[Federal Register Volume 77, Number 173 (Thursday, September 6, 2012)]
[Proposed Rules]
[Pages 54856-54859]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-21944]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0931; Directorate Identifier 2011-NM-128-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, 727C, 727-100, 727-100C, 727-200, and
727-200F series airplanes. This proposed AD was prompted by a
structural re-evaluation by the manufacturer, which identified elements
within the wing trailing edge flap area that qualify as structural
significant items (SSI). This proposed AD would require revising the
maintenance inspection program to include inspections that will give no
less than the required damage tolerance rating for certain SSIs, and
repairing cracked structure. We are proposing this AD to detect and
correct fatigue cracking of the wing trailing edge structure, which
could result in compromised structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by October 22,
2012.
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, Washington 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: 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].
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-2012-0931;
Directorate Identifier 2011-NM-128-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://
[[Page 54857]]
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
In the early 1980s, as part of its continuing work to maintain the
structural integrity of older transport category airplanes, the FAA
concluded that the incidence of fatigue cracking may increase as these
airplanes reach or exceed their design service objective (DSO). In
light of this, and as a result of increased utilization, and longer
operational lives, we determined that a supplemental structural
inspection program (SSIP) was necessary to maintain the continued
structural integrity for all airplanes in the transport fleet.
Since the establishment of the SSI Supplemental Structural
Inspection Document (SSID) D6-48040-1, we have received information
from the manufacturer, which identified elements within the wing
trailing edge flap area, which qualified as SSI. An SSI is defined as a
structural part or component that contributes significantly to carry
flight, ground, pressure, or control loads, and whose failure could
affect the structural integrity necessary for the safety of the
airplane, and whose damage tolerance or safe-life characteristics it is
necessary, therefore, to establish or confirm. Uncorrected fatigue
cracks in these structural elements could result in compromised
structural integrity of the airplane.
Issuance of FAA Advisory Circular (AC)
On March 7, 2008, we issued AC 91-56B, ``Continuing Structural
Integrity Program for Airplanes,'' (http://rgl.faa.gov/Regulatory--
and--Guidance--Library/rgAdvisoryCircular.nsf/list/AC%2091-56B/$FILE/
AC%2091-56B.pdf). That AC provides guidance material to manufacturers
and operators for use in developing a continuing structural integrity
program to ensure safe operation of older airplanes throughout their
operational lives. This guidance material applies to transport
airplanes that were certified under the fail-safe requirements of part
4b (``Airplane Airworthiness, Transport Categories'') of the Civil Air
Regulations or damage tolerance structural requirements of part 25
(``Airworthiness Standards: Transport Category Airplanes'') of the
Federal Aviation Regulations (FARs) (14 CFR part 25), and that have a
maximum gross weight greater than 75,000 pounds. The procedures set
forth in that AC are applicable to transport category airplanes
operated under subpart D (``Special Flight Operations'') of part 91
(``General Operating and Flight Rules'') of the FARs (14 CFR part 91);
part 121 (``Operating Requirements: Domestic, Flag, and Supplemental
Operations'') of the FARs (14 CFR part 121); part 125 (``Certification
and Operations: Airplanes Having a Seating Capacity of 20 or More
Passengers or a Maximum Payload of 6,000 Pounds or More and Rules
Governing Persons Onboard Such Aircraft'') of the FARs (14 CFR part
125); and part 135 (``Operating Requirements: Commuter and On-Demand
Operations and Rules Governing Persons On Board Such Aircraft'') of the
FARs (14 CFR part 135). The objective of the SSIP was to establish
inspection programs to ensure timely detection of fatigue cracking.
Development of the SSIP
In order to evaluate the effect of increased fatigue cracking with
respect to maintaining fail-safe design and damage tolerance of the
structure of The Boeing Company Model 727, 727C, 727-100, 727-100C,
727-200, and 727-200F series airplanes, Boeing conducted a structural
reassessment of those airplanes, using damage tolerance evaluation
techniques. Boeing accomplished this reassessment using the criteria
contained in FAA AC 91-56B, dated March 7, 2008, (http://rgl.faa.gov/
Regulatory--and--Guidance--Library/rgAdvisoryCircular.nsf/list/AC%2091-
56B/$FILE/AC%2091-56B.pdf), as well as Amendment 25-45, effective
December 1, 1978, of section 25.571 (``Damage-tolerance and fatigue
evaluation of structure'') of the FARs (14 CFR 25.571). During the
reassessment, members of the airline industry participated with Boeing
in working group sessions and developed the SSIP for Model 727, 727C,
727-100, 727-100C, 727-200, and 727-200F series airplanes. Engineers
and maintenance specialists from the FAA also supported these sessions.
Subsequently, based on the working group's recommendations, Boeing
developed the Supplemental Structural Inspection Document (SSID) D6-
48040-1.
Other Related Rulemaking
On May 12, 1998, the FAA issued AD 98-11-03, Amendment 39-10530 (63
FR 27455, May 19, 1999), which is applicable to all The Boeing Company
Model 727 series airplanes. On December 30, 1998, the FAA issued AD 98-
11-03 R1, Amendment 39-10983 (64 FR 989, January 7, 1999), to revise
the maintenance inspection program to include inspections that will
give no less than the required damage tolerance rating for each SSI,
and repair of cracked structure. AD 98-11-03 R1 requires that the
maintenance inspection program be revised to include inspections that
will give no less than the required damage tolerance rating for each
SSI, and repair of cracked structure. That action was prompted by a
structural re-evaluation by the manufacturer that identified additional
structural elements for which, if damage were to occur, supplemental
inspections may be required for timely crack detection. The actions
required by that AD are intended to ensure the continued structural
integrity of The Boeing Company Model 727 fleet.
Relevant Service Information
We reviewed Boeing Document D6-48040-2, Supplemental Structural
Inspection Document For Model 727 Airplanes, Appendix A, dated December
2010, which identifies SSIs within the wing trailing edge flap area
that need inspection to ensure timely detection of fatigue damage. The
inspection requirements identified in Boeing Document D6-48040-2,
Appendix A, Supplemental Structural Inspection Document For Model 727
Airplanes, dated December 2010, are intended to be accomplished in
conjunction with, not as a replacement for, the existing approved
structural inspection program.
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 revising the maintenance inspection
program to include inspections that will give no less than the required
damage tolerance rating for each SSI, repetitive inspections to detect
cracks in SSIs, and repair of any cracked structure. Before any
airplane that is subject to this proposed AD can be added to an air
carrier's operations specifications, a program for doing the
inspections required by this proposed AD must be established.
Costs of Compliance
We estimate that this proposed AD affects 206 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
[[Page 54858]]
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Revise maintenance program.......... 1 work-hour x $85 per $0 $85 $17,510
hour = $85.
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Compliance with this proposed AD would be a method of compliance
with the FAA aging airplane safety final rule (AASFR) (70 FR 5518,
February 2, 2005) for certain baseline structure of Model 727, 727C,
727-100, 727-100C, 727-200, and 727-200F series airplanes. The AASFR
final rule requires certain operators to incorporate damage tolerance
inspections into their maintenance inspection programs. These
requirements are described in paragraph (c)(1) of section 121.1109 of
the FARs (14 CFR 121.1109 (c)(1)) and paragraph (b)(1) of section
129.109 of the FARs (14 CFR 129.109(b)(1)). Accomplishment of the
actions required by this proposed AD will meet the requirements of
these CFR sections for certain baseline structure. The costs for
accomplishing the inspection portion of this proposed AD were accounted
for in the regulatory evaluation of the AASFR final rule.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
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
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]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
The Boeing Company: Docket No. FAA-2012-0931; Directorate Identifier
2011-NM-128-AD.
(a) Comments Due Date
We must receive comments by October 22, 2012.
(b) Affected ADs
None.
(c) Applicability
(1) 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.
(2) This AD requires revisions to certain operator maintenance
documents to include new actions (e.g., inspections, methods, and
compliance times.) Compliance with these actions is required by 14
CFR 91.403(c). For airplanes that have been previously modified,
altered, or repaired in the areas addressed by these inspections,
the operator may not be able to accomplish the inspections described
in the revisions. In this situation, to comply with 14 CFR
91.403(c), the operator must request approval for an alternative
method of compliance (AMOC) according to paragraph (j) of this AD.
The request should include a description of changes to the required
actions that will ensure the continued operational safety of the
airplane.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a structural re-evaluation by the
manufacturer, which identified elements within the wing trailing
edge flap area that qualify as structural significant items (SSI).
We are issuing this AD to detect and correct fatigue cracking of the
wing trailing edge structure, which could result in compromised
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Revise Maintenance Program
(1) Before the accumulation of 55,000 total flight cycles, or
within 12 months after the effective date of this AD, whichever
occurs later: Revise the maintenance program to incorporate
inspections that provide no less than the required damage tolerance
rating (DTR) for each SSI listed in Boeing Document D6-48040-2,
Supplemental Structural Inspection Document For Model 727 Airplanes,
Appendix A, dated December 2010. The required DTR value for each SSI
is identified in Boeing Document D6-48040-2, Supplemental Structural
Inspection Document For Model 727 Airplanes, Appendix A, dated
December 2010. The revision to the maintenance inspection program
must include and must be implemented in accordance with the
procedures in Section 3.0 of Boeing Document D6-48040-2,
Supplemental Structural Inspection Document For Model 727 Airplanes,
Appendix A, dated December 2010; and in accordance with the
procedures in Section 5.0, ``Damage Tolerance Rating (DTR) System
Application,'' and Section 6.0, ``SSI Discrepancy Reporting,'' of
Boeing Document D6-48040-1, Supplemental Structural Inspection
Document (SSID), Volume 1, Revision H, dated June 1994.
(2) The initial compliance time for the inspections is before
the accumulation of 55,000 total flight cycles, or within 3,000
flight cycles after 12 months from the
[[Page 54859]]
effective date of this AD, whichever occurs later.
(h) Repair
If any cracked structure is found during any inspection
specified in Boeing Document D6-48040-2, Supplemental Structural
Inspection Document For Model 727 Airplanes, Appendix A, dated
December 2010, before further flight, repair the cracked structure
using a method approved in accordance with the procedures specified
in paragraph (j) of this AD.
(i) No Alternative Actions or Intervals
After accomplishing the revision required by paragraph (g) of
this AD, no alternative actions (e.g., inspections) or intervals may
be used other than those specified in Boeing Document D6-48040-2,
Supplemental Structural Inspection Document For Model 727 Airplanes,
Appendix A, dated December 2010, unless the actions or intervals are
approved as an alternative method of compliance (AMOC) in accordance
with the procedures specified in paragraph (j) of this AD.
(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 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].
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 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 24, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-21944 Filed 9-5-12; 8:45 am]
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