[Federal Register Volume 77, Number 176 (Tuesday, September 11, 2012)]
[Proposed Rules]
[Pages 55773-55775]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-22314]


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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 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for all 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. That NPRM 
proposed 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. That NPRM was prompted by reports of 
cracks of the hinge bearing lugs of the center section ribs of the 
horizontal stabilizer. This action revises that NPRM by adding the 
requirement for rib replacement if cracking is found during certain 
inspections of this proposed AD. We are proposing this supplemental 
NPRM to detect and correct cracking in the hinge bearing lugs of the 
horizontal stabilizer center section ribs, which could result in 
failure of the lugs, resulting in the inability of the horizontal 
stabilizer to sustain the required limit loads and consequent loss of 
control of the airplane. Since these actions impose an additional 
burden over that proposed in the NPRM, we are reopening the comment 
period to allow the public the chance to comment on these proposed 
changes.

DATES: We must receive comments on this supplemental NPRM by October 
26, 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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, 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, CA 90846-0001; 
telephone 206-544-5000, extension 2; fax 206-766-5683; 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, CA 90712-4137; phone: (562) 
627-5233; 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 proposed AD. 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 issued an NPRM to amend 14 CFR part 39 to include an AD that 
would apply 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. That NPRM 
published in the Federal Register on August 26, 2011 (76 FR 53346). 
That NPRM proposed to require repetitive 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.

Actions Since NPRM (76 FR 53346, August 26, 2011) Was Issued

    Since we issued the previous NPRM (76 FR 53346, August 26, 2011), 
we determined a required corrective action was not specified by Boeing 
Alert Service Bulletin MD80-55A069, dated January 19, 2011. Therefore, 
we propose to add a requirement for rib replacement if cracking is 
found during certain inspections required by this supplemental NPRM.

Comments

    We gave the public the opportunity to comment on the previous NPRM 
(76 FR 53346, August 26, 2011). The following presents the comments 
received on the NPRM and the FAA's response to each comment.

Support for the NPRM (76 FR 53346, August 26, 2011)

    Boeing stated it supports the NPRM (76 FR 53346, August 26, 2011).

Recognition That Reporting of Findings Is Not Required

    American Airlines stated it recognizes that reporting of findings 
requested by Boeing Alert Service Bulletin MD80-55A069, dated January 
19, 2011, is not required by the NPRM (76 FR 53346, August 26, 2011).
    We acknowledge American Airlines's comment. Reporting is not 
required by the supplemental NPRM. We have not

[[Page 55774]]

changed the supplemental NPRM in this regard.

FAA's Determination

    We are proposing this supplemental NPRM 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. Certain changes described above expand the scope of 
the previous NPRM (76 FR 53346, August 26, 2011). As a result, we have 
determined that it is necessary to reopen the comment period to provide 
additional opportunity for the public to comment on this supplemental 
NPRM.

Proposed Requirements of the Supplemental NPRM

    This supplemental NPRM would require accomplishing the actions 
specified in the service information described previously, except as 
discussed under ``Differences Between the Supplemental NPRM and the 
Service Information.''

Differences Between the Supplemental NPRM 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 supplemental NPRM would not require any report.
    Boeing Alert Service Bulletin MD80-55A069, dated January 19, 2011, 
does not specify instructions for replacing a horizontal stabilizer 
center section rib. If crack length exceeds a certain specified length 
or if cracking is found during any inspection of a blend-out repair, 
paragraphs (h)(2) and (j)(2) of this supplemental NPRM 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.

Interim Action

    We consider this supplemental NPRM 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 supplemental NPRM. 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
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                     Cost per
                Action                        Labor cost           Parts cost        product                      Cost on U.S.  operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection...........................  6 work-hours x $85 per               $0             $510   $340,680 per inspection cycle.
                                        hour = $510 per
                                        inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    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 repair kit for each horizontal stabilizer rib.

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.

(a) Comments Due Date

    We must receive comments by October 26, 2012.

(b) Affected ADs

    None.

(c) Applicability

    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.

[[Page 55775]]

(d) Subject

    Air Transport Association (ATA) of America Code 55, Stabilizers.

(e) Unsafe Condition

    This AD was prompted by reports of cracks of the hinge bearing 
lugs of the center section ribs of the horizontal stabilizer. We are 
issuing this AD to detect and correct cracking in the hinge bearing 
lugs of the horizontal stabilizer center section ribs, which could 
result in failure of the lugs, resulting in the inability of the 
horizontal stabilizer to sustain the required limit loads and 
consequent loss of control of the airplane.

(f) Compliance

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

(g) Inspection of Horizontal Stabilizer Ribs Made From 7075-T7351 
Material

    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 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 thereafter at intervals not to exceed 8,200 flight 
cycles.

(h) Repair and Replacement for Cracking of 7075-T7351 Material

    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 blendout 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.
    (i) If no cracking is found, repeat the inspection thereafter at 
intervals not to exceed 3,900 flight cycles.
    (ii) If cracking is found during any inspection of the blend 
out, before further flight, do the replacement required by paragraph 
(h)(2) of this AD, and do the inspections required by paragraph 
(h)(2) of this AD at the times specified in paragraph (h)(2) of this 
AD.
    (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, using a method approved in accordance 
with the procedures specified in paragraph (l) of this AD. 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.

(i) Inspection of Horizontal Stabilizer Ribs Made From 7050-T7451 
Material

    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 thereafter at 
intervals not to exceed 11,300 flight cycles.

(j) Repair and Replacement for Cracking of 7050-T7451 Material

    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.
    (i) If no cracking is found, repeat the inspection thereafter at 
intervals not to exceed 5,800 flight cycles.
    (ii) If cracking is found during any inspection of the blend 
out, before further flight, do the replacement required by paragraph 
(j)(2) of this AD, and do the inspections required by paragraph 
(j)(2) of this AD at the times specified in paragraph (j)(2) of this 
AD.
    (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, using a method approved in accordance 
with the procedures specified in paragraph (l) of this AD. 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.

(k) No Reporting Requirement

    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.

(l) Alternative Methods of Compliance (AMOCs)

    (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.

(m) Related Information

    (1) 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, 
CA 90712-4137; phone: (562) 627-5233; fax: (562) 627-5210; email: 
[email protected].
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; 
telephone 206-544-5000, extension 2; fax 206-766-5683; 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 September 4, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-22314 Filed 9-10-12; 8:45 am]
BILLING CODE 4910-13-P