
[Federal Register Volume 80, Number 138 (Monday, July 20, 2015)]
[Proposed Rules]
[Pages 42756-42760]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-17688]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2462; Directorate Identifier 2014-NM-224-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 737-100, -200, -200C, -300, -400, -500 
series airplanes. This proposed AD was prompted by reports of cracked 
antenna support channels, skin cracking underneath the number 2 very 
high frequency (VHF) antenna, and cracking in the frames attached to 
the internal support structure. This proposed AD would require 
repetitive inspections to determine the condition of the skin and the 
internal support structure, and follow-on actions including corrective 
action as necessary. We are proposing this AD to detect and correct 
skin cracking of the fuselage which could result in separation of the 
number 2 VHF antenna from the airplane and rapid depressurization of 
the cabin.

DATES: We must receive comments on this proposed AD by September 3, 
2015.

[[Page 42757]]


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-2015-2462.

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-
2462; 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-2015-2462; 
Directorate Identifier 2014-NM-224-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 antenna support channels, skin 
cracking underneath the number 2 VHF antenna, and cracking in the 
frames attached to the internal support structure. The cracking is 
caused when the nose gear is let down, resulting in turbulent airflow 
around the antenna. The turbulent airflow causes vibration in the 
antenna, which results in the skin, as well as the internal support 
structure and frames, to crack due to fatigue. This condition, if not 
corrected, could result in separation of the antenna from the airplane 
and rapid depressurization of the cabin.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Special Attention Service Bulletin 737-53-1159, 
Revision 1, dated October 20, 2014. The service information describes 
procedures for repetitive inspections to determine the condition of the 
skin and the internal support structure, and follow-on actions 
including corrective action as 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 identified previously, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.''

Difference Between This Proposed AD and the Service Information

    Tables 7, 8, and 9 in paragraph 1.E., ``Compliance,'' of Boeing 
Special Attention Service Bulletin 737-53-1159, Revision 1, dated 
October 20, 2014, specify post-modification and post-repair 
inspections, which may be used in support of compliance with section 
121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation Regulations 14 
CFR 121.1109(c)(2) or 129.109(b)(2)). However, this NPRM does not 
propose to require those post-modification and post-repair inspections. 
This difference has been coordinated with Boeing.
    Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, 
dated October 20, 2014, 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.

Explanation of ``RC (Required for Compliance)'' 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 alternative method of compliance (AMOC) is required for any 
deviations to RC steps, including substeps and identified figures; and 
(2)

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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 609 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...........  33 work-hours x $85 per                 $0   $2,805 per inspection  $1,708,245 per
                         hour = $2,805 per                            cycle.                 inspection cycle.
                         inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary [repairs/
modifications] 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 repairs/modifications.

                                               On-condition costs
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               Action                            Labor cost                Parts cost        Cost per product
----------------------------------------------------------------------------------------------------------------
Repair and Preventive Modification..  63 work-hours x $85 per hour =           $10,432   Up to $15,787.
                                       $5,355.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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-2015-2462; Directorate Identifier 
2014 NM-224-AD.

(a) Comments Due Date

    We must receive comments by September 3, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any 
category, as identified in Boeing Special Attention Service Bulletin 
737-53-1159, Revision 1, dated October 20, 2014.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of cracked antenna support 
channels, skin cracking underneath the number 2 VHF antenna, and 
cracking in the frames attached to the internal support structure. 
We are issuing this AD to detect and correct skin cracking of the 
fuselage that could result in separation of the antenna from the 
airplane and rapid depressurization of the cabin.

(f) Compliance

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

(g) Inspection and Follow-on Actions: Group 1

    For airplanes identified as Group 1 in Boeing Special Attention 
Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014: 
Within 120 days after the effective date of this AD, inspect for 
cracking at the number 2 VHF antenna location, and do all applicable 
follow-on actions, using a method approved in accordance with the 
procedures specified in paragraph (m) of this AD.

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(h) Inspection and Follow-on Actions: Groups 2 through 6, 
Configurations 1 through 3

    For airplanes identified as Groups 2 through 6, configurations 1 
through 3 in Boeing Special Attention Service Bulletin 737-53-1159, 
Revision 1, dated October 20, 2014: Within 1,250 flight cycles after 
the effective date of this AD, do an external detailed inspection 
for cracking of the fuselage skin, as applicable, and do all 
corrective actions, in accordance with Part 1 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 737-53-
1159, Revision 1, dated October 20, 2014. Thereafter, at the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, 
dated October 20, 2014, except as required by paragraph (l)(1) of 
this AD: Do all applicable actions specified in paragraphs (h)(1) 
through (h)(4) of this AD.
    (1) Repeat the Part 1 inspection specified in paragraph (h) of 
this AD until the accomplishment of paragraphs (k)(1) and (k)(2) of 
this AD, as applicable.
    (2) Inspect for cracking at the number 2 VHF antenna location 
using internal and external detailed inspections, internal and 
external high frequency eddy current (HFEC) inspections, and an HFEC 
open-hole inspection, in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 737-53-1159, Revision 1, dated October 20, 2014. Repeat the 
inspections until the accomplishment of paragraphs (k)(1) and (k)(2) 
of this AD, as applicable.
    (3) Repair any crack found, in accordance with Part 3 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 737-53-1159, Revision 1, dated October 20, 2014, except as 
required by paragraph (l)(2) of this AD.
    (4) Do a preventive modification, in accordance with Part 4 of 
the Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 737 53 1159, Revision 1, dated October 20, 2014, except as 
specified in paragraph (l)(2) of this AD. The accomplishment of this 
preventive modification terminates the inspections required by 
paragraphs (g), (g)(1), and (h)(2) of this AD.

(i) Inspection and Follow-on Actions: Groups 3 through 6, Configuration 
4

    For airplanes identified as Groups 3 through 6, Configuration 4, 
in Boeing Special Attention Service Bulletin 737-53-1159, Revision 
1, dated October 20, 2014: At the applicable time specified in table 
10 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention 
Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014; Do 
an external detailed inspection for cracking at the outer row of 
fasteners common to the internal repair doubler, and do an internal 
general visual inspection for cracking on the modified internal 
support structure of the number 2 VHF antenna, skin, and surrounding 
stringers, channel, and frames, in accordance with the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 737-53-1159, Revision 1, dated October 20, 2014.
    (1) If any cracking is found, before further flight, repair 
using a method approved in accordance with the procedures specified 
in paragraph (m) of this AD.
    (2) If no cracking is found, repeat the inspections at the time 
specified in table 10 of paragraph 1.E., ``Compliance,'' of Boeing 
SB 737-53-1159, Revision 1, dated October 20, 2014.

(j) Post Repair/Post Modification Inspections

    For airplanes identified as Group 2, Configuration 1, and Groups 
3 through 6, Configurations 1 through 3, in Boeing Special Attention 
Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014: 
The post-repair/post-modification inspections specified in tables 7 
through 9 of paragraph 1.E., ``Compliance'' of Boeing Special 
Attention Service Bulletin 737-53-1159, Revision 1, dated October 
20, 2014, are not required by this AD.

    Note 1 to paragraph (j) of this AD: The post-repair/post-
modification inspections specified in tables 7 through 9 of 
paragraph 1.E., ``Compliance'' of Boeing Special Attention Service 
Bulletin 737-53-1159, Revision 1, dated October 20, 2014, may be 
used in support of compliance with section 121.1109(c)(2) or 
129.109(b)(2) for the Federal Aviation Regulations (14 CFR 
121.1109(c)(2) or 14 CFR 129.109(b)(2)).

(k) Terminating Action Provisions

    The following describes terminating action for the airplane 
groups and configurations, as identified in Boeing Special Attention 
Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014.
    (1) For airplanes in Group 2, Configuration 2; and Groups 3 
through 6, Configuration 2: Accomplishment of the inspections 
specified in paragraph (h)(2) of this AD terminates the repetitive 
inspection requirements of paragraph (h)(1) of this AD.
    (2) For airplanes in Group 2, Configuration 1, and Groups 3 
through 6, Configuration 1, 2, and 3: Accomplishment of the repair 
specified in paragraph (h)(3) of this AD terminates the repetitive 
inspections specified in paragraph (h)(1) and (h)(2) of this AD.
    (3) For airplanes in Group 2, Configuration 1; and Groups 3 
through 6, Configurations 1 and 3: Accomplishment of the preventive 
modification specified in paragraph (h)(4) of this AD terminates the 
initial and repetitive inspections specified in paragraphs (h), 
(h)(1), and (h)(2) of this AD.

(l) Exception to Service Bulletin Specifications

    (1) Where Boeing Special Attention Service Bulletin 737-53-1159, 
Revision 1, dated October 20, 2014 compliance is ``after the 
Revision 1 date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD. Do the inspection, in accordance with the 
Accomplishment Instructions of the Boeing Special Attention Service 
Bulletin 737-53-1159, Revision 1, dated October 20, 2014.
    (2) Where Boeing Special Attention Service Bulletin 737-53-1159, 
Revision 1, dated October 20, 2014, specifies to contact Boeing for 
appropriate action, and specifies that action as ``RC'' (Required 
for Compliance): Before further flight, repair the cracking using a 
method approved in accordance with the procedures specified in 
paragraph (m) of 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 (n)(2) of this AD.
    (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, Los Angeles 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 
(m)(4)(i) and (m)(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.

(n) 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 information on AMOCs, contact Nenita Odesa, Aerospace 
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft 
Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 
90712-4137; phone: 562-627-5210; fax: 562-627-5234; email: 
nenita.odesa@faa.gov.
    (3) 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

[[Page 42760]]

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 10, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-17688 Filed 7-17-15; 8:45 am]
 BILLING CODE 4910-13-P


