[Federal Register Volume 78, Number 167 (Wednesday, August 28, 2013)]
[Proposed Rules]
[Pages 53078-53080]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-20969]


 ========================================================================
 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. 78, No. 167 / Wednesday, August 28, 2013 / 
Proposed Rules  

[[Page 53078]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0704; Directorate Identifier 2013-NM-074-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 747-200B, -200C, -200F, -300, and 
747SR series airplanes. This proposed AD was prompted by reports of 
cracks of both lower chords and web on certain outboard struts. This 
proposed AD would require repetitive inspections for cracking of the 
lower spar chords and web, web lower spar chord modification, which 
includes inspections for cracking of the lower spar chords, and 
repetitive post modification inspections for cracking of the lower spar 
web and chord; and applicable corrective actions. We are proposing this 
AD to prevent cracked chords and web on certain outboard struts, which, 
if the chord severs, could result in reduced structural integrity of 
the diagonal brace load path and of the strut-to-wing attachment, and 
consequent separation of a strut and engine from the airplane during 
flight.

DATES: We must receive comments on this proposed AD by October 15, 
2013.

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 review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at the 
FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; 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-2013-0704; 
Directorate Identifier 2013-NM-074-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 cracks at nacelle station 300 on both lower 
chords and the web on outboard strut no. 1. Outboard strut no. 1 had 
approximately 41,300 total flight cycles and 63,300 total flight hours. 
The cracking was due to fatigue from normal operating loads. The chords 
are the main load path for the diagonal brace attach fitting. Cracked 
and severed chords and web on certain outboard struts could result in 
reduced structural integrity of the diagonal brace load path, and 
compromise the strut-to-wing attachment, which could result in 
consequent separation of a strut and engine from the airplane during 
flight.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 747-54A2237, dated March 
14, 2013. For information on the procedures and compliance times, see 
this service information at http://www.regulations.gov by searching for 
Docket No. FAA-2013-0704.

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 these 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 the Proposed AD and the Service 
Information.''
    The phrase ``corrective actions'' is used in this proposed AD. 
``Corrective actions'' are actions that correct or address any 
condition found. Corrective actions in an AD could include, for 
example, repairs.

[[Page 53079]]

Differences Between the Proposed AD and the Service Information

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

Costs of Compliance

    We estimate that this proposed AD affects 25 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....................  27 work-hours x $85 per              $0  $2,295 per          $57,375 per
                                  hour = $2,295 per                        inspection cycle.   inspection cycle.
                                  inspection cycle.
Modification...................  11 work-hours x $85 per              95  1,030.............  25,750.
                                  hour = $935.
Post Modification Inspection...  27 work-hours x $85 per               0  2,295 per           $57,375 per
                                  hour = $2,295 per                        inspection cycle.   inspection cycle.
                                  inspection cycle.
----------------------------------------------------------------------------------------------------------------

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

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2013-0704; Directorate Identifier 
2013-NM-074-AD.

(a) Comments Due Date

    We must receive comments by October 15, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-200B, 747-200C, 
747-200F, 747-300, and 747SR series airplanes, certificated in any 
category, as identified in Boeing Alert Service Bulletin 747-
54A2237, dated March 14, 2013.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 54, Nacelles/Pylons.

(e) Unsafe Condition

    This AD was prompted by reports of cracks of both lower chords 
and web on certain outboard struts. We are issuing this AD to 
prevent cracked chords and web on certain outboard struts, which, if 
the chord severs, could result in reduced structural integrity of 
the diagonal brace load path and of the strut-to-wing attachment, 
and consequent separation of a strut and engine from the airplane 
during flight.

(f) Compliance

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

(g) Initial and Repetitive Inspections

    (1) Except as required by paragraph (j)(1) of this AD, at the 
compliance time specified in table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-54A2237, dated 
March 14, 2013: Do a detailed inspection for cracking of the lower 
spar chords and web, a high frequency eddy current (HFEC) inspection 
for cracking of the lower spar chords, and all applicable repairs 
and modifications, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-54A2237, dated 
March 14, 2013, except as required by paragraph (j)(2) of this AD. 
If no cracking is found, repeat the inspections thereafter at 
intervals not to exceed 600 flight cycles, until the actions 
specified in paragraph (h) of this AD have been accomplished. Do all 
applicable corrective actions before further flight. Accomplishing a 
repair and modification, including open-hole HFEC inspections for 
cracking and applicable corrective actions required by this 
paragraph terminates the actions required by paragraphs (g) and (h) 
of this AD for the repaired and modified strut only. The open-hole 
HFEC inspection for cracking must be done before the modification.

(h) Inspection and Modification

    Except as required by paragraph (j)(1) of this AD, at the 
compliance time specified in

[[Page 53080]]

paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-54A2237, dated March 14, 2013: Do a detailed inspection for 
cracking of the lower spar chords and web, an HFEC inspection for 
cracking of the lower spar chords, a lower spar chord modification, 
including open-hole HFEC inspections for cracking in the chord and 
all applicable corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
54A2237, dated March 14, 2013, except as required by paragraph 
(j)(2) of this AD. Do all applicable corrective actions before 
further flight. Doing the actions specified in this paragraph 
terminates the requirements of paragraph (g) of this AD for the 
modified strut only. The open-hole HFEC inspection for cracking must 
be done before the modification.

(i) Post Modification Repetitive Inspections

    For airplanes on which a modification required by paragraph (g) 
or (h) of this AD has been done: At the compliance time specified in 
table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-54A2237, dated March 14, 2013, do a detailed inspection 
for any cracking of the lower spar web and chord, and do all 
applicable corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-54A2237, dated 
March 14, 2013, except as required by paragraph (j)(2) of this AD. 
Repeat the inspection thereafter at intervals not to exceed 18 
months. Do all applicable corrective actions before further flight.

(j) Exceptions

    (1) Where Boeing Alert Service Bulletin 747-54A2237, dated March 
14, 2013, specifies a compliance time after the original issue date 
on the service bulletin, this AD requires compliance within the 
specified compliance time after the effective date of this AD.
    (2) Where Boeing Alert Service Bulletin 747-54A2237, dated March 
14, 2013, specifies to contact Boeing for appropriate action: Before 
further flight, repair the crack using a method approved in 
accordance with the procedures specified in paragraph (k) of this 
AD.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office, 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 the Related Information section 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 the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO, to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.

(l) Related Information

    (1) For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6428; 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 review copies of the referenced 
service information at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue SW., Renton, Washington. For information on the 
availability of this material at the FAA, call 425-227-1221.


    Issued in Renton, Washington, on August 21, 2013.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-20969 Filed 8-27-13; 8:45 am]
BILLING CODE 4910-13-P