
[Federal Register Volume 80, Number 210 (Friday, October 30, 2015)]
[Proposed Rules]
[Pages 66841-66843]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-27447]


 ========================================================================
 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. 80, No. 210 / Friday, October 30, 2015 / 
Proposed Rules  

[[Page 66841]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4210; Directorate Identifier 2015-NM-067-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 all 
The Boeing Company Model 767 airplanes. This proposed AD was prompted 
by a determination that certain splice plate locations of the aft 
pressure bulkhead web are hidden and cannot be inspected using existing 
manufacturer service information. This proposed AD would require 
repetitive open-hole high frequency eddy current (HFEC) inspections for 
cracking of the aft pressure bulkhead web. We are issuing this AD to 
detect and correct cracking in the aft pressure bulkhead web, which 
could result in rapid decompression and loss of structural integrity.

DATES: We must receive comments on this proposed AD by December 14, 
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; 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-2015-4210.

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-
4210; 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: Wayne Lockett, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6447; fax: 425-917-6590; email: wayne.lockett@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-2015-4210; 
Directorate Identifier 2015-NM-067-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 determined that certain splice plate locations of the aft 
pressure bulkhead web at station (STA) 1582 are hidden and cannot be 
inspected visually for cracking because they are hidden due to the 
installation of splice plates up to 5 inches in width. These locations 
cannot be inspected using existing manufacturer service information; 
therefore, fastener removal and repetitive open-hole HFEC inspections 
for cracking of the aft pressure bulkhead web at STA 1582 are needed. 
We are issuing this AD to detect and correct cracking in the aft 
pressure bulkhead web at STA 1582, which, if not found and repaired, 
could result in rapid decompression and loss of structural integrity.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 767-53A0266, dated April 
20, 2015. The service information describes procedures for removing the 
aft row of fasteners from each of the splice plates and doing an open-
hole HFEC inspection for cracking in the aft pressure bulkhead at STA 
1582. 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 identified previously, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.''
    For information on the procedures and compliance times, see this 
service

[[Page 66842]]

information at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2015-4210.
    The phrase ``corrective actions'' is used in this proposed AD. 
``Corrective actions'' are actions that correct or address any 
condition found. Corrective actions in an AD could include, for 
example, repairs.

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 alternative method of 
compliance (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.

Differences Between This Proposed AD and the Service Information

    The service bulletin specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 430 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
----------------------------------------------------------------------------------------------------------------
Repetitive inspections............  Up to 46 work-hours          $0   Up to $3,910 per      Up to $1,681,300 per
                                     x $85 per hour =                  inspection cycle.     inspection cycle.
                                     $3,910 per
                                     inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

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-2015-4210; Directorate Identifier 
2015-NM-067-AD.

(a) Comments Due Date

    We must receive comments by December 14, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 767-200, -300, -
300F, and -400ER series airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

[[Page 66843]]

(e) Unsafe Condition

    This AD was prompted by a determination that areas at certain 
splice plate locations of the aft pressure bulkhead web are hidden 
and cannot be inspected using existing manufacturer service 
information; therefore, an inspection for cracking of the aft 
pressure bulkhead web at station (STA) 1582 is needed. We are 
issuing this AD to detect and correct cracking in the aft pressure 
bulkhead web, which could result in rapid decompression and loss of 
structural integrity.

(f) Compliance

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

(g) Inspections of Station (STA) 1582 Aft Pressure Bulkhead Web Under 
the Pressure Slice Plates

    At the applicable times specified in Table 1 and Table 2 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
767-53A0266, dated April 20, 2015, except as required by paragraph 
(i) of this AD: Do an open-hole high frequency eddy current (HFEC) 
inspection for cracking in the aft pressure bulkhead web at STA 
1582, and do all applicable corrective actions, in accordance with 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
767-53A0266, dated April 20, 2015, except as required by paragraph 
(h) of this AD. Do all applicable corrective actions before further 
flight. Repeat the inspections thereafter at intervals not to exceed 
12,000 flight cycles.

(h) Repair

    If any crack is found during any inspection required by this AD, 
and Boeing Alert Service Bulletin 767-53A0266, dated April 20, 2015, 
specifies to contact Boeing for repair instructions: Before further 
flight, repair the crack in accordance with the procedures specified 
in paragraph (j) of this AD. Accomplishing a repair terminates the 
inspections required by paragraph (g) of this AD in the area under 
the repair only.

(i) Exceptions to the Service Information

    Where Boeing Alert Service Bulletin 767-53A0266, dated April 20, 
2015, specifies a compliance time ``after the original issue date of 
this service bulletin,'' this AD requires compliance within the 
specified 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 paragraph (k)(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 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) Except as required by paragraph (h) of this AD: For service 
information that contains steps that are labeled as Required for 
Compliance (RC), the provisions of paragraphs (j)(4)(i) and 
(j)(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.

(k) Related Information

    (1) For more information about this AD, contact Wayne Lockett, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6447; fax: 425-917-6590; email: 
wayne.lockett@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 October 19, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-27447 Filed 10-29-15; 8:45 am]
BILLING CODE 4910-13-P


