Airworthiness Directives; Boeing Model 727 Airplanes, 7489-7492 [E8-2354]
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Federal Register / Vol. 73, No. 27 / Friday, February 8, 2008 / Proposed Rules
cost of this proposed AD to the U.S.
operators to be between $560,880 and
$747,840, or between $720 and $960 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
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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 this proposed 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.
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, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Boeing: Docket No. FAA–2008–0149;
Directorate Identifier 2007–NM–319–AD.
Comments Due Date
(a) We must receive comments by March
24, 2008.
7489
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model 737–100,
–200, –200C, –300, –400, and –500 series
airplanes, certificated in any category; as
identified in Boeing Alert Service Bulletin
737–38A1054, dated August 23, 2007.
Unsafe Condition
(d) This AD results from a report of a
separated hose assembly for the passenger
water system. We are issuing this AD to
prevent a water leak into the flight deck
ceiling, which could result in an electrical
short and possible loss of several functions
essential to safe flight.
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
Replacement
(f) Within 60 months after the effective
date of this AD, replace the existing straightto-90-degree hose assembly for the Lavatory
‘‘A’’ water supply with a new straight hose
assembly and a separate 90-degree elbow
fitting, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–38A1054, dated August
23, 2007.
Parts Installation
(g) As of the effective date of this AD, any
hose assembly part having a part number
identified in Table 1 of this AD must not be
used in any location that is subject to the
requirements of this AD. However, those
parts may be used in other locations if not
otherwise prohibited.
TABLE 1.—SPARE PARTS PROHIBITED FOR THIS AD
Airplane group identified in Boeing Alert Service Bulletin 737–38A1054,
dated August 23, 2007
1 and 2 .....................................................................................................
3 ................................................................................................................
4 ................................................................................................................
Existing part Nos.
10–61998–430, AS4471–08–0401, or AS4471–08–0404.
10–61998–25 or 10–60871–125.
10–61998–31 or 10–60871–139.
ebenthall on PRODPC61 with PROPOSALS
Alternative Methods of Compliance
(AMOCs)
Office (FSDO), or lacking a PI, your local
FSDO.
DEPARTMENT OF TRANSPORTATION
(h)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, ATTN:
Marcia Smith, Aerospace Engineer, Cabin
Safety and Environmental Systems Branch,
ANM–150S, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
917–6484; fax (425) 917–6590; has the
authority to approve AMOCs for this AD, if
requested using 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
Issued in Renton, Washington, on January
31, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–2353 Filed 2–7–08; 8:45 am]
Federal Aviation Administration
VerDate Aug<31>2005
14:33 Feb 07, 2008
Jkt 214001
[Docket No. FAA–2008–0151; Directorate
Identifier 2007–NM–347–AD]
RIN 2120–AA64
BILLING CODE 4910–13–P
PO 00000
14 CFR Part 39
Airworthiness Directives; Boeing
Model 727 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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Federal Register / Vol. 73, No. 27 / Friday, February 8, 2008 / Proposed Rules
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for all
Boeing Model 727 airplanes. This
proposed AD would require repetitive
inspections for any crack in the area of
the elevator side fitting/hinge fitting
joint and for any crack or elongation
inside and outside of the holes in the
clevis and in the lug, corrective actions
if necessary, and other specified actions.
This proposed AD results from reports
of elongated holes and cracks found in
the lugs of the attachment fittings of the
elevator quadrant upper support
assembly at the tip of the vertical fin.
We are proposing this AD to detect and
correct damage to the aft attachment
lugs of the elevator quadrant support
assembly that could lead to failure of
the lugs. This condition could accelerate
wear elsewhere in the elevator control
system, which could reduce the crew’s
ability to maintain safe flight.
DATES: We must receive comments on
this proposed AD by March 24, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://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, P.O. Box 3707, Seattle,
Washington 98124–2207.
Washington 98057–3356; telephone
(425) 917–6577; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–0151; Directorate Identifier
2007–NM–347–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
ebenthall on PRODPC61 with PROPOSALS
Examining the AD Docket
Discussion
We have received reports of elongated
holes or cracks found in the lugs of the
attachment fittings on three Boeing
Model 727 airplanes. The attachment
fittings are located on the left and right
sides of the elevator quadrant upper
support assembly at the tip of the
vertical fin. In one incident, the lug was
cracked completely through. The
airplanes had accumulated between
28,385 and 72,448 total flight hours and
between 16,387 and 47,485 total flight
cycles. Damage to the aft attachment
lugs of the elevator quadrant support
assembly could lead to failure of the
lugs. This condition, if not corrected,
could accelerate wear elsewhere in the
elevator control system, which could
reduce the crew’s ability to maintain
safe flight.
You may examine the AD docket on
the Internet at https://
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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Relevant Service Information
We have reviewed Boeing Special
Attention Service Bulletin 727–55–
0092, dated June 4, 2007. Part 2 of the
Accomplishment Instructions of the
service bulletin describes procedures for
doing repetitive detailed inspections for
any crack in the area of the elevator side
fitting/hinge fitting joint, repetitive
detailed inspections for elongation
inside and outside of the holes in the
clevis and in the lug, and high
frequency eddy current (HFEC)
inspections for any crack inside and
outside of the holes in the clevis and in
the lug. The service bulletin specifies
doing these initial inspections within 18
months of the date on the service
bulletin. The service bulletin also
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14:33 Feb 07, 2008
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specifies repeating the inspections at
intervals not to exceed 24 months, 4,000
flight hours, or 3,000 flight cycles,
whichever occurs first, until the repair
or modification specified in Part 3 of the
Accomplishment Instructions is done.
The service bulletin also describes
procedures for doing corrective actions
if necessary. The corrective actions,
which the service bulletin specifies
doing before further flight, include the
following actions:
• Repairing the elevator side fittings
and hinge fittings as specified in Part 3
of the Accomplishment Instructions if
any crack, or any hole diameter
elongation over 0.3203 inch, is found
during the inspections specified in Part
2 of the service bulletin. The repair
includes oversizing the holes,
fabricating new bushings, installing and
in-line reaming the fabricated bushings
through the entire stack-up, and
installing the elevator side fittings.
• Replacing the bushings with
fabricated bushings if any hole diameter
elongation over 0.3203 inch is found
during the inspections specified in Part
4 of the Accomplishment Instructions of
the service bulletin.
• Contacting Boeing for repair
instructions if any damage is beyond the
repair limits or any crack is found in the
area of the elevator side fitting/hinge
fitting joint, during any inspection
specified in Part 2 or Part 4 of the
Accomplishment Instructions of the
service bulletin.
The service bulletin also describes
procedures for doing other specified
actions, which include the following:
• Either installing the elevator side
fittings and access panels and restoring
the cable tension, or modifying the
elevator side fittings and hinge fittings,
if all of the holes are found acceptable
during the inspections specified in Part
2 of the Accomplishment Instructions.
The modification includes oversizing
the holes, fabricating and installing new
bushings, in-line reaming the fabricated
bushings through the entire stack-up,
and installing the elevator side fittings.
The service bulletin specifies that the
modification must be done in
conjunction with the Part 2 detailed and
HFEC inspections.
• After the repair or modification
specified in Part 3 of the
Accomplishment Instructions has been
done, doing repetitive detailed
inspections for any crack in the area of
the elevator side fitting/hinge fitting
joint and repetitive detailed inspections
for elongation inside and outside of the
holes in the clevis and in the lug as
specified in Part 4 of the
Accomplishment Instructions. The
service bulletin specifies doing the
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Federal Register / Vol. 73, No. 27 / Friday, February 8, 2008 / Proposed Rules
initial inspections within 24,000 flight
hours or 16,000 flight cycles, whichever
occurs first, after accomplishing the
repair or modification specified in Part
3 of the service bulletin. The service
bulletin also specifies repeating the
inspections at intervals not to exceed
24,000 flight hours or 16,000 flight
cycles, whichever occurs first.
FAA’s Determination and Requirements
of This Proposed AD
We are proposing this AD because we
evaluated all relevant information and
determined the unsafe condition
described previously is likely to exist or
develop in other products of the(se)
same type design(s). This proposed AD
would require accomplishing the
actions specified in the service
information described previously,
except as discussed under ‘‘Difference
between the Proposed AD and Service
Bulletin.’’
Difference Between the Proposed AD
and Service Bulletin
The service bulletin specifies to
contact the manufacturer for
instructions on how to repair certain
conditions, but this proposed AD would
require repairing those conditions in
one of the following ways:
• Using a method that we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by an
Authorized Representative for the
Boeing Commercial Airplanes
Delegation Option Authorization
Organization whom we have authorized
to make those findings.
ebenthall on PRODPC61 with PROPOSALS
Costs of Compliance
We estimate that this proposed AD
would affect 401 airplanes of U.S.
registry. We also estimate that it would
take about 2 work-hours per product to
comply with this proposed AD. The
average labor rate is $80 per work-hour.
Based on these figures, we estimate the
cost of this proposed AD to the U.S.
operators to be $64,160 or $160 per
product, per inspection cycle.
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
VerDate Aug<31>2005
14:33 Feb 07, 2008
Jkt 214001
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 determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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 this proposed 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.
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, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Boeing: Docket No. FAA–2008–0151;
Directorate Identifier 2007–NM–347–AD.
Comments Due Date
(a) We must receive comments by March
24, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Boeing Model
727, 727C, 727–100, 727–100C, 727–200, and
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7491
727–200F series airplanes, certificated in any
category.
Unsafe Condition
(d) This AD results from reports of
elongated holes and cracks found in the lugs
of the attachment fittings of the elevator
quadrant upper support assembly at the tip
of the vertical fin. We are issuing this AD to
detect and correct damage to the aft
attachment lugs of the elevator quadrant
support assembly that could lead to failure of
the lugs. This condition could accelerate
wear elsewhere in the elevator control
system, which could reduce the crew’s
ability to maintain safe flight.
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
Repetitive Inspections and Corrective/Other
Specified Actions
(f) At the applicable compliance times
specified in paragraph 1.E. of Boeing Special
Attention Service Bulletin 727–55–0092,
dated June 4, 2007, except as provided by
paragraph (g) of this AD: Do the detailed
inspection for any crack in the area of the
elevator side fitting/hinge fitting joint,
detailed inspections for elongation inside
and outside of the holes in the clevis and in
the lug, and high frequency eddy current
(HFEC) inspections for any crack inside and
outside of the holes in the clevis and in the
lug, and do all the applicable corrective
actions and other specified actions, by
accomplishing all of the applicable actions
specified in the Accomplishment
Instructions of the service bulletin, except as
provided by paragraph (h) of this AD. Repeat
the inspections thereafter at the applicable
intervals specified in paragraph 1.E. of the
service bulletin. Accomplishing the repair or
modification specified in Part 3 of the service
bulletin only terminates the repetitive
inspections specified in Part 2 of the service
bulletin.
Exception to Compliance Times
(g) Where Boeing Special Attention Service
Bulletin 727–55–0092, dated June 4, 2007,
specifies counting the compliance time from
‘‘* * * the date on this service bulletin,’’ this
AD requires counting the compliance time
from the effective date of this AD.
Exception to Corrective Actions
(h) If any damage beyond the repair limits
or any crack is found in the area of the
elevator side fitting/hinge fitting joint during
any inspection required by this AD, and
Boeing Special Attention Service Bulletin
727–55–0092, dated June 4, 2007, specifies to
contact Boeing for appropriate action: Before
further flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (i) of this AD.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Seattle Aircraft
Certification Office, FAA, ATTN: Berhane
Alazar, Aerospace Engineer, Airframe
Branch, ANM–120S, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
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Federal Register / Vol. 73, No. 27 / Friday, February 8, 2008 / Proposed Rules
(425) 917–6577; fax (425) 917–6590; has the
authority to approve AMOCs for this AD, if
requested using 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) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who 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.
Issued in Renton, Washington, on January
31, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–2354 Filed 2–7–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0152; Directorate
Identifier 2007–NM–348–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–400, –500, –600, –700,
–700C, –800, and –900 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Boeing Model 737–400, –500, –600,
–700, –700C, –800, and –900 series
airplanes. This proposed AD would
require an inspection to determine the
part and serial numbers of the
windshield wiper motors for the pilot’s
and first officer’s windshields, and the
applicable corrective action. This
proposed AD results from two reports
that the left and right windshield wipers
stopped working in flight. We are
proposing this AD to prevent failure of
the windshield wipers in wet weather,
which could result in decreased
visibility for the flightcrew.
DATES: We must receive comments on
this proposed AD by March 24, 2008.
ebenthall on PRODPC61 with PROPOSALS
SUMMARY:
VerDate Aug<31>2005
14:33 Feb 07, 2008
Jkt 214001
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://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, P.O. Box 3707, Seattle,
Washington 98124–2207.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Nick
Wilson, Aerospace Engineer, Cabin
Safety and Environmental Systems
Branch, ANM–150S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6476;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–0152; Directorate Identifier
2007–NM–348–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We have received two reports that the
left and right windshield wipers
stopped working in flight. In one
incident, the left and right windshield
wiper motors stopped at the same time
during a landing approach in wet
weather. Investigation revealed that the
power converter module for the
windshield wipers was not properly
soldered. Failure of the windshield
wipers in wet weather, if not corrected,
could result in decreased visibility for
the flightcrew.
Other Related Rulemaking
On October 2, 2003, we issued AD
2003–20–13, amendment 39–13331 (68
FR 58268, October 9, 2003), applicable
to certain Boeing Model 737–400, –500,
–600, –700, and –800 series airplanes.
That AD requires either modification of
the wiring to the windshield wiper
motors in the flight compartment or
replacement of those windshield wiper
motor/converters with new motor/
converters. That AD resulted from
reports of the windshield motors
stalling during flight. We issued that AD
to prevent a reduction in flightcrew
visibility due to stalled wiper motors
during heavy precipitation and a period
of substantial crew workload, which
could result in damage to the airplane
structure and injury to flightcrew,
passengers, or ground personnel during
final approach for landing. For certain
airplanes, accomplishing the
modification required by paragraph (b)
of AD 2003–20–13 is acceptable for
compliance with certain requirements of
this proposed AD.
Relevant Service Information
We have reviewed Boeing Service
Bulletin 737–30A1057, Revision 1,
dated October 31, 2007, for Model 737–
600, –700, –700C, –800, and –900 series
airplanes; and Boeing Alert Service
Bulletin 737–30A1059, dated September
10, 2007, for Model 737–400 and –500
series airplanes. The service bulletins
describe procedures for looking at the
windshield wiper motors for the pilot’s
and first officer’s windshields to
determine the part number and serial
number of the windshield wiper motors,
and doing the applicable corrective
action. The corrective actions include
the following:
• Replacing the windshield wiper
motor with an improved windshield
wiper motor if the part and serial
numbers cannot be read, or if the part
and serial numbers are listed in
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]]>Agencies
[Federal Register Volume 73, Number 27 (Friday, February 8, 2008)]
[Proposed Rules]
[Pages 7489-7492]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-2354]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0151; Directorate Identifier 2007-NM-347-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
[[Page 7490]]
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Boeing Model 727 airplanes. This proposed AD would require repetitive
inspections for any crack in the area of the elevator side fitting/
hinge fitting joint and for any crack or elongation inside and outside
of the holes in the clevis and in the lug, corrective actions if
necessary, and other specified actions. This proposed AD results from
reports of elongated holes and cracks found in the lugs of the
attachment fittings of the elevator quadrant upper support assembly at
the tip of the vertical fin. We are proposing this AD to detect and
correct damage to the aft attachment lugs of the elevator quadrant
support assembly that could lead to failure of the lugs. This condition
could accelerate wear elsewhere in the elevator control system, which
could reduce the crew's ability to maintain safe flight.
DATES: We must receive comments on this proposed AD by March 24, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
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, P.O. Box 3707, Seattle, Washington 98124-2207.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6577; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0151;
Directorate Identifier 2007-NM-347-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received reports of elongated holes or cracks found in the
lugs of the attachment fittings on three Boeing Model 727 airplanes.
The attachment fittings are located on the left and right sides of the
elevator quadrant upper support assembly at the tip of the vertical
fin. In one incident, the lug was cracked completely through. The
airplanes had accumulated between 28,385 and 72,448 total flight hours
and between 16,387 and 47,485 total flight cycles. Damage to the aft
attachment lugs of the elevator quadrant support assembly could lead to
failure of the lugs. This condition, if not corrected, could accelerate
wear elsewhere in the elevator control system, which could reduce the
crew's ability to maintain safe flight.
Relevant Service Information
We have reviewed Boeing Special Attention Service Bulletin 727-55-
0092, dated June 4, 2007. Part 2 of the Accomplishment Instructions of
the service bulletin describes procedures for doing repetitive detailed
inspections for any crack in the area of the elevator side fitting/
hinge fitting joint, repetitive detailed inspections for elongation
inside and outside of the holes in the clevis and in the lug, and high
frequency eddy current (HFEC) inspections for any crack inside and
outside of the holes in the clevis and in the lug. The service bulletin
specifies doing these initial inspections within 18 months of the date
on the service bulletin. The service bulletin also specifies repeating
the inspections at intervals not to exceed 24 months, 4,000 flight
hours, or 3,000 flight cycles, whichever occurs first, until the repair
or modification specified in Part 3 of the Accomplishment Instructions
is done.
The service bulletin also describes procedures for doing corrective
actions if necessary. The corrective actions, which the service
bulletin specifies doing before further flight, include the following
actions:
Repairing the elevator side fittings and hinge fittings as
specified in Part 3 of the Accomplishment Instructions if any crack, or
any hole diameter elongation over 0.3203 inch, is found during the
inspections specified in Part 2 of the service bulletin. The repair
includes oversizing the holes, fabricating new bushings, installing and
in-line reaming the fabricated bushings through the entire stack-up,
and installing the elevator side fittings.
Replacing the bushings with fabricated bushings if any
hole diameter elongation over 0.3203 inch is found during the
inspections specified in Part 4 of the Accomplishment Instructions of
the service bulletin.
Contacting Boeing for repair instructions if any damage is
beyond the repair limits or any crack is found in the area of the
elevator side fitting/hinge fitting joint, during any inspection
specified in Part 2 or Part 4 of the Accomplishment Instructions of the
service bulletin.
The service bulletin also describes procedures for doing other
specified actions, which include the following:
Either installing the elevator side fittings and access
panels and restoring the cable tension, or modifying the elevator side
fittings and hinge fittings, if all of the holes are found acceptable
during the inspections specified in Part 2 of the Accomplishment
Instructions. The modification includes oversizing the holes,
fabricating and installing new bushings, in-line reaming the fabricated
bushings through the entire stack-up, and installing the elevator side
fittings. The service bulletin specifies that the modification must be
done in conjunction with the Part 2 detailed and HFEC inspections.
After the repair or modification specified in Part 3 of
the Accomplishment Instructions has been done, doing repetitive
detailed inspections for any crack in the area of the elevator side
fitting/hinge fitting joint and repetitive detailed inspections for
elongation inside and outside of the holes in the clevis and in the lug
as specified in Part 4 of the Accomplishment Instructions. The service
bulletin specifies doing the
[[Page 7491]]
initial inspections within 24,000 flight hours or 16,000 flight cycles,
whichever occurs first, after accomplishing the repair or modification
specified in Part 3 of the service bulletin. The service bulletin also
specifies repeating the inspections at intervals not to exceed 24,000
flight hours or 16,000 flight cycles, whichever occurs first.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the(se) same type
design(s). This proposed AD would require accomplishing the actions
specified in the service information described previously, except as
discussed under ``Difference between the Proposed AD and Service
Bulletin.''
Difference Between the Proposed AD and Service Bulletin
The service bulletin specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions in one of the following ways:
Using a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by an Authorized Representative
for the Boeing Commercial Airplanes Delegation Option Authorization
Organization whom we have authorized to make those findings.
Costs of Compliance
We estimate that this proposed AD would affect 401 airplanes of
U.S. registry. We also estimate that it would take about 2 work-hours
per product to comply with this proposed AD. The average labor rate is
$80 per work-hour. Based on these figures, we estimate the cost of this
proposed AD to the U.S. operators to be $64,160 or $160 per product,
per inspection cycle.
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 determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
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.
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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Boeing: Docket No. FAA-2008-0151; Directorate Identifier 2007-NM-
347-AD.
Comments Due Date
(a) We must receive comments by March 24, 2008.
Affected ADs
(b) None.
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 elongated holes and cracks
found in the lugs of the attachment fittings of the elevator
quadrant upper support assembly at the tip of the vertical fin. We
are issuing this AD to detect and correct damage to the aft
attachment lugs of the elevator quadrant support assembly that could
lead to failure of the lugs. This condition could accelerate wear
elsewhere in the elevator control system, which could reduce the
crew's ability to maintain safe flight.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Repetitive Inspections and Corrective/Other Specified Actions
(f) At the applicable compliance times specified in paragraph
1.E. of Boeing Special Attention Service Bulletin 727-55-0092, dated
June 4, 2007, except as provided by paragraph (g) of this AD: Do the
detailed inspection for any crack in the area of the elevator side
fitting/hinge fitting joint, detailed inspections for elongation
inside and outside of the holes in the clevis and in the lug, and
high frequency eddy current (HFEC) inspections for any crack inside
and outside of the holes in the clevis and in the lug, and do all
the applicable corrective actions and other specified actions, by
accomplishing all of the applicable actions specified in the
Accomplishment Instructions of the service bulletin, except as
provided by paragraph (h) of this AD. Repeat the inspections
thereafter at the applicable intervals specified in paragraph 1.E.
of the service bulletin. Accomplishing the repair or modification
specified in Part 3 of the service bulletin only terminates the
repetitive inspections specified in Part 2 of the service bulletin.
Exception to Compliance Times
(g) Where Boeing Special Attention Service Bulletin 727-55-0092,
dated June 4, 2007, specifies counting the compliance time from ``*
* * the date on this service bulletin,'' this AD requires counting
the compliance time from the effective date of this AD.
Exception to Corrective Actions
(h) If any damage beyond the repair limits or any crack is found
in the area of the elevator side fitting/hinge fitting joint during
any inspection required by this AD, and Boeing Special Attention
Service Bulletin 727-55-0092, dated June 4, 2007, specifies to
contact Boeing for appropriate action: Before further flight, repair
the crack using a method approved in accordance with the procedures
specified in paragraph (i) of this AD.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Seattle Aircraft Certification Office, FAA,
ATTN: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
[[Page 7492]]
(425) 917-6577; fax (425) 917-6590; has the authority to approve
AMOCs for this AD, if requested using 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) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who 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.
Issued in Renton, Washington, on January 31, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-2354 Filed 2-7-08; 8:45 am]
BILLING CODE 4910-13-P
