[Federal Register: June 27, 2005 (Volume 70, Number 122)]
[Rules and Regulations]
[Page 36829-36831]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr27jn05-10]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-289-AD; Amendment 39-14167; AD 2005-13-30]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-100, -200, and -200C
Series Airplanes
AGENCY: Federal Aviation Administration, Department of Transportation.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to all Boeing Model 737-100, -200, and -200C series
airplanes, that requires repetitive inspections to detect discrepancies
of certain fuselage skin panels located just aft of the wheel well, and
repair if necessary. The actions specified by this AD are intended to
detect and correct fatigue cracking of the skin panels, which could
cause rapid decompression of the airplane. This action is intended to
address the identified unsafe condition.
DATES: Effective August 1, 2005.
The incorporation by reference of a certain publication listed in
the regulations is approved by the Director of the Federal Register as
of August 1, 2005.
ADDRESSES: The service information referenced in this AD may be
obtained from Boeing Commercial Airplanes, 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.
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) to include an airworthiness
directive (AD) that is applicable to all Boeing Model 737-100, -200,
and -200C series airplanes was published as a supplemental notice of
proposed rulemaking (NPRM) in the Federal Register on April 1, 2005 (70
FR 16761).
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment that has been
submitted on the proposed AD.
Support for the Proposed AD
The commenter supports the proposed AD.
Conclusion
We have carefully reviewed the available data, including the
comment that has been submitted, and determined that air safety and the
public interest require adopting the AD as proposed.
Interim Action
This is considered to be interim action. The manufacturer has
advised that it is developing an improved preventive modification
intended to address the identified unsafe condition for unmodified skin
areas. After this modification is developed, approved, and available,
we may consider additional rulemaking.
Cost Impact
There are about 1,000 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 390 airplanes of U.S. registry
will be affected by this AD.
The inspection will take about 47 to 88 work hours per airplane
(depending on configuration), at an average labor rate of $65 per work
hour. Based on these figures, we estimate the cost of the inspection to
be $3,055 to $5,720 per airplane, per inspection cycle.
The cost impact figure discussed above is 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.
[[Page 36830]]
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 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 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 adding the following new airworthiness
directive:
2005-13-30 Boeing: Amendment 39-14167. Docket 2002-NM-289-AD.
Applicability: All Model 737-100, -200, and -200C series
airplanes; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct fatigue cracking of the skin panels, which
could cause rapid decompression of the airplane, accomplish the
following:
Repetitive Inspections: Unmodified Skin Areas
(a) For fuselage skin panel areas that have not been modified
with stiffening angles: Before the airplane accumulates 16,000 total
flight cycles, or within 4,500 flight cycles after the effective
date of this AD, whichever occurs later, inspect the unmodified
fuselage side skins just aft of the main wheelwell, and perform all
follow-on actions, in accordance with Part I of the Accomplishment
Instructions of Boeing Service Bulletin 737-53-1065, Revision 2,
dated April 19, 2001; except as provided by paragraph (g) of this
AD. If no cracking, loose fasteners, disbonding, or damage is found:
Repeat the inspection at the time specified in paragraph 1.E.,
Compliance, of the service bulletin, as applicable, except as
provided by paragraph (d) of this AD.
Repetitive Inspections: Modified Skin Areas
(b) For fuselage skin panel areas that have been modified with
stiffening angles in accordance with Boeing Service Bulletin 737-53-
1065, dated January 4, 1985; Revision 1, dated October 12, 1989; or
Revision 2, dated April 19, 2001: Before the airplane accumulates
16,000 total flight cycles, or within 4,500 flight cycles after the
effective date of this AD, whichever occurs later, inspect the
modified areas as specified in accordance with Part I of Boeing
Service Bulletin 737-53-1065, Revision 2, dated April 19, 2001.
Repeat the inspection at the time specified in paragraph 1.E., of
the service bulletin, as applicable, except as provided by paragraph
(d) of this AD. If any cracks, loose fasteners, disbonding, or
damage is found: Repair before further flight in accordance with the
requirements of paragraph (d) of this AD.
Terminating Action for Inspections of Modified Skin Areas
(c) For fuselage skin panel areas that have been modified with
stiffening angles in accordance with Boeing Service Bulletin 737-53-
1065, dated January 4, 1985; Revision 1, dated October 12, 1989; or
Revision 2, dated April 19, 2001: At the later of the times
specified by paragraphs (c)(1) and (c)(2) of this AD, perform a
subsurface eddy current or magneto optical imaging inspection to
detect subsurface skin cracks along the edge of the bonded doubler,
in accordance with Figure 10 of Boeing Service Bulletin 737-53-1065,
Revision 2, dated April 19, 2001; except as provided by paragraph
(g) of this AD. If any cracks are found, repair before further
flight in accordance with paragraph (d) of this AD. Accomplishment
of this inspection and all applicable corrective actions terminates
the repetitive inspections required by paragraph (b) of this AD for
the modified areas.
(1) Inspect within 24,500, but not fewer than 20,000, flight
cycles after the modification of the skin.
(2) Inspect within 4,500 flight cycles after the effective date
of this AD.
Repair: Modified and Unmodified Skin Areas
(d) If any cracking is detected during any inspection required
by this AD: Do the actions specified by paragraph (d)(1) or (d)(2)
of this AD before further flight. Do the actions in accordance with
Boeing Service Bulletin 737-53-1065, Revision 2, dated April 19,
2001, except as required by paragraph (e) of this AD.
(1) Do a time-limited repair (including a detailed inspection of
the skin in the area of the repair to detect corrosion and doubler
disbonding) in accordance with Part III of the Accomplishment
Instructions of the service bulletin.
(i) After the time-limited repair has been accomplished: At
intervals not to exceed 3,000 flight cycles, perform an external
general visual inspection of the repair to detect loose or missing
fasteners, in accordance with Part III of the Accomplishment
Instructions of the service bulletin, until the actions specified in
paragraph (d)(1)(v) of this AD have been accomplished.
(ii) Within 4,500 flight cycles after the time-limited repair
has been accomplished: Perform an internal inspection of the repair
to detect cracking or doubler disbonding using general visual and
high-frequency eddy current methods, in accordance with Figure 11 of
the service bulletin, unless the actions specified in paragraph
(d)(1)(v) of this AD have been accomplished.
(iii) If any cracking is found during any inspection required by
paragraph (d)(1) of this AD: Repair before further flight in
accordance with paragraph (e) of this AD. Another approved repair
method is in Section 53-30-3, Figure 48, of the Boeing 737
Structural Repair Manual (SRM).
(iv) If any disbonding is found during any inspection required
by paragraph (d)(1) of this AD: Repair before further flight in
accordance with Part II of the service bulletin.
(v) Within 10,000 flight cycles after accomplishment of the
time-limited repair: Make the repair permanent in accordance with
Part III of the Accomplishment Instructions of the service bulletin.
Permanent repair of an area terminates the repetitive inspections
specified in this AD for that repaired area only.
(2) Do a permanent repair (including an inspection using
external subsurface eddy
[[Page 36831]]
current or magneto optical imaging methods to detect cracks at the
chem-milled step in each adjacent bay of the fuselage skin, a
detailed inspection of the skin in the area of the repair for
corrosion and doubler disbonding, and applicable corrective action)
of the cracked area, in accordance with Part II of the
Accomplishment Instructions of the service bulletin. Another
approved repair method is in Section 53-30-3, Figure 48, of the
Boeing 737 SRM. Permanent repair of an area terminates the
repetitive inspections specified in this AD for that repaired area
only.
Exceptions to Service Bulletin Procedures
(e) During any inspection required by this AD, if any
discrepancy (including cracking) is detected for which the service
bulletin specifies to contact Boeing for appropriation action:
Before further flight, repair according to a method approved by the
Manager, Seattle Aircraft Certification Office (ACO), FAA; or
according to data meeting the certification basis of the airplane
approved by an Authorized Representative for the Boeing 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.
(f) Although Boeing Service Bulletin 737-53-1065, Revision 2,
dated April 19, 2001, recommends that cracks found in Zone 2 be
reported to Boeing, this AD does not require such a report.
(g) For airplanes subject to the requirements of paragraphs (a)
and (c) of this AD: Inspections are not required in areas that are
spanned by an FAA-approved repair that has a minimum of 3 rows of
fasteners above and below the chemical-milled step. If an external
doubler covers the chemical-milled step, but does not span it by a
minimum of 3 rows of fasteners above and below, one method of
compliance with the inspection requirement of paragraphs (a) and (c)
of this AD is to inspect all chemical-milled steps covered by the
repair using internal nondestructive test (NDT) methods in
accordance with Part 6, Subject 53-30-20, of the Boeing 737 NDT
Manual. Follow-on and corrective actions must be done as specified
in this AD.
Alternative Methods of Compliance (AMOCs)
(h)(1) In accordance with 14 CFR 39.19, the Manager, Seattle
ACO, FAA, is authorized to approve AMOCs 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 an
Authorized Representative for the Boeing 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.
Incorporation by Reference
(i) Unless otherwise specified in this AD, the actions must be
done in accordance with Boeing Service Bulletin 737-53-1065,
Revision 2, dated April 19, 2001. This incorporation by reference
was approved by the Director of the Federal Register in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of this
service information, contact Boeing Commercial Airplanes, P.O. Box
3707, Seattle, Washington 98124-2207. To inspect copies of this
service information, go to the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington; or to 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.
Effective Date
(j) This amendment becomes effective on August 1, 2005.
Issued in Renton, Washington, on June 14, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-12503 Filed 6-24-05; 8:45 am]
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