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[Federal Register Volume 77, Number 102 (Friday, May 25, 2012)]
[Rules and Regulations]
[Pages 31167-31169]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-12087]

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Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
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Federal Register / Vol. 77, No. 102 / Friday, May 25, 2012 / Rules 
and Regulations

[[Page 31167]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1259; Directorate Identifier 2011-NM-181-AD; 
Amendment 39-17059; AD 2012-10-10]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 777 airplanes. This AD was prompted by reports 
of corrosion damage on the outer diameter chrome surface of the 
horizontal stabilizer pivot pins. Micro-cracks in the chrome plating of 
the pivot pin, some of which extended into the base metal, were also 
reported. This condition, if not corrected, could result in a fractured 
horizontal stabilizer pivot pin. This AD requires replacing the 
existing horizontal stabilizer pivot pins with new or reworked pivot 
pins having improved corrosion resistance, doing repetitive inspections 
after installing the pivot pins, and doing corrective actions if 
necessary. We are issuing this AD to prevent a fractured horizontal 
stabilizer pivot pin, which may cause excessive horizontal stabilizer 
freeplay and structural damage significant enough to result in loss of 
control of the airplane.

DATES: This AD is effective June 29, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of June 29, 
2012.

ADDRESSES: 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; email me.boecom@boeing.com; 
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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: James Sutherland, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-
6533; fax: 425-917-6590; email: james.sutherland@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM published in the Federal Register on December 6, 2011 (76 FR 
76066). That NPRM proposed to replace the existing horizontal 
stabilizer pivot pins with new or reworked pivot pins having improved 
corrosion resistance, doing repetitive inspections after installing the 
pivot pins, and doing corrective actions if necessary.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(76 FR 76066, December 6, 2011) and the FAA's response to each comment.

Request To Delay Rule Due to Pending Service Information

    FedEx and All Nippon Airways (ANA) requested that the release date 
of the AD be postponed until Revision 1 of Boeing Alert Service 
Bulletin 777-55A0018 is issued. FedEx stated that the horizontal 
stabilizer jacking tool used for the pivot pin removal/installation 
procedure, as specified in Boeing Alert Service Bulletin 777-55A0018, 
dated July 27, 2011, is being re-designed, and suggested that the 
release date of the AD be postponed until re-design of the tool is 
completed and Revision 1 is issued. ANA noted that Boeing does not 
recommend accomplishing Boeing Alert Service Bulletin 777-55A0018, 
dated July 27, 2011, until the anti-rotation plates and jacking tool 
are available.
    We do not agree to postpone issuing the final rule, because Boeing 
has issued Alert Service Bulletin 777-55A0018, Revision 1, dated March 
6, 2012. That service bulletin includes the new anti-rotation plates, 
and, as an alternative to having the new anti-rotation plates, a 
procedure for reworking the existing anti-rotation plates. The pin 
removal tool is an optional tool allowing operators an alternate method 
to remove the horizontal stabilizer pivot pins without the jacking 
tool. The existing tool is applicable to line numbers 1 through 40, and 
Boeing has issued rework instructions for the operators to modify 
existing tools for all Model 777 airplanes. The scope of this AD has 
not been expanded. We have updated the references in paragraphs (c), 
(g), (h), and (i) of this AD accordingly. In paragraph (j) of this AD, 
we are giving credit for actions done using Boeing Alert Service 
Bulletin 777-55A0018, dated July 27, 2011.

Other Changes to NPRM (76 FR 76066, December 6, 2011)

    The Repeat Interval columns of tables 2 and 3 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 777-55A0018, Revision 
1, dated March 6, 2012, are corrected to include the phrase ``after the 
most recent inspection.'' Therefore, we have removed the exception 
stated in paragraph (i)(1) of the NPRM (76 FR 76066, December 6, 2011).

[[Page 31168]]

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD as proposed except for minor editorial changes. We have 
determined that these minor changes:
     [Agr]re consistent with the intent that was proposed in 
the NPRM (76 FR 76066, December 6, 2011) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (76 FR 76066, December 6, 2011).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD affects 155 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Replacement of horizontal          16 work-hours x $85         $11,452  $12,812............  $1,985,860
 stabilizer pivot pins.             per hour = $1,360.
Repetitive inspections...........  22 work-hours x $85               0  $1,870 per           $289,850 per
                                    per hour = $1,870                    inspection cycle.    inspection cycle.
                                    per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspections. We have 
no way of determining the number of aircraft that might need these 
replacements.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Pivot pin or spacer replacement..............  16 work-hours x $85 per hour =          $11,452          $12,812
                                                $1,360.
----------------------------------------------------------------------------------------------------------------

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

    This AD will not have federalism implications under Executive Order 
13132. This AD will 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under 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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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):

2012-10-10 The Boeing Company: Amendment 39-17059; Docket No. FAA-
2011-1259; Directorate Identifier 2011-NM-181-AD.

(a) Effective Date

    This AD is effective June 29, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 777-200, -200LR, -
300, -300ER, and 777F series airplanes, certificated in any 
category; as identified in Boeing Alert Service Bulletin 777-
55A0018, Revision 1, dated March 6, 2012.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 55, Stabilizers.

(e) Unsafe Condition

    This AD was prompted by reports of corrosion damage on the outer 
diameter chrome surface of the horizontal stabilizer pivot pins. 
Micro-cracks in the chrome plating of the pivot pins, some of which 
extended into the base metal, were also reported. We are issuing 
this AD to prevent a fractured horizontal stabilizer pivot pin, 
which may cause excessive horizontal stabilizer freeplay and 
structural damage significant enough to result in loss of control of 
the airplane.

(f) Compliance

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

[[Page 31169]]

(g) Pivot Pin Replacement

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 777-55A0018, 
Revision 1, dated March 6, 2012, except as required by paragraph (i) 
of this AD: Replace the pivot pins of the horizontal stabilizer with 
new or reworked pivot pins, including replacing the spacer with a 
new spacer or with one that has been determined to be without 
corrosion damage or other irregularities; in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
55A0018, Revision 1, dated March 6, 2012.

(h) Repetitive Inspections

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 777-55A0018, 
Revision 1, dated March 6, 2012: Do detailed inspections for cracks, 
corrosion damage, or other irregularity of the outer and inner pivot 
pins; and an ultrasonic inspection for cracking of the outer pivot 
pins; and do all applicable corrective actions; in accordance with 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
777-55A0018, Revision 1, dated March 6, 2012. Corrective actions 
must be done before further flight. Repeat the inspections at the 
applicable interval specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 777-55A0018, Revision 1, dated March 
6, 2012.

(i) Exception

    Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 777-55A0018, Revision 1, dated March 6, 2012, specifies a 
compliance time ``after the Revision 1 date of this service 
bulletin,'' this AD requires compliance within the specified 
compliance time ``after the effective date of this AD.''

(j) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using Boeing Alert Service 
Bulletin 777-55A0018, dated July 27, 2011.

(k) 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: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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.

(l) Related Information

    For more information about this AD, contact James Sutherland, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, Washington 
98057-3356; phone: 425-917-6533; fax: 425-917-6590; email: 
james.sutherland@faa.gov.

(m) Material Incorporated by Reference

    You must use the following service information to do the actions 
required by this AD, unless the AD specifies otherwise. The Director 
of the Federal Register approved the incorporation by reference 
(IBR) of the following service information under 5 U.S.C. 552(a) and 
1 CFR part 51:
    (1) Boeing Alert Service Bulletin 777-55A0018, Revision 1, dated 
March 6, 2012.
    (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; email 
me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
    (3) You may review copies of the 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.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on May 11, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-12087 Filed 5-24-12; 8:45 am]
BILLING CODE 4910-13-P
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