[Federal Register Volume 78, Number 137 (Wednesday, July 17, 2013)]
[Proposed Rules]
[Pages 42720-42722]
From the Federal Register Online via the Government Publishing 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:
[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-2013-0546;
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
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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: [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.
(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: [email protected].
(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:
[email protected].
(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]
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