Document ID: FAA-2014-0580-0006
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2015-01-22T05:00Z

[Federal Register Volume 80, Number 14 (Thursday, January 22, 2015)]
[Rules and Regulations]
[Pages 3158-3161]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-00009]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0580; Directorate Identifier 2014-NM-081-AD; 
Amendment 39-18062; AD 2015-01-01]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 2011-09-11, 
for certain The Boeing Company Model 777-200 and -300 series airplanes. 
AD 2011-09-11 required 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. This new AD adds, 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. This 
AD was prompted by 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.

DATES: This AD is effective February 26, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 26, 
2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of June 6, 
2011 (76 FR 24354, May 2, 2011).

ADDRESSES: For service information identified in this AD, contact 
Boeing

[[Page 3159]]

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.govby 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 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: 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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2011-09-11, Amendment 39-16673 (76 FR 24354, 
May 2, 2011). AD 2011-09-11 applied to The Boeing Company Model 777-200 
and - 300 series airplanes equipped with Pratt and Whitney engines. The 
NPRM published in the Federal Register on August 26, 2014 (79 FR 
50877).

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comments received. United Airlines and 
Boeing supported the NPRM (79 FR 50877, August 26, 2014).

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this 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 (79 FR 50877, August 26, 2014) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 50877, August 26, 2014).

Costs of Compliance

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspections [retained actions from   18 work-hours x $85 per                  $0          $1,530         $82,620
 AD 2011-09-11, Amendment 39-16673    hour = $1,530.
 (76 FR 24354, May 2, 2011)].
Inspection of cover plate fasteners  8 work-hours x $85 per hour               0             680          36,720
 [new action].                        = $680.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs/
replacements that will be required based on the results of the 
inspections. We have no way of determining the number of aircraft that 
might need these repairs/replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement [retained actions from AD 2011-  35 work-hours x $85 per hour =             $420,440        $423,415
 09-11, Amendment 39-16673 (76 FR 24354,      $2,975.
 May 2, 2011)].
Inspection of electrical components and      14 work-hours x $85 per hour =                  458           1,648
 installation of new fasteners [new           $1,190.
 actions].
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this 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

[[Page 3160]]

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

2015-01-01 The Boeing Company: Amendment 39-18062; Docket No. FAA-
2014-0580; Directorate Identifier 2014-NM-081-AD.

(a) Effective Date

    This AD is effective February 26, 2015.

(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 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 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,

[[Page 3161]]

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) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(5) and (n)(6) of this AD.

(n) 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.
    (3) The following service information was approved for IBR on 
February 26, 2015.
    (i) Boeing Service Bulletin 777-54A0024, Revision 2, dated 
January 23, 2014.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
June 6, 2011 (76 FR 24354, May 2, 2011).
    (i) Boeing Service Bulletin 777-54A0024, Revision 1, dated 
November 4, 2010.
    (ii) Reserved.
    (5) 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.
    (6) You may view this service information at 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.
    (7) 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 December 22, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-00009 Filed 1-21-15; 8:45 am]
BILLING CODE 4910-13-P