[Federal Register Volume 78, Number 166 (Tuesday, August 27, 2013)]
[Proposed Rules]
[Pages 52875-52877]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-20840]
-----------------------------------------------------------------------
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).
-----------------------------------------------------------------------
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: [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-2013-0701;
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
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspections (per wing)......... 6 work-hours x $85 per $0 $510 per $54,060 per
hour = $510 per inspection cycle. inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------
\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: [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.
(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: [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 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