[Federal Register Volume 75, Number 241 (Thursday, December 16, 2010)]
[Rules and Regulations]
[Pages 78594-78596]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-31384]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0430; Directorate Identifier 2008-NM-148-AD; 
Amendment 39-16540; AD 2010-26-01]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 777-200 Series 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Model 777-200 series airplanes. This AD requires installing a new 
insulation blanket on the latch beam firewall of each thrust reverser 
(T/R) half. This AD results from an in-flight shutdown due to an engine 
fire indication; an under-cowl engine fire was extinguished after 
landing. The cause of the fire was uncontained failure of the starter 
in the engine core compartment; the fire progressed into the latch beam 
cavity and was fueled by oil from a damaged integrated drive generator 
oil line. We are issuing this AD to prevent a fire from entering the 
cowl or strut area, which could weaken T/R parts and result in reduced 
structural integrity of the T/R, possible separation of T/R parts 
during flight, and consequent damage to the airplane and injury to 
people or damage to property on the ground.

DATES: This AD is effective January 20, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of January 20, 
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.

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 (telephone 800-647-5527) is the 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: Margaret Langsted, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone 
(425) 917-6500; fax (425) 917-6590.

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 
certain Boeing Model 777-200 series airplanes. That NPRM was published 
in the Federal Register on May 7, 2009 (74 FR 21284). That NPRM 
proposed to require installing a new insulation blanket on the latch 
beam firewall of each thrust reverser (T/R) half.

Relevant Service Information

    Since we issued the NPRM, we have reviewed Boeing Alert Service 
Bulletin 777-78A0066, Revision 2, dated April 8, 2010. Boeing Service 
Bulletin 777-78A0066, Revision 1, dated March 12, 2009, was referred to 
in the original NPRM as the appropriate source of service information 
for accomplishing the proposed actions. No more work is necessary for 
airplanes on which Revision 1 of this service bulletin was used for 
doing the actions. Boeing Alert Service Bulletin 777-78A0066, Revision 
2, dated April 8, 2010, moves certain airplanes to Group 1, and 
contains minor editorial changes.
    We have revised paragraphs (c) and (g) of this AD to refer to 
Revision 2 of Boeing Alert Service Bulletin 777-78A0066, Revision 2, 
dated April 8, 2010, and paragraph (h) to add credit for accomplishing 
the specified actions in accordance with Boeing Service Bulletin 777-
78A0066, Revision 1, dated March 12, 2009.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received.

Request To Clarify Description of Unsafe Condition

    Boeing asked that we clarify the description of the unsafe 
condition by removing the words ``or strut'' from the identified 
description. Boeing stated that the unsafe condition, as currently 
written, is not correct. Boeing did not provide the reason that the 
description is not correct.
    We disagree that the description of the unsafe condition should be 
clarified by removing ``or strut'' from the description. A fire in the 
lower latch beam area that burns through an inadequate firewall may 
propagate into the strut. We have made no change to the AD in this 
regard.

Request To Clarify Applicability

    Japan Airlines International (JALI) asked for clarification of the 
applicability specified in the NPRM. JALI stated that the applicability 
specifies Model 777-200 series airplanes identified in Boeing Service 
Bulletin 777-78A0066, Revision 1, dated March 12, 2009. JALI noted that 
the service bulletin specifies its effectivity as delivered condition, 
and the proposed rule is considered to be applicable to each T/R half 
that has been installed on airplanes with the applicable serial 
numbers. JALI added that the T/R half is a replaceable line unit and 
the installed airplane and/or engine position will be changed from the 
delivered condition in the future; the T/R half that is not necessary 
for doing the requirements in the NPRM may be installed on an airplane 
identified in the applicability.
    JALI stated that, in light of these factors, it is not clear 
whether compliance with the specified actions has been met. JALI asked 
that we clarify the applicability either to note that the NPRM does not 
apply to airplanes on which a T/R is installed with a design change 
known as ``Commonality T/R,'' which is common to Model 777-300 series 
airplanes, or to change the

[[Page 78595]]

airplane serial numbers to T/R part numbers or serial numbers.
    We do not agree that the effectivity specified in Boeing Service 
Bulletin 777-78A0066, Revision 1, dated March 12, 2009, could apply to 
an airplane that has an incorrect T/R configuration because the T/R is 
a line replaceable unit and is not identified in the effectivity. The 
manufacturer has informed us that for airplanes not identified in 
Revision 1 or Revision 2 of this service bulletin, the specified T/R 
configuration is not an approved configuration. We have determined that 
it is not possible to install the T/R with the unsafe condition on 
airplanes that were manufactured after line number 413; therefore, the 
AD does not apply to those airplanes. We have made no change to the AD 
in this regard.

Request To Include Part Number and Compliance Status for T/R Halves

    JALI asked that we include the applicable part numbers of each T/R 
half and add a procedure in the NPRM to reidentify the parts as the 
part numbers change. JALI added that this change to the NPRM would 
include indicating the service bulletin number or adding a suffix to 
the serial number on the ID plate for each T/R so operators can easily 
track the applicable part number and compliance status for each T/R 
half. JALI noted that there is nothing identified in the service 
bulletin, and the only way for operators to identify the applicable 
part number and compliance status of each T/R half is by reviewing the 
maintenance record. JALI added that this would be burdensome for 
operators.
    We agree that the part numbers of each T/R half should be included 
in the service information and a procedure should be added to 
reidentify the parts as the part numbers change. Boeing Alert Service 
Bulletin 777-78A0066, Revision 2, dated April 8, 2010, includes the 
part marking provision. As stated previously, we have revised paragraph 
(c) of this AD (i.e., the AD applicability) to refer to Revision 2 of 
this service bulletin. Therefore, we have made no further change to the 
AD in this regard.

Explanation of Changes Made to This AD

    We have revised this AD to identify the legal name of the 
manufacturer as published in the most recent type certificate data 
sheet for the affected airplane models.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously. We also determined that 
these changes will not increase the economic burden on any operator or 
increase the scope of the AD.

Explanation of Change to Costs of Compliance

    Since issuance of the original NPRM, we have increased the labor 
rate used in the Costs of Compliance from $80 per work-hour to $85 per 
work-hour. The Costs of Compliance information, below, reflects this 
increase in the specified hourly labor rate.

Costs of Compliance

    We estimate that this AD affects 25 airplanes of U.S. registry. We 
also estimate that it will take about 7 work-hours per product to 
comply with this AD. The average labor rate is $85 per work-hour. 
Required parts will cost between $3,546 and $5,253 per product. Based 
on these figures, we estimate the cost of this AD to the U.S. operators 
to be between $103,525 and $146,200, or between $4,141 and $5,848 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), and
    (3) 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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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 AD:

2010-26-01 The Boeing Company: Amendment 39-16540. Docket No. FAA-
2009-0430; Directorate Identifier 2008-NM-148-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective January 20, 
2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to The Boeing Company Model 777-200 series 
airplanes, certificated in any category; as identified in Boeing 
Alert Service Bulletin 777-78A0066, Revision 2, dated April 8, 2010.

Unsafe Condition

    (d) This AD results from an in-flight shutdown due to an engine 
fire indication; an under-cowl engine fire was extinguished after 
landing. The cause of the fire was uncontained failure of the 
starter in the engine core compartment; the fire progressed into the 
latch beam cavity and was fueled by oil from a damaged integrated 
drive generator oil line. We are issuing this AD to prevent a fire 
from entering the cowl or strut area, which could weaken thrust 
reverser (T/R) parts and result in reduced structural integrity of 
the T/R, possible separation of T/R parts during flight, and 
consequent damage to the airplane and injury to people or damage to 
property on the ground.

[[Page 78596]]

Subject

    (e) Air Transport Association (ATA) of America Code 78: Exhaust.

Compliance

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

Installation of Insulation Blanket

    (g) Within 60 months or 4,500 flight cycles after the effective 
date of this AD, whichever is first: Install a new insulation 
blanket on the latch beam firewall of each T/R half by doing all the 
applicable actions specified in the Accomplishment Instructions of 
Boeing Alert Service Bulletin 777-78A0066, Revision 2, dated April 
8, 2010.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (h) Actions done before the effective date of this AD in 
accordance with Boeing Alert Service Bulletin 777-78A0066, dated 
June 5, 2008; or Boeing Service Bulletin 777-78A0066, Revision 1, 
dated March 12, 2009; are acceptable for compliance with the 
corresponding requirements of paragraph (g) of this AD.

Alternative Methods of Compliance (AMOCs)

    (i)(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. Send information to 
Attn: Margaret Langsted, Aerospace Engineer, Propulsion Branch, ANM-
140S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, Washington 
98057-3356; telephone (425) 917-6500; fax (425) 917-6590. Or, e-mail 
information to [email protected].
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.

Material Incorporated by Reference

    (j) You must use Boeing Alert Service Bulletin 777-78A0066, 
Revision 2, dated April 8, 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 NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on December 3, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-31384 Filed 12-15-10; 8:45 am]
BILLING CODE 4910-13-P