
[Federal Register Volume 78, Number 166 (Tuesday, August 27, 2013)]
[Proposed Rules]
[Pages 52875-52877]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-20840]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0701; Directorate Identifier 2013-NM-073-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 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. This proposed 
AD would require repetitive inspections for cracking of small repairs 
done on the vertical flange of the rib chord, repetitive inspections 
for cracking along the upper fillet radius of the rib chord, and a 
large repair or preventive modification if necessary. Accomplishment of 
a large repair or preventive modification would terminate the actions 
of the proposed AD. We are proposing this AD to prevent cracks in the 
rib upper chord, which could result in the inability of the wing 
structure to support the limit load condition, and consequent loss of 
structural integrity of the wing.

DATES: We must receive comments on this proposed AD by October 11, 
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 
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: Galib Abumeri, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Blvd., Suite 100, Lakewood, CA 90712-4137; 
phone: 562-627-5324; fax: 562-672-5210; email: galib.abumeri@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-2013-0701; 
Directorate Identifier 2013-NM-073-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

[[Page 52876]]

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.
    Cracks have been reported on at least 8 airplanes in the upper 
vertical flange of the wing-to-body rib upper chord at body station 
760. The cracks were detected when the airplanes had reached between 
19,700 and 49,000 total flight cycles, and between 35,000 and 54,000 
total flight hours. Cracks in the rib upper chord, if not corrected, 
could result in the inability of the wing structure to support the 
limit load condition, and consequent loss of structural integrity of 
the wing.

Related Rulemaking

    AD 90-06-09, Amendment 39-6488 (55 FR 8370, March 7, 1990), which 
affects Model 727 series airplanes, requires, among other things, 
structural modifications specified in Boeing Service Bulletin 727-57-
0112, Revision 2, dated May 19, 1988.
    AD 94-07-08, Amendment 39-8866 (59 FR 14545, March 29, 1994), which 
affects certain Boeing Model 727 series airplanes, requires structural 
inspections specified in Boeing Service Bulletin 727-57-0112, Revision 
2, dated May 19, 1988, and corrective actions if necessary. The 
corrective actions include small repairs, large repairs, and 
modifications. AD 94-07-08 requires repetitive inspections for cracks, 
but does not require repetitive inspections of small repairs. 
Accomplishment of the modification specified in AD 94-07-08 terminates 
those repetitive inspections.

Relevant Service Information

    We reviewed Boeing Service Bulletin 727-57-0112, Revision 5, dated 
July 31, 1997. For information on the procedures and compliance times, 
see this service information at http://www.regulations.gov by searching 
for Docket No. FAA-2013-0701.

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 repetitive inspections for cracking 
of any small repairs done on the vertical flange of the rib chord from 
the inboard side. The proposed AD would require a large repair or 
modification if any cracking is found. Accomplishment of a large repair 
or preventive modification would terminate the actions of the proposed 
AD.

Differences Between the Proposed AD and the Service Information

    This proposed AD would require repetitive inspections for cracks 
along the upper fillet radius of the rib chord. Boeing Service Bulletin 
727-57-0112, Revision 5, dated July 31, 1997, does not specify this 
inspection if a small repair is done. This difference has been 
coordinated with Boeing.

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 on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
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Inspections (per wing).........  6 work-hours x $85 per               $0  $510 per            $54,060 per
                                  hour = $510 per                          inspection cycle.   inspection cycle.
                                  inspection cycle.
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                                               On-Condition Costs
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                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Large repair 1,2...........................  300 work-hours x $85 per hour =             $12,139         $37,639
                                              $25,500.
Preventive modification 1,3................  57 work-hours x $85 per hour =               10,614          15,459
                                              $4,845.
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\1\ Cost for on-condition actions (either \2\ or \3\), per wing.
\2\ Cost for large repair, per wing.
\3\ Cost for preventive modification, per wing.

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.

[[Page 52877]]

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-2013-0701; Directorate Identifier 
2013-NM-073-AD.

(a) Comments Due Date

    We must receive comments by October 11, 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 57, Wings.

(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 
cracks in the rib upper chord, which could result in the inability 
of the wing structure to support the limit load condition, and 
consequent loss of structural integrity of the wing.

(f) Compliance

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

(g) Post-Repair Inspection

    For any small repair that has been done as specified in Boeing 
727 Service Bulletin 57-112; or Part III of the Accomplishment 
Instructions of Boeing Service Bulletin 727-57-0112: Within 3,500 
flight cycles after the small repair was installed or inspected as 
specified in Boeing Service Bulletin 727-57-0112, or within 18 
months after the effective date of this AD, whichever occurs latest, 
do a high frequency eddy current inspection for cracking of the 
vertical flange of the rib chord from the inboard side, and do a 
detailed (close visual) inspection for cracking along the upper 
fillet radius of the rib chord, in accordance with Part III of the 
Accomplishment Instructions of Boeing Service Bulletin 727-57-0112, 
Revision 5, dated July 31, 1997. Repeat the inspections thereafter 
at intervals not to exceed 3,500 flight cycles until accomplishment 
of the repair or modification specified in paragraph (i) or (j) of 
this AD.

(h) Inspection Definition

    For the purposes of this AD, a detailed inspection is an 
intensive examination of a specific item, installation, or assembly 
to detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at an 
intensity deemed appropriate. Inspection aids such as mirror, 
magnifying lenses, etc., may be necessary. Surface cleaning and 
elaborate procedures may be required.

(i) Corrective Action for Cracks

    If any crack is found during any inspection required by 
paragraph (g) of this AD, before further flight, do either action 
specified in paragraph (i)(1) or (i)(2) of this AD. Accomplishment 
of either action terminates the requirements of paragraphs (g) and 
(h) of this AD.
    (1) Do a large repair, in accordance with Part IV of the 
Accomplishment Instructions of Boeing Service Bulletin 727-57-0112, 
Revision 5, dated July 31, 1997.
    (2) Do a preventive modification, in accordance with Part V of 
the Accomplishment Instructions of Boeing Service Bulletin 727-57-
0112, Revision 5, dated July 31, 1997.

(j) Optional Terminating Action

    Accomplishment of the actions specified in either paragraph 
(j)(1) or (j)(2) of this AD terminates the requirements of 
paragraphs (g), (h), and (i) of this AD.
    (1) A large repair, in accordance with Part IV of the 
Accomplishment Instructions of Boeing Service Bulletin 727-57-0112, 
Revision 5, dated July 31, 1997. Any crack found must be repaired 
before further flight using a method approved in accordance with the 
procedures specified in paragraph (l) of this AD.
    (2) A preventive modification, in accordance with Part V of the 
Accomplishment Instructions of Boeing Service Bulletin 727-57-0112, 
Revision 5, dated July 31, 1997. Any crack found must be repaired 
before further flight using a method approved in accordance with the 
procedures specified in paragraph (l) of this AD.

(k) Credit for Previous Actions

    This paragraph provides credit for the inspections, large 
repair, and modification specified in this AD, if those actions were 
performed before the effective date of this AD using Boeing Service 
Bulletin 727-57-0112, Revision 4, dated October 29, 1992.

(l) 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.

(m) Related Information

    (1) For more information about this AD, contact Galib Abumeri, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles 
Aircraft Certification Office (ACO), 3960 Paramount Blvd., Suite 
100, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-672-
5210; email: galib.abumeri@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 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 August 16, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-20840 Filed 8-26-13; 8:45 am]
BILLING CODE 4910-13-P


