Airworthiness Directives; Boeing Model 727 Airplanes, 28594-28597 [E7-9799]
Download as PDF
28594
Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations
List of Subjects in 14 CFR Part 39
Actions and Compliance
(f) Unless already done, do the following
actions:
(1) Within the next 100 hours time-inservice or 3 months, whichever occurs first
after the effective date of this AD, and
thereafter repetitively during a period not to
exceed 12 months, inspect the aileron
brackets and bearings and perform the
lubrication of the aileron bearings in
accordance with Reims Aviation Industries
Service Bulletin No. F406–59, dated October
24, 2005.
(2) If corrosion is found during any
inspection required in paragraph (f)(1) of this
AD, before further flight, replace the
damaged parts in accordance with Reims
Aviation Industries Service Bulletin No.
F406–59, dated October 24, 2005.
Note 1: We established the repetitive
inspection times of this AD so that they may
coincide with annual inspections.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Note 2: We encourage you to put Reims
temporary revision No. 6 into the
maintenance program of the F406 airplane
(chapter 5 of the maintenance manual).
Adoption of the Amendment
FAA AD Differences
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
Note 3: This AD differs from the MCAI
and/or service information as follows: We
added repetitive inspection requirements in
this AD to coincide with the maintenance
requirement in the service bulletin.
PART 39—AIRWORTHINESS
DIRECTIVES
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Staff,
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: Mike Kiesov, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4144; fax: (816) 329–
4090. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD Docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.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 the
NPRM, the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Office (telephone (800) 647–
5227) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
I
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2007–11–04 Reims Aviation S.A.:
Amendment 39–15061; Docket No.
FAA–2007–26973; Directorate Identifier
2007–CE–002–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective June 26, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model F406
airplanes, serial numbers F406–0001 through
F406–0092, certificated in any category.
cprice-sewell on PRODPC61 with RULES
Subject
(d) Air Transport Association of America
(ATA) Code 57: Wings.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
This AD is issued following reports, on
several aircraft, of important corrosion found
on the ailerons bearings.
This condition, if left uncorrected, could
result in the loss of the roll control on the
airplane.
VerDate Aug<31>2005
15:01 May 21, 2007
Jkt 211001
Related Information
´ ´
(h) Refer to Direction generale de l’aviation
civile AD No. F–2005–177, dated November
9, 2005; and Reims Aviation Industries
Service Bulletin No. F406–59, dated October
24, 2005, for related information.
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
Material Incorporated by Reference
(i) You must use Reims Aviation Industries
Service Bulletin No. F406–59, dated October
24, 2005, 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 Reims Aviation Industries,
´
Aerodrome de Reims Prunay, 51360 Prunay,
A l’attention du Support Client; telephone:
+33 (0)3.26.48.46.53; fax: +33
(0)3.26.49.18.57.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City,
Missouri 64106; or 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: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on May
11, 2007.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–9618 Filed 5–21–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28254; Directorate
Identifier 2007–NM–054–AD; Amendment
39–15065; AD 2007–11–08]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 727 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
that applies to all Boeing Model 727
airplanes. The existing AD requires a
boost pump dry bay inspection to detect
leakage of fuel through an arced-through
conduit, and corrective action as
necessary. The existing AD also requires
repetitive inspections of the in-tank fuel
boost pump wiring to detect chafing of
the wire insulation, evidence of
electrical arcing, or arc-through of the
conduit wall, and applicable corrective
action; and installation of sleeving over
the in-tank fuel boost pump wires as a
method to protect the wiring from
chafing. This new AD removes certain
inspection requirements from the
E:\FR\FM\22MYR1.SGM
22MYR1
cprice-sewell on PRODPC61 with RULES
Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations
existing AD. This new AD adds new
repetitive inspections for damage of the
electrical wire and sleeve that run to the
fuel boost pump through a conduit in
the fuel tank, and arcing damage of the
conduit and signs of fuel leakage into
the conduit; applicable investigative
and corrective actions; and a new
repetitive engine fuel suction feed
operational test. Initiation of the new
inspections terminates the requirements
of the existing AD. This AD results from
reports of a fuel tank explosion on a
Model 727–200F airplane on the
ground; and of chafed wires and a
damaged power cable sleeve of a fuel
boost pump that were discovered during
an inspection required by an existing
AD on a Model 737–300 airplane. We
are issuing this AD to detect and correct
chafing of the fuel boost pump electrical
wiring and leakage of fuel into the
conduit, and to prevent electrical arcing
between the wiring and the surrounding
conduit, which could result in arcthrough of the conduit, and consequent
fire or explosion of the fuel tank.
DATES: This AD becomes effective June
6, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of June 6, 2007.
On June 28, 1999 (64 FR 33394, June
23, 1999), the Director of the Federal
Register approved the incorporation by
reference of Boeing Alert Service
Bulletin 727–28A0126, dated May 24,
1999.
We must receive any comments on
this AD by July 23, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
You may examine the contents of the
AD docket on the Internet at https://
VerDate Aug<31>2005
15:01 May 21, 2007
Jkt 211001
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Room PL–401, Washington, DC.
This docket number is FAA–2007–
28254; the directorate identifier for this
docket is 2007–NM–054-AD.
FOR FURTHER INFORMATION CONTACT:
Suzanne Lucier, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6438; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
On June 15, 1999, we issued AD 99–
12–52, amendment 39–11199 (64 FR
33394, June 23, 1999) (originally issued
on May 24, 1999, as telegraphic AD
T99–12–52). That AD applies to all
Boeing Model 727 series airplanes. That
AD requires a boost pump dry bay
inspection to detect leakage of fuel
through an arced-through conduit, and
corrective action, as necessary. That AD
also requires repetitive detailed
inspections of the in-tank fuel boost
pump wiring to detect chafing of the
wire insulation, evidence of electrical
arcing, or arc-through of the conduit
wall on Model 727 series airplanes, and
applicable corrective action; and
installation of sleeving over the in-tank
fuel boost pump wires as a method to
protect the wiring from chafing. That
AD resulted from reports of severe wear
of in-tank fuel boost pump wiring, and
arc-through of the surrounding conduit
on two Model 727 series airplanes. The
actions specified in that AD are
intended to prevent fuel tank explosion
resulting from arc-through of the fuel
boost pump wiring conduits.
Actions Since AD Was Issued
Since we issued that AD, we received
a report that a fuel tank explosion
occurred on a Model 727–200F airplane
on the ground. Investigation revealed
evidence of arcing in the metal conduit
that carries power wires from the front
spar through the fuel tank to the dry bay
of the #1 aft fuel boost pump. In a
separate incident, we received a report
from Boeing that chafed power wires
and a damaged power cable sleeve of a
fuel boost pump were discovered during
an inspection required by AD 99–12–52
on a Model 737–300 series airplane.
That inspection was done at 21,000
flight hours rather than the repetitive
interval of 30,000 flight hours specified
by that AD. The fuel boost pump
installation on certain Model 737
airplanes is almost identical to the
installation on Model 727 airplanes.
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
28595
Other Relevant Rulemaking
Operators should note that we are
considering issuing a separate AD to
address the identified unsafe condition
as it relates to Model 737 airplanes.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 727–28A0132, dated
February 22, 2007. The alert service
bulletin describes procedures for doing
new repetitive detailed inspections for
damage of the electrical wire and sleeve
that run to the fuel boost pump through
a conduit in the fuel tank, and for arcing
damage of, and signs of fuel leakage
into, the conduit; doing a new engine
fuel suction feed operational test; doing
related investigative and corrective
actions, as applicable; and sending
inspection results and damaged parts to
the manufacturer. Related investigative
and corrective actions include replacing
the wire sleeve with a new, smaller wire
sleeve; replacing, with BMS 13–
60T09C03G018 wire, any wire that is
damaged or has any part number other
than BMS 13–60T09C03G018 or BMS
13–60T12C03G018; doing leak testing of
the conduit if signs of fuel are
discovered on the wire or sleeve during
any inspection; and repairing any
damaged conduit or replacing it with a
new conduit.
AD 99–12–52 refers to Boeing Alert
Service Bulletin 727–28A0126, dated
May 24, 1999, as the appropriate source
of service information for
accomplishment of the detailed
inspection and related investigative/
corrective actions; that requirement is
new paragraph (i) in this AD. That
service bulletin has since been revised.
Revision 1, dated May 18, 2000, is
essentially the same as the original and
provides no new actions.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other airplanes of the same type
design. For this reason, we are issuing
this AD to supersede AD 99–12–52. This
new AD retains certain requirements of
the existing AD. This AD also requires
accomplishing the actions specified in
the alert service bulletin described
previously, which, when initiated,
terminates certain requirements.
Explanation of Changes Made to
Existing AD
We have revised the applicability of
the existing AD to identify model
designations as published in the most
recent type certificate data sheet for the
affected models.
E:\FR\FM\22MYR1.SGM
22MYR1
28596
Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations
The FAA has changed all references
to a ‘‘detailed visual inspection’’ in the
existing AD to ‘‘detailed inspection’’ in
this action.
Interim Action
We consider this AD interim action. If
final action is later identified, we might
consider further rulemaking then.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD; therefore, providing notice and
opportunity for public comment before
the AD is issued is impracticable, and
good cause exists to make this AD
effective in less than 30 days.
cprice-sewell on PRODPC61 with RULES
Comments Invited
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
relevant written data, views, or
arguments regarding this AD. Send your
comments to an address listed in the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–28254; Directorate Identifier
2007–NM–054–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD that might suggest a
need to modify it. We will post all
comments we receive, without change,
to https://dms.dot.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of that Web site, anyone
can find and read the comments in any
of our dockets, including the name of
the individual who sent the comment
(or signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
VerDate Aug<31>2005
15:01 May 21, 2007
Jkt 211001
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
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 the 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); 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. We prepared a
regulatory evaluation of the estimated
costs to comply with this AD and placed
it in the AD docket. See the ADDRESSES
section for a location to examine the
regulatory evaluation.
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 part 39 of the Federal
Aviation Regulations (14 CFR part 39) as
follows:
I
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–11199 (64
FR 33394, June 23, 1999) and adding the
following new airworthiness directive
(AD):
I
2007–11–08 Boeing: Docket No. FAA–2007–
28254; Directorate Identifier 2007–NM–
054–AD; Amendment 39–15065.
Effective Date
(a) This AD becomes effective June 6, 2007.
Affected ADs
(b) This AD supersedes AD 99–12–52.
Applicability
(c) This AD applies to all Boeing Model
727, 727C, 727–100, 727 –100C, 727–200,
and 727–200F series airplanes, certificated in
any category.
Unsafe Condition
(d) This AD results from reports of a fuel
tank explosion on a Model 727–200F
airplane on the ground, and chafed wires and
a damaged power cable sleeve of a fuel boost
pump that were discovered during an
inspection required by an existing AD on a
Model 737–300 airplane, which has a fuel
boost pump installation that is almost
identical to the installation on Model 727
airplanes. We are issuing this AD to detect
and correct chafing of the fuel boost pump
electrical wiring and leakage of fuel into the
conduit, and to prevent electrical arcing
between the wiring and the surrounding
conduit, which could result in arc-through of
the conduit, and consequent fire or explosion
of the fuel tank.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Certain Requirements of AD
99–12–52
(f) For airplanes with 50,000 or more total
flight hours as of June 28, 1999 (the effective
date of AD 99–12–52): Within 20 days after
June 28, 1999, accomplish the requirements
of paragraph (i) of this AD.
(g) For airplanes with less than 50,000 total
flight hours, but more than 30,000 total flight
hours, as of June 28, 1999: Within 30 days
after June 28, 1999, accomplish the
requirements of paragraph (i) of this AD.
(h) For airplanes with 30,000 total flight
hours or less, as of June 28, 1999: Within 90
days after June 28, 1999, accomplish the
requirements of paragraph (i) of this AD.
Detailed Inspection, Corrective Action, and
Installation
(i) Perform a detailed inspection of the intank fuel boost pump wire bundles, and
E:\FR\FM\22MYR1.SGM
22MYR1
28597
Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations
applicable corrective actions; and, except as
provided in paragraph (j) of this AD, install
sleeving over the wire bundles; in accordance
with Boeing Alert Service Bulletin 727–
28A0126, dated May 24, 1999; Boeing
Service Bulletin 727–28A0126, Revision 1,
dated May 18, 2000; or Boeing Alert Service
Bulletin 727–28A0132, dated February 22,
2007.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Installation: Possible Deferral
(j) Installation of sleeving over the wire
bundles, as required by paragraph (i) of this
AD, may be deferred if, within 18 months or
6,000 flight hours, whichever occurs first,
after accomplishment of the inspection and
applicable corrective actions required by
paragraph (i), the following actions are
accomplished: Perform a detailed inspection
of the in-tank fuel boost pump wire bundles,
and applicable corrective actions; and install
sleeving over the wire bundles; in accordance
with Boeing Alert Service Bulletin 727–
28A0126, dated May 24, 1999, or Boeing
Service Bulletin 727–28A0126, Revision 1,
dated May 18, 2000; or Boeing Alert Service
Bulletin 727–28A0132, dated February 22,
2007.
Repetitive Inspections and Corrective
Actions
(k) Repeat the detailed inspection and
applicable corrective actions required by
paragraphs (i) and (j) of this AD at intervals
not to exceed 30,000 flight hours, until the
initial inspection, applicable corrective
actions, and engine fuel suction feed
operational test required by paragraph (l) of
this AD have been done.
New Requirements of This AD
Inspection, Test, and Related Investigative
and Corrective Actions
(l) For all airplanes: Within 120 days after
the effective date of this AD or 5,000 flight
hours after the last inspection or corrective
action done before the effective date of this
AD as required by paragraph (i), (j), or (k), as
applicable, of this AD, whichever occurs
later, do a detailed inspection for damage of
the sleeve and electrical wire of the fuel
boost pump, and do an engine fuel suction
feed operational test; and, before further
flight, do related investigative and corrective
actions, as applicable; by doing all applicable
actions in and in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 727–28A0132, dated
February 22, 2007. Repeat the detailed
inspection and engine fuel suction feed
operational test thereafter at intervals not to
exceed 15,000 flight cycles. Accomplishment
of the initial inspection, applicable corrective
actions, and engine fuel suction feed
operational test of this paragraph terminates
the requirements of paragraphs (i), (j), and (k)
of this AD.
Inspection Report and Disposition of
Damaged Parts
(m) At the applicable time(s) specified in
paragraph (m)(1) or (m)(2) of this AD: Submit
a report of the findings (both positive and
negative) of any inspection required by this
AD and send any damaged parts to the
manufacturer, as described in Boeing Alert
Service Bulletin 727–28A0132, dated
February 22, 2007. The report must include
the information specified in Appendix A of
the alert service bulletin. Under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements contained in this AD and has
assigned OMB Control Number 2120–0056.
(1) For any inspection done after the
effective date of this AD: Submit the report
within 30 days after the inspection.
(2) For any inspection done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
Alternative Methods of Compliance
(AMOCs)
(n)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(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 appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(3) AMOCs approved previously in
accordance with AD 99–12–52 are approved
as AMOCs for the corresponding provisions
of this AD.
Material Incorporated by Reference
(o) You must use applicable Boeing service
bulletins specified in Table 1 of this AD to
perform the actions that are required by this
AD, unless the AD specifies otherwise.
TABLE 1.—ALL MATERIAL INCORPORATED BY REFERENCE
Revision level
Alert Service Bulletin 727–28A0126 ....................................................................
Alert Service Bulletin 727–28A0132 ....................................................................
Service Bulletin 727–28A0126 .............................................................................
cprice-sewell on PRODPC61 with RULES
Boeing service information
Original ..................................................
Original ..................................................
1 ............................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
Boeing Alert Service Bulletin 727–28A0132,
dated February 22, 2007; and Boeing Service
Bulletin 727–28A0126, Revision 1, dated
May 18, 2000; in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) On June 28, 1999 (64 FR 33394, June
23, 1999), the Director of the Federal Register
approved the incorporation by reference of
Boeing Alert Service Bulletin 727–28A0126,
dated May 24, 1999.
(3) Contact Boeing Commercial Airplanes,
P.O. Box 3707, Seattle, Washington 98124–
2207, for a copy of this service information.
You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
VerDate Aug<31>2005
15:01 May 21, 2007
Jkt 211001
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on May 1,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–9799 Filed 5–21–07; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
Date
May 24, 1999.
February 22, 2007.
May 18, 2000.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28253; Directorate
Identifier 2007–NM–031–AD; Amendment
39–15064; AD 2007–11–07]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–100, –200, –200C, –300,
–400, and –500 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
Frm 00011
Fmt 4700
Sfmt 4700
E:\FR\FM\22MYR1.SGM
22MYR1
Agencies
[Federal Register Volume 72, Number 98 (Tuesday, May 22, 2007)]
[Rules and Regulations]
[Pages 28594-28597]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-9799]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28254; Directorate Identifier 2007-NM-054-AD;
Amendment 39-15065; AD 2007-11-08]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) that applies to all Boeing Model 727 airplanes. The existing AD
requires a boost pump dry bay inspection to detect leakage of fuel
through an arced-through conduit, and corrective action as necessary.
The existing AD also requires repetitive inspections of the in-tank
fuel boost pump wiring to detect chafing of the wire insulation,
evidence of electrical arcing, or arc-through of the conduit wall, and
applicable corrective action; and installation of sleeving over the in-
tank fuel boost pump wires as a method to protect the wiring from
chafing. This new AD removes certain inspection requirements from the
[[Page 28595]]
existing AD. This new AD adds new repetitive inspections for damage of
the electrical wire and sleeve that run to the fuel boost pump through
a conduit in the fuel tank, and arcing damage of the conduit and signs
of fuel leakage into the conduit; applicable investigative and
corrective actions; and a new repetitive engine fuel suction feed
operational test. Initiation of the new inspections terminates the
requirements of the existing AD. This AD results from reports of a fuel
tank explosion on a Model 727-200F airplane on the ground; and of
chafed wires and a damaged power cable sleeve of a fuel boost pump that
were discovered during an inspection required by an existing AD on a
Model 737-300 airplane. We are issuing this AD to detect and correct
chafing of the fuel boost pump electrical wiring and leakage of fuel
into the conduit, and to prevent electrical arcing between the wiring
and the surrounding conduit, which could result in arc-through of the
conduit, and consequent fire or explosion of the fuel tank.
DATES: This AD becomes effective June 6, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of June 6, 2007.
On June 28, 1999 (64 FR 33394, June 23, 1999), the Director of the
Federal Register approved the incorporation by reference of Boeing
Alert Service Bulletin 727-28A0126, dated May 24, 1999.
We must receive any comments on this AD by July 23, 2007.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.
You may examine the contents of the AD docket on the Internet at
https://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-
401, Washington, DC. This docket number is FAA-2007-28254; the
directorate identifier for this docket is 2007-NM-054-AD.
FOR FURTHER INFORMATION CONTACT: Suzanne Lucier, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 917-6438; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
On June 15, 1999, we issued AD 99-12-52, amendment 39-11199 (64 FR
33394, June 23, 1999) (originally issued on May 24, 1999, as
telegraphic AD T99-12-52). That AD applies to all Boeing Model 727
series airplanes. That AD requires a boost pump dry bay inspection to
detect leakage of fuel through an arced-through conduit, and corrective
action, as necessary. That AD also requires repetitive detailed
inspections of the in-tank fuel boost pump wiring to detect chafing of
the wire insulation, evidence of electrical arcing, or arc-through of
the conduit wall on Model 727 series airplanes, and applicable
corrective action; and installation of sleeving over the in-tank fuel
boost pump wires as a method to protect the wiring from chafing. That
AD resulted from reports of severe wear of in-tank fuel boost pump
wiring, and arc-through of the surrounding conduit on two Model 727
series airplanes. The actions specified in that AD are intended to
prevent fuel tank explosion resulting from arc-through of the fuel
boost pump wiring conduits.
Actions Since AD Was Issued
Since we issued that AD, we received a report that a fuel tank
explosion occurred on a Model 727-200F airplane on the ground.
Investigation revealed evidence of arcing in the metal conduit that
carries power wires from the front spar through the fuel tank to the
dry bay of the 1 aft fuel boost pump. In a separate incident,
we received a report from Boeing that chafed power wires and a damaged
power cable sleeve of a fuel boost pump were discovered during an
inspection required by AD 99-12-52 on a Model 737-300 series airplane.
That inspection was done at 21,000 flight hours rather than the
repetitive interval of 30,000 flight hours specified by that AD. The
fuel boost pump installation on certain Model 737 airplanes is almost
identical to the installation on Model 727 airplanes.
Other Relevant Rulemaking
Operators should note that we are considering issuing a separate AD
to address the identified unsafe condition as it relates to Model 737
airplanes.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 727-28A0132, dated
February 22, 2007. The alert service bulletin describes procedures for
doing new repetitive detailed inspections for damage of the electrical
wire and sleeve that run to the fuel boost pump through a conduit in
the fuel tank, and for arcing damage of, and signs of fuel leakage
into, the conduit; doing a new engine fuel suction feed operational
test; doing related investigative and corrective actions, as
applicable; and sending inspection results and damaged parts to the
manufacturer. Related investigative and corrective actions include
replacing the wire sleeve with a new, smaller wire sleeve; replacing,
with BMS 13-60T09C03G018 wire, any wire that is damaged or has any part
number other than BMS 13-60T09C03G018 or BMS 13-60T12C03G018; doing
leak testing of the conduit if signs of fuel are discovered on the wire
or sleeve during any inspection; and repairing any damaged conduit or
replacing it with a new conduit.
AD 99-12-52 refers to Boeing Alert Service Bulletin 727-28A0126,
dated May 24, 1999, as the appropriate source of service information
for accomplishment of the detailed inspection and related
investigative/corrective actions; that requirement is new paragraph (i)
in this AD. That service bulletin has since been revised. Revision 1,
dated May 18, 2000, is essentially the same as the original and
provides no new actions.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other airplanes of the same type design. For this reason, we
are issuing this AD to supersede AD 99-12-52. This new AD retains
certain requirements of the existing AD. This AD also requires
accomplishing the actions specified in the alert service bulletin
described previously, which, when initiated, terminates certain
requirements.
Explanation of Changes Made to Existing AD
We have revised the applicability of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
[[Page 28596]]
The FAA has changed all references to a ``detailed visual
inspection'' in the existing AD to ``detailed inspection'' in this
action.
Interim Action
We consider this AD interim action. If final action is later
identified, we might consider further rulemaking then.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD; therefore, providing notice and opportunity for public comment
before the AD is issued is impracticable, and good cause exists to make
this AD effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2007-
28254; Directorate Identifier 2007-NM-054-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it. We will post all comments we receive,
without change, to https://dms.dot.gov, including any personal
information you provide. We will also post a report summarizing each
substantive verbal contact with FAA personnel concerning this AD. Using
the search function of that Web site, anyone can find and read the
comments in any of our dockets, including the name of the individual
who sent the comment (or signed the comment on behalf of an
association, business, labor union, etc.). You may review the DOT's
complete Privacy Act Statement in the Federal Register published on
April 11, 2000 (65 FR 19477-78), or you may visit https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
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
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 the 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); 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. We prepared a regulatory evaluation
of the estimated costs to comply with this AD and placed it in the AD
docket. See the ADDRESSES section for a location to examine the
regulatory evaluation.
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 part 39 of the Federal Aviation Regulations (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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-11199 (64 FR 33394, June 23, 1999) and adding the
following new airworthiness directive (AD):
2007-11-08 Boeing: Docket No. FAA-2007-28254; Directorate Identifier
2007-NM-054-AD; Amendment 39-15065.
Effective Date
(a) This AD becomes effective June 6, 2007.
Affected ADs
(b) This AD supersedes AD 99-12-52.
Applicability
(c) This AD applies to all Boeing Model 727, 727C, 727-100, 727
-100C, 727-200, and 727-200F series airplanes, certificated in any
category.
Unsafe Condition
(d) This AD results from reports of a fuel tank explosion on a
Model 727-200F airplane on the ground, and chafed wires and a
damaged power cable sleeve of a fuel boost pump that were discovered
during an inspection required by an existing AD on a Model 737-300
airplane, which has a fuel boost pump installation that is almost
identical to the installation on Model 727 airplanes. We are issuing
this AD to detect and correct chafing of the fuel boost pump
electrical wiring and leakage of fuel into the conduit, and to
prevent electrical arcing between the wiring and the surrounding
conduit, which could result in arc-through of the conduit, and
consequent fire or explosion of the fuel tank.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Certain Requirements of AD 99-12-52
(f) For airplanes with 50,000 or more total flight hours as of
June 28, 1999 (the effective date of AD 99-12-52): Within 20 days
after June 28, 1999, accomplish the requirements of paragraph (i) of
this AD.
(g) For airplanes with less than 50,000 total flight hours, but
more than 30,000 total flight hours, as of June 28, 1999: Within 30
days after June 28, 1999, accomplish the requirements of paragraph
(i) of this AD.
(h) For airplanes with 30,000 total flight hours or less, as of
June 28, 1999: Within 90 days after June 28, 1999, accomplish the
requirements of paragraph (i) of this AD.
Detailed Inspection, Corrective Action, and Installation
(i) Perform a detailed inspection of the in-tank fuel boost pump
wire bundles, and
[[Page 28597]]
applicable corrective actions; and, except as provided in paragraph
(j) of this AD, install sleeving over the wire bundles; in
accordance with Boeing Alert Service Bulletin 727-28A0126, dated May
24, 1999; Boeing Service Bulletin 727-28A0126, Revision 1, dated May
18, 2000; or Boeing Alert Service Bulletin 727-28A0132, dated
February 22, 2007.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Installation: Possible Deferral
(j) Installation of sleeving over the wire bundles, as required
by paragraph (i) of this AD, may be deferred if, within 18 months or
6,000 flight hours, whichever occurs first, after accomplishment of
the inspection and applicable corrective actions required by
paragraph (i), the following actions are accomplished: Perform a
detailed inspection of the in-tank fuel boost pump wire bundles, and
applicable corrective actions; and install sleeving over the wire
bundles; in accordance with Boeing Alert Service Bulletin 727-
28A0126, dated May 24, 1999, or Boeing Service Bulletin 727-28A0126,
Revision 1, dated May 18, 2000; or Boeing Alert Service Bulletin
727-28A0132, dated February 22, 2007.
Repetitive Inspections and Corrective Actions
(k) Repeat the detailed inspection and applicable corrective
actions required by paragraphs (i) and (j) of this AD at intervals
not to exceed 30,000 flight hours, until the initial inspection,
applicable corrective actions, and engine fuel suction feed
operational test required by paragraph (l) of this AD have been
done.
New Requirements of This AD
Inspection, Test, and Related Investigative and Corrective Actions
(l) For all airplanes: Within 120 days after the effective date
of this AD or 5,000 flight hours after the last inspection or
corrective action done before the effective date of this AD as
required by paragraph (i), (j), or (k), as applicable, of this AD,
whichever occurs later, do a detailed inspection for damage of the
sleeve and electrical wire of the fuel boost pump, and do an engine
fuel suction feed operational test; and, before further flight, do
related investigative and corrective actions, as applicable; by
doing all applicable actions in and in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 727-
28A0132, dated February 22, 2007. Repeat the detailed inspection and
engine fuel suction feed operational test thereafter at intervals
not to exceed 15,000 flight cycles. Accomplishment of the initial
inspection, applicable corrective actions, and engine fuel suction
feed operational test of this paragraph terminates the requirements
of paragraphs (i), (j), and (k) of this AD.
Inspection Report and Disposition of Damaged Parts
(m) At the applicable time(s) specified in paragraph (m)(1) or
(m)(2) of this AD: Submit a report of the findings (both positive
and negative) of any inspection required by this AD and send any
damaged parts to the manufacturer, as described in Boeing Alert
Service Bulletin 727-28A0132, dated February 22, 2007. The report
must include the information specified in Appendix A of the alert
service bulletin. Under the provisions of the Paperwork Reduction
Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget
(OMB) has approved the information collection requirements contained
in this AD and has assigned OMB Control Number 2120-0056.
(1) For any inspection done after the effective date of this AD:
Submit the report within 30 days after the inspection.
(2) For any inspection done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(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 appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(3) AMOCs approved previously in accordance with AD 99-12-52 are
approved as AMOCs for the corresponding provisions of this AD.
Material Incorporated by Reference
(o) You must use applicable Boeing service bulletins specified
in Table 1 of this AD to perform the actions that are required by
this AD, unless the AD specifies otherwise.
Table 1.--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Boeing service information Revision level Date
----------------------------------------------------------------------------------------------------------------
Alert Service Bulletin 727-28A0126....... Original.................... May 24, 1999.
Alert Service Bulletin 727-28A0132....... Original.................... February 22, 2007.
Service Bulletin 727-28A0126............. 1........................... May 18, 2000.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of Boeing Alert Service Bulletin 727-
28A0132, dated February 22, 2007; and Boeing Service Bulletin 727-
28A0126, Revision 1, dated May 18, 2000; in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) On June 28, 1999 (64 FR 33394, June 23, 1999), the Director
of the Federal Register approved the incorporation by reference of
Boeing Alert Service Bulletin 727-28A0126, dated May 24, 1999.
(3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for a copy of this service information. You
may review copies at the FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or 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:
https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on May 1, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-9799 Filed 5-21-07; 8:45 am]
BILLING CODE 4910-13-P