[Federal Register: July 17, 2006 (Volume 71, Number 136)]
[Rules and Regulations]
[Page 40391-40394]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17jy06-4]
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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.
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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 http://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 http://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
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Average Number of U.S.-
Action Work labor rate Cost per airplane registered Fleet cost
hours per hour airplanes
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Inspection, per inspection cycle 10-100 $80 $800-$8,000, per 230 $184,000-$1,840,00
inspection cycle. 0, per inspection
cycle.
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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.
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
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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.
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Boeing Alert Service Bulletin 737-55-A1020, Revision 1, dated
August 20, 1976, contains the following effective pages:
[[Page 40394]]
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Page No. Revision level shown on page Date shown on page
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1, 11-27................................ 1............................... August 20, 1976.
2-10.................................... Original........................ May 20, 1976.
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Boeing Alert Service Bulletin 737-55-A1020, Revision 2, dated
February 11, 1977, contains the following effective pages:
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Page No. Revision level shown on page Date shown on page
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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.
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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 http://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 http://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