```

[Federal Register Volume 81, Number 32 (Thursday, February 18, 2016)]
[Proposed Rules]
[Pages 8157-8160]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-03297]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-3697; Directorate Identifier 2015-NM-143-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 supersede Airworthiness Directive (AD) 2011-01-
15, which applies to certain The Boeing Company Model 757-200, -200CB, 
and -300 series airplanes. AD 2011-01-15 currently requires repetitive 
inspections for cracking of the fuselage skin of the crown skin panel 
along the chem-milled step at stringers S-4L (left) and S-4R (right), 
from stations (STA) 297 through STA 439, and repair, if necessary. AD 
2011-01-15 also includes terminating action for the repetitive 
inspections of the repaired areas only. Since we issued AD 2011-01-15, 
we received reports of the initiation of new fatigue cracking in the 
fuselage skin of the crown skin panel along locally thinned channels 
adjacent to the chem-milled steps. This proposed AD would add 
repetitive inspections for cracking in additional areas and repair if 
necessary. This proposed AD would also remove airplanes from the 
applicability in AD 2011-01-15. This proposed AD would also add an 
optional skin panel replacement which would terminate all inspections 
and an optional preventative modification that would terminate certain 
inspections. We are proposing this AD to detect and correct fatigue 
cracking of the fuselage skin of the crown skin panel, which could 
result in pressure venting and consequent rapid decompression of the 
airplane.

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, 3855 
Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; telephone: 
206-544-5000, extension 2; fax: 206-766-5683; 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-
3697.

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-
3697; 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: Eric Schrieber, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 
562-627-5348; fax: 562-627-5210; email: eric.schrieber@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-3697; 
Directorate Identifier 2015-NM-143-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

    On December 28, 2010, we issued AD 2011-01-15, Amendment 39-16572 
(76 FR 1351, January 10, 2011), for certain The Boeing Company Model 
757-200, -200CB, and -300 series airplanes. AD 2011-01-15 requires 
repetitive inspections for cracking of the fuselage skin of the crown 
skin panel along the

[[Page 8158]]

chem-milled step at stringers S-4L and S-4R, from stations (STA) 297 
through STA 439, and repair if necessary. AD 2011-01-15 also includes 
terminating action for the repetitive inspections of the repaired areas 
only. AD 2011-01-15 resulted from reports of cracking in the fuselage 
skin of the crown skin panel. We issued AD 2011-01-15 to detect and 
correct fatigue cracking of the fuselage skin of the crown skin panel, 
which could result in pressure venting and consequent rapid 
decompression of the airplane.

Actions Since AD 2011-01-15, Amendment 39-16572 (76 FR 1351, January 
10, 2011), Was Issued

    The preamble to AD 2011-01-15, Amendment 39-16572 (76 FR 1351, 
January 10, 2011), specifies that we consider the requirements 
``interim action.'' AD 2011-01-15 explains that we might consider 
further rulemaking if final action is later identified. We now have 
determined that it is necessary to initiate further rulemaking to add 
repetitive inspections for cracking in additional areas for certain 
airplanes, and repair if necessary.
    We have removed Model 757-200 CB series airplanes from the 
applicability because the crown skins on those airplanes are 
manufactured differently and therefore are not affected by the 
identified unsafe condition.
    We have also determined that the external detailed inspection that 
is allowed as an option in AD 2011-01-15, Amendment 39-16572 (76 FR 
1351, January 12, 2011), does not adequately address the identified 
unsafe condition. Only eddy current inspections are adequate to address 
the identified unsafe condition.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Special Attention Service Bulletin 757-53-0097, 
Revision 2, dated July 28, 2015. The service information describes 
procedures for repetitive external sliding probe eddy current (EC) and 
external spot-probe-medium-frequency EC inspections for cracking of the 
crown skin panel, repair, a preventive modification, and replacement of 
the crown skin panel. 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. For information on the 
procedures and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
3697.

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.

Costs of Compliance

    We estimate that this proposed AD affects 652 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
----------------------------------------------------------------------------------------------------------------
Inspections (Zone 1) [Retained   2 work-hour x $85 per   $0...............  $170 per           $110,840 per
 actions from AD 2011-01-15,      hour = $170 per                            inspection cycle.  inspection
 Amendment 39[dash]16572 (76 FR   inspection cycle.                                             cycle.
 1351, January 10, 2011)].
Inspections (Zones 2 and 3)      Up to 4 work-hours x    $0...............  Up to $340 per     $221,680 per
 [new proposed action].           $85 per hour = Up to                       inspection cycle.  inspection
                                  $340 per inspection                                           cycle.
                                  cycle.
Optional modification..........  Up to 615 work-hours x  Up to $26,496....  Up to $78,771....  Up to
                                  $85 per hour = Up to                                          $51,358,692.
                                  $52,275.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition actions specified in this proposed 
AD.
    We have received no definitive data that would enable us to provide 
a cost estimate for the optional replacement 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 have 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 that the proposed 
regulation:

[[Page 8159]]

    (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 removing Airworthiness Directive (AD) 
2011-01-15, Amendment 39-16572 (76 FR 1351, January 10, 2011), and 
adding the following new AD:

The Boeing Company: Docket No. FAA-2016-3697; Directorate Identifier 
2015-NM-143-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by April 4, 
2016.

(b) Affected ADs

    This AD replaces AD 2011-01-15, Amendment 39-16572 (76 FR 1351, 
January 10, 2011).

(c) Applicability

    (c) This AD applies to The Boeing Company Model 757-200 and -300 
series airplanes, certificated in any category, as identified in 
Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, 
dated July 28, 2015.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of the initiation of fatigue 
cracking in the fuselage skin of the crown skin panel along locally 
thinned channels adjacent to the chem-milled steps. We are issuing 
this AD to detect and correct fatigue cracking of the fuselage skin 
of the crown skin panel, which could result in pressure venting and 
consequent rapid decompression of the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    Do the applicable inspections required by paragraphs (g)(1), 
(g)(2), and (g)(3) of this AD.
    (1) For all airplanes: At the applicable time specified in table 
1 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention 
Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015: Do 
the inspection specified in paragraph (g)(1)(i) or (g)(1)(ii) of 
this AD in accordance with the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 757-53-0097, Revision 2, dated 
July 28, 2015. Repeat the inspection thereafter at the applicable 
times specified in table 1 of paragraph 1.E., ``Compliance,'' of 
Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, 
dated July 28, 2015. Accomplishing the preventative modification 
specified in paragraph (j)(1) of this AD or the replacement 
specified in paragraph (j)(2) of this AD terminates the inspections 
required by this paragraph.
    (i) Do an external sliding probe eddy current (EC) inspection 
for cracking of the crown skin panel at stringers S-4L (left) and S-
4R (right).
    (ii) Do an external spot-probe-medium-frequency EC inspection 
for cracking of the crown skin panel at stringers S-4L and S-4R.
    (2) For airplanes on which any crack is found during any 
inspection required by paragraph (g)(1) of this AD; or any repair is 
installed that covers the Zone 1 inspection area specified in Boeing 
Special Attention Service Bulletin 757-53-0097, Revision 2, dated 
July 28, 2015; or any preventive modification is installed as 
specified in Part 3 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 757-53-0097, Revision 2, dated 
July 28, 2015: At the applicable time specified in table 2 of 
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service 
Bulletin 757-53-0097, Revision 2, dated July 28, 2015, except as 
required by paragraph (k)(1) of this AD: Do the inspection specified 
in paragraph (g)(2)(i) or (g)(2)(ii) of this AD, in accordance with 
the Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 757-53-0097, Revision 2, dated July 28, 2015. Repeat the 
inspection thereafter at the applicable times specified in table 2 
of paragraph 1.E., ``Compliance,'' of Boeing Special Attention 
Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015. 
Accomplishing the replacement specified in paragraph (j)(2) of this 
AD terminates the inspections required by this paragraph.
    (i) Do an external sliding probe EC inspection for cracking of 
the crown skin panel at stringers S-2L, S-3L, and S-3R, as 
applicable.
    (ii) Do an external spot-probe-medium-frequency EC inspection 
for cracking of the crown skin panel at stringers S-2L, S-3L, and S-
3R, as applicable.
    (3) For airplanes on which any crack is found during any 
inspection required by paragraph (g)(1) of this AD; or any repair is 
installed that covers the Zone 1 inspection area specified in Boeing 
Special Attention Service Bulletin 757-53-0097, Revision 2, dated 
July 28, 2015; or any preventive modification is installed as 
specified in Part 3 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 757-53-0097, Revision 2, dated 
July 28, 2015: At the applicable time specified in table 3 of 
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service 
Bulletin 757-53-0097, Revision 2, dated July 28, 2015, except as 
required by paragraph (k)(1) of this AD: Do the inspection specified 
in paragraph (g)(3)(i) or (g)(3)(ii) of this AD, in accordance with 
the Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 757-53-0097, Revision 2, dated July 28, 2015. Repeat the 
inspection thereafter at the applicable times specified in table 3 
of paragraph 1.E., ``Compliance,'' of Boeing Special Attention 
Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015. 
Accomplishing the replacement specified in paragraph (j)(2) of this 
AD terminates the inspections required by this paragraph.
    (i) Do an external sliding probe EC inspection for cracking of 
the crown skin panel at stringers S-3L and S-3R.
    (ii) Do an external spot-probe-medium-frequency EC inspection 
for cracking of the crown skin panel at stringers S-3L and S-3R.

(h) Post-Preventive Modification Supplemental Inspections

    For airplanes on which a preventive modification has been 
installed as specified in Part 3 of the Accomplishment Instructions 
of Boeing Special Attention Service Bulletin 757-53-0097, Revision 
2, dated July 28, 2015: At the applicable time specified in table 4 
of paragraph 1.E., ``Compliance,'' of Boeing Special Attention 
Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015; do 
eddy current and detailed inspections for cracking of the applicable 
areas of the fuselage skin of the doublers, triplers, and fillers of 
the preventive modification, in accordance with the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 757-53-
0097, Revision 2, dated July 28, 2015. Repeat the inspection 
thereafter at the applicable times specified in table 4 of paragraph 
1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 
757-53-0097, Revision 2, dated July 28, 2015.

(i) Repair

    If any cracking is found during any inspection required by 
paragraph (g)(1), (g)(2), (g)(3), or (h) of this AD, repair before 
further flight using a method approved in accordance with the 
procedures specified in paragraph (m) of this AD. Doing the repair 
ends the repetitive inspections for the repaired area only.

(j) Optional Terminating Actions

    (1) Accomplishing the preventative modification, including doing 
high frequency EC inspections for cracking around existing fastener 
holes, in accordance with Part 3 of the Accomplishment Instructions 
of Boeing Special Attention Service Bulletin 757-53-0097, Revision 
2, dated July 28, 2015, except

[[Page 8160]]

as required by paragraphs (k)(2) and (k)(3) of this AD, terminates 
the inspections required by paragraph (g)(1) of this AD, provided 
the preventative modification is done before further flight after 
accomplishing an inspection required by paragraph (g) of this AD.
    (2) Replacing the crown skin panel between STA 297 and STA 439, 
S-4L to S-4R, using a method approved in accordance with the 
procedures specified in paragraph (m) of this AD, terminates the 
inspections required by paragraphs (g)(1), (g)(2), and (g)(3) of 
this AD.

(k) Exceptions to Service Information Specifications and Preventative 
Modification

    (1) Where Boeing Special Attention Service Bulletin 757-53-0097, 
Revision 2, dated July 28, 2015, specifies a compliance time ``after 
the Revision 2 date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (2) Where Boeing Special Attention Service Bulletin 757-53-0097, 
Revision 2, dated July 28, 2015, specifies to contact Boeing for 
repair instructions: Before further flight, repair using a method 
approved in accordance with the procedures specified in paragraph 
(m) of this AD.
    (3) If any cracking is found during any inspection specified in 
paragraph (j)(1) of this AD, before further flight, repair using a 
method approved in accordance with the procedures specified in 
paragraph (m) of this AD.

(l) Credit for Previous Actions

    (1) This paragraph provides credit for Zone 1 inspections 
required by paragraph (g) of this AD, if those actions were 
performed before the effective date of this AD using Boeing Special 
Attention Service Bulletin 757-53-0097, dated November 22, 2010, 
which was incorporated by reference in AD 2011-01-15, Amendment 39-
16572 (76 FR 1351, January 10, 2011).
    (2) This paragraph provides credit for the Zone 1 inspection 
required by paragraph (g) of this AD, if those actions were 
performed before the effective date of this AD, using Boeing Special 
Attention Service Bulletin 757-53-0097, Revision 1, dated January 6, 
2011, which is not incorporated by reference in this AD.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles 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 (m)(1) of this AD. 
Information may be emailed to: 9-ANM-LAACO-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. 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, Los Angeles ACO, to make those findings. For a repair 
method 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) AMOCs approved for AD 2011-01-15, Amendment 39-16572 (76 FR 
1351, January 10, 2011), are not approved as AMOCs for the 
corresponding provisions of paragraph (g) of this AD.
    (5) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(m)(5)(i) and (m)(5)(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.

(n) Related Information

    (1) For more information about this AD, contact Eric Schrieber, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles 
Aircraft Certification Office (ACO), 3960 Paramount Boulevard, 
Lakewood, CA 90712-4137; phone: 562-627-5348; fax: 562-627-5210; 
email: Eric.Schrieber@faa.gov.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; 
telephone: 206-544-5000, extension 2; fax: 206-766-5683; 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 February 8, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-03297 Filed 2-17-16; 8:45 am]
 BILLING CODE 4910-13-P
```