80_FR_9703 80 FR 9667 - Airworthiness Directives; The Boeing Company Airplanes

80 FR 9667 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 36 (February 24, 2015)

Page Range9667-9669
FR Document2015-03677

We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This proposed AD was prompted by reports of fatigue cracking found at the left-side and right-side upper frame, at a certain area. This proposed AD would require repetitive medium frequency eddy current (MFEC) inspections for cracking of the left-side and right-side upper frame, and repair (including open hole high frequency eddy current (HFEC) inspections for cracking of fastener holes) if necessary. This proposed AD also provides an optional preventative modification which would terminate the repetitive inspections at the modified location. We are proposing this AD to detect and correct fatigue cracking, which if not corrected, can grow in size and result in a severed frame, which could lead to rapid decompression and reduced structural integrity of the airplane.

Federal Register, Volume 80 Issue 36 (Tuesday, February 24, 2015) 
[Federal Register Volume 80, Number 36 (Tuesday, February 24, 2015)]
[Proposed Rules]
[Pages 9667-9669]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-03677]


========================================================================
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. 36 / Tuesday, February 24, 2015 / 
Proposed Rules

[[Page 9667]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0246; Directorate Identifier 2014-NM-187-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 
certain The Boeing Company Model 737-300, -400, and -500 series 
airplanes. This proposed AD was prompted by reports of fatigue cracking 
found at the left-side and right-side upper frame, at a certain area. 
This proposed AD would require repetitive medium frequency eddy current 
(MFEC) inspections for cracking of the left-side and right-side upper 
frame, and repair (including open hole high frequency eddy current 
(HFEC) inspections for cracking of fastener holes) if necessary. This 
proposed AD also provides an optional preventative modification which 
would terminate the repetitive inspections at the modified location. We 
are proposing this AD to detect and correct fatigue cracking, which if 
not corrected, can grow in size and result in a severed frame, which 
could lead to rapid decompression and reduced structural integrity of 
the airplane.

DATES: We must receive comments on this proposed AD by April 10, 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, 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-
0246.

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-
0246; 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: [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-2015-0246; 
Directorate Identifier 2014-NM-187-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 received reports of fatigue cracking found at frame station 360 
between stringer 13 and stringer 14. At the time of crack detection, 
the airplanes had accumulated between 37,826 to 42,986 total flight 
cycles. The reported cracks ranged from 0.35 inches to 1.5 inches in 
length. Cracking of the left-side or right-side upper frame at station 
360 between stringer 13 and stringer 14, if not corrected, can grow in 
size and result in a severed frame, which could lead to rapid 
decompression and reduced structural integrity of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 737-53A1339, dated August 
12, 2014. This service information describes procedures for inspections 
for cracking of the left-side and right-side upper frame, at station 
360 between stringer 13 and stringer 14; repair, and optional 
preventative modification. For information on the procedures and 
compliance times, see this service information. This service 
information is reasonably available; see ADDRESSES for ways to access 
this service information.

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.''

[[Page 9668]]

Explanation of ``RC'' Steps in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directives 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.
    Steps that are identified as RC in any service information must be 
done to comply with the proposed AD. However, steps that are not 
identified as RC are recommended. Those steps that are not identified 
as RC may be deviated from using accepted methods in accordance with 
the operator's maintenance or inspection program without obtaining 
approval of an alternative method of compliance (AMOC), provided the 
steps identified as RC can be done and the airplane can be put back in 
a serviceable condition. Any substitutions or changes to steps 
identified as RC will require approval of an AMOC.

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin 737-53A1339, dated August 12, 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.

Costs of Compliance

    We estimate that this proposed AD affects 109 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....................  14 work-hours x $85 per              $0  $1,190 per          $129,710 per
                                  hour = $1,190 per                        inspection cycle.   inspection cycle.
                                  inspection cycle.
Preventative modification        15 work-hours x $85 per              $0  $1,275 per          $138,975 per
 (optional).                      hour = $1,275 per                        inspection cycle.   inspection cycle.
                                  inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
actions 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 actions:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair and open hole HFEC inspection.......  36 work-hours x $85 per hour =                   $0          $3,060
                                              $3,060.
----------------------------------------------------------------------------------------------------------------

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 proposed 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 9669]]


The Boeing Company: Docket No. FAA-2015-0246; Directorate Identifier 
2014-NM-187-AD.

(a) Comments Due Date

    We must receive comments by April 10, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 737-300, -400, and -
500 series airplanes, certificated in any category, as identified in 
Boeing Alert Service Bulletin 737-53A1339, dated August 12, 2014.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of fatigue cracking found at the 
left-side and right-side upper frame, at station 360 between 
stringer 13 and stringer 14. We are issuing this AD to detect and 
correct fatigue cracking of the left-side and right-side upper frame 
at station 360 between stringer 13 and stringer 14, which if not 
corrected, can grow in size and result in a severed frame, which 
could lead to rapid decompression and reduced structural integrity 
of the airplane.

(f) Compliance

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

(g) Repetitive Inspections for Cracking

    At the applicable times specified in table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1339, dated 
August 12, 2014, except as required by paragraph (i)(2) of this AD: 
Do a medium frequency eddy current (MFEC) inspection for cracking on 
the left-side and right-side of the upper frame at Station 360 
between stringer 13 and stringer 14, in accordance with Part 2 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-53A1339, dated August 12, 2014. If no cracking is found, repeat 
the inspections at the applicable times specified in Table 1 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-53A1339, dated August 12, 2014. Accomplishment of the actions 
specified in paragraph (j) of this AD terminates the repetitive 
inspections required by this paragraph at the modified area only.

(h) Repair

    If any cracking is found during any inspection required by 
paragraph (g) of this AD: Before further flight, repair the cracking 
including doing an open hole high frequency eddy current (HFEC) 
inspection for cracking of the holes, in accordance with Part 3 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-53A1339, dated August 12, 2014, except as required by paragraph 
(i)(1) of this AD. Repair of any crack terminates the repetitive 
inspection requirements of paragraph (g) of this AD for the repaired 
area only. If any cracking is found during any inspection required 
by this paragraph, repair using a method approved in accordance with 
the procedures specified in paragraph (l) of this AD.

(i) Exceptions to the Service Information

    (1) Where Boeing Alert Service Bulletin 737-53A1339, dated 
August 12, 2014, specifies contacting Boeing for repair 
instructions: Before further flight, repair using a method approved 
in accordance with the procedures specified in paragraph (l) of this 
AD.
    (2) Where Boeing Alert Service Bulletin 737-53A1339, dated 
August 12, 2014, 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) Optional Preventative Modification

    Modification of an inspection area specified in paragraph (g) of 
this AD, including doing open hole and surface HFEC inspections for 
cracking of the area to be modified, in accordance with Part 4 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-53A1339, dated August 12, 2014, except as required by paragraph 
(i)(1) of this AD, terminates the repetitive inspections required by 
paragraph (g) of this AD at the modified location only.

(k) Post-Repair and Post-Modification Inspections

    The post-repair and post-modification inspections specified in 
Tables 4 and 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 737-53A1339, dated August 12, 2014, are not 
required by this AD.
    Note 1 to paragraph (k) of this AD: The post-repair and post-
modification inspections specified in Tables 4 and 5 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1339, 
dated August 12, 2014, 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 14 CFR 129.109(b)(2)).

(l) 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 (m)(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 required by this AD if it is approved by 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 (i)(1) of this AD: If any 
service information contains steps that are identified as RC 
(Required for Compliance), those steps must be done to comply with 
this AD; any steps that are not identified as RC are recommended. 
Those steps that are not identified 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 steps identified as RC can be done and the airplane can be put 
back in a serviceable condition. Any substitutions or changes to 
steps identified as RC require approval of an AMOC.

(m) 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: 
[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 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 11, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-03677 Filed 2-23-15; 8:45 am]
BILLING CODE 4910-13-P

9667 Proposed Rules Federal Register Vol. 80, No. 36 Tuesday, February 24, 2015 This section of the FEDERAL REGISTER 30, West Building Ground Floor, Room comments on the overall regulatory, contains notices to the public of the proposed W12–140, 1200 New Jersey Avenue SE., economic, environmental, and energy issuance of rules and regulations. The Washington, DC 20590. aspects of this proposed AD. We will purpose of these notices is to give interested • Hand Delivery: Deliver to Mail consider all comments received by the persons an opportunity to participate in the address above between 9 a.m. and 5 closing date and may amend this rule making prior to the adoption of the final p.m., Monday through Friday, except proposed AD because of those rules. Federal holidays. comments. For service information identified in We will post all comments we DEPARTMENT OF TRANSPORTATION this proposed AD, contact Boeing receive, without change, to http:// Commercial Airplanes, Attention: Data www.regulations.gov, including any Federal Aviation Administration & Services Management, P. O. Box 3707, personal information you provide. We MC 2H–65, Seattle, WA 98124–2207; will also post a report summarizing each 14 CFR Part 39 telephone 206–544–5000, extension 1; substantive verbal contact we receive fax 206–766–5680; Internet https:// about this proposed AD. [Docket No. FAA–2015–0246; Directorate Identifier 2014–NM–187–AD] www.myboeingfleet.com. You may view Discussion this referenced service information at RIN 2120–AA64 the FAA, at the FAA, Transport We received reports of fatigue Airplane Directorate, 1601 Lind Avenue cracking found at frame station 360 Airworthiness Directives; The Boeing SW., Renton, WA. For information on between stringer 13 and stringer 14. At Company Airplanes the availability of this material at the the time of crack detection, the AGENCY: Federal Aviation FAA, call 425–227–1221. It is also airplanes had accumulated between Administration (FAA), DOT. available on the Internet at http:// 37,826 to 42,986 total flight cycles. The www.regulations.gov by searching for reported cracks ranged from 0.35 inches ACTION: Notice of proposed rulemaking and locating Docket No. FAA–2015– to 1.5 inches in length. Cracking of the (NPRM). left-side or right-side upper frame at 0246. SUMMARY: We propose to adopt a new station 360 between stringer 13 and airworthiness directive (AD) for certain Examining the AD Docket stringer 14, if not corrected, can grow in The Boeing Company Model 737–300, You may examine the AD docket on size and result in a severed frame, –400, and –500 series airplanes. This the Internet at http:// which could lead to rapid proposed AD was prompted by reports www.regulations.gov by searching for decompression and reduced structural of fatigue cracking found at the left-side and locating Docket No. FAA–2015– integrity of the airplane. and right-side upper frame, at a certain 0246; or in person at the Docket Related Service Information Under 1 area. This proposed AD would require Management Facility between 9 a.m. CFR Part 51 repetitive medium frequency eddy and 5 p.m., Monday through Friday, current (MFEC) inspections for cracking except Federal holidays. The AD docket We reviewed Boeing Alert Service of the left-side and right-side upper contains this proposed AD, the Bulletin 737–53A1339, dated August 12, frame, and repair (including open hole regulatory evaluation, any comments 2014. This service information describes high frequency eddy current (HFEC) received, and other information. The procedures for inspections for cracking inspections for cracking of fastener street address for the Docket Office of the left-side and right-side upper holes) if necessary. This proposed AD (phone: 800–647–5527) is in the frame, at station 360 between stringer 13 also provides an optional preventative ADDRESSES section. Comments will be and stringer 14; repair, and optional modification which would terminate the available in the AD docket shortly after preventative modification. For repetitive inspections at the modified receipt. information on the procedures and location. We are proposing this AD to compliance times, see this service FOR FURTHER INFORMATION CONTACT: detect and correct fatigue cracking, information. This service information is Wayne Lockett, Aerospace Engineer, reasonably available; see ADDRESSES for which if not corrected, can grow in size Airframe Branch, ANM–120S, FAA, and result in a severed frame, which ways to access this service information. Seattle Aircraft Certification Office could lead to rapid decompression and (ACO), 1601 Lind Avenue SW., Renton, FAA’s Determination reduced structural integrity of the WA 98057–3356; phone: 425–917–6447; We are proposing this AD because we airplane. fax: 425–917–6590; email: evaluated all the relevant information DATES: We must receive comments on wayne.lockett@faa.gov. and determined the unsafe condition this proposed AD by April 10, 2015. SUPPLEMENTARY INFORMATION: described previously is likely to exist or ADDRESSES: You may send comments, Comments Invited develop in other products of the same using the procedures found in 14 CFR type design. tkelley on DSK3SPTVN1PROD with PROPOSALS 11.43 and 11.45, by any of the following We invite you to send any written relevant data, views, or arguments about Proposed AD Requirements methods: • Federal eRulemaking Portal: Go to this proposal. Send your comments to This proposed AD would require http://www.regulations.gov. Follow the an address listed under the ADDRESSES accomplishing the actions specified in instructions for submitting comments. section. Include ‘‘Docket No. FAA– the service information described • Fax: 202–493–2251. 2015–0246; Directorate Identifier 2014– previously, except as discussed under • Mail: U.S. Department of NM–187–AD’’ at the beginning of your ‘‘Differences Between This Proposed AD Transportation, Docket Operations, M– comments. We specifically invite and the Service Information.’’ VerDate Sep<11>2014 16:04 Feb 23, 2015 Jkt 235001 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 E:\FR\FM\24FEP1.SGM 24FEP1

9668 Federal Register / Vol. 80, No. 36 / Tuesday, February 24, 2015 / Proposed Rules Explanation of ‘‘RC’’ Steps in Service Steps that are identified as RC in any specifies to contact the manufacturer for Information service information must be done to instructions on how to repair certain The FAA worked in conjunction with comply with the proposed AD. conditions, but this proposed AD would industry, under the Airworthiness However, steps that are not identified as require repairing those conditions in Directives Implementation Aviation RC are recommended. Those steps that one of the following ways: are not identified as RC may be deviated Rulemaking Committee (ARC), to • In accordance with a method that enhance the AD system. One from using accepted methods in we approve; or enhancement was a new process for accordance with the operator’s annotating which steps in the service maintenance or inspection program • Using data that meet the information are required for compliance without obtaining approval of an certification basis of the airplane, and with an AD. Differentiating these steps alternative method of compliance that have been approved by the Boeing from other tasks in the service (AMOC), provided the steps identified Commercial Airplanes Organization information is expected to improve an as RC can be done and the airplane can Designation Authorization (ODA) whom owner’s/operator’s understanding of be put back in a serviceable condition. we have authorized to make those crucial AD requirements and help Any substitutions or changes to steps findings. provide consistent judgment in AD identified as RC will require approval of an AMOC. Costs of Compliance compliance. The steps identified as RC (required for compliance) in any service Differences Between This Proposed AD We estimate that this proposed AD information identified previously have a and the Service Information affects 109 airplanes of U.S. registry. direct effect on detecting, preventing, resolving, or eliminating an identified Boeing Alert Service Bulletin 737– We estimate the following costs to unsafe condition. 53A1339, dated August 12, 2014, comply with this proposed AD: ESTIMATED COSTS Cost on U.S. Action Labor cost Parts cost Cost per product operators Inspections ............................................. 14 work-hours × $85 per hour = $1,190 $0 $1,190 per inspec- $129,710 per in- per inspection cycle. tion cycle. spection cycle. Preventative modification (optional) ....... 15 work-hours × $85 per hour = $1,275 $0 $1,275 per inspec- $138,975 per in- per inspection cycle. tion cycle. spection cycle. We estimate the following costs to do would be required based on the results way of determining the number of any necessary on-condition actions that of the proposed inspection. We have no aircraft that might need these actions: ON-CONDITION COSTS Cost per Action Labor cost Parts cost product Repair and open hole HFEC inspection ...................... 36 work-hours × $85 per hour = $3,060 ...................... $0 $3,060 Authority for This Rulemaking Regulatory Findings under the criteria of the Regulatory Title 49 of the United States Code We determined that this proposed AD Flexibility Act. specifies the FAA’s authority to issue would not have federalism implications List of Subjects in 14 CFR Part 39 rules on aviation safety. Subtitle I, under Executive Order 13132. This Air transportation, Aircraft, Aviation section 106, describes the authority of proposed AD would not have a safety, Incorporation by reference, the FAA Administrator. Subtitle VII: substantial direct effect on the States, on Safety. Aviation Programs, describes in more the relationship between the national detail the scope of the Agency’s Government and the States, or on the The Proposed Amendment authority. distribution of power and Accordingly, under the authority We are issuing this rulemaking under responsibilities among the various delegated to me by the Administrator, the authority described in Subtitle VII, levels of government. the FAA proposes to amend 14 CFR part Part A, Subpart III, Section 44701: For the reasons discussed above, I 39 as follows: ‘‘General requirements.’’ Under that certify this proposed regulation: section, Congress charges the FAA with (1) Is not a ‘‘significant regulatory PART 39—AIRWORTHINESS promoting safe flight of civil aircraft in action’’ under Executive Order 12866, DIRECTIVES air commerce by prescribing regulations (2) Is not a ‘‘significant rule’’ under 1. The authority citation for part 39 tkelley on DSK3SPTVN1PROD with PROPOSALS for practices, methods, and procedures the DOT Regulatory Policies and ■ the Administrator finds necessary for Procedures (44 FR 11034, February 26, continues to read as follows: safety in air commerce. This proposed 1979), Authority: 49 U.S.C. 106(g), 40113, 44701. regulation is within the scope of that (3) Will not affect intrastate aviation authority because it addresses an unsafe in Alaska, and § 39.13 [Amended] condition that is likely to exist or (4) Will not have a significant ■ 2. The FAA amends § 39.13 by adding develop on products identified in this economic impact, positive or negative, the following new airworthiness rulemaking action. on a substantial number of small entities directive (AD): VerDate Sep<11>2014 16:04 Feb 23, 2015 Jkt 235001 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 E:\FR\FM\24FEP1.SGM 24FEP1

Federal Register / Vol. 80, No. 36 / Tuesday, February 24, 2015 / Proposed Rules 9669 The Boeing Company: Docket No. FAA– paragraph, repair using a method approved method to be approved, the repair must meet 2015–0246; Directorate Identifier 2014– in accordance with the procedures specified the certification basis of the airplane, and the NM–187–AD. in paragraph (l) of this AD. approval must specifically refer to this AD. (4) Except as required by paragraph (i)(1) (a) Comments Due Date (i) Exceptions to the Service Information of this AD: If any service information We must receive comments by April 10, (1) Where Boeing Alert Service Bulletin contains steps that are identified as RC 2015. 737–53A1339, dated August 12, 2014, (Required for Compliance), those steps must specifies contacting Boeing for repair be done to comply with this AD; any steps (b) Affected ADs instructions: Before further flight, repair that are not identified as RC are None. using a method approved in accordance with recommended. Those steps that are not the procedures specified in paragraph (l) of identified as RC may be deviated from using (c) Applicability this AD. accepted methods in accordance with the This AD applies to The Boeing Company (2) Where Boeing Alert Service Bulletin operator’s maintenance or inspection Model 737–300, –400, and –500 series 737–53A1339, dated August 12, 2014, program without obtaining approval of an airplanes, certificated in any category, as specifies a compliance time ‘‘after the AMOC, provided the steps identified as RC identified in Boeing Alert Service Bulletin original issue date of this service bulletin,’’ can be done and the airplane can be put back 737–53A1339, dated August 12, 2014. this AD requires compliance within the in a serviceable condition. Any substitutions (d) Subject specified time after the effective date of this or changes to steps identified as RC require AD. approval of an AMOC. Air Transport Association (ATA) of America Code 53: Fuselage. (j) Optional Preventative Modification (m) Related Information (e) Unsafe Condition Modification of an inspection area (1) For more information about this AD, specified in paragraph (g) of this AD, contact Wayne Lockett, Aerospace Engineer, This AD was prompted by reports of including doing open hole and surface HFEC Airframe Branch, ANM–120S, FAA, Seattle fatigue cracking found at the left-side and inspections for cracking of the area to be right-side upper frame, at station 360 Aircraft Certification Office (ACO), 1601 Lind modified, in accordance with Part 4 of the Avenue SW., Renton, WA 98057–3356; between stringer 13 and stringer 14. We are Accomplishment Instructions of Boeing Alert issuing this AD to detect and correct fatigue phone: 425–917–6447; fax: 425–917–6590; Service Bulletin 737–53A1339, dated August email: wayne.lockett@faa.gov. cracking of the left-side and right-side upper 12, 2014, except as required by paragraph frame at station 360 between stringer 13 and (2) For service information identified in (i)(1) of this AD, terminates the repetitive this AD, contact Boeing Commercial stringer 14, which if not corrected, can grow inspections required by paragraph (g) of this in size and result in a severed frame, which Airplanes, Attention: Data & Services AD at the modified location only. Management, P. O. Box 3707, MC 2H–65, could lead to rapid decompression and reduced structural integrity of the airplane. (k) Post-Repair and Post-Modification Seattle, WA 98124–2207; telephone 206– Inspections 544–5000, extension 1; fax 206–766–5680; (f) Compliance Internet https://www.myboeingfleet.com. You The post-repair and post-modification Comply with this AD within the may view this referenced service information inspections specified in Tables 4 and 5 of compliance times specified, unless already at the FAA, Transport Airplane Directorate, paragraph 1.E., ‘‘Compliance,’’ of Boeing done. 1601 Lind Avenue SW., Renton, WA. For Alert Service Bulletin 737–53A1339, dated information on the availability of this (g) Repetitive Inspections for Cracking August 12, 2014, are not required by this AD. material at the FAA, call 425–227–1221. Note 1 to paragraph (k) of this AD: The At the applicable times specified in table post-repair and post-modification inspections Issued in Renton, Washington, on February 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing specified in Tables 4 and 5 of paragraph 1.E., 11, 2015. Alert Service Bulletin 737–53A1339, dated ‘‘Compliance,’’ of Boeing Alert Service August 12, 2014, except as required by Jeffrey E. Duven, Bulletin 737–53A1339, dated August 12, paragraph (i)(2) of this AD: Do a medium Manager, Transport Airplane Directorate, 2014, may be used in support of compliance frequency eddy current (MFEC) inspection Aircraft Certification Service. with section 121.1109(c)(2) or 129.109(b)(2) for cracking on the left-side and right-side of of the Federal Aviation Regulations (14 CFR [FR Doc. 2015–03677 Filed 2–23–15; 8:45 am] the upper frame at Station 360 between 121.1109(c)(2) or 14 CFR 129.109(b)(2)). BILLING CODE 4910–13–P stringer 13 and stringer 14, in accordance with Part 2 of the Accomplishment (l) Alternative Methods of Compliance Instructions of Boeing Alert Service Bulletin (AMOCs) 737–53A1339, dated August 12, 2014. If no (1) The Manager, Seattle Aircraft DEPARTMENT OF DEFENSE cracking is found, repeat the inspections at Certification Office (ACO), FAA, has the the applicable times specified in Table 1 of authority to approve AMOCs for this AD, if Office of the Secretary paragraph 1.E., ‘‘Compliance,’’ of Boeing requested using the procedures found in 14 Alert Service Bulletin 737–53A1339, dated CFR 39.19. In accordance with 14 CFR 39.19, 32 CFR Part 251 August 12, 2014. Accomplishment of the send your request to your principal inspector [Docket ID: DOD–2014–OS–0058] actions specified in paragraph (j) of this AD or local Flight Standards District Office, as terminates the repetitive inspections required appropriate. If sending information directly RIN 0790–AJ28 by this paragraph at the modified area only. to the manager of the ACO, send it to the attention of the person identified in National Language Service Corps (h) Repair paragraph (m)(1) of this AD. Information may (NLSC) If any cracking is found during any be emailed to: 9–ANM-Seattle-ACO-AMOC- inspection required by paragraph (g) of this Requests@faa.gov. AGENCY: Under Secretary of Defense for AD: Before further flight, repair the cracking (2) Before using any approved AMOC, Personnel and Readiness, DoD. including doing an open hole high frequency notify your appropriate principal inspector, ACTION: Proposed rule. eddy current (HFEC) inspection for cracking or lacking a principal inspector, the manager of the holes, in accordance with Part 3 of the of the local flight standards district office/ tkelley on DSK3SPTVN1PROD with PROPOSALS SUMMARY: This rule establishes in the Accomplishment Instructions of Boeing Alert certificate holding district office. Code of Federal Regulations the Service Bulletin 737–53A1339, dated August (3) An AMOC that provides an acceptable National Language Services Corps 12, 2014, except as required by paragraph level of safety may be used for any repair (i)(1) of this AD. Repair of any crack required by this AD if it is approved by (NLSC) by describing the program and terminates the repetitive inspection Boeing Commercial Airplanes Organization its responsibilities per the January 2013 requirements of paragraph (g) of this AD for Designation Authorization (ODA) that has National Defense Authorization Act the repaired area only. If any cracking is been authorized by the Manager, Seattle which authorized the Secretary of found during any inspection required by this ACO, to make those findings. For a repair Defense to establish the NLSC as a VerDate Sep<11>2014 16:04 Feb 23, 2015 Jkt 235001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 E:\FR\FM\24FEP1.SGM 24FEP1


Document Created: 2015-12-18 13:23:27
Document Modified: 2015-12-18 13:23:27
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionProposed Rules
ActionNotice of proposed rulemaking (NPRM).
DatesWe must receive comments on this proposed AD by April 10, 2015.
ContactWayne 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: [email protected]
FR Citation80 FR 9667 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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