[Federal Register: November 18, 2003 (Volume 68, Number 222)]
[Rules and Regulations]
[Page 64980-64982]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18no03-2]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-150-AD; Amendment 39-13367; AD 2003-23-03]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-100, -200, and -200C
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain Boeing Model 737-100, -200, and -200C
series airplanes, that currently requires repetitive inspections to
detect discrepancies in the upper and lower skins of the fuselage lap
joint, and repair if necessary. This amendment adds new inspections,
reduces the repetitive inspection intervals for certain airplanes, and
mandates a terminating modification. The actions specified by this AD
are intended to detect and correct discrepancies in the upper and lower
skins of the fuselage lap joint and circumferential joint, which could
result in sudden fracture and failure of a lap joint or circumferential
joint and rapid decompression of the airplane fuselage. This action is
intended to address the identified unsafe condition.
DATES: Effective December 23, 2003.
The incorporation by reference of Boeing Alert Service Bulletin
737-53A1224, Revision 1, dated March 14, 2002, as listed in the
regulations, is approved by the Director of the Federal Register as of
December 23, 2003.
The incorporation by reference of Boeing Alert Service Bulletin
737-53A1224, dated August 17, 2000, as listed in the regulations, was
approved previously by the Director of the Federal Register as of
September 11, 2000 (65 FR 51750, August 25, 2000).
ADDRESSES: The service information referenced in this AD may be
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle,
Washington 98124-2207. This information may be examined at the Federal
Aviation Administration (FAA), Transport Airplane Directorate, Rules
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of
the Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Suzanne Lucier, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6438; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 2000-17-04,
amendment 39-11878 (65 FR 51750, August 25, 2000), which is applicable
to certain Boeing Model 737-100, -200, and -200C series airplanes, was
published in the Federal Register on July 21, 2003 (68 FR 43045). The
action proposed to require repetitive inspections to detect
discrepancies in the upper and lower skins of the fuselage lap joint,
and repair if necessary. The action proposed adding new inspections,
reducing the repetitive inspection intervals for certain airplanes, and
mandating a terminating modification.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule as proposed.
Change to Labor Rate Estimate
We have reviewed the figures we have used over the past several
years to calculate AD costs to operators. To account for various
inflationary costs in the airline industry, we find it necessary to
increase the labor rate used in these calculations from $60 per work
hour to $65 per work hour. The cost impact information, below, reflects
this increase in the specified hourly labor rate.
Cost Impact
There are approximately 291 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 60 airplanes of U.S. registry
will be affected by this AD.
The inspections that are currently required by AD 2000-17-04 take
approximately 575 work hours per airplane to accomplish, at an average
labor rate of $65 per work hour. Based on these figures, the cost
impact of the currently required inspections on U.S. operators is
estimated to be $2,242,500, or $37,375 per airplane.
The new inspections that are required by this new AD will take
approximately 341 work hours per airplane to accomplish, at an average
labor rate of $65 per work hour. Based on these figures, the cost
impact of the new inspections of this AD on U.S. operators is estimated
to be $1,329,900, or $22,165 per airplane.
The terminating modification that is required by this new AD will
take approximately 15,000 work hours per airplane to accomplish, at an
average labor rate of $65 per work hour. Based on these figures, the
cost impact of the modification of this AD on U.S. operators is
estimated to be $58,500,000, or $975,000 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the requirements of this
AD action, and that no operator would accomplish those actions in the
future if this AD were not adopted. The cost impact figures discussed
in AD rulemaking actions represent only the time necessary to perform
the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
Regulatory Impact
The regulations adopted herein 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. Therefore, it
is determined that this final rule does not
[[Page 64981]]
have federalism implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. Section 39.13 is amended by removing amendment 39-11878 (65 FR
51750, August 25, 2000), and by adding a new airworthiness directive
(AD), amendment 39-13367, to read as follows:
2003-23-03 Boeing: Amendment 39-13367. Docket 2002-NM-150-AD.
Supersedes AD 2000-17-04, Amendment 39-11878.
Applicability: Model 737-100, -200, and -200C series airplanes;
line numbers 1 through 291 inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct discrepancies in the upper and lower skins
of the fuselage lap joint and circumferential joint, which could
result in sudden fracture and failure of a lap joint or
circumferential joint and rapid decompression of the airplane
fuselage, accomplish the following:
Requirements of AD 2000-17-04, Amendment 39-11878
Initial and Repetitive Inspections
(a) Perform the applicable (initial and repetitive) inspections
as specified in Figures 1 through 4 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1224, dated
August 17, 2000, to detect discrepancies (i.e., cracks, pillowing,
corrosion, delamination, or loose or missing fasteners) in the upper
and lower skins of the fuselage lap joint. Perform the inspections
at the applicable times specified in Tables 1 and 2 of section 1.E.
`Compliance' of the alert service bulletin, in accordance with the
alert service bulletin; except that where Table 1 specifies a
compliance time of ``airplane flight cycles at time of service
bulletin release,'' this AD requires a compliance time of ``airplane
flight cycles as of September 11, 2000 (the effective date of AD
2000-17-04, amendment 39-11878).''
Repair
(b) Prior to further flight: Repair any discrepancies detected
during any inspection required by paragraph (a) of this AD in
accordance with Boeing Alert Service Bulletin 737-53A1224, dated
August 17, 2000; repair any discrepancies detected during any
inspection required by paragraph (c) of this AD in accordance with
Boeing Alert Service Bulletin 737-53A1224, Revision 1, dated March
14, 2002. If any discrepancy is detected and the alert service
bulletin specifies that the manufacturer may be contacted for
disposition of certain repairs, prior to further flight, repair in
accordance with a method approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or in accordance with data meeting
the type certification basis of the airplane approved by a Boeing
Company Designated Engineering Representative who has been
authorized by the Manager, Seattle ACO, to make such findings.
New Requirements of This AD
Compliance Times
(c) Where the compliance times in Section 1.E. `Compliance' of
Boeing Alert Service Bulletin 737-53A1224, Revision 1, dated March
14, 2002, specify a compliance time interval calculated ``from
release of service bulletin,'' this AD requires compliance within
the interval specified in the service bulletin ``after the effective
date of this AD.'' In addition, where the compliance time for the
initial and repetitive inspections in Tables 1 through 3 of section
1.E. `Compliance' of the service bulletin specifies ``airplane
flight cycles at time of service bulletin release,'' this AD
requires a compliance time of ``airplane flight cycles as of the
effective date of this AD.''
Initial and Repetitive Inspections
(d) Except as provided by paragraph (e) of this AD: Perform the
applicable (initial and repetitive) inspections as specified in
Figures 1 through 9 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1224, Revision 1, dated March 14,
2002, to detect discrepancies (i.e., cracks, pillowing, corrosion,
delamination, or loose or missing fasteners) in the upper and lower
skins of the fuselage lap joint and circumferential joint. Perform
the inspections at the applicable times specified in Tables 1 and 2
of section 1.E. ``Compliance'' of the alert service bulletin, in
accordance with the alert service bulletin, until accomplishment of
paragraph (f) of this AD. Accomplishment of this paragraph
terminates the inspections required by paragraph (a) of this AD.
(e) For airplanes that have accumulated more than 70,000 total
flight cycles as of the effective date of this AD: Do the first
repeat inspection at the earlier of the times specified in paragraph
(e)(1) or (e)(2) of this AD, and repeat the inspection thereafter at
intervals not to exceed 1,000 flight cycles.
(1) Within 2,000 flight cycles after the last inspection done
per AD 2000-17-04.
(2) Within 1,000 flight cycles after the last inspection done
per AD 2000-17-04, or within 500 flight cycles after the effective
date of this AD, whichever is later.
Terminating Modification
(f) Perform the modification of the skin of all fuselage lap
joints between body stations 259.5 and 1016 per part IV of the Work
Instructions of Boeing Alert Service Bulletin 737-53A1224, Revision
1, dated March 14, 2002; at the applicable times specified in Table
3 of section 1.E. ``Compliance'' of the alert service bulletin; in
accordance with the alert service bulletin. Accomplishment of this
paragraph terminates the repetitive inspection requirements of this
AD.
Alternative Methods of Compliance
(g)(1) In accordance with 14 CFR 39.19, the Manager, Seattle
ACO, is authorized to approve alternative methods of compliance
(AMOC) for this AD.
(2) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by a
Boeing Company Designated Engineering Representative who has been
authorized by the Manager, Seattle ACO, to make such findings.
Incorporation by Reference
(h) Unless otherwise specified by this AD, the actions shall be
done in accordance with Boeing Alert Service Bulletin 737-53A1224,
dated August 17, 2000; and Boeing Alert Service Bulletin 737-
53A1224, Revision 1, dated March 14, 2002; as applicable.
(1) The incorporation by reference of Boeing Alert Service
Bulletin 737-53A1224, Revision 1, dated March 14, 2002, is approved
by the Director of the Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) The incorporation by reference of Boeing Alert Service
Bulletin 737-53A1224, dated August 17, 2000, was approved previously
by the Director of the Federal Register as of September 11, 2000 (65
FR 51750, August 25, 2000).
(3) Copies may be obtained from Boeing Commercial Airplane
Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
Effective Date
(i) This amendment becomes effective on December 23, 2003.
[[Page 64982]]
Issues in Renton, Washington, on November 7, 2003.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-28492 Filed 11-17-03; 8:45 am]
BILLING CODE 4910-13-P