragraph (c) of this AD: Boeing Service Bulletin 727-
53-0041, Revision 4, dated July 27, 1973 is specified in Boeing 
Document D6-54860 ``Aging Airplane Service Bulletin Structural 
Modification Program--Model 727,'' Revision C, dated December 11, 
1989 as mandated by AD 90-06-09, Amendment 39-6488 (55 FR 8370, 
March 7, 1990).

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(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 detect and 
correct cracking in stringers or frames originating at or near 
stringer-to-frame attachment fastener holes, which could result in 
reduced structural integrity of the airplane, and decompression of 
the cabin.

(f) Compliance

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

(g) Inspections

    Before the accumulation of 16,000 total flight cycles, or within 
3,000 flight cycles after the effective date of this AD, whichever 
occurs later, do a high frequency eddy current inspection and a 
general visual inspection for cracking in stringers and frames 
originating at or near stringer-to-frame attachment fastener holes, 
in accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 727-53-0041, Revision 6, dated September 5, 1991. Repeat 
the inspections thereafter at intervals not to exceed 6,000 flight 
cycles until the modification specified by paragraph (h) of this AD 
is accomplished. If any crack is found during any inspection 
required by paragraph (g) of this AD: Before further flight, repair 
or modify the affected stringer-to-frame attachment locations, in 
accordance with Part V, ``Repair Data'' of the Accomplishment 
Instructions of Boeing Service Bulletin 727-53-0041, Revision 6, 
dated September 5, 1991.

(h) Modification

    Modifying the affected stringer-to-frame attachment locations, 
in accordance with Part IV, ``Preventive Modification Data,'' of the 
Accomplishment Instructions of Boeing Service Bulletin 727-53-0041, 
Revision 6, dated September 5, 1991, terminates the repetitive 
inspections required by paragraph (g) of this AD.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles 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 paragraph (j)(1) of this AD. 
Information may be emailed to: 9-ANM-LAACO-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, Los Angeles Aircraft 
Certification Office (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.

(j) Related Information

    (1) For more information about this AD, contact Chandra Ramdoss, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles 
Aircraft Certification Office (ACO), 3960 Paramount Boulevard, 
Lakewood, CA 90712-4137; phone: (562) 627-5239; fax: (562) 627-5210; 
email: chandraduth.ramdoss@faa.gov.
    (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 view this referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

[[Page 13934]]

    Issued in Renton, Washington, on March 5, 2014.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-05428 Filed 3-11-14; 8:45 am]
BILLING CODE 4910-13-P
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