Document ID: FAA-2013-0704-0005
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2013-12-16T05:00Z

[Federal Register Volume 78, Number 241 (Monday, December 16, 2013)]
[Rules and Regulations]
[Pages 76047-76049]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-29051]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0704; Directorate Identifier 2013-NM-074-AD; 
Amendment 39-17695; AD 2013-24-18]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 747-200B, -200C, -200F, -300, and 747SR series 
airplanes. This AD was prompted by reports of cracks of both lower 
chords and web on certain outboard struts. This AD requires 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 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

[[Page 76048]]

consequent separation of a strut and engine from the airplane during 
flight.

DATES: This AD is effective January 21, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 21, 
2014.

ADDRESSES: 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, 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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Docket Management Facility, U.S. 
Department of Transportation, Docket Operations, M-30, West Building 
Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 
20590.

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: nathan.p.weigand@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to the specified products. The 
NPRM published in the Federal Register on August 28, 2013 (78 FR 
53078). The NPRM proposed to 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comment received. Boeing stated that it 
supports the NPRM (78 FR 53078, August 28, 2013).

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting the 
AD as proposed except for minor editorial changes. We have determined 
that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 53078, August 28, 2013) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 53078, August 28, 2013).

Costs of Compliance

    We estimate that this AD affects 25 airplanes of U.S. registry.
    We estimate the following costs to comply with this 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 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

    This AD will not have federalism implications under Executive Order 
13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under 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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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.

[[Page 76049]]

Sec.  39.13  [Amended]

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

2013-24-18 The Boeing Company: Amendment 39-17695; Docket No. FAA-
2013-0704; Directorate Identifier 2013-NM-074-AD.

(a) Effective Date

    This AD is effective January 21, 2014.

(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

    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

    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 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 paragraph (l) of this AD. Information may be 
emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO, to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.

(l) Related Information

    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: 
nathan.p.weigand@faa.gov.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Alert Service Bulletin 747-54A2237, dated March 14, 
2013.
    (ii) Reserved.
    (3) For Boeing 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.
    (4) You may view this service information at FAA, 1601 Lind 
Avenue SW., Renton, Washington. For information on the availability 
of this material at the FAA, call 425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on November 26, 2013.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-29051 Filed 12-13-13; 8:45 am]
BILLING CODE 4910-13-P