[Federal Register: October 6, 2003 (Volume 68, Number 193)]
[Proposed Rules]
[Page 57639-57642]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06oc03-16]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-49-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 767-200, -300, and -300F
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all Boeing Model 767-200, -300,
and -300F series airplanes. This proposal
[[Page 57640]]
would require repetitive inspections of the aft pressure bulkhead web,
and corrective action, if necessary. This action is necessary to detect
and correct fatigue cracks in the aft pressure bulkhead web, which
could result in uncontrolled rapid decompression. This action is
intended to address the identified unsafe condition.
DATES: Comments must be received by November 20, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2003-NM-49-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232.
Comments may also be sent via the Internet using the following address: 9-anm-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2003-NM-49-AD'' in the subject line and need not
be submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 or 2000 or
ASCII text.
The service information referenced in the proposed rule may be
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle,
Washington 98124-2207. This information may be examined at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington.
FOR FURTHER INFORMATION CONTACT: Suzanne Masterson, Airframe Branch,
ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue,
SW., Renton, Washington 98055-4056; telephone (425) 917-6441; fax (425)
917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this action may be changed in
light of the comments received.
Submit comments using the following format:
[sbull] Organize comments issue-by-issue. For example, discuss a
request to change the compliance time and a request to change the
service bulletin reference as two separate issues.
[sbull] For each issue, state what specific change to the proposed
AD is being requested.
[sbull] Include justification (e.g., reasons or data) for each
request.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this action must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2003-NM-49-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 2003-NM-49-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received reports of fatigue cracks at the aft pressure
bulkhead web on Boeing Model 737 and 747 series airplanes. This
condition, if not detected and corrected, could result in uncontrolled
rapid decompression.
The aft pressure bulkhead web on Boeing Model 767-200, -300, and -
300F series airplanes is almost identical to that on the affected
Boeing Model 737 and 747 series airplanes. Therefore, those Boeing
Model 767-200, -300, and -300F series airplanes may be subject to the
unsafe condition revealed on the Boeing Model 737 and 747 series
airplanes.
Other Relevant Rulemaking
The FAA has previously issued AD 1999-08-23, amendment 39-11132 (64
FR 19879, May 10, 1999), applicable to certain Boeing Model 737 series
airplanes. That AD requires repetitive inspections to detect cracking
in the web of the aft pressure bulkhead at body station 1016 at the aft
fastener row attachment to the ``Y'' chord; and corrective actions, if
necessary. This proposed AD would not affect the current requirements
of that AD.
The FAA has also previously issued AD 2000-15-08, amendment 39-
11840 (65 FR 47255, September 6, 2000), applicable to certain Boeing
Model 747 series airplanes. That AD requires repetitive inspections for
damage or cracking of the aft pressure bulkhead; cracking of the
bulkhead web-to-Y-ring lap joint area; cracking of the upper segment of
the bulkhead web; and cracking of the upper and lower segments of the
aft bulkhead web. This proposed AD would not affect the current
requirements of that AD.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Alert Service Bulletin
767-53A0087, dated October 21, 1999, which describes procedures for
performing repetitive high frequency eddy current inspections for
fatigue cracking of the aft pressure bulkhead web and contacting Boeing
for repair or inspection instructions. Accomplishment of the actions
specified in the service bulletin is intended to adequately address the
identified unsafe condition.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other products of similar type design, the proposed
AD would require accomplishment of the actions specified in the service
bulletin described previously, except as discussed below.
Differences Between Proposed Rule and Service Bulletin
Operators should note that, although the service bulletin specifies
that the manufacturer may be contacted for disposition of certain
repair conditions, this proposal would require the repair of those
conditions to be accomplished per a method approved by the FAA, or per
data meeting the type certification basis of the airplane approved by a
Boeing Company Designated Engineering Representative who has been
authorized by the FAA to make such findings.
Operators should also note that, although the service bulletin
specifies that the manufacturer may be contacted for certain inspection
details, this proposal would require an alternative method of
compliance to be approved as required by sections 39.15, 39.17, and
39.19 of the Code of Federal Regulations (14 CFR 39.15, 39.17, 39.19).
Operators should also note that, although the service bulletin does
not
[[Page 57641]]
list a grace period in the compliance times, this proposal adds a grace
period to the compliance times. The FAA finds that such a grace period
will keep airplanes from being grounded unnecessarily.
Changes to 14 CFR Part 39/Effect on the Proposed AD
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness
directives system. The regulation now includes material that relates to
altered products, special flight permits, and alternative methods of
compliance (AMOCs). Because we have now included this material in part
39, only the office authorized to approve AMOCs is identified in each
individual AD.
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 848 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 357 airplanes of U.S. registry
would be affected by this proposed AD, that it would take approximately
14 work hours per airplane to accomplish the proposed inspection, and
that the average labor rate is $65 per work hour. Based on these
figures, the cost impact of the proposed AD on U.S. operators is
estimated to be $324,870, or $910 per airplane, per inspection cycle.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the proposed requirements
of this AD action, and that no operator would accomplish those actions
in the future if this proposed 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 proposed herein 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. Therefore, it
is determined that this proposal would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I certify that 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) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new
airworthiness directive:
Boeing: Docket 2003-NM-49-AD.
Applicability: Model 767-200, -300, -300F series airplanes, as
listed in Boeing Alert Service Bulletin 767-53A0087, dated October
21, 1999; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct fatigue cracks in the aft pressure
bulkhead web, which could result in uncontrolled rapid
decompression, accomplish the following:
Initial and Repetitive Inspections
(a) Do high frequency eddy current inspections of the aft
pressure bulkhead web, per the Accomplishment Instructions of Boeing
Alert Service Bulletin 767-53A0087, dated October 21, 1999; at the
later of the applicable ``Threshold'' and ``Grace Period'' times
specified in Table 1 of this AD. Table 1 as follows:
Table 1.--Compliance Times for Inspection
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Compliance times
For -------------------------------------------
Threshold Grace period
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(1) Group 1 airplanes as Prior to the Within 18 months or
identified in the service accumulation of within 3,000
bulletin. 37,500 total flight flights after the
cycles. effective date of
this AD, whichever
comes first.
(2) Group 2 and 3 airplanes Prior to the Within 18 months or
as identified in the accumulation of within 3,000
service bulletin. 50,000 total flight flights after the
cycles. effective date of
this AD, whichever
comes first.
(3) Group 4 airplanes as Prior to the Within 18 months or
identified in the service accumulation of within 3,000
bulletin. 40,000 total flight flights after the
cycles. effective date of
this AD, whichever
comes first.
------------------------------------------------------------------------
(b) If no crack is found during any inspection required by
paragraph (a), repeat the high frequency eddy current inspections at
intervals specified in paragraphs (b)(1) or (b)(2) of this AD, as
applicable:
(1) For Group 1 and 2 airplanes, at intervals not to exceed
6,000 flight cycles, per the Accomplishment Instructions of Boeing
Alert Service Bulletin 767-53A0087, dated October 21, 1999.
(2) For Group 3 and 4 airplanes, at intervals not to exceed
12,000 flight cycles, per the Accomplishment Instructions of Boeing
Alert Service Bulletin 767-53A0087, dated October 21, 1999.
[[Page 57642]]
Corrective Actions
(c) If any crack is found during any inspection required by
paragraph (a) or (b) of this AD and Boeing Alert Service Bulletin
767-53A0087, dated October 21, 1999, specifies to contact Boeing for
repair: Before further flight, repair per a method approved by the
Manager, Seattle Aircraft Certification Office (ACO), FAA; or per
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.
For a repair method to be approved, the approval must specifically
reference this AD.
Previously Installed Repairs
(d) If previously installed repairs are installed in the
inspection area, and Boeing Alert Service Bulletin 767-53A0087,
dated October 21, 1999, specifies to contact Boeing for inspection
details, an alternative method of compliance must be approved as
required by sections 39.15, 39.17, and 39.19 of the Code of Federal
Regulations (14 CFR 39.15, 39.17, 39.19).
Alternative Methods of Compliance
(e) In accordance with 14 CFR 39.19, the Manager, Seattle
Aircraft Certification Office, FAA, is authorized to approve
alternative methods of compliance for this AD.
Issued in Renton, Washington, on September 29, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-25230 Filed 10-3-03; 8:45 am]
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