[Federal Register Volume 81, Number 32 (Thursday, February 18, 2016)]
[Proposed Rules]
[Pages 8164-8166]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-03138]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-0463; Directorate Identifier 2015-NM-155-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 all 
The Boeing Company Model 777 airplanes. This proposed AD was prompted 
by a report of an incident involving a landing in which the pilots 
needed to input corrections due to airplane yaw and roll to the right; 
the main landing gear (MLG) aft trunnion pin was later found to be 
fractured. This proposed AD would require identification and 
replacement of certain MLG aft trunnion pins. We are proposing this AD 
to prevent a fractured MLG aft trunnion pin, which could result in 
collapse of the MLG and consequent loss of control of the airplane 
during landing.

DATES: We must receive comments on this proposed AD by April 4, 2016.

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 NPRM, contact Boeing 
Commercial Airplanes, Attention: Data & Services Management, P.O. Box 
3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-5000, 
extension 1; fax: 206-766-5680; Internet https://www.myboeingfleet.com. 
You may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2016-0463.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
0463; 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: Narinder Luthra, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6513; fax: 415-917-6590; 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-2016-0463; 
Directorate Identifier 2015-NM-155-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 a report of an incident involving a landing in 
which the pilots needed to input corrections due to airplane yaw and 
roll to the right; the MLG aft trunnion pin was later found to be 
fractured. Other damage included minor damage to the gear beam and 
trunnion door panel and a broken tie rod. Analysis of the fractured pin 
showed that the crack started from an area of heat damage introduced 
during manufacturing. A review of gear overhaul records indicated that 
other pins manufactured by the same supplier had similar signs of heat 
damage, suspected to have been caused by abusive chrome grinding. This 
evidence suggests that the heat damage occurred during manufacturing, 
so it is possible that other airplanes have aft trunnion pins with 
similar heat damage. This condition, if not corrected, could result in 
collapse of the MLG and consequent loss of control of the airplane 
during landing.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 777-32A0103, Revision 1, 
dated December 10, 2015. The service information describes procedures 
for identifying and replacing certain MLG aft trunnion pins. This 
service information is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

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.

[[Page 8165]]

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin 777-32A0103, Revision 1, dated 
December 10, 2015, limits the effectivity to Model 777 airplanes, line 
numbers 1 through 1330 inclusive. However, this proposed AD does not 
propose to limit the applicability to those line numbers. The 
applicability of this proposed AD includes all The Boeing Company Model 
777-200, 777-200LR, 777-300, 777-300ER, and 777F series airplanes. 
Because the affected trunnion pins are rotable parts, we have 
determined that these parts could later be installed on airplanes that 
were initially delivered with acceptable pins, thereby subjecting those 
airplanes to the unsafe condition. This difference has been coordinated 
with Boeing.

Explanation of ``RC'' Steps in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which steps in the service information are required for 
compliance with an AD. Differentiating these steps from other tasks in 
the service information is expected to improve an owner's/operator's 
understanding of crucial AD requirements and help provide consistent 
judgment in AD compliance. The steps identified as Required for 
Compliance (RC) in any service information identified previously have a 
direct effect on detecting, preventing, resolving, or eliminating an 
identified unsafe condition.
    For service information that contains steps that are labeled as RC, 
the following provisions apply: (1) The steps labeled as RC, including 
substeps under an RC step and any figures identified in an RC step, 
must be done to comply with the AD, and an AMOC is required for any 
deviations to RC steps, including substeps and identified figures; and 
(2) steps not labeled as RC may be deviated from using accepted methods 
in accordance with the operator's maintenance or inspection program 
without obtaining approval of an AMOC, provided the RC steps, including 
substeps and identified figures, can still be done as specified, and 
the airplane can be put back in an airworthy condition.

Costs of Compliance

    We estimate that this proposed AD affects 123 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
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Inspection..........................  2 work-hours x $85 per               $0             $170          $20,910
                                       hour = $170.
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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 inspection. 
We have no way of determining the number of aircraft that might need 
this repair:

                                               On-Condition Costs
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                                                                                                     Cost per
                  Action                                Labor cost                 Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement of aft trunnion pin...........  34 work-hours x $85 per hour =              $5,291           $8,181
                                             $2,890.
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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

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):


[[Page 8166]]


The Boeing Company: Docket No. FAA-2016-0463; Directorate Identifier 
2015-NM-155-AD.

(a) Comments Due Date

    We must receive comments by April 4, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 777-200, 777-
200LR, 777-300, 777-300ER, and 777F series airplanes, certificated 
in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
gear.

(e) Unsafe Condition

    This AD was prompted by a report of an incident involving a 
landing in which the pilots needed to input corrections due to 
airplane yaw and roll to the right; the main landing gear (MLG) aft 
trunnion pin was later found to be fractured. We are issuing this AD 
to prevent a fractured MLG aft trunnion pin, which could result in 
collapse of the MLG and consequent loss of control of the airplane 
during landing.

(f) Compliance

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

(g) Aft Trunnion Pin Identification

    Within 36 months after the effective date of this AD, identify 
the serial number and marking of the MLG aft trunnion pins, in 
accordance with Part 1 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 777-32A0103, Revision 1, dated December 10, 
2015.

(h) MLG Aft Trunnion Pin Replacement

    For any MLG aft trunnion pin that begins with serial number 
``EGL'' or ``MAL,'' on which no ``BASE METAL INSPECTED'' marking is 
found, replace with a new or serviceable MLG aft trunnion pin within 
36 months after the effective date of this AD, in accordance with 
Part 2 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 777-32A0103, Revision 1, dated December 10, 2015.

(i) Part Installation Prohibition

    As of the effective date of this AD, no person may install, on 
any airplane, any MLG aft trunnion pin that begins with serial 
number ``EGL'' or ``MAL'' and is not marked ``BASE METAL 
INSPECTED.''

(j) Credit for Previous Actions

    (1) This paragraph provides credit for the actions specified in 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Multi-Operator Message (MOM) 
MOM-MOM15-0303-01B, dated May 13, 2015, which is not incorporated by 
reference in this AD.
    (2) 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 777-32A0103, dated September 11, 2015, which is not 
incorporated by reference in this AD.

(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 paragraph (l)(1) 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, modification, or alteration 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. To be approved, the 
repair method, modification deviation, or alteration deviation must 
meet the certification basis of the airplane and the approval must 
specifically refer to this AD.
    (4) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(k)(4)(i) and (k)(4)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. An AMOC is required for any deviations to RC steps, 
including substeps and identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(l) Related Information

    (1) For more information about this AD, contact Narinder Luthra, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6513; 
fax: 415-917-6590; 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, WA 98124-2207; telephone: 206-544-
5000, extension 1; fax: 206-766-5680; Internet https://www.myboeingfleet.com. You may view this service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
WA. For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on February 6, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate Aircraft Certification 
Service.
[FR Doc. 2016-03138 Filed 2-17-16; 8:45 am]
 BILLING CODE 4910-13-P