
[Federal Register Volume 80, Number 141 (Thursday, July 23, 2015)]
[Proposed Rules]
[Pages 43642-43645]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-17955]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2958; Directorate Identifier 2014-NM-248-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 787 airplanes. This proposed AD was prompted 
by the disclosure that the inner diameters of some batches of landing 
gear pins were not shot peened in accordance with design specifications 
and need to be replaced. This proposed AD would require inspection for 
improperly manufactured landing gear pins, and replacement if 
necessary. We are proposing this AD to detect and correct insufficient 
shot peening that could lead to stress corrosion cracking and failure 
of the landing gear pin, and cause landing gear collapse and inability 
to control the airplane at high speeds on the ground.

DATES: We must receive comments on this proposed AD by September 8, 
2015.

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, WA 98124-2207;

[[Page 43643]]

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-2015-2958.

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-2015-
2958; 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: Melanie Violette, Senior Aerospace 
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6422; fax: 425-917-6590; email: 
melanie.violette@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-2015-2958; 
Directorate Identifier 2014-NM-248-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 indicating that the inner diameters of 
some batches of landing gear pins were not shot peened and need to be 
replaced. On high strength steel parts, shot peening increases fatigue 
life and reduces the likelihood of stress corrosion cracking. Stress 
corrosion cracking, if not corrected, could result in failure of the 
landing gear pin, and consequent landing gear collapse and the 
inability to control the airplane at high speeds on the ground.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin B787-81205-SB320022-00, 
Issue 001, dated November 14, 2014. The service information describes 
procedures for the inspection for improperly manufactured landing gear 
pins (parts that were not shot peened), and replacement if necessary. 
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 of this NPRM.

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, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.'' Refer to this service information for details on the 
procedures and compliance times.

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin B787-81205-SB320022-00, Issue 001, 
dated November 14, 2014, limits the effectivity in Group 2 to airplanes 
delivered prior to the publication of Boeing Alert Service Bulletin 
B787-81205-SB320022-00, Issue 001, dated November 14, 2014. However, 
this NPRM does not propose to include that limitation. The 
applicability of this proposed AD includes all The Boeing Company Model 
787 airplanes. Because the affected landing gear pins are rotable 
parts, we have determined that these parts could later be installed on 
production airplanes, thereby subjecting those airplanes to the unsafe 
condition. This difference has been coordinated with Boeing.

Costs of Compliance

    We estimate that this proposed AD affects 13 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
----------------------------------------------------------------------------------------------------------------
Inspection............................  3 work-hours x $85 per                $0            $255          $3,315
                                         hour = $255.
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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 
these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                 Action                           Labor cost            Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement.............................  Up to 19 work-hours x $85          $35,569  Up to $37,184
                                           per hour = $1,615.
----------------------------------------------------------------------------------------------------------------


[[Page 43644]]

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 RC (required for 
compliance) 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 
Required for Compliance (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.

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):

The Boeing Company: Docket No. FAA-2015-2958; Directorate Identifier 
2014-NM-248-AD.

(a) Comments Due Date

    We must receive comments by September 8, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 787 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 the disclosure that the inner diameters 
of some batches of landing gear pins were not shot peened in 
accordance with design specifications and need to be replaced. We 
are issuing this AD to detect and correct insufficient shot peening 
that could lead to stress corrosion cracking and failure of the 
landing gear pin, and cause landing gear collapse and inability to 
control the airplane at high speeds on the ground.

(f) Compliance

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

(g) Inspection and Replacement

    At the applicable time specified in paragraph 5, ``Compliance,'' 
of Boeing Alert Service Bulletin B787-81205-SB320022-00, Issue 001, 
dated November 14, 2014, do a landing gear pin part number and 
serial number inspection, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin B787-81205-SB320022-
00, dated November 14, 2014. A review of airplane maintenance or 
delivery records is acceptable in lieu of this inspection if the 
part number and serial number of the installed landing gear pins can 
be conclusively determined from that review.
    (1) If no part number or serial number is found that matches the 
list of affected pin numbers: No further action is required by this 
paragraph at that pin location.
    (2) If any part number or serial number is found that matches 
the list of affected pin numbers: At the applicable time specified 
in paragraph 5, ``Compliance,'' of Boeing Alert Service Bulletin 
B787-81205-SB320022-00, Issue 001, dated November 14, 2014, replace 
the affected pin with a pin that does not have an affected part 
number and serial number, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin B787-81205-SB320022-
00, Issue 001, dated November 14, 2014.

(h) Parts Installation Prohibition

    As of the effective date of this AD, no person may install on 
any airplane a landing gear pin having an affected part or serial 
number identified in Boeing Alert Service Bulletin B787-81205-
SB320022-00, Issue 001, dated November 14, 2014.

(i) 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 (j)(1) 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

[[Page 43645]]

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.
    (4) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(i)(4)(i) and (i)(4)(ii) 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.

(j) Related Information

    (1) For more information about this AD, contact Melanie 
Violette, Senior Aerospace Engineer, Airframe Branch, ANM-120S, FAA, 
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., 
Renton, WA 98057-3356; phone: 425-917-6422; fax: 425-917-6590; 
email: melanie.violette@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, 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.

    Issued in Renton, Washington, on July 14, 2015.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-17955 Filed 7-22-15; 8:45 am]
 BILLING CODE 4910-13-P


