[Federal Register Volume 76, Number 166 (Friday, August 26, 2011)]
[Proposed Rules]
[Pages 53346-53348]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-21853]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0909; Directorate Identifier 2011-NM-027-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model DC-9-81 (MD-
81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88
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 the
products listed above. This proposed AD would require repetitive high
frequency eddy current (HFEC) inspections for cracking of the left and
right rib hinge bearing lugs of the aft face of the center section of
the horizontal stabilizer; measuring crack length and blending out
cracks; and replacing the horizontal stabilizer center section rib, if
necessary. This proposed AD was prompted by reports of cracks of the
hinge bearing lugs of the center section ribs of the horizontal
stabilizer. We are proposing this AD to detect and correct cracking in
the hinge bearing lugs of the horizontal stabilizer center section
ribs, which would result in failure of the lugs, and consequent
inability of the horizontal stabilizer to sustain the required limit
loads and loss of control of the airplane.
DATES: We must receive comments on this proposed AD by October 11,
2011.
ADDRESSES: You may send comments 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,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; e-mail
[email protected]; 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: Roger Durbin, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
phone: 562-627-5233; fax: 562-627-5210; e-mail: [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-2011-0909;
Directorate Identifier 2011-NM-027-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
We received reports of cracks on Model MD-80 series airplanes and
on Model MD-90-30 airplanes. The cracks were found on the aft face of
the center section left and right hinge bearing lugs on either the left
or right, or in two cases, on both sides of the center section ribs of
the horizontal stabilizer. Cracks were reported on Model MD-80
airplanes that had accumulated 23,700 to 41,963 total flight hours, and
23,300 to 35,294 total flight cycles. The cause of the cracking has not
been determined. Undetected cracking in the hinge bearing lugs of the
center section of the left and right ribs, if not corrected, could
result in failure of the hinge bearing lugs and consequent inability of
the horizontal stabilizer to sustain required limit loads and loss of
control of the airplane.
Related Rulemaking
The proposed AD affects Model MD-80 series airplanes. We issued AD
2011-01-11, Amendment 39-16565 (76 FR 430, January 5, 2011) to address
the identified unsafe condition on Model MD-90-30 airplanes, on
December 22, 2010. AD 2011-01-11 requires similar actions as proposed
in this NPRM.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin MD80-55A069, dated
January 19, 2011. That service bulletin describes procedures for
repetitive high frequency eddy current (HFEC) inspections for cracking
of the left and right rib hinge bearing lugs of the aft face of the
center
[[Page 53347]]
section of the horizontal stabilizer; measuring crack length and
blending out cracks; and replacement of the horizontal stabilizer
center section rib, if necessary.
FAA's Determination and Proposed AD Requirements
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 these same type
designs. This proposed AD would require accomplishing the actions
specified in the service information described previously, except as
discussed under ``Differences Between the Proposed AD and the Service
Information.''
Differences Between the Proposed AD and the Service Information
Although Boeing Alert Service Bulletin MD80-55A069, dated January
19, 2011, specifies to send the inspection results to the manufacturer,
this proposed AD would not require any report.
Interim Action
We consider this proposed AD interim action since investigation is
ongoing and no terminating action has been developed yet. The
manufacturer is currently developing a modification that will address
the unsafe condition identified in this AD. Once this modification is
developed, approved, and available, we may consider additional
rulemaking.
Costs of Compliance
We estimate that this proposed AD affects 668 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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Inspection.......................... 6 work-hours x $85 per $0 $510 $340,680
hour = $510 per
inspection cycle.
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We have received no definitive data that would enable us to provide
labor cost estimates for the on-condition actions (blend-out repair(s)
or replacement of center section rib(s)) specified in this proposed AD.
However, we have been advised that replacement parts would be $14,500
per horizontal stabilizer rib crack repair kit.
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-2011-0909; Directorate Identifier
2011-NM-027-AD.
Comments Due Date
(a) We must receive comments by October 11, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to The Boeing Company Model DC-9-81 (MD-81),
DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88
airplanes, certificated in any category, as identified in Boeing
Alert Service Bulletin MD80-55A069, dated January 19, 2011.
Subject
(d) Air Transport Association (ATA) of America Code 55:
Stabilizers.
Unsafe Condition
(e) This AD was prompted by reports of cracks of the hinge
bearing lugs of the center section ribs of the horizontal
stabilizer. We are proposing this AD to detect and correct cracking
in the hinge bearing lugs of the horizontal stabilizer center
section ribs, which would result in failure of the lugs, and
consequent inability of the horizontal stabilizer to sustain the
required limit loads and loss of control of the airplane.
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
Actions on Horizontal Stabilizer Ribs Made From 7075-T7351 Material
(g) For Group 1 airplanes, as identified in Boeing Alert Service
Bulletin MD80-55A069, dated January 19, 2011: Before the
accumulation of 23,000 total flight cycles, or within 4,383 flight
cycles after the effective
[[Page 53348]]
date of this AD, whichever occurs later, do a high frequency eddy
current (HFEC) inspection for cracking of the left and right rib
hinge bearing lugs of the aft face of the center section of the
horizontal stabilizer, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin MD80-55A069, dated
January 19, 2011. For any crack-free lug, repeat the inspection on
that lug thereafter at intervals not to exceed 8,200 flight cycles.
(h) If, during any inspection required by paragraph (g) of this
AD, any crack is found, before further flight, measure the length of
the crack between the points specified in Boeing Alert Service
Bulletin MD80-55A069, dated January 19, 2011. Do the action in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin MD80-55A069, dated January 19, 2011.
(1) If the crack length between points `A' and `B' is less than
or equal to 0.15 inch and the crack length between points `C' and
`D' is less than or equal to 0.05 inch: Before further flight, blend
out the crack, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin MD80-55A069, dated January 19, 2011.
Within 15,600 flight cycles after doing the blend out, do an HFEC
inspection of the blend out on the center section rib hinge bearing
lug for cracking, in accordance with the Accomplishment Instructions
of Boeing Alert Service Bulletin MD80-55A069, dated January 19,
2011, and repeat that inspection thereafter at intervals not to
exceed 3,900 flight cycles.
(2) If the crack length between points `A' and `B' is greater
than 0.15 inch or the crack length between points `C' and `D' is
greater than 0.05 inch: Before further flight, replace the
horizontal stabilizer center section rib with a new horizontal
stabilizer center section rib, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin MD80-55A069, dated
January 19, 2011. Repeat the inspection required by paragraph (g) of
this AD one time before the accumulation of 23,000 total flight
cycles on the new horizontal stabilizer center section rib, and
thereafter at intervals not to exceed 11,300 flight cycles.
Actions on Horizontal Stabilizer Ribs Made From 7050-T7451 Material
(i) For Group 2 airplanes, as identified in Boeing Alert Service
Bulletin MD80-55A069, dated January 19, 2011: Before the
accumulation of 23,000 total flight cycles, or within 4,383 flight
cycles after the effective date of this AD, whichever occurs later,
do an HFEC inspection for cracking of the left and right rib hinge
bearing lugs of the aft face of the center section of the horizontal
stabilizer, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin MD80-55A069, dated January 19, 2011.
For any crack-free lug, repeat the inspection on that lug thereafter
at intervals not to exceed 11,300 flight cycles.
(j) If, during any inspection required by paragraph (i) of this
AD, any crack is found, before further flight, measure the length of
the crack between the points specified in and in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin MD80-
55A069, dated January 19, 2011.
(1) If the crack length between points `A' and `B' is less than
or equal to 0.15 inch and the crack length between points `C' and
`D' is less than or equal to 0.05 inch: Before further flight, blend
out the crack, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin MD80-55A069, dated January 19, 2011.
Within 15,600 flight cycles after doing the blend out, do an HFEC
inspection of the blend out on the center section rib hinge bearing
lug for cracking, in accordance with the Accomplishment Instructions
of Boeing Alert Service Bulletin MD80-55A069, dated January 19,
2011, and repeat that inspection thereafter at intervals not to
exceed 5,800 flight cycles.
(2) If the crack length between points `A' and `B' is greater
than 0.15 inch or the crack length between points `C' and `D' is
greater than 0.05 inch: Before further flight, replace the
horizontal stabilizer center section rib with a new horizontal
stabilizer center section rib, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin MD80-55A069, dated
January 19, 2011. Repeat the inspection required by paragraph (i) of
this AD one time before the accumulation of 23,000 total flight
cycles on the new horizontal stabilizer center section rib, and
thereafter at intervals not to exceed 11,300 flight cycles.
No Reporting Requirement
(k) Although Boeing Alert Service Bulletin MD80-55A069, dated
January 19, 2011, specifies to submit certain information to the
manufacturer, this AD does not include that requirement.
Alternative Methods of Compliance (AMOCs)
(l)(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 the Related Information
section of this AD.
(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 ACO to
make those findings. For a repair method to be approved, the repair
must meet the certification basis of the airplane and 14 CFR 25.571,
Amendment 45, and the approval must specifically refer to this AD.
Related Information
(m) For more information about this AD, contact Roger Durbin,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood,
California 90712-4137; phone: 562-627-5233; fax 562-627-5210; e-
mail: [email protected].
(n) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; e-mail
[email protected]; 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 19, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-21853 Filed 8-25-11; 8:45 am]
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