[Federal Register Volume 77, Number 234 (Wednesday, December 5, 2012)]
[Rules and Regulations]
[Pages 72200-72203]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-29405]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1220; Directorate Identifier 2012-NM-208-AD;
Amendment 39-17277; AD 2012-24-07]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: We are adopting a new airworthiness directive (AD) for certain
The Boeing Company Model 787-8 airplanes. This AD requires ensuring
that lockwire is installed correctly on the engine fuel feed manifold
couplings. This AD also requires inspecting the assembly of the engine
fuel feed manifold rigid and full flexible couplings. This AD was
prompted by reports of fuel leaks due to improperly assembled engine
fuel feed manifold couplings. We are issuing this AD to detect and
correct improperly assembled couplings, which could result in fuel
leaks and consequent fuel exhaustion, engine power loss or shutdown, or
leaks on hot engine parts that could lead to a fire.
DATES: This AD is effective December 5, 2012.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of December 5,
2012.
We must receive comments on this AD by January 22, 2013.
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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
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 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 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: Sherry Vevea, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6514; fax: 425-917-6590; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We have received reports of fuel leaks on two different in-service
airplanes, and the subsequent discovery of several improperly assembled
engine fuel feed manifold couplings on in-service and production
airplanes. The improper coupling installations, which occurred during
production, have included couplings with missing or improperly
installed lockwire, parts within the couplings installed in the wrong
locations, incorrect parts installed in the couplings, and couplings
that have extra parts installed. These conditions, if not corrected,
could result in fuel leaks, which could lead to fuel exhaustion, engine
power loss or shutdown, or leaks on hot engine parts that could lead to
a fire.
[[Page 72201]]
Relevant Service Information
We reviewed Boeing Multi Operator Message MOM-MOM-12-0838-01B(R2),
including Attachment A, dated November 25, 2012. For information on the
procedures and compliance times, see this service information at http://www.regulations.gov by searching for Docket No. FAA-2012-1220.
FAA's Determination
We are issuing 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.
AD Requirements
This AD requires accomplishing the actions specified in the service
information described previously, except as discussed under
``Differences Between the AD and the Service Information.''
The phrase ``related investigative actions'' might be used in this
AD. ``Related investigative actions'' are follow-on actions that (1)
are related to the primary actions, and (2) further investigate the
nature of any condition found. Related investigative actions in an AD
could include, for example, inspections.
In addition, the phrase ``corrective actions'' might be used in
this AD. ``Corrective actions'' are actions that correct or address any
condition found. Corrective actions in an AD could include, for
example, repairs.
Differences Between the AD and the Service Information
For engine fuel feed manifold couplings that have not been
previously inspected, Boeing Multi Operator Message MOM-MOM-12-0838-
01B(R2), including Attachment A, dated November 25, 2012, recommends
accomplishment of all actions specified in Action 1) within 7 days.
This AD, however, requires only that operators ensure the correct
lockwire installation within 7 days; the compliance time for the
remaining actions is 21 days. We have determined that the additional
time for the remaining actions is warranted, based on the assurance
that the lockwire is installed correctly.
In addition, for engine fuel feed manifold full flexible couplings
that have been previously inspected, Boeing Multi Operator Message MOM-
MOM-12-0838-01B(R2), including Attachment A, dated November 25, 2012,
specifies that operators do not need to re-inspect these couplings if
review of the airplane maintenance records conclusively demonstrates
that the corresponding actions are equivalent to steps 1 through 6 of
Action 1) of Boeing Multi Operator Message MOM-MOM-12-0838-01B(R2),
including Attachment A, dated November 25, 2012. We have determined
that the potential for not identifying incorrect parts during prior
inspection of the full flexible coupling warrants re-inspecting these
couplings; this AD therefore requires inspection of these full flexible
couplings.
These differences have been coordinated with Boeing.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
improperly assembled engine fuel feed manifold couplings could result
in fuel leaks and consequent fuel exhaustion, engine power loss or
shutdown, or leaks on hot engine parts that could lead to a fire.
Therefore, we find that notice and opportunity for prior public comment
are impracticable and that good cause exists for making this amendment
effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send any written data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include the docket number FAA-2012-1220 and
Directorate Identifier 2012-NM-208-AD at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this AD. We will
consider all comments received by the closing date and may amend this
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 AD.
Costs of Compliance
We estimate that this AD affects 3 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
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Coupling inspection, o[dash]ring 10 work-hours x $85 per $54 $904 $2,712
replacement, retainer ring hour = $850.
installation, blade seal
inspection, and lockwire
installation.
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We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
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
[[Page 72202]]
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 adding the following new airworthiness
directive (AD):
2012-24-07 The Boeing Company: Amendment 39-17277; Docket No. FAA-
2012-1220; Directorate Identifier 2012-NM-208-AD.
(a) Effective Date
This AD is effective December 5, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 787-8 airplanes,
certificated in any category, serial numbers 34485, 34486, 34488,
34490, 34493, 34494, 34497, 34502, 34506 through 34508 inclusive,
34514, 34515, 34521, 34744 through 34747 inclusive, 34822, 34824,
34829, 34832, 34834 through 34838 inclusive, 35938, 36276 through
36278 inclusive, 38319, 38320, 38330, 38466, 38471, 40748, and
40899.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 28, Fuel.
(e) Unsafe Condition
This AD was prompted by reports of fuel leaks due to improperly
assembled engine fuel feed manifold couplings. We are issuing this
AD to detect and correct improperly assembled couplings, which could
result in fuel leaks and consequent fuel exhaustion, engine power
loss or shutdown, or leaks on hot engine parts that could lead to a
fire.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection
Except as provided by paragraph (h) of this AD: Do the actions
specified in paragraphs (g)(1) and (g)(2) of this AD, in accordance
with Action 1) of Boeing Multi Operator Message MOM-MOM-12-0838-
01B(R2), including Attachment A, dated November 25, 2012.
(1) Within 7 days after the effective date of this AD, ensure
that the lockwire installation on the rigid and full flexible
couplings is correct.
(2) Within 21 days after the effective date of this AD, inspect
the rigid and full flexible couplings for correct assembly,
including replacement of the o-rings with new o-rings, confirmation
that the proper retainer rings are installed in the full flexible
coupling, a general visual inspection for damage of the blade seals,
and all applicable corrective actions. Do all applicable corrective
actions before further flight.
(h) Requirements Based on Previous Accomplishment
(1) For airplanes on which the fuel couplings have been
inspected before the effective date of this AD as specified in
``Method 1: AMM Method'' of Boeing Multi Operator Message MOM-MOM-
12-0838-01B, dated November 11, 2012, which is not incorporated by
reference in this AD; or Boeing Multi Operator Message MOM-MOM-12-
0838-01B(R1), dated November 14, 2012, which is not incorporated by
reference in this AD: A review of the airplane maintenance records
is acceptable for compliance with the requirements of paragraph
(g)(1) of this AD, if the records conclusively demonstrate that
lockwire was installed correctly using a method equivalent to step
6.a. of Action 1) of Boeing Multi Operator Message MOM-MOM-12-0838-
01B(R2), including Attachment A, dated November 25, 2012.
(2) For airplanes on which the fuel couplings have been
inspected before the effective date of this AD as specified in
``Method 2: Non-Invasive Method'' of Boeing Multi Operator Message
MOM-MOM-12-0838-01B, dated November 11, 2012, which is not
incorporated by reference in this AD; or Boeing Multi Operator
Message MOM-MOM-12-0838-01B(R1), dated November 14, 2012, which is
not incorporated by reference in this AD: The actions specified in
paragraph (g)(1) of this AD are not required.
(3) For airplanes on which the rigid fuel couplings have been
inspected before the effective date of this AD as specified in
``Method 1: AMM Method'' or ``Method 2: Non-Invasive Method'' of
Boeing Multi Operator Message MOM-MOM-12-0838-01B, dated November
11, 2012, which is not incorporated by reference in this AD; or
Boeing Multi Operator Message MOM-MOM-12-0838-01B(R1), dated
November 14, 2012, which is not incorporated by reference in this
AD: The actions specified in paragraph (g)(2) of this AD are not
required for the rigid fuel couplings only. However, the actions
specified in paragraph (g)(2) of this AD are required for the full
flexible couplings, even if inspected prior to the effective date of
this AD as specified in Boeing Multi Operator Message MOM-MOM-12-
0838-01B, dated November 11, 2012, which is not incorporated by
reference in this AD; or Boeing Multi Operator Message MOM-MOM-12-
0838-01B(R1), dated November 14, 2012, which is not incorporated by
reference in this AD.
(i) No Reporting Requirement
Boeing Multi Operator Message MOM-MOM-12-0838-01B(R2), including
Attachment A, dated November 25, 2012, specifies reporting to Boeing
any anomalies found during inspection of the assembly of the rigid
and full flexible couplings, including anomalies of the lockwire
installation. This AD does not require any report.
(j) Special Flight Permit
Special flight permits may be issued in accordance with sections
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199) to operate the airplane to a location where the airplane
can be modified, provided the lockwire is correctly installed on the
engine fuel feed manifold rigid and full flexible couplings in
accordance with paragraph (g)(1) of this AD.
(k) 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 the Related Information
section of this AD. Information may be emailed 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.
(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.
(l) Related Information
(1) For more information about this AD, contact Sherry Vevea,
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA
98057-3356; phone: 425-917-6514; fax: 425-917-6590; email:
[email protected].
[[Page 72203]]
(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 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.
(m) 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.
(i) Boeing Multi Operator Message MOM-MOM-12-0838-01B(R2),
including Attachment A, dated November 25, 2012. The document number
and issue date are identified on page 1 of Boeing Multi Operator
Message MOM-MOM-12-0838-01B(R2), including Attachment A, dated
November 25, 2012, and on each page of Attachment A; no other page
of this document contains this information.
(ii) Reserved.
(3) 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.
(4) You may view this service information at 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.
(5) 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 November 28, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-29405 Filed 12-4-12; 8:45 am]
BILLING CODE 4910-13-P