Airworthiness Directives; Boeing Model 737-100, -200, and -200C Series Airplanes, 40391-40394 [06-6152]
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Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules and Regulations
40391
Actions
Compliance
Procedures
Verify that the current flight idle blade angles
are set at 12 degrees. If not already set to 12
degrees, set the flight idle blade angles to 12
degrees.
Within the next 100 hours time-in-service after
August 21, 2006 (the effective date of this
AD).
Follow Mitsubishi Aircraft International, Inc.
Service Bulletin No. SB016/61–001, dated
March 18, 1980.
Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(f) The Manager, Forth Worth Aircraft
Certification Office (ACO), FAA, ATTN: Rao
Edupuganti, Aerospace Engineer, Fort Worth
ACO, ASW–150, Rotorcraft Directorate, FAA,
2601 Meacham Boulevard, Fort Worth, Texas
76137–4298; telephone: 817–222–5284;
facsimile: 817–222–5960, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Federal Aviation Administration
Material Incorporated by Reference
(g) You must do the actions required by
this AD following the instructions in
Mitsubishi Aircraft International, Inc. Service
Bulletin No. SB016/61–001, dated March 18,
1980. The Director of the Federal Register
approved the incorporation by reference of
this service bulletin in accordance with 5
U.S.C. 552(a) and 1 CFR part 51. To get a
copy of this service information, contact
Mitsubishi Heavy Industries, Ltd., 4951
Airport Parkway, Suite 800, Addison, Texas
75001 telephone: 972–934–5480; facsimile:
972–934–5488. To review copies of this
service information, go to the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, go to: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html or call (202) 741–6030. To
view the AD docket, go to the Docket
Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW.,
Nassif Building, Room PL–401, Washington,
DC 20590–001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
2006–23644; Directorate Identifier 2006–CE–
03–AD.
Issued in Kansas City, Missouri, on July 5,
2006.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 06–6179 Filed 7–14–06; 8:45 am]
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14 CFR Part 39
[Docket No. FAA–2006–24432; Directorate
Identifier 2005–NM–227–AD; Amendment
39–14678; AD 2006–14–07]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–100, –200, and –200C Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Boeing Model
737 series airplanes. That AD currently
requires inspection of the elevator tab
inboard hinge support structure to
detect fatigue cracking and corrective
action if necessary. That AD also
provides an optional terminating action.
This new AD adds airplanes to the
applicability and requires new
repetitive inspections. For airplanes
having elevators with laminated rear
spars, this new AD requires repetitive
inspections for interlaminar corrosion,
delamination, or disbonding in the rear
spar, repetitive inspections for cracking
in the spar web, and repair including
related investigative/corrective actions
if necessary. For airplanes having
elevators with solid rear spars, this new
AD requires repetitive inspections for
cracking in the spar web and repair
including related investigative/
corrective actions if necessary. This AD
results from reports of cracks in the
elevator rear spar web at the tab hinge
bracket locations. We are issuing this
AD to detect and correct cracking,
corrosion, interlaminar corrosion,
delamination, and disbonding in the
elevator rear spar, which may reduce
elevator stiffness and lead to in-flight
vibration. In-flight vibration may lead to
elevator and horizontal stabilizer
damage and reduced controllability of
the airplane.
DATES: This AD becomes effective
August 21, 2006.
The Director of the Federal Register
approved the incorporation by reference
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of certain publications listed in the AD
as of August 21, 2006.
ADDRESSES: You may examine 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., Nassif Building, Room PL–401,
Washington, DC.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
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:
Examining the Docket
You may examine the airworthiness
directive (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 street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 76–11–05 R1,
amendment 39–6234 (54 FR 25709, June
19, 1989). The existing AD applies to
certain Boeing Model 737 series
airplanes. That NPRM was published in
the Federal Register on April 13, 2006
(71 FR 19144). That NPRM proposed to
continue to require inspection of the
elevator tab inboard hinge support
structure to detect fatigue cracking and
corrective action if necessary. That
NPRM also proposed to continue to
provide an optional terminating action
for the existing inspections. That NPRM
proposed to add airplanes to the
applicability and to require new
repetitive inspections. For airplanes
having elevators with laminated rear
spars, that NPRM proposed to require
repetitive inspections for interlaminar
corrosion, delamination, or disbonding
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Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules and Regulations
in the rear spar, repetitive inspections
for cracking in the spar web, and repair
including related investigative/
corrective actions if necessary. For
airplanes having elevators with solid
rear spars, that NPRM proposed to
require repetitive inspections for
cracking in the spar web and repair
including related investigative/
corrective actions if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. No comments
have been received on the NPRM or on
the determination of the cost to the
public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed.
Costs of Compliance
There are about 1,355 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
ESTIMATED COSTS
Action
Inspection, per inspection cycle
Average
labor rate
per hour
Work
hours
10–100
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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 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.
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Cost per airplane
$80
$800–$8,000,
cycle.
per
inspection
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 14 CFR part 39 as
follows:
I
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 39–6234 (54
FR 25709, June 19, 1989) and by adding
the following new airworthiness
directive (AD):
I
2006–14–07 Boeing: Amendment 39–14678.
Docket No. FAA–2006–24432;
Directorate Identifier 2005–NM–227–AD.
Effective Date
(a) This AD becomes effective August 21,
2006.
Affected ADs
(b) This AD supersedes AD 76–11–05 R1.
Applicability
(c) This AD applies to Boeing Model 737–
100, –200, and –200C series airplanes,
certificated in any category; as identified in
Boeing Alert Service Bulletin 737–55A1078,
dated October 27, 2005.
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Number of
U.S.-registered
airplanes
230
Fleet cost
$184,000–$1,840,000, per inspection cycle.
Unsafe Condition
(d) This AD results from reports of cracks
in the elevator rear spar web at the tab hinge
bracket locations. We are issuing this AD to
detect and correct cracking, corrosion,
interlaminar corrosion, delamination, and
disbonding in the elevator rear spar, which
may reduce elevator stiffness and lead to inflight vibration. In-flight vibration may lead
to elevator and horizontal stabilizer damage
and reduced controllability of the airplane.
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
76–11–05 R1
(f) For Model 737–100, –200, and –200C
series airplanes, line number 001 through
491 inclusive: Within the next 300 hours
time-in-service after July 24, 1989 (the
effective date of AD 76–11–05 R1), unless
accomplished within the last 700 hours timein-service, and at intervals thereafter not to
exceed 1,000 hours time-in-service, conduct
the inspection required by paragraph (g) of
this AD. Accomplishing the initial
inspections specified in paragraph (j) of this
AD terminates the requirements of this
paragraph.
(g) For Model 737–100, –200, and –200C
series airplanes, line number 001 through
491 inclusive: At the times specified in
paragraph (f) of this AD, inspect for excessive
deflection of the elevator tab, right and left
hand, in accordance with the inspection
procedures specified in Section III, Part I,
paragraphs C. and D., of Boeing Alert Service
Bulletin 737–55–A1020, Revision 1, dated
August 20, 1976; Revision 2, dated February
11, 1977; or 737–55A1020, Revision 3, dated
December 22, 1988. If the elevator tab-toelevator relative deflection exceeds 1/10
inch, prior to further flight, modify the
elevator in accordance with paragraph (h) of
this AD. Accomplishing the initial
inspections specified in paragraph (j) of this
AD terminates the requirements of this
paragraph.
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(h) For Model 737–100, –200, and –200C
series airplanes, line number 001 through
491 inclusive: Installation of one of the
modifications specified in Boeing Alert
Service Bulletin 737–55–A1020, Revision 1,
dated August 20, 1976; 737–55–A1020,
Revision 2, dated February 11, 1977; or 737–
55A1020, Revision 3, dated December 22,
1988; Section III, Part II, including
installation of the bolt retainer clips or the
preventive modification specified in Boeing
Service Bulletin 737–55–1022, Section III,
Part II, dated April 15, 1977; is considered
terminating action for the inspection
requirements of paragraph (g) of this AD.
New Requirements of This AD
Determine Elevator Group Number or
Elevator Configuration Number
(i) Within 1,000 flight hours or 750 flight
cycles after the effective date of this AD,
whichever occurs first, determine the
elevator group number or the elevator
configuration number in accordance with
Appendix A of Boeing Alert Service Bulletin
737–55A1078, dated October 27, 2005.
Initial and Repetitive Inspections
(j) At the applicable time specified in
Tables 2 and 3 of paragraph 1.E.
‘‘Compliance’’ of Boeing Alert Service
Bulletin 737–55A1078, dated October 27,
2005, except where the alert service bulletin
specifies a compliance time from the release
date of the alert service bulletin, this AD
requires the compliance time after the
effective date of this AD: Do the applicable
initial detailed and special detailed
inspections for interlaminar corrosion,
cracking, delamination, or disbonding in the
rear spar by doing all the applicable actions
specified in Parts I, II, and III of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–55A1078, dated October
27, 2005; except where step 3. of Part III of
the alert service bulletin specifies to do a
special detailed inspection for spar
interlaminar corrosion as given in Figure 3,
this AD requires all actions specified in
Figure 3 to be done (a detailed inspection for
interlaminar corrosion and disbonding and a
special detailed inspection for interlaminar
corrosion and delamination). Doing the
initial inspections terminates the
requirements of paragraphs (f) and (g) of this
AD.
(k) Repeat the inspections specified in
paragraph (j) of this AD at the applicable time
specified in Tables 4 and 5 of paragraph 1.E.
‘‘Compliance’’ of Boeing Alert Service
Bulletin 737–55A1078, dated October 27,
2005; except where Table B.4 in Appendix B
of the alert service bulletin specifies
compliance times in flight hours or flight
cycles, this AD requires the actions specified
in Table B.4 be done at the earlier of the
compliance times in flight hours or flight
cycles.
Corrective Actions
(l) If any interlaminar corrosion, cracking,
delamination, or disbonding is found during
any inspection required by this AD: Before
further flight, use Appendix C of Boeing
Alert Service Bulletin 737–55A1078, dated
October 27, 2005, to determine the permitted
repairs, and do the applicable repair,
including related investigative and corrective
actions, by doing all the applicable actions
specified in Parts IV through VIII (Interim
Repairs) and Part IX (Time-limited Repair) of
the Accomplishment Instructions of the alert
service bulletin, except as provided by
paragraphs (n) and (o) of this AD.
(m) If the time-limited repair specified in
Part IX of the Accomplishment Instructions
of Boeing Alert Service Bulletin 737–
55A1078, dated October 27, 2005, is done: At
the time specified in Table 6 of paragraph
1.E. ‘‘Compliance’’ of the alert service
bulletin, do the applicable repair, including
related investigative and corrective actions,
by doing all the applicable actions specified
in Parts IV through VI (Interim Repairs) of the
alert service bulletin. Thereafter, do the
repetitive inspections specified in paragraph
(k) of this AD.
(n) Where Boeing Alert Service Bulletin
737–55A1078, dated October 27, 2005,
specifies to contact the manufacturer for
appropriate action for the inspar rib
replacement or for more instructions if any
crack is outside the limit specified in the
service bulletin: Before further flight, repair
in accordance with a method approved by
the Manager, Seattle Aircraft Certification
Office (ACO), FAA; or using a method
approved in accordance with paragraph (p) of
this AD.
(o) Where step 3.a. of Part III of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–55A1078, dated October
27, 2005, specifies that if interlaminar
corrosion is found, spar replacement is
required, this AD requires spar replacement
if interlaminar corrosion, delamination, or
disbonding is found. Where step 3.C. of
Appendix C of the alert service bulletin
specifies that for laminated spars that have
interlaminar corrosion, only repair options B,
C, and D are permitted, this AD specifies that
for laminated spars that have interlaminar
corrosion, delamination, or disbonding, only
repair options B, C, and D are permitted.
Alternative Methods of Compliance
(AMOCs)
(p)(1) The Manager, 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) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by 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.
(4) Accomplishing the Interim Repair
Option C or D specified in the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–55A1078, dated October
27, 2005, is an AMOC for the structural
modification requirements specified in
paragraph A. of AD 90–06–02, amendment
39–6489, that are done in accordance with
Boeing Alert Service Bulletins 737–55-A1020
or 737–55A1020, or Boeing Service Bulletin
737–55–1022 only. All provisions of AD 90–
06–02 that do not specifically reference these
service bulletins remain fully applicable and
must be complied with.
(5) AMOCs approved previously in
accordance with AD 76–11–05 R1, are
approved as AMOCs for the corresponding
provisions of paragraphs (f) through (h) of
this AD.
Material Incorporated by Reference
(q) You must use the applicable service
bulletins listed in Table 1 of this AD to
perform the actions that are required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference of these
documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
TABLE 1.—MATERIAL INCORPORATED BY REFERENCE
Service Bulletin
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Boeing
Boeing
Boeing
Boeing
Boeing
Revision level
Alert Service Bulletin 737–55A1020 ..............................................................................................
Alert Service Bulletin 737–55A1020 ..............................................................................................
Alert Service Bulletin 737–55A1020 ..............................................................................................
Alert Service Bulletin 737–55A1078 ..............................................................................................
Service Bulletin 737–55–1022 .......................................................................................................
Date
1 .......................
2 .......................
3 .......................
Original .............
Original .............
August 20, 1976.
February 11, 1977.
December 22, 1988.
October 27, 2005.
April 15, 1977.
Boeing Alert Service Bulletin 737–55–
A1020, Revision 1, dated August 20, 1976,
contains the following effective pages:
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Page No.
Revision level
shown on page
Date shown on page
1, 11–27 ......................................................................................................................................................
2–10 ............................................................................................................................................................
1 .......................
Original .............
August 20, 1976.
May 20, 1976.
Page No.
Revision level
shown on page
Date shown on page
1, 3, 6, 10–12, 14, 16, 25 ...........................................................................................................................
2, 4, 5, 7–9 .................................................................................................................................................
13, 15, 17–24, 26, 27 .................................................................................................................................
2 .......................
Original .............
1 .......................
February 11, 1977.
May 20, 1976.
August 20, 1976.
Boeing Alert Service Bulletin 737–55–
A1020, Revision 2, dated February 11, 1977,
contains the following effective pages:
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 Docket
Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW.,
Room PL–401, Nassif Building, Washington,
DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records
Administration (NARA). For information on
the availability of this material at the 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 July 3,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–6152 Filed 7–14–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2006–24813; Airspace
Docket No. 06–AAL–16]
Modification of Legal Description of
Class D and E Airspace; Fairbanks,
Fort Wainwright Army Airfield, AK
Federal Aviation
Administration (FAA), DOT.
ACTION: Direct final rule Correction;
request for comments.
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AGENCY:
SUMMARY: The U.S. Army will soon be
changing the name of Fort (Ft.)
Wainwright Army Airfield (AAF) to
Ladd AAF. This action amends the
airport name accordingly for each of the
Class D and Class E airspace
descriptions in FAA Order 7400.9N.
This action also amends an altitude
omission which currently does not exist
in the FAA Order 7400.9N. This action
also redefines the airspace description
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to account for recent updates to the
airfield coordinates.
DATES: This direct final rule is effective
on 0901 UTC, November 23, 2006.
Comments for inclusion in the Rules
Docket must be received on or before
August 16, 2006.
ADDRESSES: Send comments on this
proposal to the Docket Management
System, U.S. Department of
Transportation, Room Plaza 401, 400
Seventh Street, SW., Washington, DC
20590–0001. You must identify the
docket number FAA–2006–24813/
Airspace Docket No. 06–AAL–16, at the
beginning of your comments. You may
also submit comments on the Internet at
https://dms.dot.gov. You may review the
public docket containing the proposal,
any comments received, and any final
disposition in person in the Docket
Office between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The Docket Office (telephone
1–800–647–5527) is on the plaza level
of the Department of Transportation
NASSIF Building at the above address.
FOR FURTHER INFORMATION CONTACT: Gary
Rolf, Federal Aviation Administration,
222 West 7th Avenue, Box 14,
Anchorage, AK 99513–7587; telephone
number (907) 271–5898; fax: (907) 271–
2850; e-mail: gary.ctr.rolf@faa.gov.
Internet address: https://
www.alaska.faa.gov/at.
SUPPLEMENTARY INFORMATION: The
coordinates for this airspace docket are
based on North American Datum 83.
The Class D airspace and Class E
airspace areas designated as 700/1200
foot transition areas are published in
paragraph 5000 and 6005 respectively,
in FAA Order 7400.9N, Airspace
Designations and Reporting Points,
dated September 1, 2005, and effective
September 15, 2005, which is
incorporated by reference in 14 CFR
71.1. The Class D and E airspace
designations listed in this document
would be published subsequently in the
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Order. Additionally, the present
exclusionary clause listed in the Class
E5 description is removed. The
exclusionary language is redundant and
therefore, unnecessary.
The Direct Final Rule Procedure
The FAA anticipates that this
regulation will not result in adverse or
negative comment and therefore, is
issuing it as a direct final rule. Previous
actions of this nature have not been
controversial and have not resulted in
adverse comments or objections. Unless
a written adverse or negative comment,
or written notice of intent to submit an
adverse or negative comment is received
within the comment period, the
regulation will become effective on the
date specified above. After the close of
the comment period, the FAA will
publish a document in the Federal
Register indicating that no adverse or
negative comments were received and
confirming the date on which the final
rule will become effective. If the FAA
does receive, within the comment
period, an adverse or negative comment,
or written notice of intent to submit
such a comment, a document
withdrawing the direct final rule will be
published in the Federal Register, and
a notice of proposed rulemaking may be
published with a new comment period.
Comments Invited
Interested parties are invited to
participate in this rulemaking by
submitting such written data, views, or
arguments, as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
developing reasoned regulatory
decisions on the proposal. Comments
are specifically invited on the overall
regulatory, aeronautical, economic,
environmental, and energy-related
aspects of the proposal.
Communications should identify both
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]]>Agencies
[Federal Register Volume 71, Number 136 (Monday, July 17, 2006)]
[Rules and Regulations]
[Pages 40391-40394]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-6152]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24432; Directorate Identifier 2005-NM-227-AD;
Amendment 39-14678; AD 2006-14-07]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-100, -200, and -200C
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Boeing Model 737 series airplanes. That
AD currently requires inspection of the elevator tab inboard hinge
support structure to detect fatigue cracking and corrective action if
necessary. That AD also provides an optional terminating action. This
new AD adds airplanes to the applicability and requires new repetitive
inspections. For airplanes having elevators with laminated rear spars,
this new AD requires repetitive inspections for interlaminar corrosion,
delamination, or disbonding in the rear spar, repetitive inspections
for cracking in the spar web, and repair including related
investigative/corrective actions if necessary. For airplanes having
elevators with solid rear spars, this new AD requires repetitive
inspections for cracking in the spar web and repair including related
investigative/corrective actions if necessary. This AD results from
reports of cracks in the elevator rear spar web at the tab hinge
bracket locations. We are issuing this AD to detect and correct
cracking, corrosion, interlaminar corrosion, delamination, and
disbonding in the elevator rear spar, which may reduce elevator
stiffness and lead to in-flight vibration. In-flight vibration may lead
to elevator and horizontal stabilizer damage and reduced
controllability of the airplane.
DATES: This AD becomes effective August 21, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of August 21,
2006.
ADDRESSES: You may examine 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., Nassif Building,
Room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.
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:
Examining the Docket
You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 76-11-05 R1, amendment
39-6234 (54 FR 25709, June 19, 1989). The existing AD applies to
certain Boeing Model 737 series airplanes. That NPRM was published in
the Federal Register on April 13, 2006 (71 FR 19144). That NPRM
proposed to continue to require inspection of the elevator tab inboard
hinge support structure to detect fatigue cracking and corrective
action if necessary. That NPRM also proposed to continue to provide an
optional terminating action for the existing inspections. That NPRM
proposed to add airplanes to the applicability and to require new
repetitive inspections. For airplanes having elevators with laminated
rear spars, that NPRM proposed to require repetitive inspections for
interlaminar corrosion, delamination, or disbonding
[[Page 40392]]
in the rear spar, repetitive inspections for cracking in the spar web,
and repair including related investigative/corrective actions if
necessary. For airplanes having elevators with solid rear spars, that
NPRM proposed to require repetitive inspections for cracking in the
spar web and repair including related investigative/corrective actions
if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. No comments have been received on the NPRM or
on the determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed.
Costs of Compliance
There are about 1,355 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Average Number of U.S.-
Action Work labor rate Cost per airplane registered Fleet cost
hours per hour airplanes
----------------------------------------------------------------------------------------------------------------
Inspection, per inspection cycle 10-100 $80 $800-$8,000, per 230 $184,000-$1,840,00
inspection cycle. 0, 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 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 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.
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 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 39-6234 (54 FR 25709, June 19, 1989) and by adding
the following new airworthiness directive (AD):
2006-14-07 Boeing: Amendment 39-14678. Docket No. FAA-2006-24432;
Directorate Identifier 2005-NM-227-AD.
Effective Date
(a) This AD becomes effective August 21, 2006.
Affected ADs
(b) This AD supersedes AD 76-11-05 R1.
Applicability
(c) This AD applies to Boeing Model 737-100, -200, and -200C
series airplanes, certificated in any category; as identified in
Boeing Alert Service Bulletin 737-55A1078, dated October 27, 2005.
Unsafe Condition
(d) This AD results from reports of cracks in the elevator rear
spar web at the tab hinge bracket locations. We are issuing this AD
to detect and correct cracking, corrosion, interlaminar corrosion,
delamination, and disbonding in the elevator rear spar, which may
reduce elevator stiffness and lead to in-flight vibration. In-flight
vibration may lead to elevator and horizontal stabilizer damage and
reduced controllability of the airplane.
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 76-11-05 R1
(f) For Model 737-100, -200, and -200C series airplanes, line
number 001 through 491 inclusive: Within the next 300 hours time-in-
service after July 24, 1989 (the effective date of AD 76-11-05 R1),
unless accomplished within the last 700 hours time-in-service, and
at intervals thereafter not to exceed 1,000 hours time-in-service,
conduct the inspection required by paragraph (g) of this AD.
Accomplishing the initial inspections specified in paragraph (j) of
this AD terminates the requirements of this paragraph.
(g) For Model 737-100, -200, and -200C series airplanes, line
number 001 through 491 inclusive: At the times specified in
paragraph (f) of this AD, inspect for excessive deflection of the
elevator tab, right and left hand, in accordance with the inspection
procedures specified in Section III, Part I, paragraphs C. and D.,
of Boeing Alert Service Bulletin 737-55-A1020, Revision 1, dated
August 20, 1976; Revision 2, dated February 11, 1977; or 737-
55A1020, Revision 3, dated December 22, 1988. If the elevator tab-
to-elevator relative deflection exceeds 1/10 inch, prior to further
flight, modify the elevator in accordance with paragraph (h) of this
AD. Accomplishing the initial inspections specified in paragraph (j)
of this AD terminates the requirements of this paragraph.
[[Page 40393]]
(h) For Model 737-100, -200, and -200C series airplanes, line
number 001 through 491 inclusive: Installation of one of the
modifications specified in Boeing Alert Service Bulletin 737-55-
A1020, Revision 1, dated August 20, 1976; 737-55-A1020, Revision 2,
dated February 11, 1977; or 737-55A1020, Revision 3, dated December
22, 1988; Section III, Part II, including installation of the bolt
retainer clips or the preventive modification specified in Boeing
Service Bulletin 737-55-1022, Section III, Part II, dated April 15,
1977; is considered terminating action for the inspection
requirements of paragraph (g) of this AD.
New Requirements of This AD
Determine Elevator Group Number or Elevator Configuration Number
(i) Within 1,000 flight hours or 750 flight cycles after the
effective date of this AD, whichever occurs first, determine the
elevator group number or the elevator configuration number in
accordance with Appendix A of Boeing Alert Service Bulletin 737-
55A1078, dated October 27, 2005.
Initial and Repetitive Inspections
(j) At the applicable time specified in Tables 2 and 3 of
paragraph 1.E. ``Compliance'' of Boeing Alert Service Bulletin 737-
55A1078, dated October 27, 2005, except where the alert service
bulletin specifies a compliance time from the release date of the
alert service bulletin, this AD requires the compliance time after
the effective date of this AD: Do the applicable initial detailed
and special detailed inspections for interlaminar corrosion,
cracking, delamination, or disbonding in the rear spar by doing all
the applicable actions specified in Parts I, II, and III of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
55A1078, dated October 27, 2005; except where step 3. of Part III of
the alert service bulletin specifies to do a special detailed
inspection for spar interlaminar corrosion as given in Figure 3,
this AD requires all actions specified in Figure 3 to be done (a
detailed inspection for interlaminar corrosion and disbonding and a
special detailed inspection for interlaminar corrosion and
delamination). Doing the initial inspections terminates the
requirements of paragraphs (f) and (g) of this AD.
(k) Repeat the inspections specified in paragraph (j) of this AD
at the applicable time specified in Tables 4 and 5 of paragraph 1.E.
``Compliance'' of Boeing Alert Service Bulletin 737-55A1078, dated
October 27, 2005; except where Table B.4 in Appendix B of the alert
service bulletin specifies compliance times in flight hours or
flight cycles, this AD requires the actions specified in Table B.4
be done at the earlier of the compliance times in flight hours or
flight cycles.
Corrective Actions
(l) If any interlaminar corrosion, cracking, delamination, or
disbonding is found during any inspection required by this AD:
Before further flight, use Appendix C of Boeing Alert Service
Bulletin 737-55A1078, dated October 27, 2005, to determine the
permitted repairs, and do the applicable repair, including related
investigative and corrective actions, by doing all the applicable
actions specified in Parts IV through VIII (Interim Repairs) and
Part IX (Time-limited Repair) of the Accomplishment Instructions of
the alert service bulletin, except as provided by paragraphs (n) and
(o) of this AD.
(m) If the time-limited repair specified in Part IX of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
55A1078, dated October 27, 2005, is done: At the time specified in
Table 6 of paragraph 1.E. ``Compliance'' of the alert service
bulletin, do the applicable repair, including related investigative
and corrective actions, by doing all the applicable actions
specified in Parts IV through VI (Interim Repairs) of the alert
service bulletin. Thereafter, do the repetitive inspections
specified in paragraph (k) of this AD.
(n) Where Boeing Alert Service Bulletin 737-55A1078, dated
October 27, 2005, specifies to contact the manufacturer for
appropriate action for the inspar rib replacement or for more
instructions if any crack is outside the limit specified in the
service bulletin: Before further flight, repair in accordance with a
method approved by the Manager, Seattle Aircraft Certification
Office (ACO), FAA; or using a method approved in accordance with
paragraph (p) of this AD.
(o) Where step 3.a. of Part III of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-55A1078, dated
October 27, 2005, specifies that if interlaminar corrosion is found,
spar replacement is required, this AD requires spar replacement if
interlaminar corrosion, delamination, or disbonding is found. Where
step 3.C. of Appendix C of the alert service bulletin specifies that
for laminated spars that have interlaminar corrosion, only repair
options B, C, and D are permitted, this AD specifies that for
laminated spars that have interlaminar corrosion, delamination, or
disbonding, only repair options B, C, and D are permitted.
Alternative Methods of Compliance (AMOCs)
(p)(1) The Manager, 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) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by 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.
(4) Accomplishing the Interim Repair Option C or D specified in
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-55A1078, dated October 27, 2005, is an AMOC for the structural
modification requirements specified in paragraph A. of AD 90-06-02,
amendment 39-6489, that are done in accordance with Boeing Alert
Service Bulletins 737-55-A1020 or 737-55A1020, or Boeing Service
Bulletin 737-55-1022 only. All provisions of AD 90-06-02 that do not
specifically reference these service bulletins remain fully
applicable and must be complied with.
(5) AMOCs approved previously in accordance with AD 76-11-05 R1,
are approved as AMOCs for the corresponding provisions of paragraphs
(f) through (h) of this AD.
Material Incorporated by Reference
(q) You must use the applicable service bulletins listed in
Table 1 of this AD to perform the actions that are required by this
AD, unless the AD specifies otherwise. The Director of the Federal
Register approved the incorporation by reference of these documents
in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Table 1.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
Boeing Alert Service Bulletin 737- 1............................... August 20, 1976.
55A1020.
Boeing Alert Service Bulletin 737- 2............................... February 11, 1977.
55A1020.
Boeing Alert Service Bulletin 737- 3............................... December 22, 1988.
55A1020.
Boeing Alert Service Bulletin 737- Original........................ October 27, 2005.
55A1078.
Boeing Service Bulletin 737-55-1022..... Original........................ April 15, 1977.
----------------------------------------------------------------------------------------------------------------
Boeing Alert Service Bulletin 737-55-A1020, Revision 1, dated
August 20, 1976, contains the following effective pages:
[[Page 40394]]
----------------------------------------------------------------------------------------------------------------
Page No. Revision level shown on page Date shown on page
----------------------------------------------------------------------------------------------------------------
1, 11-27................................ 1............................... August 20, 1976.
2-10.................................... Original........................ May 20, 1976.
----------------------------------------------------------------------------------------------------------------
Boeing Alert Service Bulletin 737-55-A1020, Revision 2, dated
February 11, 1977, contains the following effective pages:
----------------------------------------------------------------------------------------------------------------
Page No. Revision level shown on page Date shown on page
----------------------------------------------------------------------------------------------------------------
1, 3, 6, 10-12, 14, 16, 25.............. 2............................... February 11, 1977.
2, 4, 5, 7-9............................ Original........................ May 20, 1976.
13, 15, 17-24, 26, 27................... 1............................... August 20, 1976.
----------------------------------------------------------------------------------------------------------------
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 Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif
Building, Washington, DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the 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 July 3, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-6152 Filed 7-14-06; 8:45 am]
BILLING CODE 4910-13-P
