[Federal Register Volume 74, Number 200 (Monday, October 19, 2009)]
[Proposed Rules]
[Pages 53442-53445]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-24986]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0913; Directorate Identifier 2009-NM-101-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-600, -700, -700C, -
800, and -900 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Boeing Model 737-600, -700, -700C, -800, and -900 series
airplanes. This proposed AD would require inspections for scribe lines
in the fuselage skin at lap joints, the splice strap at certain butt
joints, the skin or doubler at certain approved repair doublers, and
the skin at decal locations; and related investigative and corrective
actions if necessary. This proposed AD results from reports of scribe
line damage found adjacent to the skin lap joints, decals, and wing-to-
body fairings. We are proposing this AD to detect and correct scribe
lines, which can develop into fatigue cracks in the skin. Undetected
fatigue cracks can grow and cause sudden decompression of the airplane.
DATES: We must receive comments on this proposed AD by December 3,
2009.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail [email protected];
Internet https://www.myboeingfleet.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information
on the availability of this material at the FAA, call 425-227-1221 or
425-227-1152.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office
[[Page 53443]]
(telephone 800-647-5527) is in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6447; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0913;
Directorate Identifier 2009-NM-101-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received reports indicating that scribe lines have been
found by multiple operators on Boeing Model 737-600, -700, -700C, -800,
and -900 series airplanes. The scribe lines appear to have been made on
the skin when sealant was removed as part of preparing the airplane for
repainting. One Model 737-700 operator reported scribe lines found
around the wing-to-body fairing between stringer 26L and stringer 25R
at station (STA) 727D to STA 727E. A second Model 737-700 operator
reported six vertical scribe lines up to 42 inches long on the upper
aft fuselage between stringer 5R and stringer 9R at STA 847 to STA 887.
Another 737-700 operator reported scribe lines along stringer 24L and
stringer 24R between STA 178 to STA 500B. The depth of the scribe lines
ranged from 0.001 inch to 0.004 inch. The airplanes had accumulated
between 595 and 17,571 total flight cycles. No cracks as a result of
scribe lines found on Model 737-600, -700, -700C, -800, and -900
airplanes have been reported to Boeing.
Related ADs
This proposed AD is similar to two existing ADs. AD 2006-07-12,
amendment 39-14539 (71 FR 16211, March 31, 2006), applies to Boeing
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD
2007-19-07, amendment 39-15198 (72 FR 60244, October 24, 2007), applies
to Boeing Model 757-200, -200PF, and -200CB series airplanes. Those ADs
require inspections to detect scribe lines in the fuselage skin at
certain lap joints, butt joints, external repair doublers, and other
areas; and related investigative/corrective actions if necessary. Those
actions resulted from reports of fuselage skin cracks adjacent to the
skin lap joints on airplanes that had scribe lines.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 737-53A1289, dated
January 14, 2009. That service bulletin describes procedures for
inspecting for scribe lines in the fuselage skin at lap joints, the
splice strap at certain butt joints, the skin or doubler at certain
approved repair doublers, and the skin at decal locations. That service
bulletin specifies removing paint and sealant from affected areas
before the initial inspection. The service bulletin specifies that the
compliance time for the inspections ranges between before accumulating
14,000 total flight cycles plus the first scribe line opportunity, and
75,000 total flight cycles, depending on the inspection location, or
within 4,000 flight cycles after the date the service bulletin was
issued (whichever occurs later).
That service bulletin specifies related investigative and
corrective actions. The related investigative actions include
performing repetitive detailed, high frequency eddy current,
ultrasonic, and/or ultrasonic phased array inspections of the scribe
lines to detect cracks. The repetitive inspection interval ranges
between 1,000 and 10,000 flight cycles, depending on the condition
found. The corrective actions include repairing scribe lines and
cracks. The service bulletin specifies to repair cracks before further
flight.
That service bulletin also specifies repairing scribe lines before
further flight, except when a limited return to service (LRTS) program
for qualifying scribe lines would allow return to service for a limited
period before scribe lines are repaired. The LRTS program includes
repetitive inspections to detect cracks where scribe lines are found.
To qualify for an LRTS program, scribe lines must meet certain criteria
based on their depth and location. That service bulletin specifies
final repair by using the structural repair manual or contacting Boeing
for instructions, which would eliminate the need for the repetitive
inspections of the LRTS program. The repetitive intervals for the LRTS
program range from 2,500 flight cycles to 10,000 flight cycles after
the scribe line is found, depending on the inspection location.
That service bulletin notes that certain inspections would not be
necessary under the following conditions:
The airplane has never been stripped or repainted, or the
airplane was stripped or repainted after July 1, 2007.
The airplane has never had decals installed, or decals
were installed after July 1, 2007.
For each repair, the airplane has never been stripped or
repainted since the repair was installed or the repair was installed
after July 1, 2007.
The area under the wing-to-body fairings has never been
stripped or repainted or the airplane was stripped or repainted after
July 1, 2007.
No sealant has been removed except in accordance with the
specified sealant removal processes given in Appendix A of the service
bulletin.
That service bulletin specifies submitting inspection results to
Boeing. The service bulletin also provides procedures for addressing
scribe lines detected before the initial inspection threshold.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
This proposed AD would require accomplishing the actions specified in
the service information described previously, except as discussed under
``Differences Between the Proposed AD and Service Bulletin.'' The
proposed AD would also require sending the inspection results to
Boeing.
Differences Between the Proposed AD and Service Bulletin
Where the service bulletin specifies contacting the manufacturer
for instructions on how to repair certain conditions, this proposed AD
would require repairing those conditions in one of the following ways:
Using a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by an Authorized Representative
for the
[[Page 53444]]
Boeing Commercial Airplanes Delegation Option Authorization
Organization whom we have authorized to make those findings.
Costs of Compliance
We estimate that this proposed AD would affect 782 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
Table--Estimated Costs
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Number of
Average U.S.-
Action Work hours labor rate Parts Cost per product registered Fleet cost
per hour airplanes
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Inspection........................... 53 $80 $0 $4,240 per inspection cycle....................... 782 $3,315,680 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 determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979), and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Boeing: Docket No. FAA-2009-0913; Directorate Identifier 2009-
NM-101-AD.
Comments Due Date
(a) We must receive comments by December 3, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737-600, -700, -700C, -800,
and -900 series airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin 737-53A1289, dated
January 14, 2009.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This AD results from reports of scribe line damage found
adjacent to the skin lap joints, decals, and wing-to-body fairings.
The Federal Aviation Administration is issuing this AD to detect and
correct scribe lines, which can develop into fatigue cracks in the
skin. Undetected fatigue cracks can grow and cause sudden
decompression of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Inspection
(g) At the applicable times specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1289, dated
January 14, 2009 (``the service bulletin''), except as provided in
paragraph (h) of this AD, do detailed external inspections for
scribe lines in the fuselage skin at lap joints, the splice strap at
certain butt joints, the skin or doubler at certain approved repair
doublers, and the skin at decals; and do all applicable related
investigative and corrective actions, by accomplishing all actions
specified in the Accomplishment Instructions of the service
bulletin, except as provided by paragraph (i) of this AD.
Note 1: The inspection exceptions described in subparagraphs
1.a. through 1.e. in paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1289, dated January 14, 2009, apply to this
AD.
Exceptions to Service Bulletin Specifications
(h) Where Boeing Alert Service Bulletin 737-53A1289, dated
January 14, 2009, specifies a compliance time after the date on the
service bulletin, this AD requires compliance within the specified
compliance time after the effective date of this AD.
(i) Where Boeing Alert Service Bulletin 737-53A1289, dated
January 14, 2009, specifies to contact Boeing for appropriate
action, accomplish applicable actions using a method approved in
accordance with the procedures specified in paragraph (k) of this
AD.
Report
(j) At the applicable time specified in paragraph (j)(1) or
(j)(2) of this AD: Submit a report of the findings (both positive
and negative) of the inspections required by paragraph (g) of this
AD. You may use Appendix B of Boeing Alert Service Bulletin 737-
53A1289, dated January 14, 2009. Send the report to Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
The report must contain, at a minimum, the inspection results, a
description of any discrepancies found, the airplane serial number,
and the number of flight cycles and flight hours on the airplane.
Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501
et seq.), the Office of Management and Budget (OMB) has approved the
information collection requirements contained in this AD and has
assigned OMB Control Number 2120-0056.
[[Page 53445]]
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle Aircraft Certification Office, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information to ATTN:
Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM-120S, FAA,
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057-3356; telephone (425) 917-6447; fax (425)
917-6590. Or, e-mail information to [email protected].
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane, and the approval must specifically refer to this
AD.
Issued in Renton, Washington, on October 5, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-24986 Filed 10-16-09; 8:45 am]
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