[Federal Register: October 17, 2008 (Volume 73, Number 202)]
[Proposed Rules]
[Page 61747-61749]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17oc08-18]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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[[Page 61747]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1103; Directorate Identifier 2008-NM-048-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727-100 and 727-200 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 727-100 and 727-200 series airplanes. This
proposed AD would require repetitive internal and external high
frequency eddy current, mid frequency eddy current, low frequency eddy
current, and magneto optic imaging inspections to detect cracks,
corrosion, delamination, and materials loss in the lower fastener row
of the lower skin and the upper fastener row of the upper skin, and
corrective actions if necessary. This proposed AD results from a report
of decompression in a Boeing Model 737 airplane at flight level 290. We
are proposing this AD to detect and correct scratches and excessive
reduction in material thickness from excessive blend-out or corrosion,
which could lead to premature cracking in the lap joint. Such cracking
could adversely affect the structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by December 1,
2008.
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 AD, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
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 (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6577; 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-2008-1103;
Directorate Identifier 2008-NM-048-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 received a report of decompression in a Boeing Model 737
airplane at flight level (FL) 290. An investigation revealed that the
skin flapped between stringer (S)-4R and S-5R from body station (BS)
300 to BS 328. Examination of the skin showed cracks initiating at
scratches in the lower skin of a lap joint that was cold-bonded in
production. The lap splice had been separated for rework. These
conditions, if not corrected, may result in scratches and excessive
reduction in material thickness from excessive blend out or corrosion,
which could lead to premature cracking in the lap joint. Such cracking
could adversely affect the structural integrity of the airplane.
The cold-bonded lap joints on certain Boeing Model 727 airplanes
are similar to those on the affected Model 737 and Model 747 airplanes.
Therefore, all of these models may be subject to the same unsafe
condition.
Other Relevant Rulemaking
On November 7, 2003, we issued AD 2003-23-03, amendment 39-13367
(68 FR 64980, dated November 18, 2003), for certain Boeing Model 737-
100, -200, and -200C series airplanes. That AD requires repetitive
inspections to detect discrepancies in the upper and lower skins of the
fuselage lap joint and circumferential joint, and repair if necessary.
That AD requires a terminating modification for the repetitive
inspections.
On June 9, 2004, we issued AD 2004-13-02, amendment 39-13682 (69 FR
35237, June 24, 2004), for certain Boeing Model 747-100, -200B, and -
200F series airplanes. That AD requires initial and repetitive
inspections to find discrepancies in the upper and lower skins of the
fuselage lap joints, and repair if necessary.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 727-53A0223, dated
March 28, 2002. The service bulletin describes procedures for
repetitive internal and external high frequency eddy current (HFEC),
mid frequency eddy current (MFEC), low frequency eddy current (LFEC),
and magneto optic imaging (MOI) inspections to detect cracks,
corrosion, delamination, and materials loss in the lower fastener row
of the lower skin and the upper fastener
[[Page 61748]]
row of the upper skin, and corrective actions if necessary. The
corrective actions include repairing all cracks; repairing skin
material loss that is greater than 10%; separating, cleaning, and
refastening corroded areas where skin loss is less than 10%; and
replacing remaining fasteners with serviceable fasteners, if necessary.
The service bulletin also specifies compliance times for initial
HFEC, MFEC, LFEC, and MOI inspections ranging between 9 months or 1,500
flight cycles, whichever is earlier, and 60 months or 7,500 flight
cycles, whichever is earlier, depending on number of flight cycles on
the airplane. The service bulletin also specifies repetitive intervals
for HFEC, MFEC, LFEC, and MOI inspections every 2,000 or 7,000 flight
cycles, or every 4 years, depending on inspection area and type.
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 Rule and Referenced Service
Bulletin.''
Differences Between the Proposed Rule and Referenced Service Bulletin
Operators should note that, although the Accomplishment
Instructions of Boeing Alert Service Bulletin 727-53A0223, dated March
28, 2002, describes procedures for reporting all cracks and evidence of
corrosion to Boeing, this proposed AD would not require that action.
Costs of Compliance
We estimate that this proposed AD would affect 73 airplanes of U.S.
registry. We also estimate that it would take about 56 work hours per
product to comply with this proposed AD. The average labor rate is $80
per work hour. Based on these figures, we estimate the cost of this
proposed AD to the U.S. operators to be $327,040, or $4,480 per
product, 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 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, 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-2008-1103; Directorate Identifier 2008-NM-
048-AD.
Comments Due Date
(a) We must receive comments by December 1, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 727-100 and 727-200 series
airplanes, certificated in any category; as identified in Boeing
Alert Service Bulletin 727-53A0223, dated March 28, 2002.
Unsafe Condition
(d) This proposed AD results from a report of decompression in a
Boeing Model 737 airplane at flight level 290. We are proposing this
AD to detect and correct scratches and excessive reduction in
material thickness from excessive blend-out or corrosion, which
could lead to premature cracking in the lap joint. Such cracking
could adversely affect the structural integrity of the airplane.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Inspections and Corrective Actions
(f) Except as provided by paragraphs (f)(1), (f)(2), and
(f)(3)of this AD, at the applicable compliance times and repeat
intervals listed in paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 727-53A0223, dated March 28, 2002: Do repetitive
internal and external high frequency eddy current, mid frequency
eddy current, low frequency eddy current, and magneto optic imaging
inspections to detect cracks, corrosion, delamination, and materials
loss in the lower fastener row of the lower skin and the upper
fastener row of the upper skin, and corrective actions by
accomplishing all the applicable actions specified in the
Accomplishment Instructions of the service bulletin. The applicable
corrective actions must be done before further flight.
(1) Where paragraph 1.E., ``Compliance,'' of the service
bulletin identifies airplanes, ``Airplane Fight Cycles (f/c) at time
of SB Release,'' this AD affects those airplanes with the specified
flight cycles as of the effective date of this AD.
(2) Where paragraph 1.E., ``Compliance,'' of the service
bulletin specifies ``Initial Inspection Threshold From SB Rel Upper
and Lower Skin,'' the AD requires compliance within the specified
compliance times after the effective date of this AD.
(3) Where paragraph 1.E., ``Compliance,'' of the service
bulletin specifies ``Repeat every * * *,'' this AD requires
compliance at intervals not to exceed the specified flight cycles or
years.
No Reporting
(g) Although Boeing Alert Service Bulletin 727-53A0223, dated
March 28, 2002, specifies to submit information to the manufacturer,
this AD does not include that requirement.
[[Page 61749]]
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, Seattle Aircraft Certification Office, FAA,
ATTN: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S,
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057-3356; telephone (425) 917-6577; fax (425)
917-6590; has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19.
(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 appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(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 September 29, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-24763 Filed 10-16-08; 8:45 am]
BILLING CODE 4910-13-P