81 FR 40205 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 119 (June 21, 2016)

We propose to adopt 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 proposed 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 proposed AD would 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 proposing this AD to detect and correct cracking of the strut side skin; 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.

[Federal Register Volume 81, Number 119 (Tuesday, June 21, 2016)]
[Proposed Rules]
[Pages 40205-40208]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-14293]


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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]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 747-200B, 747-300, 747-400, 747-400D, 
and 747-400F series airplanes. This proposed 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 proposed 
AD would 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 
proposing this AD to detect and correct cracking of the strut side 
skin; 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.

DATES: We must receive comments on this proposed AD by August 5, 2016.

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.

[[Page 40206]]

    For service information identified in this NPRM, contact Boeing 
Commercial Airplanes, Attention: Data & Services Management, P.O. Box 
3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, 
extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. 
You may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2016-7261.

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-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 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 
(ACO), 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-2016-7261; 
Directorate Identifier 2016-NM-004-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We have received a report indicating cracking in both the aluminum 
strut side skin, and CRES outer spring beam support fitting. This 
condition, if not corrected, 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.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-54A2245, dated 
December 18, 2015. The service information describes procedures for 
repetitive high 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.

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.'' For information on the procedures and compliance times, 
see this service information at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2016-7261.
    The phrase ``related investigative actions'' is used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that (1) are related to the primary action, and (2) further investigate 
the nature of any condition found. Related investigative actions in an 
AD could include, for example, inspections.
    The phrase ``corrective actions'' is used in this proposed AD. 
``Corrective actions'' correct or address any condition found. 
Corrective actions in an AD could include, for example, repairs.

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin 747-54A2245, dated December 18, 2015, 
specifies to contact the manufacturer for certain instructions, but 
this proposed AD would require accomplishment of repair methods, 
modification deviations, and alteration deviations 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 320 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
----------------------------------------------------------------------------------------------------------------
Inspection...............  291 work-hours x $85 per               $0  $24,735 per           $7,915,200 per
                            hour = $24,735 per                         inspection cycle.     inspection cycle.
                            inspection cycle.
Modification.............  Up to 490 work-hours x             56,414  Up to $98,064.......  Up to $31,380,480.
                            $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,

[[Page 40207]]

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-2016-7261; Directorate Identifier 
2016-NM-004-AD.

(a) Comments Due Date

    We must receive comments by August 5, 2016.

(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, dated December 18, 2015.

(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; 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.

(f) Compliance

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

(g) Repetitive Inspections

    Except as provided by paragraph (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, dated 
December 18, 2015, 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, dated December 18, 2015, 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, dated December 18, 2015, 
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.

(h) Terminating Actions

    Within the applicable compliance time specified in paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-54A2245, 
dated December 18, 2015, 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, dated December 18, 2015, except as required by paragraph 
(i)(3) of this AD. Do all applicable related investigative and 
corrective actions before further flight. 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, dated 
December 18, 2015, 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, 
dated December 18, 2015, 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, dated 
December 18, 2015, 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 (j) of this AD.

(j) 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 (k)(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, 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 (j)(4)(i) and 
(j)(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

[[Page 40208]]

still be done as specified, and the airplane can be put back in an 
airworthy condition.

(k) Related Information

    (1) For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 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 view this referenced service 
information at the FAA, 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 June 3, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-14293 Filed 6-20-16; 8:45 am]
BILLING CODE 4910-13-P