Airworthiness Directives; Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes, 21251-21254 [E9-9926]
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Federal Register / Vol. 74, No. 87 / Thursday, May 7, 2009 / Rules and Regulations
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
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:
■
2009–09–08 Boeing: Amendment 39–15894.
Docket No. FAA–2008–1239; Directorate
Identifier 2008–NM–131–AD.
Effective Date
(a) This airworthiness directive (AD) is
effective June 11, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747–
100, 747–100B, 747–100B SUD, 747–200B,
747–200C, 747–200F, 747–300, 747–400,
747–400D, 747–400F, 747SR, and 747SP
series airplanes, certificated in any category;
as identified in Boeing Alert Service Bulletin
747–53A2651, dated June 12, 2008.
Unsafe Condition
(d) This AD results from reports of cracks
in the radius detail of the upper lobe
doublers. We are issuing this AD to detect
and correct cracks in the upper lobe
doublers. Such cracks could result in
significant degradation of the fuselage
structure and reduce its ability to carry flight
loads from the vertical stabilizer, which
could adversely affect the controllability of
the airplane.
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
Inspection(s) and Corrective Action
(f) At the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2651, dated
June 12, 2008, except as required by
paragraph (i) of this AD, do an external
surface high frequency eddy current
inspection to detect cracks in the radius
detail of the upper lobe doubler on both sides
of the airplane, and the applicable corrective
action, by accomplishing all the applicable
actions specified in the Accomplishment
Instructions of the service bulletin, except as
required by paragraphs (g) and (h) of this AD.
The applicable corrective action must be
done before further flight. As applicable,
VerDate Nov<24>2008
16:03 May 06, 2009
Jkt 217001
repeat the inspection thereafter at the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2651, dated June 12, 2008.
(g) Where Boeing Alert Service Bulletin
747–53A2651, dated June 12, 2008,
paragraph 3.B., Work Instructions, PART 3,
Step 1, specifies a sealant application ‘‘from
STA 2520 to STA 2521,’’ this AD requires a
sealant application ‘‘from STA 2491 to STA
2521’’ on both sides of the airplane.
(h) Where Boeing Alert Service Bulletin
747–53A2651, dated June 12, 2008, specifies
to contact Boeing for repair instructions
instead of repairing or replacing any cracked
upper lobe doubler in accordance with the
service bulletin, this AD requires, before
further flight, repairing any cracked upper
lobe doubler using a method approved in
accordance with the procedures specified in
paragraph (j) of this AD.
(i) Where Boeing Alert Service Bulletin
747–53A2651, dated June 12, 2008, specifies
a compliance time after the date on the
service bulletin, this AD requires compliance
within the specified compliance time after
the effective date of this AD.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN: Ivan
Li, Aerospace Engineer, Airframe Branch,
ANM–120S, FAA, Seattle ACO, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 917–6437; fax (425)
917–6590.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
(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.
Material Incorporated by Reference
(k) You must use Boeing Alert Service
Bulletin 747–53A2651, dated June 12, 2008,
to do the actions required by this AD, unless
the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
PO 00000
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21251
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on April 22,
2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–9925 Filed 5–6–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1070; Directorate
Identifier 2008–NM–087–AD; Amendment
39–15893; AD 2009–09–07]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–100, –200, –200C, –300,
–400, and –500 Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for all
Boeing Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
For all airplanes, this AD requires
repetitive overhaul of the retract
actuator beam of the main landing gear
(MLG). For certain airplanes, this AD
requires repetitive inspections for
damage of the retract actuator beam, and
related investigative and corrective
actions if necessary. This AD results
from reports of broken retract actuator
beams of the MLG and the subsequent
failure of the MLG to fully retract. We
are issuing this AD to detect and correct
broken retract actuator beams of the
MLG, which could cause damage to the
beam arm, hydraulic tubing, and flight
control cables. Damage to the flight
control cables could result in loss of
control of the airplane.
DATES: This AD is effective June 11,
2009.
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21252
Federal Register / Vol. 74, No. 87 / Thursday, May 7, 2009 / Rules and Regulations
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of June 11, 2009.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207;
telephone 206–544–9990; fax 206–766–
5682; e-mail DDCS@boeing.com;
Internet https://
www.myboeingfleet.com.
related investigative and corrective
actions if necessary.
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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6440; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Request To Change Overhaul
Requirements
Continental Airlines (CAL) asks that
we not mandate overhaul of the retract
actuator beam using the instructions
specified in the Accomplishment
Instructions of Boeing Service Bulletin
737–32A1355, Revision 2, dated March
5, 2008. CAL states that the reason for
release of Boeing Service Bulletin 737–
32A1355, Revision 2, is Boeing’s
concern regarding shop process
deficiencies at some repair facilities
where correct overhaul procedures were
not followed. CAL finds this reasoning
detrimental to all operators that follow
correct overhaul procedures at their
repair facilities.
CAL landing gear components,
including the retract actuator beams of
the left and right main landing gear, are
time controlled per the Boeing 737–300/
–500 Maintenance Program and are
scheduled to be overhauled at 10-year
intervals at an FAA-approved landing
gear overhaul facility. CAL also makes
the following recommendations
regarding Boeing Service Bulletin 737–
32A1355, Revision 2:
• The stripping of all chrome and
nickel plating specified in Step 4 of
Figure 2 should be included as an
option, as in the Boeing 737 Component
Maintenance Manual (CMM), Section
32–00–05.
• The nital etch inspection of
machined surfaces specified only in
Step 9 of Figure 2 should not be limited
to machined surfaces.
• The stress relieving of the part
specified in Step 10 of Figure 2 should
be an optional step, as specified in
Boeing 737 CMM, Section 32–00–05.
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that would apply to all
Boeing Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
That NPRM was published in the
Federal Register on October 8, 2008 (73
FR 58906). For all airplanes, that NPRM
proposed to require repetitive overhaul
of the retract actuator beam of the main
landing gear (MLG). For certain
airplanes, that NPRM proposed to
require repetitive inspections for
damage of the retract actuator beam, and
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received from
the commenters.
Support for the NPRM
Boeing concurs with the contents of
the NPRM.
• The shot peening of the entire part
specified in Step 12 of Figure 2 should
be limited to the machined areas of the
part since the geometry of the actuator
beam does not allow for effective shot
peening of the entire area.
• A caution note for arc burns
associated with grounding (similar to
Step 14) should be included in Step 13
of Figure 2.
We disagree that using the
instructions specified in the
Accomplishment Instructions of Boeing
Service Bulletin 737–32A1355, Revision
2, dated March 5, 2008, to perform the
overhaul of the retract actuator beam
should not be mandated. Revision 2 of
Boeing Service Bulletin 737–32A1355
references improved overhaul
procedures, and those procedures are
required by this AD. However,
according to the provisions of paragraph
(i) of this AD, we may approve a request
for using different overhaul procedures
if the request includes data that prove
that those procedures would provide an
acceptable level of safety. We have not
changed the AD in this regard.
We acknowledge the request for
changes to Boeing Service Bulletin 737–
32A1355, Revision 2. At the present
time, Boeing has not issued a revised
service bulletin with the changes.
However, if Boeing Service Bulletin
737–32A1355, Revision 2, is revised
after issuance of this AD, we might
consider approving the revised service
bulletin as an alternative method of
compliance (AMOC) with the
requirements of this AD. We have not
changed the AD in this regard.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
as proposed.
Costs of Compliance
We estimate that this AD affects 652
airplanes of U.S. registry. The following
table provides the estimated costs for
U.S. operators to comply with this AD.
ESTIMATED COSTS
Action/airplane group
Overhaul for Group 1; Configurations 1, 2, and 3.
Inspection for Group 1, Configuration 3.
VerDate Nov<24>2008
16:03 May 06, 2009
Average labor
rate per hour
Work hours
Parts cost
Number of
U.S.-registered
airplanes
Cost per product
Fleet cost
64
None ...........
$5,120, per overhaul cycle ..
652
$3,338,240
1
Jkt 217001
$80
80
None ...........
$80, per inspection cycle .....
525
42,000
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Federal Register / Vol. 74, No. 87 / Thursday, May 7, 2009 / Rules and Regulations
Authority for This Rulemaking
§ 39.13
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
■
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979), and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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.
VerDate Nov<24>2008
16:03 May 06, 2009
Jkt 217001
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
2009–09–07 Boeing: Amendment 39–15893.
Docket No. FAA–2008–1070; Directorate
Identifier 2008–NM–087–AD.
Effective Date
(a) This airworthiness directive (AD) is
effective June 11, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Boeing Model
737–100, –200, –200C, –300, –400, and –500
series airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from reports of broken
retract actuator beams of the main landing
gear (MLG) and the subsequent failure of the
MLG to fully retract. We are issuing this AD
to detect and correct broken retract actuator
beams of the MLG, which could result in
damage to the beam arm, hydraulic tubing,
and flight control cables. Damage to the flight
control cables could result in loss of control
of the airplane.
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
Inspection and Related Investigative and
Corrective Actions/Overhaul
(f) Except as provided by paragraphs (g)
and (h) of this AD: At the applicable times
specified in paragraph 1.E. of Boeing Service
Bulletin 737–32A1355, Revision 2, dated
March 5, 2008, inspect for damage of the
retract actuator beam of the MLG and
overhaul the retract actuator beam, as
applicable, by doing all the applicable
actions specified in the Accomplishment
Instructions of Boeing Service Bulletin 737–
32A1355, Revision 2, dated March 5, 2008.
Do all applicable related investigative and
corrective actions before further flight.
Repeat the applicable inspection or overhaul
thereafter at the applicable time specified in
paragraph 1.E. of Boeing Service Bulletin
737–32A1355, Revision 2, dated March 5,
2008.
Exceptions to Service Information
(g) Where Boeing Service Bulletin 737–
32A1355, Revision 2, dated March 5, 2008,
specifies a compliance time after ‘‘* * * the
date on this service bulletin,’’ this AD
requires compliance within the specified
compliance time after the effective date of
this AD.
(h) Boeing Service Bulletin 737–32A1355,
Revision 2, dated March 5, 2008, specifies
that the actions are for airplanes with new
MLG retract actuator beams that have not
been overhauled having part number (P/N)
65–46108–15 and subsequent dash numbers;
and new or overhauled MLG retract actuator
beams having P/N 65–46108–14 and previous
dash numbers. However, this AD is not
limited to new or overhauled beams. This AD
requires that the actions required by
PO 00000
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Fmt 4700
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21253
paragraph (f) of this AD be done on airplanes
with any MLG retract actuator beam having
those P/Ns.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN:
Nancy Marsh, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 917–6440; fax (425) 917–6590; or e-mail
information to 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office.
(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.
Material Incorporated by Reference
(j) You must use Boeing Service Bulletin
737–32A1355, Revision 2, dated March 5,
2008, to do the actions required by this AD,
unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207; telephone 206–
544–9990; fax 206–766–5682; e-mail
DDCS@boeing.com; Internet https://
www.myboeingfleet.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
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21254
Federal Register / Vol. 74, No. 87 / Thursday, May 7, 2009 / Rules and Regulations
Issued in Renton, Washington, on April 22,
2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–9926 Filed 5–6–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1275; Directorate
Identifier 2007–NM–167–AD; Amendment
39–15892; AD 2009–09–06]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–100, –200, –200C, –300,
–400, and –500 Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Boeing Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
This AD requires repetitive detailed and
high frequency eddy current inspections
to detect cracks of the backup
intercostals and the upper sill of the
forward airstair doorway, and
applicable corrective actions. This AD
also provides for an optional
terminating action, which would
eliminate the need for repetitive
inspections. This AD results from a
report indicating that cracks were found
in the backup intercostals and upper sill
web of the forward airstair doorway. We
are issuing this AD to detect and correct
fatigue cracking of the backup
intercostals and upper sill web of the
forward airstair doorway, which could
result in a rapid loss of cabin pressure.
DATES: This AD is effective June 11,
2009.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of June 11, 2009.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet&fnl;
https://www.myboeingfleet.com.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
VerDate Nov<24>2008
16:03 May 06, 2009
Jkt 217001
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6450; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that would apply to
certain Boeing Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes. That NPRM was published in
the Federal Register on December 5,
2008 (73 FR 74080). That NPRM
proposed to require repetitive detailed
and high frequency eddy current
inspections to detect cracks of the
backup intercostals and the upper sill of
the forward airstair doorway, and
applicable corrective actions. That
NPRM also provided an optional
terminating action, which would
eliminate the need for repetitive
inspections.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received from
the two commenters.
Support for the NPRM
Boeing concurs with the contents of
the NPRM.
Request for Clarification
Southwest Airlines requests more
information regarding alternative
procedures for airplanes that have had
the airstair door deactivated per Boeing
Service Bulletin 737–52–1092.
Southwest Airlines asks whether
instructions developed by operators, for
open and close of an airstair door after
deactivation per Boeing Service Bulletin
737–52–1092, will be considered
approved equivalent procedures.
No alternative procedures have been
established that have general FAA
approval; however, according to the
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Fmt 4700
Sfmt 4700
provisions of paragraph (h) of the final
rule we may approve requests for
different compliance methods if the
requests include data that prove that the
new methods would provide an
acceptable level of safety.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
as proposed.
Costs of Compliance
There are 1,712 airplanes of the
affected design in the worldwide fleet.
This AD affects 509 airplanes of U.S.
registry. The inspections take 2 work
hours per airplane, at an average labor
rate of $80 per work hour. Based on
these figures, the estimated cost of the
AD for U.S. operators is $81,440, or
$160 per airplane, per inspection cycle.
The optional terminating action, if
done, would take 9 work hours, at an
average labor rate of $80 per work hour.
Required parts cost between $533 and
$566 per airplane, depending on the
airplane configuration. Based on these
figures, the estimated cost of the
optional terminating action would range
between $1,253 and $1,286 per airplane,
depending on the airplane
configuration.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
E:\FR\FM\07MYR1.SGM
07MYR1
]]>Agencies
[Federal Register Volume 74, Number 87 (Thursday, May 7, 2009)]
[Rules and Regulations]
[Pages 21251-21254]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-9926]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1070; Directorate Identifier 2008-NM-087-AD;
Amendment 39-15893; AD 2009-09-07]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-100, -200, -200C, -
300, -400, and -500 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Boeing Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes. For all airplanes, this AD requires repetitive overhaul of
the retract actuator beam of the main landing gear (MLG). For certain
airplanes, this AD requires repetitive inspections for damage of the
retract actuator beam, and related investigative and corrective actions
if necessary. This AD results from reports of broken retract actuator
beams of the MLG and the subsequent failure of the MLG to fully
retract. We are issuing this AD to detect and correct broken retract
actuator beams of the MLG, which could cause damage to the beam arm,
hydraulic tubing, and flight control cables. Damage to the flight
control cables could result in loss of control of the airplane.
DATES: This AD is effective June 11, 2009.
[[Page 21252]]
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of June 11,
2009.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207; telephone 206-544-9990; fax 206-766-5682; e-mail DDCS@boeing.com;
Internet https://www.myboeingfleet.com.
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 AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6440; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness directive (AD) that would apply to
all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes. That NPRM was published in the Federal Register on October
8, 2008 (73 FR 58906). For all airplanes, that NPRM proposed to require
repetitive overhaul of the retract actuator beam of the main landing
gear (MLG). For certain airplanes, that NPRM proposed to require
repetitive inspections for damage of the retract actuator beam, and
related investigative and corrective actions if necessary.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received from the commenters.
Support for the NPRM
Boeing concurs with the contents of the NPRM.
Request To Change Overhaul Requirements
Continental Airlines (CAL) asks that we not mandate overhaul of the
retract actuator beam using the instructions specified in the
Accomplishment Instructions of Boeing Service Bulletin 737-32A1355,
Revision 2, dated March 5, 2008. CAL states that the reason for release
of Boeing Service Bulletin 737-32A1355, Revision 2, is Boeing's concern
regarding shop process deficiencies at some repair facilities where
correct overhaul procedures were not followed. CAL finds this reasoning
detrimental to all operators that follow correct overhaul procedures at
their repair facilities.
CAL landing gear components, including the retract actuator beams
of the left and right main landing gear, are time controlled per the
Boeing 737-300/-500 Maintenance Program and are scheduled to be
overhauled at 10-year intervals at an FAA-approved landing gear
overhaul facility. CAL also makes the following recommendations
regarding Boeing Service Bulletin 737-32A1355, Revision 2:
The stripping of all chrome and nickel plating specified
in Step 4 of Figure 2 should be included as an option, as in the Boeing
737 Component Maintenance Manual (CMM), Section 32-00-05.
The nital etch inspection of machined surfaces specified
only in Step 9 of Figure 2 should not be limited to machined surfaces.
The stress relieving of the part specified in Step 10 of
Figure 2 should be an optional step, as specified in Boeing 737 CMM,
Section 32-00-05.
The shot peening of the entire part specified in Step 12
of Figure 2 should be limited to the machined areas of the part since
the geometry of the actuator beam does not allow for effective shot
peening of the entire area.
A caution note for arc burns associated with grounding
(similar to Step 14) should be included in Step 13 of Figure 2.
We disagree that using the instructions specified in the
Accomplishment Instructions of Boeing Service Bulletin 737-32A1355,
Revision 2, dated March 5, 2008, to perform the overhaul of the retract
actuator beam should not be mandated. Revision 2 of Boeing Service
Bulletin 737-32A1355 references improved overhaul procedures, and those
procedures are required by this AD. However, according to the
provisions of paragraph (i) of this AD, we may approve a request for
using different overhaul procedures if the request includes data that
prove that those procedures would provide an acceptable level of
safety. We have not changed the AD in this regard.
We acknowledge the request for changes to Boeing Service Bulletin
737-32A1355, Revision 2. At the present time, Boeing has not issued a
revised service bulletin with the changes. However, if Boeing Service
Bulletin 737-32A1355, Revision 2, is revised after issuance of this AD,
we might consider approving the revised service bulletin as an
alternative method of compliance (AMOC) with the requirements of this
AD. We have not changed the AD in this regard.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD as proposed.
Costs of Compliance
We estimate that this AD affects 652 airplanes of U.S. registry.
The following table provides the estimated costs for U.S. operators to
comply with this AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action/airplane group Work hours Average labor Parts cost Cost per product registered Fleet cost
rate per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Overhaul for Group 1; Configurations 64 $80 None.................... $5,120, per overhaul 652 $3,338,240
1, 2, and 3. cycle.
Inspection for Group 1, Configuration 1 80 None.................... $80, per inspection 525 42,000
3. cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 21253]]
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979), and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2009-09-07 Boeing: Amendment 39-15893. Docket No. FAA-2008-1070;
Directorate Identifier 2008-NM-087-AD.
Effective Date
(a) This airworthiness directive (AD) is effective June 11,
2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Boeing Model 737-100, -200, -200C, -
300, -400, and -500 series airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from reports of broken retract actuator
beams of the main landing gear (MLG) and the subsequent failure of
the MLG to fully retract. We are issuing this AD to detect and
correct broken retract actuator beams of the MLG, which could result
in damage to the beam arm, hydraulic tubing, and flight control
cables. Damage to the flight control cables could result in loss of
control of the airplane.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Inspection and Related Investigative and Corrective Actions/Overhaul
(f) Except as provided by paragraphs (g) and (h) of this AD: At
the applicable times specified in paragraph 1.E. of Boeing Service
Bulletin 737-32A1355, Revision 2, dated March 5, 2008, inspect for
damage of the retract actuator beam of the MLG and overhaul the
retract actuator beam, as applicable, by doing all the applicable
actions specified in the Accomplishment Instructions of Boeing
Service Bulletin 737-32A1355, Revision 2, dated March 5, 2008. Do
all applicable related investigative and corrective actions before
further flight. Repeat the applicable inspection or overhaul
thereafter at the applicable time specified in paragraph 1.E. of
Boeing Service Bulletin 737-32A1355, Revision 2, dated March 5,
2008.
Exceptions to Service Information
(g) Where Boeing Service Bulletin 737-32A1355, Revision 2, dated
March 5, 2008, specifies a compliance time after ``* * * the date on
this service bulletin,'' this AD requires compliance within the
specified compliance time after the effective date of this AD.
(h) Boeing Service Bulletin 737-32A1355, Revision 2, dated March
5, 2008, specifies that the actions are for airplanes with new MLG
retract actuator beams that have not been overhauled having part
number (P/N) 65-46108-15 and subsequent dash numbers; and new or
overhauled MLG retract actuator beams having P/N 65-46108-14 and
previous dash numbers. However, this AD is not limited to new or
overhauled beams. This AD requires that the actions required by
paragraph (f) of this AD be done on airplanes with any MLG retract
actuator beam having those P/Ns.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. Send information to
ATTN: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM-120S,
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057-3356; telephone (425) 917-6440; fax (425)
917-6590; or e-mail information to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
(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.
Material Incorporated by Reference
(j) You must use Boeing Service Bulletin 737-32A1355, Revision
2, dated March 5, 2008, to do the actions required by this AD,
unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington
98124-2207; telephone 206-544-9990; fax 206-766-5682; e-mail
DDCS@boeing.com; Internet https://www.myboeingfleet.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
[[Page 21254]]
Issued in Renton, Washington, on April 22, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-9926 Filed 5-6-09; 8:45 am]
BILLING CODE 4910-13-P
