Document ID: FAA-2011-1259-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Boeing Co. Airplanes
Posted Date: 2011-12-06T05:00Z

[Federal Register Volume 76, Number 234 (Tuesday, December 6, 2011)]
[Proposed Rules]
[Pages 76066-76068]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-31312]

 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 76, No. 234 / Tuesday, December 6, 2011 / 
Proposed Rules  

[[Page 76066]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1259; Directorate Identifier 2011-NM-181-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 777 airplanes. This proposed 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, which may cause 
excessive horizontal stabilizer freeplay and structural damage 
significant enough to result in loss of control of the airplane. This 
proposed AD would require 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 proposing this 
AD to correct the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by January 20, 
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; 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 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: 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: 

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-2011-1259; 
Directorate Identifier 2011-NM-181-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 have received 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, which may cause 
excessive horizontal stabilizer freeplay and structural damage 
significant enough to result in loss of control of the airplane.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 777-55A0018, dated July 
27, 2011. The service information describes procedures for replacing 
the inner and outer 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.
    That service bulletin describes procedures for doing repetitive 
detailed inspections for cracks, corrosion damage, or other 
irregularities of the outer and inner pivot pins after their 
replacement, and doing corrective actions if necessary. That service 
bulletin also describes procedures for doing repetitive ultrasonic 
inspections for cracks of the outer pivot pins after their replacement, 
and doing corrective actions if necessary. Corrective actions include 
replacing any pivot pin having cracking, corrosion damage, or other 
irregularities, with a new or serviceable pivot pin.
    The compliance time for replacing the inner and outer pivot pins is 
the later of: (1) Before the accumulation of 16,000 total flight 
cycles, or within 3,000 days after the issuance of the original 
certificate of airworthiness or the original export certificate 
(whichever occurs first); and (2) within 750 days

[[Page 76067]]

``after the original issue date of this service bulletin.'' The first 
post-replacement inspection is within 32,000 flight cycles or 6,000 
days (whichever occurs first after the pin replacement). The repetitive 
inspection interval is 16,000 flight cycles or 3,000 days (whichever 
occurs first); or 12,000 flight cycles or 3,000 days (whichever occurs 
first); depending on airplane group.

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 described previously.

Costs of Compliance

    We estimate that this proposed AD affects 155 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed 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 proposed 
inspections. We have no way of determining the number of aircraft that 
might need these replacements.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                   Action                              Labor cost               Parts cost      Cost per 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

    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-2011-1259; Directorate Identifier 
2011-NM-181-AD.

(a) Comments Due Date

    We must receive comments by January 20, 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, dated July 27, 2011.

(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 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, which may cause excessive horizontal stabilizer freeplay 
and

[[Page 76068]]

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.

(g) Pivot Pin Replacement

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 777-55A0018, dated 
July 27, 2011, except as required by paragraph (i)(2) 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, dated July 27, 2011.

(h) Repetitive Inspections

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 777-55A0018, dated 
July 27, 2011: 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, dated July 27, 2011. 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, dated July 27, 2011, except as provided by 
paragraph (i)(1) of this AD.

    Note 1: The Accomplishment Instructions of Boeing Alert Service 
Bulletin 777-55A0018, dated July 27, 2011, might refer to other 
procedures. When the words ``refer to'' are used and the operator 
has an accepted alternative procedure, the accepted alternative 
procedure can be used to comply with the AD. When the words ``in 
accordance with'' are included in the instruction, the procedure in 
the design approval holder document must be used to comply with the 
AD.

(i) Exceptions

    The following exceptions to Boeing Alert Service Bulletin 777-
55A0018, dated July 27, 2011, apply to this AD.
    (1) Where the Repeat Interval column of tables 2 and 3 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
777-55A0018, dated July 27, 2011, specify a compliance time, this AD 
requires compliance within the specified compliance time after the 
most recent inspection.
    (2) Where paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 777-55A0018, dated July 27, 2011, specifies a 
compliance time ``after the original issue date of this service 
bulletin,'' this AD requires compliance within the specified 
compliance time ``after the effective date 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: 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.

(k) Related Information

    (1) 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.
    (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. 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 November 23, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-31312 Filed 12-5-11; 8:45 am]
BILLING CODE 4910-13-P