Document ID: FAA-2015-5809-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2015-11-20T05:00Z

[Federal Register Volume 80, Number 224 (Friday, November 20, 2015)]
[Proposed Rules]
[Pages 72621-72624]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-29617]

[[Page 72621]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-5809; Directorate Identifier 2015-NM-055-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 supersede Airworthiness Directive (AD) 2006-19-
12, which applies to certain The Boeing Model 777-200 and -300 series 
airplanes. AD 2006-19-12 currently requires inspecting the lower web of 
the aft fairing of the engine struts for any discoloration and doing 
any related investigative and corrective action if necessary; 
inspecting the heat shield castings for any damage and doing any 
corrective action if necessary; installing gap cover strips; and 
replacing insulation blankets with new insulation blankets. Since we 
issued AD 2006-19-12, we have received a report that an aft fairing 
lower spar web exceeded the allowable conductivity limits. This 
proposed AD would also require, depending on airplane configuration, 
one-time or repetitive detailed inspections for cracking and 
deformation, as applicable, of the aft fairing lower structure, and 
one-time or repetitive conductivity inspections of the aft fairing 
lower structure and related investigative and corrective actions if 
necessary. This proposed AD also adds airplanes to the applicability. 
We are proposing this AD to detect and correct degradation of the aft 
fairing lower web, which could lead to cracking of the web and could 
allow flammable fluids to leak into the heat shield pan castings, and 
consequent increased risk of an uncontained fire and subsequent 
structural damage.

DATES: We must receive comments on this proposed AD by January 4, 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.
    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. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-5809.

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-2015-
5809; 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: Sue Lucier, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917-
6438; fax: 425-917-6590; email: suzanne.lucier@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 ADDRESSES section. Include ``Docket No. FAA-2015-5809; 
Directorate Identifier 2015-NM-055-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 September 13, 2006, we issued AD 2006-19-12, Amendment 39-14769 
(71 FR 55727, September 25, 2006), for certain Boeing Model 777-200 and 
-300 series airplanes. AD 2006-19-12 requires inspecting the lower web 
of the aft fairing of engine struts for any discoloration and doing any 
related investigative and corrective action if necessary; inspecting 
the heat shield castings for any damage and doing any corrective action 
if necessary; installing gap cover strips; and replacing insulation 
blankets with new insulation blankets. AD 2006-19-12 resulted from a 
report that several discolored fairing lower webs and some damaged/
deteriorated insulation blankets were found in the aft fairings of 
engine struts. We issued AD 2006-19-12 to prevent cracking of lower 
webs of the aft fairings, which could result in flammable hydraulic 
fluid leaking onto or near an ignition source, and possibly result in 
an uncontrollable fire in the engine strut area.

Actions Since AD 2006-19-12, Amendment 39-14769 (71 FR 55727, September 
25, 2006) Was Issued

    Since we issued AD 2006-19-12, Amendment 39-14769 (71 FR 55727, 
September 25, 2006), we have received a report that an aft fairing 
lower spar web exceeded the allowable conductivity limits. An 
investigation concluded that wear to the pan casting and gap cover 
strips allowed increased heat into the aft fairing heat shield cavity, 
which exceeded the thermal capability of the insulation blankets.

Related Service Information Under 1 CFR Part 51

    We have reviewed Boeing Service Bulletin 777-54-0026, Revision 2, 
dated January 5, 2012. The service information describes procedures for 
a detailed inspection of the gap cover strips and heat shield pan 
castings for damage, corrective actions, and installation of new gap 
cover strip fillers, new velcro strips, and new aft fairing insulation 
blankets.
    We reviewed Boeing Special Attention Service Bulletin 777-54-0038, 
dated March 6, 2015. The service information describes procedures for 
one-time and repetitive detailed inspections for any cracking and 
deformation, as applicable, of the aft fairing lower structure; 
conductivity

[[Page 72622]]

inspections of the aft fairing lower structure; and related 
investigative and corrective actions.
    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 of this 
NPRM.

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 2006-19-12, 
Amendment 39-14769 (71 FR 55727, September 25, 2006). In addition, this 
proposed AD would add airplanes to the applicability of this AD. This 
proposed AD would also require accomplishing the actions specified in 
the service information described previously.
    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'' are actions that correct or address any 
condition found. Corrective actions in an AD could include, for 
example, repairs.

Change to AD 2006-19-12, Amendment 39-14769 (71 FR 55727, September 25, 
2006)

    Since AD 2006-19-12, Amendment 39-14769 (71 FR 55727, September 25, 
2006) was issued, the AD format has been revised, and certain 
paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have been redesignated in this proposed AD, as 
listed in the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                     Corresponding  requirement in this
   Requirement in AD 2006-19-12                  proposed AD
------------------------------------------------------------------------
 paragraph (f)                       paragraph (g)
 paragraph (g)                       paragraph (h)
 paragraph (h)                       paragraph (i)
------------------------------------------------------------------------

Costs of Compliance

    We estimate that this proposed AD affects 99 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 and other actions      Up to 11 work-      Up to $16,179,      Up to $17,114,      Up to $1,694,286,
 [retained actions from AD 2006-   hours x $85 per     depending on        depending on        depending on
 19[dash]12, Amendment 39-14769    hour = $935,        airplane            airplane            airplane
 (71 FR 55727, September 25,       depending on        configuration.      configuration.      configuration
 2006)].                           airplane
                                   configuration.
Inspections [new proposed         Up to 24            $0................  Up to $2,040,       Up to $201,960,
 action].                          work[dash]hours x                       depending on        depending on
                                   $85 per hour =                          airplane            airplane
                                   $2,040, depending                       configuration.      configuration
                                   on airplane
                                   configuration.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary related 
investigative and corrective actions that would be required based on 
the results of the proposed inspection. We have no way of determining 
the number of aircraft that might need these inspections and 
replacements:

                                               On-Condition costs
----------------------------------------------------------------------------------------------------------------
                 Action                           Labor cost            Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Related Investigative Actions...........  Up to 36 work[dash]hours x              $0  Up to $3,060, depending on
                                           $85 per hour = $3,060,                      airplane configuration
                                           depending on airplane
                                           configuration.
Corrective Actions......................  Up to 38 work[dash]hours x               0  Up to $3,230, depending on
                                           $85 per hour = $3,230,                      airplane configuration
                                           depending on airplane
                                           configuration.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, all 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 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.

[[Page 72623]]

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) 
2006-19-12, Amendment 39-14769 (71 FR 55727, September 25, 2006), and 
adding the following new AD:

The Boeing Company: Docket No. FAA-2015-5809; Directorate Identifier 
2015-NM-055-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by January 4, 
2016.

(b) Affected ADs

    This AD replaces AD 2006-19-12, Amendment 39-14769 (71 FR 55727, 
September 25, 2006).

(c) Applicability

    This AD applies to The Boeing Company Model 777-200, -200LR, -
300, -300ER, and 777F series airplanes, certified in any category, 
as identified in Boeing Special Attention Service Bulletin 777-54-
0038, dated March 6, 2015.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report that an aft fairing lower spar 
web exceeded the allowable conductivity limits. An investigation 
concluded that wear to the pan casting and gap cover strips allowed 
increased heat into the aft fairing heat shield cavity. We are 
proposing this AD to detect and correct degradation of the aft 
fairing lower web, which could lead to cracking of the web and could 
allow flammable fluids to leak into the heat shield pan castings, 
and consequent increased risk of an uncontained fire and subsequent 
structural damage.

(f) Compliance

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

(g) Retained Inspection, Installation, and Replacement Actions With No 
Changes

    This paragraph restates the actions required by paragraph (f) of 
AD 2006-19-12, Amendment 39-14769 (71 FR 55727, September 25, 2006), 
with no changes. For Model 777-200 and -300 series airplanes 
identified in Boeing Special Attention Service Bulletin 777-54-0021, 
Revision 1, dated March 16, 2006: Except as provided by paragraph 
(h) of this AD, within 12 months after October 30, 2006 (the 
effective date of AD 2006-19-12), do the actions specified in 
paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD, in 
accordance with the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 777-54-0021, Revision 1, dated March 16, 
2006.
    (1) Do a general visual inspection of the lower web of the aft 
fairing for any discoloration and do any related investigative 
action.
    (2) Do a general visual inspection of the heat shield castings 
for any damage (crack(s), dent(s), gouge(s), warpage, fretting, or 
missing/loose nutplates).
    (3) Install gap cover strips on the heat shield pans.
    (4) Replace insulation blankets on the heat shield pans with new 
insulation blankets.

(h) Retained Repair Instructions

    This paragraph restates the actions required by paragraph (g) of 
AD 2006-19-12, Amendment 39-14769 (71 FR 55727, September 25, 2006), 
with no changes. If any damage, discoloration, heat damage, or crack 
is found during any inspection required by paragraph (g) of this AD: 
Before further flight, do all applicable corrective actions in 
accordance with a method approved by the Manager, Seattle Aircraft 
Certification Office (ACO), FAA, or in accordance with the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 777-54-0021, Revision 1, dated March 16, 2006.

(i) Retained Credit for Previous Actions With Revised Format

    This paragraph restates the credit provided by paragraph (h) of 
AD 2006-19-12, Amendment 39-14769 (71 FR 55727, September 25, 2006), 
with revised format. This paragraph provides credit for actions 
required by paragraph (g) of this AD, if those actions were 
performed before October 30, 2006 (the effective date of AD 2006-19-
12, Amendment 39-14769 (71 FR 55727, September 25, 2006)) using 
Boeing Special Attention Service Bulletin 777-54-0021, dated June 
23, 2005, except where Boeing Special Attention Service Bulletin 
777-54-0021, dated June 23, 2005, does not provide an International 
Annealed Copper Standard (IACS) value for determining the results of 
the inspection for heat damage, the maximum acceptable IACS value is 
42 percent. Boeing Special Attention Service Bulletin 777-54-0021, 
dated June 23, 2005, is not incorporated by reference in this AD.

(j) New Requirements: Detailed and Conductivity Inspections and Related 
Investigative and Corrective Actions (Repetitive Inspections for 
Certain Airplanes)

    Within 24 months after the effective date of this AD: Do 
detailed and conductivity inspections of the aft fairing lower 
structure for cracks and deformation, as applicable, and do all 
applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 777-54-0038, dated March 6, 2015. Do all 
applicable related investigative and corrective actions before 
further flight. For Group 1, Configurations 1 and 3 airplanes, and 
Group 2, Configuration 1, airplanes, identified in Boeing Special 
Attention Service Bulletin 777-54-0038, dated March 6, 2015, repeat 
the inspections thereafter at intervals not to exceed 24 months 
until the terminating action specified in paragraph (k) of this AD 
is done.

(k) Optional Terminating Action

    Accomplishing a detailed inspection of the gap cover strips and 
heat shield pan castings for damage and applicable corrective 
actions, and installation of new gap cover strip fillers, new velcro 
strips, and new aft fairing insulation blankets, in accordance with 
the Accomplishment Instructions of Boeing Service Bulletin 777-54-
0026, Revision 2, dated January 5, 2012, concurrently with 
accomplishing detailed and conductivity inspections and all 
applicable related investigative and corrective actions required by 
paragraph (j) of this AD, terminates the repetitive inspections 
specified in paragraph (j) of this AD; except where Boeing Service 
Bulletin 777-54-0026, Revision 2, dated January 5, 2012, specifies 
to contact the manufacturer, repair using a method approved in 
accordance with the procedures specified in paragraph (l) of 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

[[Page 72624]]

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 airplane, and the approval must 
specifically refer to this AD.
    (4) AMOCs approved for AD 2006-19-12, Amendment 39-14769 (71 FR 
55727, September 25, 2006) are approved as AMOCs for the 
corresponding provisions of paragraphs (g), (h), and (i) of this AD.

(m) Related Information

    (1) For more information about this AD, contact Sue Lucier, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917-
6438; fax: 425-917-6590; email: suzanne.lucier@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 November 12, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-29617 Filed 11-19-15; 8:45 am]
BILLING CODE 4910-13-P