[Federal Register Volume 76, Number 234 (Tuesday, December 6, 2011)]
[Proposed Rules]
[Pages 76066-76068]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-31312]
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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.
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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).
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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
[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: 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: [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-2011-1259;
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
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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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.
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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
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Action Labor cost Parts cost Cost per product
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Pivot pin or spacer replacement............ 16 work-hours x $85 per hour $11,452 $12,812
= $1,360.
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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: [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 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: [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; email
[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 November 23, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-31312 Filed 12-5-11; 8:45 am]
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