AD 2017-02-04

[Federal Register Volume 82, Number 24 (Tuesday, February 7, 2017)]
[Rules and Regulations]
[Pages 9489-9492]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2017-01341]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7261; Directorate Identifier 2016-NM-004-AD; 
Amendment 39-18783; AD 2017-02-04]
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, 747-300, 747-400, 747-400D, and 747-
400F series airplanes. This AD was prompted by a report of cracking in 
both the aluminum strut side skin, and corrosion resistant steel (CRES) 
outer spring beam support fitting. This AD requires inspections, 
related investigative and corrective actions, and a fastener 
installation modification. We are issuing this AD to address the unsafe 
condition on these products.

[[Page 9490]]


DATES: This AD is effective March 14, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 14, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Boeing Commercial Airplanes, Attention: Contractual & Data 
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 
90740-5600; telephone 562-797-1717; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
7261.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
7261; 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: Bill Ashforth, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6432; fax: 425-917-6590; email: <a href="/cdn-cgi/l/email-protection#eb89828787c58a98838d84999f83ab8d8a8ac58c849d"><span class="__cf_email__" data-cfemail="f193989d9ddf908299979e838599b1979090df969e87">[email&#160;protected]</span></a>.

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 certain The Boeing Company 
Model 747-200B, 747-300, 747-400, 747-400D, and 747-400F series 
airplanes. The NPRM published in the Federal Register on June 21, 2016 
(81 FR 40205). The NPRM was prompted by a report of cracking in both 
the aluminum strut side skin, and corrosion resistant steel (CRES) 
outer spring beam support fitting. The NPRM proposed to require 
repetitive high frequency eddy current (HFEC) inspections for cracking 
in the strut side skin, an open-hole HFEC inspection for cracking, 
applicable related investigative and corrective actions, and a fastener 
installation modification. We are issuing this AD to detect and correct 
cracking of the strut side skin and spring beam support fitting; such 
cracking could result in the failure of the outer spring beam support 
fitting, which could cause separation of a strut and engine from the 
airplane during flight.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Requests To Include Additional Clarification of Service Information

    Boeing, Delta Airlines (DAL), and KLM Royal Dutch Airlines (KLM) 
requested that we revise paragraphs (g), (h), and (i) of the proposed 
AD to include Boeing Service Bulletin Information Notice 747-54A2245 IN 
02, dated February 11, 2016; and Boeing Service Bulletin Information 
Notice 747-54A2245 IN 03, dated May 13, 2016. The commenters all 
mentioned that without the information contained in the requested 
information notices, the requirements of the proposed AD cannot be 
fully accomplished.
    We partially agree with the request to revise paragraphs (g), (h), 
and (i) of this AD to include new information that clarifies how to 
accomplish the required tasks specified in this AD. However, there is 
new service information that includes the same additional information. 
We have revised this AD to refer to Boeing Alert Service Bulletin 747-
54A2245, Revision 1, dated September 20, 2016, as the appropriate 
source of service information to use for the actions required by this 
AD. Boeing Alert Service Bulletin 747-54A2245, Revision 1, dated 
September 20, 2016, includes additional information discovered during 
validation of Boeing Alert Service Bulletin 747-54A2245, dated December 
18, 2015. Boeing Alert Service Bulletin 747-54A2245, Revision 1, dated 
September 20, 2016, clarifies the procedures for the fastener removal, 
drill ream, and spot facing steps, and provides additional access 
instructions, but does not include any new actions. Additionally, we 
have added a new paragraph (j) to this AD to give credit for actions 
performed before the effective date of this AD, using Boeing Alert 
Service Bulletin 747-54A2245, dated December 18, 2015. We have 
redesignated subsequent paragraphs accordingly.

Request To Clarify the Unsafe Condition Statement

    Boeing requested that we revise the unsafe condition statement by 
clarifying the location of the cracking. Boeing reported that cracking 
has been found not only in the strut side skin, but also in the spring 
beam support fitting.
    We agree with the request to clarify the unsafe condition 
statement. We have revised the Discussion section of this final rule, 
and paragraph (e) of this AD accordingly. The unsafe condition 
statement has been removed from the SUMMARY section of this final rule.

Request To Revise the Costs of Compliance

    Boeing requested that we revise the Costs of Compliance to reflect 
updated work-hours to do the inspection. Boeing specified that the 
hours necessary to do the inspection were re-evaluated to be 4 work-
hours, and the new information was disclosed in Boeing Service Bulletin 
Information Notice 747-54A2245 IN 01, dated December 23, 2015.
    We agree with the request, and have revised the Costs of Compliance 
section of this final rule to reflect the updated work-hours.

Request To Revise Compliance Time for Repetitive Inspections

    KLM requested that we revise the compliance time for the repetitive 
inspections from 500 flight cycles to 1,250 flight cycles. KLM pointed 
out that during the 747 Structures Task Group meetings organized to 
support strut modification, Boeing had established a design goal to 
tolerate one major load path failure and still meet regulatory 
requirements with a longer inspection interval. KLM also indicated that 
the time required for the repetitive inspections is a large burden.
    We disagree with the request to revise the compliance time for the 
repetitive inspections. In 1993, the Model 747 Structures Task Group 
did not foresee this level of damage occurring. Through damage 
tolerance analysis, the original equipment manufacturer (OEM) has 
determined that 500 flight cycles is the maximum number of flight 
cycles that provides an acceptable level of safety, and the FAA agrees 
with that analysis. Additionally, as discussed previously, the OEM has 
revised the time required to do the repetitive inspections from 291 
work-hours to 4 work-hours in the new service information referenced 
previously, reducing the burden to operators. We have not revised the

[[Page 9491]]

compliance time for the repetitive inspections; however, we have 
revised this AD to refer to the new service information referenced 
previously.

Request To Clarify How Certain Parts May Be Used for Terminating Action

    DAL requested clarification of the use of certain parts (fillers) 
for the terminating action required for all airplanes. DAL pointed out 
that certain parts are specifically named to include the airplane 
engine model (CF6-80C2), and that this could preclude the terminating 
action or lead to a non-compliant installation for airplanes with Pratt 
& Whitney (PW) 4000 engines installed.
    We agree with the request for clarification because it should make 
this AD easier to interpret. We have revised paragraph (h) of this AD 
to specify that part numbers 321U2400-5600, 321U2400-5601, and 
321U2400-5602 may be used for airplanes with General Electric CF6-80 
engines and PW4000 engines.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-54A2245, Revision 1, 
dated September 20, 2016. The service information describes procedures 
for repetitive HFEC inspections for cracking in the strut side skin, an 
open-hole HFEC inspection for cracking, applicable related 
investigative and corrective actions, and a fastener installation 
modification. 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.

Costs of Compliance

    We estimate that this AD affects 320 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
----------------------------------------------------------------------------------------------------------------
Inspection.......................  4 work-hours x $85               $0  $340 per inspection  $108,800 per
                                    per hour = $340                      cycle.               inspection cycle.
                                    per inspection
                                    cycle.
Modification.....................  Up to 490 work-              56,414  Up to $98,064......  Up to $31,380,480.
                                    hours x $85 per
                                    hour = $41,650.
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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.


Sec.  39.13  [Amended]

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

2017-02-04 The Boeing Company: Amendment 39-18783; Docket No. FAA-
2016-7261; Directorate Identifier 2016-NM-004-AD.

(a) Effective Date

    This AD is effective March 14, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-200B, 747-300, 
747-400, 747-400D, and 747-400F series airplanes, certificated in 
any category, equipped with General Electric (GE) CF6-80 series 
engines or Pratt & Whitney PW4000 series engines; as identified in 
Boeing Alert Service Bulletin 747-54A2245, Revision 1, dated 
September 20, 2016.

(d) Subject

    Air Transport Association (ATA) of America Code 54; Nacelles/
pylons.

(e) Unsafe Condition

    This AD was prompted by a report of cracking in both the 
aluminum strut side skin, and corrosion resistant steel (CRES) outer 
spring beam support fitting. We are issuing this AD to detect and 
correct cracking of the strut side skin and spring beam support 
fitting; such cracking could result in

[[Page 9492]]

the failure of the outer spring beam support fitting, which could 
cause 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) Repetitive Inspections

    Except as provided by paragraphs (i)(1) and (i)(2) of this AD, 
at the applicable compliance time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-54A2245, 
Revision 1, dated September 20, 2016, do a surface high frequency 
eddy current (HFEC) inspection for cracking of the strut side skin, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-54A2245, Revision 1, dated September 20, 2016, 
except as required by paragraph (i)(3) of this AD. Repeat the 
inspection thereafter at the applicable times specified in paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-54A2245, 
Revision 1, dated September 20, 2016, until the actions required by 
paragraph (h) of this AD are done. If any cracking is found, do the 
actions specified in paragraph (h) of this AD before further flight.

(h) Terminating Actions

    Within the applicable compliance time specified in paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-54A2245, 
Revision 1, dated September 20, 2016, except as provided by 
paragraphs (i)(1) and (i)(2) of this AD: Do a fastener hole open-
hole HFEC inspection for cracking, applicable related investigative 
and corrective actions, and a fastener installation modification, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-54A2245, Revision 1, dated September 20, 2016, 
except as required by paragraph (i)(3) of this AD. Do all applicable 
related investigative and corrective actions before further flight. 
Part numbers 321U2400-5600, 321U2400-5601, and 321U2400-5602 may be 
used for modification of airplanes with GE CF6-80 engines and PW4000 
engines. Doing the actions required by this paragraph terminates the 
repetitive inspections required by paragraph (g) of this AD.

(i) Exceptions to Service Information

    (1) Where Boeing Alert Service Bulletin 747-54A2245, Revision 1, 
dated September 20, 2016, specifies a compliance time ``after the 
original issue date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (2) The Condition column in table 1 and table 2 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-54A2245, 
Revision 1, dated September 20, 2016, refers to total flight cycles 
``at the original issue date of this service bulletin.'' This AD, 
however, applies to the airplanes with the specified total flight 
cycles as of the effective date of this AD.
    (3) Although Boeing Alert Service Bulletin 747-54A2245, Revision 
1, dated September 20, 2016, specifies to contact Boeing for repair 
instructions, and specifies that action as ``RC'' (Required for 
Compliance), this AD requires repair before further flight using a 
method approved in accordance with the procedures specified in 
paragraph (k) of this AD.

(j) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD, using Boeing Alert Service 
Bulletin 747-54A2245, dated December 18, 2015.

(k) 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 (l)(1) of this AD. 
Information may be emailed to: <a href="/cdn-cgi/l/email-protection#536a7e121d1e7e00363227273f367e12101c7e121e1c107e0136222636202720133532327d343c25"><span class="__cf_email__" data-cfemail="162f3b57585b3b45737762627a733b5755593b575b59553b44736763736562655670777738717960">[email&#160;protected]</span></a>.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Seattle ACO, to make those findings. To be approved, the 
repair method, modification deviation, or alteration deviation must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) Except as required by paragraph (i)(3) of this AD, for 
service information that contains steps that are labeled as Required 
for Compliance (RC), the provisions of paragraphs (k)(4)(i) and 
(k)(4)(ii) of this AD 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.

(l) Related Information

    (1) For more information about this AD, contact Bill Ashforth, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6432; 
fax: 425-917-6590; email: <a href="/cdn-cgi/l/email-protection#15777c79793b74667d737a67617d557374743b727a63"><span class="__cf_email__" data-cfemail="086a61646426697b606e677a7c60486e6969266f677e">[email&#160;protected]</span></a>.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(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 747-54A2245, Revision 1, dated 
September 20, 2016.
    (ii) Reserved.
    (3) For Boeing service information identified in this AD, 
contact Boeing Commercial Airplanes, Attention: Contractual & Data 
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 
90740-5600; telephone 562-797-1717; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
    (4) You may view this 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.
    (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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on January 12, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-01341 Filed 2-6-17; 8:45 am]
 BILLING CODE 4910-13-P