Document ID: FAA-2014-0580-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2014-08-26T04:00Z

[Federal Register Volume 79, Number 165 (Tuesday, August 26, 2014)]
[Proposed Rules]
[Pages 50877-50880]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-20221]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0580; Directorate Identifier 2014-NM-081-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 supersede Airworthiness Directive (AD) 2011-09-
11, which applies to certain The Boeing Company Model 777-200 and -300 
series airplanes. AD 2011-09-11 currently requires repetitive 
inspections for hydraulic fluid contamination of the interior of the 
strut disconnect assembly; repetitive inspections for discrepancies of 
the interior of the strut disconnect assembly, if necessary; repetitive 
inspections of the exterior of the strut disconnect assembly for 
cracks, if necessary; corrective action if necessary; and an optional 
terminating action for the inspections. Since we issued AD 2011-09-11, 
we have received reports of side and top cover plates installed with 
missing fastener bolts, which results in an unsealed opening on the 
system disconnect assembly. This proposed AD would add, for certain 
airplanes, an inspection of the side and top cover plates to determine 
if all cover plate attach fasteners have been installed, and installing 
any missing fasteners including doing an inspection for damage, and 
repair if necessary. We are proposing this AD to detect and correct 
hydraulic fluid contamination, which can cause cracking of titanium 
parts in the system disconnect assembly; and also to detect and correct 
missing fasteners, which results in unsealed openings on the system 
disconnect assembly. Both unsafe conditions can compromise the engine 
firewall and result in fire hazards for both the engine compartment and 
the strut.

DATES: We must receive comments on this proposed AD by October 10, 
2014.

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, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. 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 by searching for and locating Docket No. FAA-2014-
0580; 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: Kevin Nguyen, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6501; fax: 425-917-6590; email: kevin.nguyen@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the

[[Page 50878]]

ADDRESSES section. Include ``Docket No. FAA-2014-0580; Directorate 
Identifier 2014-NM-081-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

    On April 12, 2011, we issued AD 2011-09-11, Amendment 39-16673 (76 
FR 24354, May 2, 2011), for The Boeing Company Model 777-200 and -300 
series airplanes equipped with Pratt and Whitney engines. AD 2011-09-11 
requires repetitive inspections for hydraulic fluid contamination of 
the interior of the strut disconnect assembly; repetitive inspections 
for discrepancies of the interior of the strut disconnect assembly, if 
necessary; repetitive inspections of the exterior of the strut 
disconnect assembly for cracks, if necessary; corrective action if 
necessary; and an optional terminating action for the inspections. AD 
2011-09-11 resulted from reports of system disconnect boxes 
contaminated with hydraulic fluid, which led to subsequent cracking of 
titanium parts in the system disconnect assembly. We issued AD 2011-09-
11 to detect and correct hydraulic fluid contamination, which can cause 
cracking of titanium parts in the system disconnect assembly, resulting 
in compromise of the engine firewall. A cracked firewall can allow fire 
in the engine area to enter the strut and can lead to an uncontained 
engine strut fire if flammable fluid is present. Cracking of the 
disconnect box may also reduce the effectiveness of the fire 
extinguishing system in the engine compartment and could contribute to 
an uncontained engine fire. In addition, a cracked disconnect box can 
leak flammable fluids into the engine compartment, which can initiate 
an engine fire, and lead to one or both fire conditions discussed 
above.

Actions Since AD 2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 
2011) Was Issued

    Since we issued AD 2011-09-11, Amendment 39-16673 (76 FR 24354, May 
2, 2011), we have received reports of side and top cover plates 
installed with two fastener bolts on airplanes on which a replacement 
of the titanium system disconnect assembly was accomplished in 
accordance with AD 2011-09-11. An operator reported that the side and 
top cover plates were only temporarily installed with two fasteners for 
each cover plate; additional bolts were not in the kits, and the 
service bulletin did not provide instructions to install the remaining 
bolts. Missing fasteners will allow for fastener holes on the cover 
plates to be not closed off, and cover plates to be loose and not 
sealed tightly against the disconnect box assembly, resulting in 
compromise of the engine firewall. This compromise of the engine 
firewall can lead to a fire breach and hazardous effects that have the 
same effects as the disconnect box with cracks. In addition, loose 
cover plates on the electrical side of the disconnect box, and 
vibration from the airplane and engine can cause damage to the 
electrical connectors and wire routing into, through, and out of the 
disconnect box. Damaged electrical connectors or wires can cause 
unwanted engine indication and crew alerting system (EICAS) messages or 
non-responsive action by the crew when there are actual EICAS messages. 
Damaged electrical connectors or wires can create an ignition source 
for flammable fluids and result in an uncontained strut fire or fuel 
explosion.

Relevant Service Information

    We reviewed Boeing Service Bulletin 777-54A0024, Revision 2, dated 
January 23, 2014. 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-2014-0580.

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 retain all requirements of AD 2011-09-11, 
Amendment 39-16673 (76 FR 24354, May 2, 2011). This proposed AD would 
add, for certain airplanes, an inspection of the side and top cover 
plates to determine if all cover plate attach fasteners have been 
installed, and installing any missing fasteners including doing an 
inspection for damage, and repair if necessary.

Costs of Compliance

    We estimate that this proposed AD affects 54 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspections [retained actions from AD   18 work-hours x $85 per               $0          $1,530         $82,620
 2011-09-11, Amendment 39-16673 (76 FR   hour = $1,530.
 24354, May 2, 2011)].
Inspection of cover plate fasteners     8 work-hours x $85 per                 0             680          36,720
 [new proposed action].                  hour = $680.
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    We estimate the following costs to do any necessary repairs/
replacements that would be required based on the results of the 
proposed inspections. We have no way of determining the number of 
aircraft that might need these repairs/replacements:

[[Page 50879]]

                                               On-Condition Costs
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                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
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Replacement [retained actions from AD 2011-09-  35 work-hours x $85 per hour =          $420,440        $423,415
 11, Amendment 39-16673 (76 FR 24354, May 2,     $2,975.
 2011)].
Inspection of electrical components and         14 work-hours x $85 per hour =               458           1,648
 installation of new fasteners [new proposed     $1,190.
 actions].
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    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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 have 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 that the 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 removing Airworthiness Directive (AD) 
2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011), and adding 
the following new AD:

The Boeing Company: Docket No. FAA-2014-0580; Directorate Identifier 
2014-NM-081-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by October 10, 
2014.

(b) Affected ADs

    This AD replaces AD 2011-09-11, Amendment 39-16673 (76 FR 24354, 
May 2, 2011).

(c) Applicability

    This AD applies to The Boeing Company Model 777-200 and -300 
series airplanes, certificated in any category; equipped with Pratt 
and Whitney engines; as identified in Boeing Service Bulletin 777-
54A0024, Revision 2, dated January 23, 2014.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
Pylons.

(e) Unsafe Condition

    This AD was prompted by reports of system disconnect boxes that 
have been contaminated with hydraulic fluid and, in one incident, 
led to subsequent cracking of titanium parts in the system 
disconnect assembly. We have received reports of side and top cover 
plates installed with missing fastener bolts, which results in an 
unsealed opening on the system disconnect assembly. We are issuing 
this AD to detect and correct hydraulic fluid contamination, which 
can cause cracking of titanium parts in the system disconnect 
assembly; and also to detect and correct missing fasteners, which 
results in unsealed openings on the system disconnect assembly. Both 
unsafe conditions can compromise the engine firewall and result in 
fire hazards for both the engine compartment and the strut.

(f) Compliance

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

(g) Retained Inspections and Corrective Actions With Revised Service 
Information

    This paragraph restates the requirements of paragraph (g) of AD 
2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011), with 
revised service information. Within 12 months after June 6, 2011 
(the effective date of AD 2011-09-11): Do a general visual 
inspection for hydraulic fluid contamination of the interior of the 
strut disconnect assembly, in accordance with Part 1 of the 
Accomplishment Instructions of Boeing Service Bulletin 777-54A0024, 
Revision 1, dated November 4, 2010; or Revision 2, dated January 23, 
2014. As of the effective date of this AD, use only Boeing Service 
Bulletin 777-54A0024, Revision 2, dated January 23, 2014, for 
accomplishing the actions in this paragraph.
    (1) For airplanes on which no hydraulic fluid contamination is 
found (Condition 1): Repeat the general visual inspection required 
by paragraph (g) of this AD thereafter at intervals not to exceed 
6,000 flight cycles or 750 days, whichever occurs first.
    (2) For airplanes on which hydraulic fluid contamination is 
found (Condition 2): Before further flight, do a detailed inspection 
for discrepancies (e.g., hydraulic fluid coking, heat discoloration, 
cracks, and etching or pitting) of the interior of the strut 
disconnect assembly, in accordance with Part 2 of the Accomplishment 
Instructions of Boeing Service Bulletin 777-54A0024, Revision 1, 
dated November 4, 2010; or Revision 2, dated January 23, 2014. As of 
the effective date of this AD, use only Boeing Service Bulletin 777-
54A0024, Revision 2, dated January 23, 2014, for accomplishing the 
actions in this paragraph.
    (i) For airplanes on which no discrepancy is found during the 
inspection required by paragraph (g)(2) of this AD (Condition 2A): 
Repeat the detailed inspection required by paragraph (g)(2) of this 
AD thereafter at

[[Page 50880]]

intervals not to exceed 6,000 flight cycles or 750 days, whichever 
occurs first.
    (ii) For airplanes on which hydraulic fluid coking or heat 
discoloration is found but no cracking, etching, or pitting is found 
during the inspection required by paragraph (g)(2) of this AD 
(Condition 2B): Do the actions required by paragraph (g)(2)(ii)(A) 
and (g)(2)(ii)(B) of this AD.
    (A) Within 300 flight cycles after doing the inspection required 
by paragraph (g)(2) of this AD: Do a detailed inspection of the 
exterior of the strut disconnect assembly for cracks, in accordance 
with Part 3 of the Accomplishment Instructions of Boeing Service 
Bulletin 777-54A0024, Revision 1, dated November 4, 2010; or 
Revision 2, dated January 23, 2014; and repeat the detailed 
inspection thereafter at intervals not to exceed 300 flight cycles. 
As of the effective date of this AD, use only Boeing Service 
Bulletin 777-54A0024, Revision 2, dated January 23, 2014, for 
accomplishing the actions in this paragraph.
    (B) Within 6,000 flight cycles or 750 days after hydraulic fluid 
coking and/or heat discoloration was found during the inspection 
required by paragraph (g)(2) of this AD, whichever occurs first: 
Replace the titanium system disconnect assembly with an Inconel 
system, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Service Bulletin 777-54A0024, Revision 1, dated November 
4, 2010; or Revision 2, dated January 23, 2014. As of the effective 
date of this AD, use only Boeing Service Bulletin 777-54A0024, 
Revision 2, dated January 23, 2014, for accomplishing the actions in 
this paragraph.

(h) Retained Corrective Action With Revised Service Information

    This paragraph restates the requirements of paragraph (h) of AD 
2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011), with 
revised service information. For airplanes on which any crack, 
etching, or pitting is found during any inspection required by 
paragraph (g)(2) or (g)(2)(ii)(A) of this AD (Condition 3): Before 
further flight, replace the titanium system disconnect assembly with 
an Inconel system, in accordance with Part 4 of the Accomplishment 
Instructions of Boeing Service Bulletin 777-54A0024, Revision 1, 
dated November 4, 2010; or Revision 2, dated January 23, 2014. As of 
the effective date of this AD, use only Boeing Service Bulletin 777-
54A0024, Revision 2, dated January 23, 2014, for accomplishing the 
actions in this paragraph.

(i) Retained Optional Terminating Action With Revised Service 
Information

    This paragraph restates the requirements of paragraph (i) of AD 
2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011), with 
revised service information. Replacing the titanium system 
disconnect assembly with an Inconel system disconnect assembly in 
accordance with Part 4 of the Accomplishment Instructions of Boeing 
Service Bulletin 777-54A0024, Revision 1, dated November 4, 2010; or 
Revision 2, dated January 23, 2014; terminates the actions required 
by paragraphs (g) and (h) of this AD. As of the effective date of 
this AD, use only Boeing Service Bulletin 777-54A0024, Revision 2, 
dated January 23, 2014, for accomplishing the actions in this 
paragraph.

(j) New Inspection and Corrective Action

    For airplanes on which the system disconnect assembly has been 
replaced in accordance with Part 4 of the Accomplishment 
Instructions of Boeing Service Bulletin 777-54A0024, dated April 1, 
2010; or Revision 1, dated November 4, 2010: Within 1,125 days after 
the effective date of this AD, do a detailed inspection of the cover 
plate fasteners to determine if all cover plate attach fasteners are 
installed, in accordance with Part 5 of the Accomplishment 
Instructions of Boeing Service Bulletin 777-54A0024, Revision 2, 
dated January 23, 2014. If any fastener is missing, before further 
flight, install fasteners (including doing a detailed inspection for 
damage of the electrical components and repairing any damaged 
components), in accordance with Part 6 of the Accomplishment 
Instructions of Boeing Service Bulletin 777-54A0024, Revision 2, 
dated January 23, 2014.

(k) Credit for Previous Actions

    This paragraph restates the credit provided by paragraph (j) of 
AD 2011-09-11, Amendment 39-16673 (76 FR 24354, May 2, 2011). This 
paragraph provides credit for the corresponding actions required by 
paragraphs (g), (h), and (i) of this AD, if those actions were 
performed before June 6, 2011 (the effective date of AD 2011-09-11) 
using Boeing Service Bulletin 777-54A0024, dated April 1, 2010, 
which is not incorporated by reference in this AD.

(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: 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.

(m) Related Information

    (1) For more information about this AD, contact Kevin Nguyen, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle 
Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, 
WA 98057-3356; phone: 425-917-6501; fax: 425-917-6590; email: 
kevin.nguyen@faa.gov.
    (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 August 15, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-20221 Filed 8-25-14; 8:45 am]
BILLING CODE 4910-13-P