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[Federal Register Volume 76, Number 251 (Friday, December 30, 2011)]
[Proposed Rules]
[Pages 82210-82212]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-33544]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1412 Directorate Identifier 2011-NM-158-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 777-200 and -300 series airplanes. 
This proposed AD was prompted by reports of cracked retract actuator 
fuse pins that can fail earlier than the previously determined safe 
life limit of the pins. A fractured retract actuator fuse pin can cause 
the main landing gear (MLG) to extend without restriction and attempt 
to lock into position under high dynamic loads. This proposed AD would 
require an inspection for the part number of the fuse pin, and 
replacement of the pin if necessary. We are proposing this AD to 
prevent structural damage to the side and drag brace lock assemblies, 
which could result in landing gear collapse during touchdown, rollout, 
or taxi.

DATES: We must receive comments on this proposed AD by February 13, 
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, WA 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-2011-1412; 
Directorate Identifier 2011-NM-158-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 cracked retract actuator fuse pins that 
can fail earlier than previously determined safe life limit of the 
pins. A fractured retract actuator fuse pin can cause the main landing 
gear (MLG) to extend without restriction and attempt to lock into 
position under high dynamic loads. Unrestricted MLG extension could 
cause structural damage to the side and drag brace lock assemblies. 
This condition, if not corrected, could result in structural damage to 
the side and drag brace lock assemblies, which could result in landing 
gear collapse during touchdown, rollout, or taxi.

Relevant Service Information

    We reviewed Boeing Special Attention Service Bulletin 777-32-0083, 
Revision 1, dated February 17, 2011. The service information describes 
procedures for inspecting the retract actuator fuse pin to identify the 
part number of the pin and, if an affected pin is found, replacing it 
with a new part number pin.

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 these same type 
designs.

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 35 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 82211]]

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
              Action                        Labor cost            Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspection........................  4 work-hours x $85 per                 $0             $340          $11,900
                                     hour = $340.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary pin 
replacements that would be required based on the results of the 
proposed inspection. 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
----------------------------------------------------------------------------------------------------------------
Pin replacement...............  1 work-hour x $85 per   $769 per pin...............  $854 per pin.
                                 hour = $85 per pin.
----------------------------------------------------------------------------------------------------------------

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-2011-1412; Directorate Identifier 
2011-NM-158-AD.

(a) Comments Due Date

    We must receive comments by February 13, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 777-200 and -300 
series airplanes, certificated in any category, as identified in 
Boeing Special Attention Service Bulletin 777-32-0083, Revision 1, 
dated February 17, 2011.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 32, Main landing gear.

(e) Unsafe Condition

    This AD was prompted by reports of cracked retract actuator fuse 
pins that can fail earlier than the previously determined safe life 
limit of the pins. A fractured retract actuator fuse pin can cause 
the main landing gear (MLG) to extend without restriction and 
attempt to lock into position under high dynamic loads. We are 
issuing this AD to prevent structural damage to the side and drag 
brace lock assemblies, which could result in landing gear collapse 
during touchdown, rollout, or taxi.

(f) Compliance

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

(g) Inspection of Retract Actuator Fuse Pin

    Within 6 months after the effective date of this AD: Inspect the 
part number of the fuse pins of the left and right MLG retract 
actuators, in accordance with the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 777-32-0083, Revision 1, 
dated February 17, 2011. A review of airplane maintenance records is 
acceptable in lieu of this inspection if the part number of the 
installed actuator fuse pin can be conclusively determined from that 
review.
    (1) If any retract actuator fuse pin having part number 
112W1769-3 is found installed, no further action is required by this 
paragraph for that fuse pin.
    (2) If any retract actuator fuse pin having part number 
112W1769-1 is found installed and the pin has accumulated more than 
10,000 total flight cycles as of the effective date of this AD: 
Within 6 months after the effective date of this AD, replace the 
fuse pin with a new part number 112W1769-3 fuse pin, in accordance 
with the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 777-32-0083, Revision 1, dated February 17, 2011.
    (3) If any retract actuator fuse pin having part number 
112W1769-1 is found installed and the pin has accumulated 8,000 or 
more, but fewer than or equal to 10,000 total flight cycles, as of 
the effective date of this AD: Before the accumulation of 10,000 
total flight cycles on the pin, or within 12 months after the 
effective date of this AD, whichever occurs later, replace the fuse 
pin with a new part number 112W1769-3 fuse pin, in accordance with 
the Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 777-32-0083, Revision 1, dated February 17, 2011.

[[Page 82212]]

    (4) If any retract actuator fuse pin having part number 
112W1769-1 is found installed and the pin has accumulated fewer than 
8,000 total flight cycles as of the effective date of this AD: 
Before the accumulation of 8,000 total flight cycles on the pin, or 
within 24 months after the effective date of this AD, whichever 
occurs later, replace the fuse pin with a new part number 112W1769-3 
fuse pin, in accordance with the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 777-32-0083, Revision 1, 
dated February 17, 2011.

(h) Parts Installation

    As of the effective date of this AD, no person may install a 
retract actuator fuse pin having P/N 112W1769-1 on any airplane.

(i) Credit for Actions Accomplished in Accordance With Previous Service 
Information

    Actions done before the effective date of this AD in accordance 
with Boeing Special Attention Service Bulletin 777-32-0083, dated 
February 5, 2009, are acceptable for compliance with the 
corresponding requirements 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 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, 
WA 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 December 23, 2011.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-33544 Filed 12-29-11; 8:45 am]
BILLING CODE 4910-13-P
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