[Federal Register Volume 76, Number 84 (Monday, May 2, 2011)]
[Rules and Regulations]
[Pages 24354-24356]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-9674]
[[Page 24354]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0026; Directorate Identifier 2010-NM-104-AD;
Amendment 39-16673; AD 2011-09-11]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 777-200 and -
300 Series Airplanes Equipped With Pratt and Whitney Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD 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;
and corrective action if necessary. This AD also provides an optional
terminating action for the inspections. 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 are issuing this AD 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 core, which can initiate an
engine fire, and lead to one or both fire conditions discussed above.
DATES: This AD is effective June 6, 2011.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of June 6, 2011.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail [email protected];
Internet https://www.myboeingfleet.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington. 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; 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 Document 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, Propulsion Branch, ANM-
140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; phone: 425-917-6501; fax:
425-917-6590; e-mail: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness directive (AD) that would apply to
the specified products. That NPRM published in the Federal Register on
January 20, 2011 (76 FR 3566). That NPRM proposed to require 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; and corrective action if necessary. That NPRM
also provided an optional terminating action for the inspections.
Comments
We gave the public the opportunity to participate in developing
this AD. We have considered the comment received. Boeing concurs with
the NPRM.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting the
AD as proposed.
Costs of Compliance
We estimate that this AD affects 53 airplanes of U.S. registry. We
also estimate that it takes about 48 work-hours per product to comply
with this AD. The average labor rate is $85 per work-hour. Required
parts cost about $122,617 per product. Based on these figures, we
estimate the cost of this AD to the U.S. operators to be $6,714,941, or
$122,697 per product.
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.
[[Page 24355]]
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):
2011-09-11 The Boeing Company: Amendment 39-16673; Docket No. FAA-
2011-0026; Directorate Identifier 2010-NM-104-AD.
Effective Date
(a) This AD is effective June 6, 2011.
Affected ADs
(b) None.
Applicability
(c) 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 1, dated November 4, 2010.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 54: Nacelles/Pylons.
Unsafe Condition
(e) This AD was prompted by reports of system disconnect boxes
that have been contaminated with hydraulic fluid, in which one case
a crack was found. We are issuing this AD 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 core, which can initiate an engine
fire and lead to one or both fire conditions discussed above.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Inspections and Corrective Actions
(g) Within 12 months after the effective date of this AD: 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.
(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.
(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; and repeat
the detailed inspection thereafter at intervals not to exceed 300
flight cycles.
(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.
(h) 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.
Optional Terminating Action
(i) 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, terminates the actions required
by this AD.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(j) Actions accomplished before the effective date of this AD
according to Boeing Alert Service Bulletin 777-54A0024, dated April
1, 2010, are considered acceptable for compliance with the
corresponding actions specified in this AD.
Alternative Methods of Compliance (AMOCs)
(k)(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 the Related Information
section of this AD. Information may be e-mailed 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.
Related Information
(l) For more information about this AD, contact Kevin Nguyen,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office (ACO), 1601 Lind Avenue, SW., Renton, Washington 98057-3356;
phone: 425-917-6501; fax: 425-917-6590; e-mail:
[email protected].
Material Incorporated by Reference
(m) You must use Boeing Service Bulletin 777-54A0024, Revision
1, dated November 4, 2010, to do the actions required by this AD,
unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; e-mail
[email protected]; Internet https://www.myboeingfleet.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
[[Page 24356]]
Issued in Renton, Washington, on April 12, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-9674 Filed 4-29-11; 8:45 am]
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